High Altitude Balloon Project
March 11, 2006
Team:
Michael Corbett ([email protected])
John Holtkamp ([email protected])
Jessica Williams ([email protected])
Sean Stevens ([email protected])
Brian Wirick ([email protected])
Advisors:
Dr. Mitch Wolff ([email protected])
Dr. Joseph Slater ([email protected])
Dr. Ruby Mawasha ([email protected])
Dr. Zhiqiang Wu ([email protected])
ME 490 – 491
Engineering Design
Wright State University
Dayton, OH
Abstract
The goals of this project were to design and build a payload to be attached to a
weather balloon that would reach an altitude of 100,000 feet and return safely to earth.
The payload contained both experiments and tracking equipment such as a GPS (Global
Positioning System) receiver and amateur (HAM) radio. The payload was first launched
to test the communication and tracking equipment and to define the launch procedures.
The remaining launches were to contain the experiments and improved command module
that implemented redundant tracking systems.
Experiments that were performed
included a solar cell study at high altitudes and altitude profiling of temperature, pressure,
and humidity.
This project used a collaboration of mechanical and electrical engineers to ensure
that all components of the project were designed and working properly. The electrical
engineers focused on a timer circuit for the camera, directional and omni-directional
antennas, and the solar cell experiment. The mechanical engineers focused on designing
the payload to withstand extreme conditions, creating a weather balloon filling
mechanism, predicting the flight path of the balloon, developing the balloon tracking
method, integrating all systems, and designing other experiments.
This project established the high altitude balloon program at Wright State
University. The experiments performed were significant for a variety of reasons. Very
little testing has been done on solar cells at high altitudes and this project helped increase
the knowledge base. Determining the effects of low temperature, pressure, and humidity
on the electronics can also aid in the development of more robust systems.
2
Introduction
Weather balloons have been used for many years by meteorologists to study
weather patterns in the upper atmosphere. Recently there has been increasing interest in
other studies that could be performed using weather balloons in “near space”
environment. The exact definition varies, but “near space” is often considered the area of
the earth’s atmosphere between approximately 100,000 and 200,000 feet 1 . Universities
and other scientific institutes, such as University of Montana and NASA Glenn Explorer
Post, Cleveland, OH, have been developing programs that build experimental payloads so
that they can analyze the data gathered after a successful launch. The goal of this senior
design project was to develop a ballooning program for Wright State University.
There are several areas of interest in high altitude balloon experiments. These
include radiation effects on solar cells, wireless communication, guidance, and detailed
maps of atmospheric conditions in relation to altitude. This wide span of information
could be used in many areas such as for military aircraft and for natural disaster rescue
teams. High bandwidth wireless communication between the ground and the balloon, as
well as between multiple balloons could be used to design communication methods and
systems between high altitude unmanned air vehicles (UAV). There is also hope that
balloons could be used in natural disaster situations (for example, the aftermath of
hurricane Katrina) as temporary communication towers for cell phones.
Balloon launches currently are at the mercy of the speed and direction of the jet
stream winds. Because of the uncontrollable nature of the winds, balloon launches have
uncertainty in the landing location of the payload. A guidance system would be able to
direct the payload to land in an unpopulated area and away from any bodies of water. If
3
this could be implemented, then retrieval time for the payload would be greatly reduced,
the chance of recovery would be significantly higher, and the distance that the payload
travels would no longer be determined solely by the high altitude winds.
In direct correlation with a guidance system, a method to extend flight time would
also lend itself useful to data collection and as a temporary communication hub. One
possible method to guide the payload is to maneuver the balloon in and out of different
wind currents, blowing it one direction first and then in another direction. This could be
achieved through the use of ballast released at proper times, and by bleeding helium out
of the balloon at designated altitudes. Guiding the balloon in this manner could gain
additional hours of flight time to collect experimental data. Unfortunately, adding a
system with ballasts could cause the payload to weigh much more than the Federal
Aviation Administration (FAA) twelve pound maximum weight regulation. Therefore,
this method cannot be tested while staying with this type of balloon payload.
Solar cell research at high altitudes would provide valuable information as well.
Knowing how solar cells perform in the “near space” environment will allow companies
to modify their products to be suitable for these extreme conditions. If solar cells can be
designed to perform well with the increase of radiation at around sixty to seventy
thousand feet, they may be used as an auxiliary power source for high altitude military
aircraft. Solar cells may also be a potential source of power for balloon payloads. This
would remove the need to have heavy batteries powering all equipment and provide more
room for experiments.
The experiments to obtain temperature, humidity, and pressure data at different
altitudes could help to bring about a more up to date temperature, humidity, and pressure
4
profile. Research indicates that it has been nearly 50 years 2 since data has been gathered
for this type of study and it is unknown whether the data is accurate for all seasons of the
year. If future groups could launch a payload at different times throughout the year,
accurate plots could be made for altitudes up to 100,000 feet for the entire year. With
this information, companies designing aeronautical systems would be able to account for
specific atmospheric conditions at various altitudes during any of the seasons to develop
products that are more robust.
Design Problem and Approach
There were multiple tasks that needed to be completed to make the project a
success.
The first and biggest task was designing a command module that would
withstand extreme environmental conditions and transmit GPS coordinates to aid the
team in recovering the payload once it had been launched.
Other tasks included
designing a balloon filling mechanism, choosing how to connect the payload components
together, deciding which balloons, gas, and parachutes to use, constructing a gas tank
transport crate, creating pre-launch and launch procedures, and designing initial
experiments to be performed.
The first steps taken in the project were to assemble the team and brainstorm on
the approaches and experiments to be performed. Some of the experiments proposed for
the project were solar cell studies of voltage and current at high altitudes, guiding the
payload to land in a desired location, achieving high bandwidth communication with the
ground, taking temperature, pressure, and humidity measurements during flight, and
taking pictures from the payload for publicity purposes. A timeline was then set for the
5
completion of tasks, and duties were assigned to team members. The breakdown of the
initial timeline and responsibilities are shown in Tables 1 and 2 in the Appendix. After
more research had been done and progress was slowed due to uncontrollable factors, it
was decided that some of the tasks would not be possible to complete in the timeframe
allotted. The actual time line of accomplishments and outline of responsibilities are
shown in Tables 3 and 4 of the Appendix.
Once the group came to a consensus concerning the desired outcomes of the
project, research began to determine the best way to proceed. Presently, there are a few
colleges such as the University of Cincinnati (UC) 3 and the University of Kentucky 4
which are launching similar high altitude balloons and performing their own experiments.
There are also many simpler projects being done by an Explorer Post affiliated with
NASA Glenn Research Center 5 and other such institutions. Each group designs and
performs experiments and builds off of other groups’ successes and failures.
This
communication and sharing of information rather than being in strict competition allows
future projects to evolve and to be more successful.
For instance, the Wright State University group visit to UC provided insight into
designing and building the payload box, as well as in choosing the core electronics such
as the HAM radios. Though many of the parts purchased for the current project were
different than the ones used by UC, it was helpful to have an idea of what to look for or
avoid. UC was also able to give advice on testing the GPS prior to launch and using a
pre-launch checklist. Several of the Wright State team members also witnessed a launch
performed by the aforementioned Explorer group. Being present at a launch provided
valuable information regarding launch procedures, time frames, and necessary supplies.
6
There were a number of design constraints in constructing and launching a
payload. The first regulations that needed to be considered were outlined by the Federal
Aviation Administration (FAA) Title 49 US Code 14 CFR part 101 6 .
The FAA
regulations give specific limits on the weight of the payload. The payload could not
weigh more than 12 pounds total, with no more than 6 pounds for a single box. This was
to ensure that if a plane would hit it, no significant damage would be done to the plane.
A light payload was also optimal for experimental purposes because it had a better
chance of reaching 100,000 feet since the balloon did not have to be inflated as much to
provide the required lift. There were also restrictions on the string used to attach the
components to each other and to the balloon. The string had to break under a 50 pound
load. If the balloon was to be launched at night, it must have a flashing beacon on it that
would be visible from five miles away. Some of the guidelines also specified the launch
conditions. The balloon could not be launched over a populated area or if there was more
than 50% cloud cover.
The operating environment limited the way the payload could be built. The box
needed to be lightweight, yet strong enough to take the impact of hitting the ground with
the velocity dictated by the parachute. The walls of the payload also needed to be a
thermal insulator in order to keep the inside of the box at an acceptable temperature for
the electronics. This meant that a process had to be used to make the insulating material
stronger and heat transfer involving conduction, convection, and radiation on all sides of
the box needed to be considered.
The main economic consideration for this project was to stay within a reasonable
budget and not to waste monetary resources.
7
The starting budget was $3000, but
additional money became available later into the project. While this budget might seem
gtenerous, many of the parts needed were expensive. The majority of the parts were onetime purchases. Once a payload command box was assembled, it could be reused for
future launches if it was recovered. The start-up expenses included:
•
HAM radios for the balloon payload command boxes
•
Foxhunting beacon
•
Mobile HAM radio ground unit
•
Receivers and directional antennas for foxhunting
•
GPS receivers and antennas for the payloads
•
Hand-held GPS receiver for tracking down the balloon
•
Laptop to run predictions, record data, and connect to the HAM radio for APRS
(Automatic Position Reporting System) 7 tracking
•
Microprocessors
•
Parachutes and string
•
Cameras and timer circuits
•
Screamer circuit for locating the box after landing
•
Payload box construction materials
Each launch required a balloon and sufficient Helium to fill the balloon until it provided
enough lift. Each of the experiments had a cost associated with it as well. A detailed
break down of the expenses can be seen in Table 5 of the Appendix.
8
Calculations and Testing
To try to keep all of the components within their optimal operating conditions, the
walls of the payload box were made of materials with high thermal resistivity. A thermal
analysis was performed on the walls of the box to determine how cold the inside
temperatures of the box would be. This was done using the ANSYS finite element
analysis package.
The procedure to set up the problem to analyze the heat transfer through the walls
of the payload can be found in the Appendix.
Once a solution was obtained, the
temperatures throughout the payload box could be seen. A picture showing how the
temperature varies throughout the box has been included in the Appendix (Figure 1 is a
view of the inside of the box, Figure 2 is a view of the outside of the box).
In order to do the analysis, it was necessary to know certain constants such as the
heat transfer coefficient of the different faces of the box and the thermal conductivity of
the Styrofoam that made up the walls of the box.
The thermal conductivity was
calculated using the resistivity of the Styrofoam. This resistivity was labeled on the
Styrofoam when it was purchased. To find the thermal conductivity, the thickness of the
material was divided by the resistivity. In the case of the payload box, the material was
F *inches
.
0.5 inches thick and the resistivity was 3.3 hours*°BTU
2
In order to solve for the heat transfer coefficients relating to the different surfaces
of the payload, Fundamentals of Heat and Mass Transfer 8 was used as a resource.
Detailed hand calculations showing how the coefficients were computed can be found in
the Appendix.
9
Once the values for the heat transfer coefficients and the thermal conductivity
were determined, they could be used in the analysis in ANSYS. All of the faces on the
inside and outside of the box had heat transfer coefficients set for them. The temperature
on the outside of the box was set at -70°C, which was the lowest temperature the payload
was expected to experience.
The pictures seen in the Appendix (Figures 1 and 2) show only 1/8 of the entire
box. It was possible to analyze the entire box using just this portion because the box was
symmetric about three planes. All of the thin edges, where the rest of the box would be
attached to the analyzed portion, had the thermal gradient set to zero. This boundary
condition tells the program that the portion of the box that was drawn was a piece of a
whole, symmetric object.
Once the analysis was completed, the different temperatures the inside faces of
the box reached could be seen. The center of each face on the payload box had the
warmest temperature on the surface of the box and the corner had the coolest temperature
on the surface. Looking at the colored bar along the bottom of the page, the correlation
between temperatures and color could be seen. This analysis helped the team to see how
effective the walls of the payload box would be in keeping the electronics from reaching
temperatures below their operating ranges.
Calculations were also performed to determine the size of the parachute that was
needed to carry a payload of 12 pounds to the ground with a maximum landing speed of
15 feet per second. The volume and type of gas to be used in the balloon to provide the
amount of lift necessary to carry the payload was determined as well. Equations derived
10
in Fluid Dynamics were used to perform these calculations. The basic equations used
were:
Ideal Gas Law:
P∀ = mRT
Buoyancy:
FB = ρ air g∀balloon
Drag Coefficient:
CD =
FD
1
ρV 2 A
2
In the above equations, P is the pressure, ∀ is the volume, m is the mass, R is the gas
constant, T is the temperature, FB is the buoyancy force, ρ is the density, g is the
B
acceleration due to gravity, CD is the drag coefficient, FD is the drag force, V is the
velocity, and A is the area. Detailed calculations can be found in the Appendix. The
results showed that a parachute with a 6.35 foot diameter was needed. The two gases that
were compared were helium and hydrogen. The calculations showed that less hydrogen
would be needed to create the desired lift and would be less expensive. To create the
same amount of lift, 282.44 ft3 of helium would be needed or 261.629 ft3 of hydrogen.
For safety reasons, helium was selected for use in the balloons despite the lower cost of
hydrogen.
As mentioned previously, the temperature inside the payload box needed to be
maintained at a moderate level in order to ensure the electronic equipment could function
properly. The components of the payload were tested in a freezer to ensure that they
could withstand the expected temperatures outside of the box at 100,000 feet which could
reportedly2 range from –70 to 100 degrees Celsius (shade side and sun side of the box,
respectively). Although temperatures inside the payload were not expected to reach these
extreme temperatures, components were chosen that would perform the best in a broad
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range of temperatures. For the first payload constructed, different types of batteries were
tested with some of the components in a freezer that maintained a temperature of -13°C.
The types of batteries tested were Nickel-Metal Hydride, Alkaline, and Nickel Cadmium.
The batteries were each placed in the freezer for 2.5 hours, which is the expected flight
time of the payload during a launch. Voltages were tested every 15 minutes to determine
the performance of the battery. At the end of the tests, it was determined that NickelMetal Hydride performed the best and would be used to power the electronics of the
payload. Tabulated results of these tests can be seen in Table 6 of the Appendix. When
constructing the second payload, component and system level tests were performed using
dry ice. Dry ice is able to maintain a temperature of -78.5°C. The air surrounding the
dry ice in a cooler was measured to be an average of -45°C. In the tests with the dry ice,
in addition to testing the robustness of the payload components, lithium ion 9-V batteries
were tested in comparison to alkaline 9-V batteries over the duration of approximately
three hours. At the end of the three hours, the voltages of the alkaline and lithium ion
batteries exposed directly to the air in the cooler showed that the lithium ion batteries
performed significantly better in extreme cold. The lithium ion batteries initially read 8.9
V, and after 3 hours dropped down to 7.8 V. The alkaline batteries initially read 9.2 V,
and after 3 hours dropped down to less than 3 V.
First Launch
For the initial launch, some of the tasks that needed to be completed included
choosing equipment, designing and constructing the fill valve and the payload box,
disassembling a camera and attaching it to a timer circuit, integrating a GPS system with
12
a HAM radio, getting a HAM radio license, running pre-launch predictions, and choosing
a launch site. The timer circuit was needed on the camera so pictures could be taken at a
set interval over a designated time period. The GPS tracking system needed the GPS
chip, an antenna to receive information from satellites so that its location could be
determined, and a HAM radio to communicate with the ground. A Technician Class (or
higher) licensed radio amateur must be present to oversee the use of the HAM radio to
transmit GPS data. A fill valve and nozzle needed to be designed and built to be able to
get the helium from 244 cubic foot tanks into the weather balloon. Predictions also
needed to be made based on wind patterns to determine where the payload would land if
it was launched.
The first steps taken were to research and purchase equipment for the payload box
and equipment for the ground. The payload box was to include a GPS receiver, a
transmitter, a temperature measuring device, a camera, and a screamer circuit. A Garmin
15L was chosen for the GPS. The 15L was able to run on low voltages between 3.5 and
5.5 volts. A Kenwood TH-D7A was chosen to be used as the transmitter. This particular
HAM radio was picked because it contained a built in TNC (terminal node controller).
The TNC is a device that can translate the text strings received from the GPS into a signal
that could be transmitted over the national APRS frequency (144.390 MHz). It could
also be used for custom packet operation on any allowed frequency in the 2 meter band.
A digital camera was selected because more pictures could be stored and all components
of the camera would be reusable. To take the pictures, a timer circuit was connected to
the camera so a picture would be taken once a minute. An Onset HOBO Temperature
Logger 9 was selected to measure the temperature both inside and outside the box. The
13
HOBO is a small device that had an internal thermistor and the ability to attach an
external thermocouple. It would record the temperatures in pre-selected time intervals to
onboard memory.
These temperatures could later be extracted with the use of a
computer. The screamer circuit was made from a dissected smoke detector and was to be
used to help locate the payload once it had landed.
The box itself was constructed out of 1.5 inch thick foam insulation that had an Rvalue of 13. The inside of the box was a 9 inch cube and the Auto Cad design of the
walls can be seen in Figures 1 and 2 of the Appendix. The foam was coated with
Monokote to increase the structural properties of the walls and the chances of the box
surviving impact. The equipment was attached to peg board that formed an X inside the
box. The X shape of the peg board was used to increase the structural integrity of the
box. A covering was made for the box out of rip-stop nylon (design found in Figure 3 of
the Appendix). The covering had D-rings sewn onto it to connect the box to the reducing
ring and to more payload boxes together in series. A diagram of the entire balloon
assembly can be seen in Figure 4 of the Appendix.
Once the payload box was constructed, the entire package was kicked down a
flight of stairs. This was to test the durability of the box, components, and connections
between components. During the system level testing, problems were encountered with
both the HAM radio and the GPS receiver. The HAM radio would occasionally get into
a loop where it continually reset itself. Further investigation showed that the voltage
going into the radio from the battery would drop to zero and then go back up to 7.8V.
The radio would then reset itself. It was discovered that a HAM radio battery would do
this if its charge was too close to depletion. Fully recharging the battery would resolve
14
the problem. The GPS that was being used, a Garmin 15L, had more severe problems.
The first GPS purchased broke in-between tests. It stopped updating the coordinates and
output only zeros. The reason why it started malfunctioning was never determined, and
the chip was sent back to the manufacturer for replacement. The second GPS chip that
was received was plugged in and output a coordinate for a location in Taiwan. Once the
GPS was reset with the aid of a computer, it was able to acquire satellites and output a
valid longitude, latitude, and altitude. Unfortunately, this GPS chip had a tendency to
lock up once power was removed. It was possible to quickly fix the problem by resetting
the chip. Once these problems were resolved, the communication system was fully
functional.
In order to pick a launch site, wind data from the past ten years was analyzed and
put through a path prediction program called Balloon Track 10 to make predictions of
where the balloon was to land. Depending on the strength of the winds at higher
altitudes, the balloon could travel 300 or more miles during its short (approximately 2.5-3
hour) flight. The prediction data was used to create a scatter plot of potential landing
locations. A single prediction run could be plotted using Google Maps, Yahoo Maps, or
a similar Internet based mapping software from within Balloon Track. For multiple
points, Xastir 11 was used. Xastir is an open-source APRS mapping and tracking package
that is a native Linux application. An X-Windows emulation environment was set up on
the laptop dedicated for the balloon project. Xastir was the same program that was used
for tracking the balloon during flight. County maps were downloaded from the US
Census Bureau 12 for the areas of interest. Example plots showing flight predictions can
be found in Figures 5 and 6 of the Appendix.
15
After reviewing a large range of
predictions, it was decided that a balloon launch would be canceled if the most recent
upper air wind forecast contained any five data points with winds above 100 knots, or any
one data point with winds above 120 knots.
The first launch took place on January 15, 2006. The balloon was launched from
the municipal airport in Portland, IN. There was less than 5% cloud cover and the
surface winds were less than one mile per hour. The temperature outside was -6°C
(22°F). The balloon took approximately 45 minutes to fill and used slightly more than
one tank of helium (one tank contains 244 cubic feet helium) to achieve the desired lift.
An equation from the Montana Space Grant Consortium web site 13 was used to
determine the weight of the counter balance. The counterbalance was used to determine
when the balloon had enough lift. Empirical data was used to create the following
equation:
Counter Weight = 1.2*(weight payload + weight parachute + weight balloon) – weight balloon
Equipment checks were made once all of the batteries and antennas were attached. All
components appeared to be working and the tracking program on the laptop computer
was receiving coordinates from the GPS.
The release of the balloon occurred around 9:10 A.M. The release went smoothly
and the balloon went almost straight up. Once the payload was in the air, it had a
pendulum motion as it ascended. The first fifteen minutes of the flight went according to
plan. The ground unit was able to successfully track the movements of the payload.
Once the balloon reached approximately 11,000 feet, the transmissions received stopped
updating. Repeater stations throughout Ohio and Indiana were able to receive the packets
transmitted by the onboard radio and record them on the Internet. An analysis of these
packets showed that for approximately four hours the payload transmitted the same
16
coordinates, altitude, and velocity.
By using knowledge of which repeaters logged
packets and the wind prediction data, the location of the payload was estimated to be east
of Cincinnati, OH. While no one has called to say that our first box has been found, there
is still hope that someone will contact Wright State. Once the payload is retrieved, the
data stored on board will be analyzed.
The packets that were received from the GPS before it locked-up were analyzed
and compared to the wind data collected from the weather station at Wilmington, OH 14 .
The data analysis from the first launch can be seen in Figures 7 and 8 of the Appendix.
The general trend was that the payload moved slightly slower than the wind speed due to
drag. The direction of the flight was not completely with the wind. Both the flight path
and the wind direction were toward the southeast, but the correlation was less than
expected. This was due to two factors:
1. The GPS data was not updated frequently enough to be very accurate.
2. The payload was swinging below the balloon in a pendulum type motion as the
entire system moved in a southeast direction. This would add some error to the
direction that the GPS indicated the system was moving.
Remaining Launches
After the first launch, results were gathered and hypotheses were made regarding
the failure of the command box. Some of these ideas included failure of the GPS chip,
failure of the HAM radio, broken wire connections, or low voltages and currents supplied
by the batteries. Any one of these ideas, or a combination of them, was a possible mode
17
of failure. More research was done concerning failures related to GPS systems and it was
concluded that the GPS probably locked up.
In order to avoid this problem on a future launch, it was decided to include
redundant GPS systems in one payload, as well as a constant tone beacon to be utilized in
foxhunting as a backup tracking system. A Parallax BASIC Stamp 15 was set up to
manage sensor data (temperature, pressure, and humidity), and acquire coordinates from
three different GPS chips. This information was transmitted directly to a computer on the
ground via HAM radios and was also stored on the BASIC Stamp for analysis when the
payload was recovered or in case there would be a problem transmitting it to the ground
in real time. The code pertaining to the GPS information and sensor input was written
entirely by the group. The BASIC Stamp Syntax and Reference Manual 16 and online help
through forums 17 were used as references to speed up the learning process since no
member of the group had worked with a BASIC Stamp microprocessor prior to this
project. The source code for the programs used to reset the Stamp, read the contents of
the memory, and run the main storage and transmission loop are included in the
Appendix.
A fourth GPS chip was used to transmit to the APRS digipeater network. A
digipeater is a digital repeating station that is set up to receive data packets transmitted,
and retransmit them to increase the range over which the packet can be received. The
APRS packet eventually reaches an IGate (Internet Gateway), which puts the information
on the Internet, cataloged by both the call sign of the HAM operator and by the time and
date. If the team’s receiving antenna became unable to pick up the transmissions because
18
the payload was out of range, the information could be accessed later to track the flight
path.
Foxhunting was implemented as a backup system in case all the GPS chips failed.
The system was set up so a beacon would transmit a pattern of tones in Morse code (.--
... ..- / -... .- .-.. .-.. --- --- -.
which translates to “WSU Balloon”) that could
be picked up by the use of directional antennas. With several directional antennas, the
group would be able to figure out where the transmitter was located. This is done by
having antennas at different locations. Each antenna is slowly swept in an arc while
being held horizontally in front of the user. The user listens for when the signal is
strongest and gets a general idea as to what direction the transmission is coming from
relative to their position. Each person using a directional antenna for foxhunting should
have a compass. The compass is to be used with a map to plot the best direction in order
to narrow down the search area. It is vital that everyone involved with foxhunting stay in
communication because each reported direction is considered simultaneously to
determine where the transmitter is.
Using all of these methods, it was the hope of the group that the second payload
would be found once it was launched.
On March 4th, 2006, the group headed to
Huntington, Indiana with hopes to have a successful launch and recovery. The balloon
was inflated while the rest of the group worked on testing the GPS system with the
BASIC Stamp.
The previous night the entire system had been tested and worked
perfectly, but at the launch site the GPS chips were not functioning correctly. After three
and a half hours it was discovered that two of the GPS antennas were too close to each
19
other. This close proximity caused them to jam all the GPS receivers in a 200 foot
radius. The problem was fixed, but by that time, the batteries in the HAM radios had
been used for too long and were judged not to be dependable for an entire flight.
Preparations are being made for another launch attempt. On the next launch, the
electrical engineers in the group will be implementing a solar cell test which will be
monitoring the current and voltage output of solar cells placed on the outside walls of the
payload box. Pressure, humidity, and additional temperature readings will be taken as
well. Once a launch is successfully performed and the data acquired from the launch is
analyzed, the Wright State University Balloon Program will have been successfully
established and the members of the group will consider the project a success.
Future Goals
Though the group has accomplished much in the process of establishing the
Wright State University High Altitude Balloon Program, there were many ideas for
experiments that were unable to be implemented into a flight because the course only
lasted two quarters. The following list contains examples of these experiments:
•
A propulsion system to guide the balloon back toward Wright State
University
•
An air release valve to control when and at what altitude the balloon will
burst
•
Tests involving wireless communication between two balloons that are
launched simultaneously
20
•
An experiment where a small plane, powered by solar cells, with
inflatable wings would be launched from the payload
Initially the group hoped to implement some, if not all, of these experiments into the
project, but it became apparent that this would not be possible due to time constraints.
The proposed experiments are projects that can be undertaken by future groups.
Starting a High Altitude Ballooning program at Wright State University was a
challenging task. Advice was taken from other groups, but there was much the Wright
State group had to learn on their own. Now that the Wright State group has started the
program, they have been able to share the information gathered through research and
system checks to help other groups, such as Cedarville University, start their own
programs. Five students and an advisor came to Wright State to get ideas of what a
balloon project might entail. The mechanical engineers from the Wright State group
spoke to them about Wright State program. Information was given regarding payload
construction and communications to prevent them from struggling with the same
problems faced in this project. It is the desire of the current group that future Wright
State groups will communicate with other local schools to help others and get ideas on
how to improve their own program.
Organizations such as Central State University and AFIT (Air Force Institute of
Technology) have shown interest in the Wright State program. It was intended that one
of Wright State’s launches would have tests from another organization implemented into
Wright State’s payload. Unfortunately, this was not able to happen in the time frame of
this project. While giving a presentation on the balloon project at DCASS (DaytonCincinnati Aerospace Sciences Symposium) on March 8, 2006, AFIT expressed interest
21
in testing long range 802.11 wireless communication in a future launch. There could be
some interaction between Wright State and AFIT in the future to perform different
system experiments.
With a working payload, specific launching procedures and guidelines in place,
future groups will be able to start designing more advanced and detailed experiments. It
would be in the best interest of future groups to spend the first several weeks going
through the process of researching the components being used in the command box and
rebuilding the exact payload box and system that the current Wright State group had
made.
This will increase their understanding of how the system works, and how
experiments can be integrated into the current system.
It will also give them an
understanding of the assembly so more payloads could be constructed if one became
damaged or unrecoverable.
Conclusion
The Wright State Balloon project began with the expectation that it would be a
straightforward process to create a program for launching payloads, and within two
quarters, complex tests could be integrated into the system to be performed during a
flight. It became clear as the first box was being designed and built that the project
entailed more development and design aspects than the group had anticipated. After the
unfortunate loss of the first payload, it was determined that the complex tests planned for
would most likely not make it into one of the current group’s launches. Instead, the
current group decided to focus on establishing the program and a detailed system in
22
which launches could take place with a significantly greater chance of recovering the
payload.
The failed recovery was analyzed and different modes of failure were suggested.
The weak areas in the original design were investigated and improvements were made to
the system to create a more robust communications box. Studies were performed on GPS
chips and their high failure rate. It was soon realized that a single GPS chip was not
reliable enough to depend on it as the only means of locating a payload. The decision
was made to implement multiple GPS chips from different manufacturers in the same
payload. Also, the group began looking into foxhunting. This way, a failure of any
single component would not cause the payload box to be unrecoverable, and future
groups would have a better idea of which GPS chips performed the best in high altitude
applications.
Most of the components in the new payload were integrated with a BASIC Stamp.
The BASIC Stamp is a microprocessor that is able to store information from the flight,
and could be used for future groups to perform basic algorithms to control their
experiments. Learning how to use the Stamp, wiring the circuit, and writing code for it to
be integrated with multiple GPS chips and sensors was a time consuming task.
This is just a small example of how the work that has been done in the last two
quarters has established the program. Despite the fact that not all the experiments that
were originally planned could be accomplished in the given timeframe, the work that has
been done by the group has been invaluable. The Wright State Balloon group is proud to
say they have successfully established the Wright State Balloon Program that can be
continued for years to come.
23
1
Samson, Victoria. "Space Security." CDI Center for Defense Information. 25 Sept. 2003.
<http://www.cdi.org/friendlyversion/printversion.cfm?documentID=1726>.
2
"U.S. Standard Atmosphere 1976." United States Committee on Extension. 05 Oct.
2005 <http://modelweb.gsfc.nasa.gov/atmos/us_standard.html>.
3
Urbaniak, Matthew. "Getting Started, Overview and Suggestions/Lessons Learned." University of
Cincinnati, OH. 28 Sept. 2005.
4
"Big Blue 3." 30 Apr. 2005. University of Kentucky. <http://www.engr.uky.edu/bigblue/index.php>.
5
Schilling, Herb. "Explorers Post 632 - BalloonSat." NASA. 29 Sept. 2005
<http://explorersposts.grc.nasa.gov/post632>.
6
"Electronic Code of Federal Regulations." 27 July 2005. National Archives and Records Administration.
10 Oct. 2005 <http://ecfr.gpoaccess.gov/cgi/t/text/textidx?c=ecfr&sid=e2c906490f4ce4ab73256388a218eb0d&rgn=div5&view=text&node=14:2.0.1.3.1
5&idno=14>.
7
Automatic Position Reporting System. 24 Sept. 2001. 09 Oct. 2005
<http://web.usna.navy.mil/~bruninga/aprs.html>.
8
Dewitt, David P., and Frank P. Incropera. Fundamentals of Heat Transfer. 5th ed. Hoboken: John Wiley
& Sons, 2002.
9
Onset. 10 May 2005. 20 Oct. 2005 <http://www.onsetcomp.com/>.
10
Von Glahn, Rick. "Balloon Track for Windows." 10 Dec. 2004. Edge of Space Sciences. 14 Oct. 2005
<http://www.eoss.org/wbaltrak/>.
11
XASTIR. 1 Nov. 2005. 17 Oct. 2005 <http://www.xastir.org/>.
12
"2005 First Edition TIGER/Line Files." 1 Dec. 2005. U.S. Census Bureau.
<http://www.census.gov/geo/www/tiger/tiger2005fe/tgr2005fe.html>.
13
Allen, Jacqueline. "Borealis: The Montana Space Grant Consortium High Altitude Balloon Program."
Montana Space Grant Consortium. 29 Sept. 2005 <http://spacegrant.montana.edu/borealis/>.
14
Oolman, Larry. "Weather." University of Wyoming. <http://weather.uwyo.edu/upperair/sounding.html>.
15
Parallax. 2002. 20 Oct. 2005 <http://www.parallax.com/>.
16
Martin, Jeff, Jon Williams, Ken Gracey, Artistides Alvarez, and Stephanie Lindsay. Basic Stamp Syntax
and Reference Manual. 2005. 7-486.
17
Corbett, Michael W. "Converting a Digital Temperature Reading to ASCII Values." Parallac. 24 Feb.
2006. 24 Feb. 2006 <Basic Stamp>.
24
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12,%20&%20AC12/Reference%20Material/A12%20B12%20AC12%20Referenc
e%20Manual%20RevD.pdf>.
"Airport Information." <http://www.airnav.com/airports/>.
Allen, Jacqueline. "Borealis: The Montana Space Grant Consortium High Altitude
Balloon Program." Montana Space Grant Consortium. 29 Sept. 2005
<http://spacegrant.montana.edu/borealis/>.
"Ansys Tutorials." 2004. FTM Studios. 05 Mar. 2006
<http://www.carbodydesign.com/tutorials/ansys.html>.
APRS. 25 Apr. 2003. 09 Oct. 2005 <http://www.winaprs.org/>.
Automatic Position Reporting System. 24 Sept. 2001. 09 Oct. 2005
<http://web.usna.navy.mil/~bruninga/aprs.html>.
"Basic Stamp (OWL2) to TLC2543 analog to digital converter." EME Systems. 22 Dec.
2005. <http://www.emesystems.com/OL2tlc2543.htm>.
"Basic Stamp Microcontroller." 2002. Parallax. <http://www.parallax.com/index.asp>.
"Big Blue 3." 30 Apr. 2005. University of Kentucky.
<http://www.engr.uky.edu/bigblue/index.php>.
Carmichael, Ralph. "Properties Of The U.S. Standard Atmosphere 1976." 25 Jan. 2005.
Public Domain Aeronautical Software. 10 Oct. 2005
<http://www.pdas.com/atmos.htm>.
Cengel, Yunas A., and Michael A. Boles. Thermodynamics: An Engineering Approach.
4th ed. New York, New York: The McGraw-Hill Company, 2002.
Corbett, Michael W. "Converting a Digital Temperature Reading to ASCII Values."
Parallac. 24 Feb. 2006. 24 Feb. 2006 <Basic Stamp>.
Dewitt, David P., and Frank P. Incropera. Fundamentals of Heat Transfer. 5th ed.
Hoboken: John Wiley & Sons, 2002.
"Electronic Code of Federal Regulations." 27 July 2005. National Archives and Records
Administration. 10 Oct. 2005 <http://ecfr.gpoaccess.gov/cgi/t/text/textidx?c=ecfr&sid=e2c906490f4ce4ab73256388a218eb0d&rgn=div5&view=text&n
ode=14:2.0.1.3.15&idno=14>.
"EM-401 GPS Engine Board with Active Antenna Product Guide." Global Sat.
<http://www.sparkfun.com/datasheets/GPS/EM-401%20User%20Manual.pdf>.
Fox, Robert W., Alan T. McDonald, and Philip J. Pritchard. Introduction to Fluid
Mechanics. 6th ed. Vol. 2. Hoboken: John Wiley & Sons, 2004. 433-439.
"GPS Sensor Boards GPS25-LVC, GPS25-LVS, GPS25-HVS Technical Specifications."
Garmin. 2000.
<http://www.garmin.com/manuals/GPS25LPSeries_TechnicalSpecification.pdf>.
"HIH-4000-003." Honeywell. 2004.
<http://catalog.sensing.honeywell.com/printfriendly.asp?FAM=humiditymoisture
&PN=HIH-4000-003>.
Holtkamp, John C. "Questions about Handheld Ham Radios." Eham.net. 08 Feb. 2006.
08 Feb. 2006 <MobileHam>.
Holtkamp, John C. "Signal Generator." Eham.net. 15 Feb. 2006. 15 Feb. 2006
<FoxHunting>.
"Image 20." Chart. The Spcae Science Division at the Naval Research Lab. 05 Oct. 2005
<http://spacescience.nrl.navy.mil/images/image20.gif>.
"INTRODUCTION TO UPPER ATMOSPHERIC SCIENCE." Naval Research Lab. 05
Oct. 2005 <http://spacescience.nrl.navy.mil/introupatmsci.html>.
Kroo, Ilan. "Standard Atmosphere Computations." 14 Apr. 1997. Aircraft Aerodynamics
and Design Group. 05 Oct. 2005 <http://aero.stanford.edu/StdAtm.html>
Martin, Jeff, Jon Williams, Ken Gracey, Artistides Alvarez, and Stephanie Lindsay.
Basic Stamp Syntax and Reference Manual. 2005. 7-486.
Monokote. 1996. 20 Oct. 2005 <http://www.monokote.com/>.
Onset. 10 May 2005. 20 Oct. 2005 <http://www.onsetcomp.com/>.
Oolman, Larry. "GFS Maps." University of Wyoming.
<http://weather.uwyo.edu/models/fcst/index.html?MODEL=gfs003>.
Oolman, Larry. "Weather." University of Wyoming.
<http://weather.uwyo.edu/upperair/sounding.html>.
Parallax. 2002. 20 Oct. 2005 <http://www.parallax.com/>.
Picone, J. M., D. P. Drob, R. R. Meier, and A. E. Hedin. "NRLMSISE-00: A New
Empirical Model of the Atmosphere." 29 Oct. 2002. Universities Space Research
Association. 04 Oct. 2005
<http://www.nrl.navy.mil/content.php?P=03REVIEW105>.
"Pocket Tracker." Byonics. <http://www.byonics.com/pockettracker/>.
Salo, T J. "Minnesota's High-Altitude Amateur Radio Balloon Project." 1999. University
of Minnesota. <http://www.tc.umn.edu/~tjs/Balloons.html>.
Samson, Victoria. "Space Security." CDI Center for Defense Information. 25 Sept. 2003.
<http://www.cdi.org/friendlyversion/printversion.cfm?documentID=1726>.
Schilling, Herb. "Explorers Post 632 - BalloonSat." NASA. 29 Sept. 2005
<http://explorersposts.grc.nasa.gov/post632>.
"SDX15A4." Honeywell.
<http://catalog.sensing.honeywell.com/datasheet.asp?FAM=Pressure&PN=SDX1
5A4>.
"Search Results for KD8CKD." Aprsworld.net.
<http://db.aprsworld.net/datamart/switch.php?call=kd8ckd&table=position&maps
=yes>.
"Sony GXB5210 GPS Reciever Data." 26 Aug. 2005. Synergy Systems, LLC.
<http://www.synergygps.com/SONY%20GXB5210%20GPS%20Receiver%20Data.pdf>.
Stanley, Mark. "1976 U.S. Standard Atmosphere." 22 Oct. 2000. 05 Oct. 2005
<http://nis-www.lanl.gov/~stanleym/dissertation/node19.html>.
"TinyTrak3." Byonics. <http://www.byonics.com/tinytrak/>.
United Solar Ovonic. 2005. U.S. General Services Administration. 12 Oct. 2005
<http://www.uni-solar.com/index.asp>.
Urbaniak, Matthew. "Getting Started, Overview and Suggestions/Lessons Learned."
University of Cincinnati, OH. 28 Sept. 2005.
"U.S. Standard Atmosphere 1976." United States Committee on Extension. 05 Oct. 2005
<http://modelweb.gsfc.nasa.gov/atmos/us_standard.html>.
Von Glahn, Rick. "Balloon Track for Windows." 10 Dec. 2004. Edge of Space Sciences.
14 Oct. 2005 <http://www.eoss.org/wbaltrak/>.
Von Glahn, Rick. "Edge of Space Sciences." 15 Jan. 1995. <http://www.eoss.org/>.
XASTIR. 1 Nov. 2005. 17 Oct. 2005 <http://www.xastir.org/>.
Appendix
Figure 1: ANSYS steady state heat transfer solution. The inside of a 1/8 portion of the box is shown.
Figure 2: ANSYS steady state heat transfer solution. The outside of a 1/8 portion of the box is shown.
Figure 3: Puzzle piece design of the first payload box. The second payload box was a
similar design but the exact dimensions were adjusted due to the different foam
thickness.
Figure 4: Scale drawings of the first payload box including dimensions. The second payload box was a similar design but the exact
dimensions were adjusted due to the different foam thickness.
Figure 5: Rip-stop nylon cover for the payload. Dimensions were shown so that the cover could be sewn to exact specifications to
provide a snug fit around the box.
Balloon
Parachute
Reducing
Ring
Payload
Box
Antenna
Figure 6: Diagram (not to scale) of the entire system.
Figure 7: Predictions for 10 years of data for the target November launch date +/- 4 days. The launch location was Ft. Wayne, IN.
The clustering of landing sites near Lake Erie suggested that the launch site should be moved further south in Indiana.
Figure 8: Predictions for the first launch. The launch location is Portland, IN. The wind data is from the morning of the actual
launch. Mapped predictions are based on Balloon Track (marked “BT”) and a custom-made model (marked “M”) analyses.
Speed vs Altitude
70.0
60.0
Speed (mph)
50.0
40.0
30.0
20.0
Wind File
GPS
10.0
0.0
0
2000
4000
6000
8000
10000
12000
14000
Altitude (ft.)
Figure 9: Speed reported by the GPS receiver and transmitted to the ground plotted versus altitude. It is compared with the wind
speed since the balloon should move approximately with the wind speed. The values are consistently below the wind data due
to drag.
Direction vs Altitude
200
180
160
Direction
(degrees)
140
120
100
80
60
Wind File
GPS
40
20
0
0
2000
4000
6000
8000
10000
12000
14000
Altitude (ft.)
Figure 10: Heading reported by the GPS receiver and transmitted to the ground versus altitude. It is compared with the wind
direction since the balloon should move approximately with the wind. The correlation between the GPS flight path and the
wind data path was less than expected, but both suggest the balloon moved roughly toward the southeast.
Choosing Project
Brain Storming
Forming Team
Landing Predictions
1st launch
11/28/0511/29/05
2nd launch
02/11/06
3rd launch
03/04/06
Budget for 1st launch
Ordering for 1st launch
Building Controls Box
Camera Timer
Data Storage
Filling Valve
HAM License
Thermocouples
Solar Cell Experiment
Air Release Valve
Parachute Deploy
Tethered Balloons
Alternative Comunications
Guidance System/Device
Object Launched off
Antenna
Box Design
Pressure/Humidity Readings
Thermal Analysis
Analysis of Results
Table 1: Old Gantt Chart timeline.
03/13/0
6
Week 2
8
03/06/0
6
Week 2
7
02/27/0
6
Week 2
6
02/20/0
6
Week 2
5
02/13/0
6
Week 2
4
02/06/0
6
Week 2
3
01/30/0
6
Week 2
2
01/23/0
6
Week 2
1
01/16/0
6
Week 2
0
01/09/0
6
Week 1
9
01/02/0
6
Week 1
8
12/26/0
5
Week 1
7
Winter Quarter
12/19/0
5
Week 1
6
12/12/1
0
Week 1
5
12/05/0
5
Week 1
4
11/28/0
5
Week 1
3
11/21/0
5
Week 1
2
11/14/0
5
Week 1
1
11/07/0
5
Week 1
0
10/31/0
5
Week 9
Christmas Break
10/24/0
5
Week 8
10/17/0
5
Week 7
10/10/0
5
Week 6
10/03/0
5
Week 5
09/26/0
5
Week 4
09/19/0
5
Week 3
09/12/0
5
Week 2
09/05/0
5
Week 1
Fall Quarter
Original
Mike
John
Jessica
Brian
Sean
Camera Timer
x
x
xx - Primary
Data Storage
x
x
x - Secondary
x
x
xx
xx
x
x
xx
x
Filling Valve
x
xx
Thermocouples
xx
x
x
xx
Solar Cell Experiment
x
Air Release Valve
Parachute Deploy
x
xx
Tethered Balloons
x
x
Alternative Communications
xx
Guidance System/Device
x
xx
Object Launched off
xx
Predictions
xx
x
Antenna
Box Design
xx
Pressure/Humidity Readings
x
Thermal Analysis
xx
Table 2: Old responsibilities list.
x
xx
x
Choosing Project
Forming Team
Brain Storming
1st launch
1/15/06
3/4/06
2nd launch
3rd launch
Box Transmitter Research
GPS Reasearch
Landing Predictions
Budget for 1st launch
HAM License
Ordering for 1st launch
Camera Timer
Screamer Circuit
Filling Valve
Box Design
Equipment Trouble Shooting
Building 1st Controls Box
Thermocouples
Reducing Ring Connector
Payload Antennas
Freezer Test
Durrability Test
Results Analysis
Alternative Comunications
Ordering for 2nd and 3rd launches
Building 2nd Controls Box
Building 3rd Controls Box
Data Storage
Solar Cell Experiment
Basic Stamp Programing
Directional Antennas
Pressure/Humidity Readings
2nd Payload Wire/Solder
3rd Payload Wire/Solder
ANSYS Thermal Analysis
Table 3: New Gantt Chart timeline.
03/06/0
6
Week 2
7
02/27/0
6
Week 2
6
02/20/0
6
Week 2
5
02/13/0
6
Week 2
4
02/06/0
6
Week 2
3
01/30/0
6
Week 2
2
01/23/0
6
Week 2
1
01/16/0
6
Week 2
0
01/09/0
6
Week 1
9
01/02/0
6
Week 1
8
12/26/0
5
Week 1
7
Winter Quarter
12/19/0
5
Week 1
6
12/12/1
0
Week 1
5
12/05/0
5
Week 1
4
11/28/0
5
Week 1
3
11/21/0
5
Week 1
2
11/14/0
5
Week 1
1
11/07/0
5
Week 1
0
10/31/0
5
Week 9
10/24/0
5
Week 8
Christmas Break
10/17/0
5
Week 7
10/10/0
5
Week 6
10/03/0
5
Week 5
09/26/0
5
Week 4
09/19/0
5
Week 3
09/12/0
5
Week 2
Actual Time Line
09/05/0
5
Week 1
Fall Quarter
Actual
Mike
John
Jessica
Brian
Sean
Camera Timer
x
x
xx - Primary
Screamer Circuit
x
x
x - Secondary
Data Storage
xx
Filling Valve
xx
Thermocouples
xx
Reducing Ring Connector
xx
Solar Cell Experiment
x
xx
xx
x
x
x
x
x
Alternative Communications
xx
Basic Stamp Programming
xx
x
x
Predictions
xx
x
Antenna
Box Design
Pressure/Humidity Readings
xx
x
xx
xx
2nd Payload Wire/Solder
x
xx
HAM Radio Research
xx
x
x
GPS Research
x
x
x
Freezer Test
xx
xx
Durability Test
x
Thermal Analysis
Data Analysis
x
x
Air Release Valve
x
x
x
xx
Parachute Deploy
x
xx
Tethered Balloons
x
x
Guidance System/Device
Object Launched off
x
xx
x
xx
xx
Table 4: New responsibilities list.
Ordered/
Shipped/
Received Product
O / S / R Spherachutes Parachute - 12 panel, 84" diameter
O / S / R Kenwood TM-D700A Ground HAM Unit
O / S / R Kenwood TH-D7AG Air HAM Unit
Cancelled Garmin GPS 15L-W (low-voltage, wires out) ($71.15)
Cancelled Garmin GPS Antenna GA 27c ($59.39)
O / S / R Garmin GPS 15L-W (low-voltage, wires out)
O / S / R Garmin GPS Antenna GA 27c
O / S / R Balloon - 1500 gram
O / S / R Garmin GPS eTrex Legend C - handheld
O / S / R Laplink DB9 cable - HAM to PC
O / S / R Dell C400 laptop
O / S / R 500' 100-lb Dacron
O / S / R HP PhotoSmart M22
Store
Plastic knitting hoop
Store
Rip Stop Nylon
Store
Polypro braided strap
Store
Buckle (x2)
Store
Buckle (x2)
Store
Metal D-rings (3x4-pack)
Store
1.5" Foam Insulation (24"x96")
Store
2x4 92" long
Store
Fill valve supplies
Store
Peg board
Store
Plywood
Store
Monokote (2x6' roll)
Store
Caribiners, fill valve supplies, gloves
WSU
2x 244 cu. ft. tanks Helium (2 tanks=2*36.75)
Store
Helium tank frame lumber and tiestraps
Ph / S / R HOBO Thermocouple Logger and Boxcar Software
Store
Fill valve supplies (round 2)
Store
Duct tape and batteries
Store
Hand warmers
Store
Monokote (2x6' roll) round 2
Store
Magmount antenna
Store
Smoke Alarm
O / S / R Garmin GPS 15L-W (low-voltage, wires out)
Store
Batteries and connectors
Vendor
http://www.spherachutes.com/spher.html via PayPal
http://www.gigaparts.com/parts/profile.php?sku=zkw-tm-d700a
http://www.gigaparts.com/parts/profile.php?sku=zkw-th-d7ag
Price
Shipping Total
$85.00
$475.00
$319.00
$6.00
$0.00
$0.00
$91.00
$475.00
$319.00
$69.12
$19.99
$125.00
$196.12
$4.18
$450.00
$7.95
$102.51
$13.99
$20.97
$8.80
$5.98
$5.38
$4.77
$10.52
$2.44
$27.36
$3.53
$4.99
$21.98
$40.02
$73.50
$64.70
$115.00
$7.76
$30.93
$1.98
$21.98
$34.99
$4.97
$69.12
$68.02
$7.89
$4.99
$0.00
$9.96
$10.46
$22.73
$6.07
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$20.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$7.95
$0.00
$77.01
$24.98
$125.00
$206.08
$14.64
$472.73
$14.02
$102.51
$13.99
$20.97
$8.80
$5.98
$5.38
$4.77
$10.52
$2.44
$27.36
$3.53
$4.99
$21.98
$40.02
$73.50
$64.70
$135.00
$7.76
$30.93
$1.98
$21.98
$34.99
$4.97
$77.07
$68.02
https://www.dbmarine.com/Sales/product-all.asp?C=GPS+%2F+Plotters
https://www.dbmarine.com/sales/product-all.asp?C=GPS+%2F+Plotters
http://www.thetwistergroup.com/product/010-00240-02%20W04048.html
http://cgi.ebay.com/ws/eBayISAPI.dll?ViewItem&item=5822189147&rd=1&sspagename=STRK%
https://secure.scientificsales.com/Details.cfm?ProdID=129&category=8
http://www.thetwistergroup.com/product/010-00358-00%20W00021.html
http://www.pcconnection.com/ProductDetail?Sku=187075
https://www.e-topco.com/commerce/store/viewitem.asp?idproduct=426
http://www.coastalkites.com/Merchant2/merchant.mv?Screen=PROD&Store_Code=247&Produc
http://cgi.ebay.com/ws/eBayISAPI.dll?ViewItem&item=7557756675
Jo Ann Fabric
Jo Ann Fabric
Jo Ann Fabric
Jo Ann Fabric
Jo Ann Fabric
Jo Ann Fabric
Lowes
Lowes
Lowes
Lowes
Lowes
RC Hobby Center
Lowes
WSU - through Greg Wilt
Lowes
Onset computer corporation
Lowes
Lowes
Dick's Sporting Goods
RC Hobby Center
Radio Shack
Home Depot
http://www.thetwistergroup.com/product/010-00240-02%20W04048.html
Radio Shack
Table 5: Bill of Materials
Ordered/
Shipped/
Received Product
O/S/R
Store
Store
Store
Store
O/S/R
O/S/R
O/S/R
O/S/R
O/S/R
Store
Store
Store
Store
Store
O/S/R
O/S/R
O/S/R
O/S/R
O/S/R
O/S/R
O/S/R
Store
Store
Store
Store
Store
Store
Store
Store
Store
O/S/R
Store
Store
Store
Store
Store
Balloon - 1500 gram
Antenna cable connector
Batteries and tarp
Antenna cable connectors
Shipping GPS to Garmin
BASIC Stamp two BS2p24 (one is a kit)
Kenwood TH-D7AG Air HAM Unit (2)
Spherachutes Parachute - 12 panel, 84" diameter (2)
Humidity & Pressure Sensors (2 each)
EM-401 GPS receiver (2)
Misc. parts
Misc. antenna parts
Box insulation board
Box cover material
Velcro
Garmin GPS 25-LVS (2)
Five antenna for GPS receivers
A410 Digital Camera (2)
Misc. Electronics
A12 GPS receiver (2)
GXB5210 GPS receiver kit (2)
PocketTracker
Lithium Batteries
Misc payload parts
Misc. circuit parts
PC Board and supplies
Hand warmers
Misc. circuit parts
Solder
Caribiners
Helium
Foxhunting radios
Filling valve supplies and batteries
Misc. circuit parts
Camera memory cards
Misc. circuit parts
Foamcore
Vendor
https://secure.scientificsales.com/Details.cfm?ProdID=129&category=8
Radio Shack
Meijer
Electronix
UPS Store
www.parallax.com
http://www.gigaparts.com/parts/profile.php?sku=zkw-th-d7ag
http://www.spherachutes.com/spher.html via PayPal
www.newarkinone.com
www.sparkfun.com
Midwest Surplus Electronics
Home Depot
Lowes
Jo Ann Fabric
Lowes
http://www.gpscity.com
http://www.kawamall.com
http://www.buy.com/prod/Canon_PowerShot_A410_3_2_Megapixel_Digital_Camera_w_3_2x_Zo
http://www.futurlec.com
http://www.thalesnavigation.com
http://www.synergy-gps.com
direct via paypal
Batteries Plus
Radio Shack
Midwest Surplus Electronics
Radio Shack
Dick's Sporting Goods
Radio Shack
Radio Shack
Meijer
Weiler Welding
http://www.universal-radio.com
Lowes
Radio Shack
Best Buy
Radio Shack
Meijer
Table 5: Bill of Materials
Price
$125.00
$5.29
$23.96
$4.27
$6.26
$278.95
$638.00
$170.00
$125.72
$147.80
$21.10
$18.38
$9.55
$72.57
$23.91
$259.90
$75.00
$259.98
$18.60
$159.00
$345.60
$50.00
$48.00
$3.18
$10.21
$12.48
$5.98
$57.68
$2.99
$46.51
$65.17
$559.80
$29.60
$40.62
$81.98
$12.73
$5.88
Shipping Total
$0.00
$0.00
$0.00
$0.00
$0.00
$7.63
$0.00
$6.00
$19.12
$3.11
$0.00
$0.00
$0.00
$0.00
$0.00
$11.48
$8.00
$8.44
$16.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$0.00
$30.00
$0.00
$0.00
$0.00
$0.00
$0.00
$125.00
$5.29
$23.96
$4.27
$6.26
$286.58
$638.00
$176.00
$144.84
$150.91
$21.10
$18.38
$9.55
$72.57
$23.91
$271.38
$83.00
$268.42
$34.60
$159.00
$345.60
$50.00
$48.00
$3.18
$10.21
$12.48
$5.98
$57.68
$2.99
$46.51
$65.17
$589.80
$29.60
$40.62
$81.98
$12.73
$5.88
Ordered/
Shipped/
Received Product
Store
Store
Store
O/S/R
O/S/R
O/S/R
Store
Store
Store
Store
O/S/R
O/S/R
O/S/R
Store
Store
Battery holders
Monokote
Caulk and spray foam insulation
1500g balloon (2)
TTL -> RS-232 chips
144MHz beacon (2)
Smoke Alarm
Misc. Electronics
Misc. Electronics
Misc. Electronics
DS 1822 Digital Thermometers
Tiny Track III and USB->Serial cable
Icom P7A and Kenwood battery packs
Lithium Batteries
Gift card as payment for box cover
Vendor
Radio Shack
RC Hobby Center
Meijer
http://www.scientificsales.com
http://www.futurlec.com
www.silcom.com via PayPal
Home Depot
Midwest Surplus Electronics
Midwest Surplus Electronics
Midwest Surplus Electronics
http://www.newarkinone.com
http://www.byonics.com
http://www.universal-radio.com
Batteries Plus
Applebee's
Table 5: Bill of Materials
Price
$20.72
$32.97
$8.98
$250.00
$5.80
$113.30
$5.30
$15.12
$7.08
$1.17
$38.70
$112.00
$255.90
$93.32
$60.00
Shipping Total
$0.00
$0.00
$0.00
$0.00
$4.00
$0.00
$0.00
$0.00
$0.00
$0.00
$20.57
$0.00
$24.00
$0.00
$0.00
$20.72
$32.97
$8.98
$250.00
$9.80
$113.30
$5.30
$15.12
$7.08
$1.17
$59.27
$112.00
$279.90
$93.32
$60.00
$0.00
$0.00
$0.00
$7,613.96
Freezer Battery Tests (-13°F)
Time
HAM 1
(hours:minutes)
(Volts)
0:00
10.06
0:15
5.6
0:30
3.66
0:45
2.76
1:00
2.11
1:15
1.81
1:30
1.61
1:45
1.5
2:00
1.38
2:15
1.37
2:30
-2:45
-3:00
--
HAM 2
(Volts)
10.84
4.31
2.47
1.58
1.23
1.02
0.87
0.79
0.73
0.68
0.65
0.63
0.63
Alkaline
(Volts)
5.94
5.64
5.46
5.75
5.14
5.04
4.94
4.84
4.75
4.68
----
Reyovac
NiMH (Volts)
5.53
5.41
5.31
5.24
5.19
5.14
5.12
5.09
5.07
5.04
----
NiCd
(Volts)
5.25
5.08
4.99
4.89
4.88
4.83
4.81
4.8
4.78
4.78
----
Table 6: Initial battery tests in a chest freezer. HAM radio batteries (custom NiCd)
performed very poorly. Standard size batteries all performed moderately well,
though no measurements of the current were made.
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1702
3947.0485
8400.8428
280
2
20
G2
1703
3947.0536
8400.8329
0
0
20
G3
1704
3947.1211
8400.9120
0
0
20
G1
1705
3947.0485
8400.8428
280
2
20
G3
1706
3947.1211
8400.9028
0
0
19
G1
1707
3947.0485
8400.8428
280
2
20
G2
1708
3947.0536
8400.8329
0
0
20
G3
1709
3947.1179
8400.8953
0
0
20
G1
1710
3947.0485
8400.8428
280
2
20
G2
1711
3947.0536
8400.8329
0
0
21
G3
1712
3947.1179
8400.8953
0
0
20
G1
1713
3947.0485
8400.8428
280
2
20
G2
1714
3947.0536
8400.8329
0
0
20
G3
1715
3947.1179
8400.8953
0
0
20
G1
1717
3947.0485
8400.8428
280
2
19
G2
1717
3947.0536
8400.8329
0
0
19
G3
1718
3947.1179
8400.8953
0
0
19
G1
1720
3947.0485
8400.8428
280
2
18
G2
1720
3947.0536
8400.8329
0
0
18
G3
1721
3947.1179
8400.8953
0
0
17
G1
1723
3947.0485
8400.8428
280
2
17
G2
1724
3947.0536
8400.8329
0
0
17
G3
1725
3947.1179
8400.8953
0
0
16
G1
1726
3947.0485
8400.8428
280
2
16
G2
1727
3947.0536
8400.8329
0
0
16
G3
1728
3947.1179
8400.8953
0
0
15
G1
1729
3947.0485
8400.8428
280
2
15
G2
1730
3947.0536
8400.8329
0
0
15
G3
1731
3947.1179
8400.8953
0
0
14
G1
1732
3947.0485
8400.8428
280
2
14
G2
1733
3947.0536
8400.8329
0
0
14
G3
1734
3947.1179
8400.8953
0
0
14
G1
1735
3947.0485
8400.8428
280
2
13
G2
1736
3947.0536
8400.8329
0
0
13
G3
1737
3947.1179
8400.8953
0
0
13
G1
1738
3947.0485
8400.8428
280
2
13
G2
1739
3947.0536
8400.8329
0
0
13
G3
1740
3947.1179
8400.8953
0
0
12
G1
1742
3947.0485
8400.8428
280
2
12
G2
1742
3947.0536
8400.8329
0
0
12
G3
1743
3947.1179
8400.8953
0
0
12
G1
1745
3947.0485
8400.8428
280
2
12
G2
1745
3947.0536
8400.8329
0
0
12
G3
1747
3947.1179
8400.8953
0
0
12
G1
1748
3947.0485
8400.8428
280
2
11
G2
1749
3947.0536
8400.8329
0
0
11
G3
1750
3947.1179
8400.8953
0
0
11
G1
1751
3947.0485
8400.8428
280
2
11
G2
1752
3947.0536
8400.8329
0
0
11
G3
1753
3947.1179
8400.8953
0
0
11
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1702
3947.0485
8400.8428
280
2
20
G2
1703
3947.0536
8400.8329
0
0
20
G3
1704
3947.1211
8400.9120
0
0
0
20
G1
1705
3947.0485
8400.8428
280
2
20
G3
1706
3947.1211
8400.9028
0
0
0
19
G1
1707
3947.0485
8400.8428
280
2
20
G2
1708
3947.0536
8400.8329
0
0
20
G3
1709
3947.1179
8400.8953
0
0
0
20
G1
1710
3947.0485
8400.8428
280
2
20
G2
1711
3947.0536
8400.8329
0
0
21
G3
1712
3947.1179
8400.8953
0
0
0
20
G1
1713
3947.0485
8400.8428
280
2
20
G2
1714
3947.0536
8400.8329
0
0
20
G3
1715
3947.1179
8400.8953
0
0
0
20
G1
1717
3947.0485
8400.8428
280
2
19
G2
1717
3947.0536
8400.8329
0
0
19
G3
1718
3947.1179
8400.8953
0
0
0
19
G1
1720
3947.0485
8400.8428
280
2
18
G2
1720
3947.0536
8400.8329
0
0
18
G3
1721
3947.1179
8400.8953
0
0
0
17
G1
1723
3947.0485
8400.8428
280
2
17
G2
1724
3947.0536
8400.8329
0
0
17
G3
1725
3947.1179
8400.8953
0
0
0
16
G1
1726
3947.0485
8400.8428
280
2
16
G2
1727
3947.0536
8400.8329
0
0
16
G3
1728
3947.1179
8400.8953
0
0
0
15
G1
1729
3947.0485
8400.8428
280
2
15
G2
1730
3947.0536
8400.8329
0
0
15
G3
1731
3947.1179
8400.8953
0
0
0
14
G1
1732
3947.0485
8400.8428
280
2
14
G2
1733
3947.0536
8400.8329
0
0
14
G3
1734
3947.1179
8400.8953
0
0
0
14
G1
1735
3947.0485
8400.8428
280
2
13
G2
1736
3947.0536
8400.8329
0
0
13
G3
1737
3947.1179
8400.8953
0
0
0
13
G1
1738
3947.0485
8400.8428
280
2
13
G2
1739
3947.0536
8400.8329
0
0
13
G3
1740
3947.1179
8400.8953
0
0
0
12
G1
1742
3947.0485
8400.8428
280
2
12
G2
1742
3947.0536
8400.8329
0
0
12
G3
1743
3947.1179
8400.8953
0
0
0
12
G1
1745
3947.0485
8400.8428
280
2
12
G2
1745
3947.0536
8400.8329
0
0
12
G3
1747
3947.1179
8400.8953
0
0
0
12
G1
1748
3947.0485
8400.8428
280
2
11
G2
1749
3947.0536
8400.8329
0
0
11
G3
1750
3947.1179
8400.8953
0
0
0
11
G1
1751
3947.0485
8400.8428
280
2
11
G2
1752
3947.0536
8400.8329
0
0
11
G3
1753
3947.1179
8400.8953
0
0
0
11
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1754
3947.0485
8400.8428
280
2
11
G2
1755
3947.0536
8400.8329
0
0
11
G3
1756
3947.1179
8400.8953
0
0
11
G1
1757
3947.0485
8400.8428
280
2
11
G2
1758
3947.0536
8400.8329
0
0
11
G3
1759
3947.1179
8400.8953
0
0
11
G1
1800
3947.0485
8400.8428
280
2
10
G2
1801
3947.0536
8400.8329
0
0
10
G3
1802
3947.1179
8400.8953
0
0
10
G1
1803
3947.0485
8400.8428
280
2
10
G2
1804
3947.0536
8400.8329
0
0
10
G3
1805
3947.1179
8400.8953
0
0
10
G1
1807
3947.0485
8400.8428
280
2
10
G2
1807
3947.0536
8400.8329
0
0
11
G3
1808
3947.1179
8400.8953
0
0
10
G1
1809
3947.0528
8400.8509
278
0
0
10
G2
1810
3947.0536
8400.8329
0
0
10
G3
1811
3947.1381
8400.9683
0.6
0
10
G1
1813
3947.0665
8400.8494
-33
0
0
10
G2
1814
3947.0562
8400.8429
288.6
0
0
9
G3
1815
3947.1027
8400.9579
0.4
0
9
G1
1816
3947.0559
8400.8521
295.7
0
0
9
G2
1817
3947.0530
8400.8380
298.9
0
0
9
G3
1818
3947.0569
8400.7959
550.3
0.8
0
9
G1
1819
3947.0540
8400.8488
280.8
0
0
9
G2
1820
3947.0644
8400.8428
297
0
0
9
G3
1821
3947.0494
8400.8391
363.5
0.2
0
9
G1
1822
3947.0526
8400.8478
289.7
0
0
9
G2
1823
3947.0561
8400.8399
296.9
0
0
9
G3
1824
3947.0567
8400.8076
363.6
0
0
9
G1
1825
3947.0520
8400.8477
291
0
0
9
G2
1826
3947.0606
8400.8413
296.7
0
0
9
G3
1827
3947.0303
8400.8198
363.6
0
0
9
G1
1828
3947.0518
8400.8475
281.8
0
0
9
G2
1829
3947.0534
8400.8426
287.4
0
0
9
G3
1830
3946.8119
8400.7919
363.6
4.3
4
8
G1
1831
3947.0515
8400.8478
287
0
0
8
G2
1832
3947.0525
8400.8383
298.3
0
0
8
G3
1833
3946.9198
8400.8110
363.6
1.1
1
8
G1
1834
3947.0512
8400.8478
294.2
0
0
8
G2
1836
3947.0561
8400.8433
305.5
0
0
8
G3
1837
3947.0491
8400.8468
206.7
0
0
7
G1
1838
3947.0506
8400.8479
297.4
0
0
7
G2
1839
3947.0533
8400.8395
285.2
0
0
7
G3
1840
3947.0521
8400.8358
244.6
0
0
7
G1
1841
3947.0504
8400.8472
287.1
0
0
7
G2
1842
3947.0560
8400.8429
283.2
0
0
6
G3
1843
3947.0526
8400.8363
258
0
0
6
G1
1844
3947.0509
8400.8474
306.4
0
0
6
G2
1845
3947.0473
8400.8399
299.9
0
0
6
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1754
3947.0485
8400.8428
280
2
11
G2
1755
3947.0536
8400.8329
0
0
11
G3
1756
3947.1179
8400.8953
0
0
0
11
G1
1757
3947.0485
8400.8428
280
2
11
G2
1758
3947.0536
8400.8329
0
0
11
G3
1759
3947.1179
8400.8953
0
0
0
11
G1
1800
3947.0485
8400.8428
280
2
10
G2
1801
3947.0536
8400.8329
0
0
10
G3
1802
3947.1179
8400.8953
0
0
0
10
G1
1803
3947.0485
8400.8428
280
2
10
G2
1804
3947.0536
8400.8329
0
0
10
G3
1805
3947.1179
8400.8953
0
0
0
10
G1
1807
3947.0485
8400.8428
280
2
10
G2
1807
3947.0536
8400.8329
0
0
11
G3
1808
3947.1179
8400.8953
0
0
0
10
G1
1809
3947.0528
8400.8509
278
0
0
10
G2
1810
3947.0536
8400.8329
0
0
10
G3
1811
3947.1381
8400.9683
0
0.6
0
10
G1
1813
3947.0665
8400.8494
-33
0
0
10
G2
1814
3947.0562
8400.8429
288.6
0
0
9
G3
1815
3947.1027
8400.9579
0
0.4
0
9
G1
1816
3947.0559
8400.8521
295.7
0
0
9
G2
1817
3947.053
8400.8380
298.9
0
0
9
G3
1818
3947.0569
8400.7959
550.3
0.8
0
9
G1
1819
3947.054
8400.8488
280.8
0
0
9
G2
1820
3947.0644
8400.8428
297
0
0
9
G3
1821
3947.0494
8400.8391
363.5
0.2
0
9
G1
1822
3947.0526
8400.8478
289.7
0
0
9
G2
1823
3947.0561
8400.8399
296.9
0
0
9
G3
1824
3947.0567
8400.8076
363.6
0
0
9
G1
1825
3947.052
8400.8477
291
0
0
9
G2
1826
3947.0606
8400.8413
296.7
0
0
9
G3
1827
3947.0303
8400.8198
363.6
0
0
9
G1
1828
3947.0518
8400.8475
281.8
0
0
9
G2
1829
3947.0534
8400.8426
287.4
0
0
9
G3
1830
3946.8119
8400.7919
363.6
4.3
4
8
G1
1831
3947.0515
8400.8478
287
0
0
8
G2
1832
3947.0525
8400.8383
298.3
0
0
8
G3
1833
3946.9198
8400.8110
363.6
1.1
1
8
G1
1834
3947.0512
8400.8478
294.2
0
0
8
G2
1836
3947.0561
8400.8433
305.5
0
0
8
G3
1837
3947.0491
8400.8468
206.7
0
0
7
G1
1838
3947.0506
8400.8479
297.4
0
0
7
G2
1839
3947.0533
8400.8395
285.2
0
0
7
G3
1840
3947.0521
8400.8358
244.6
0
0
7
G1
1841
3947.0504
8400.8472
287.1
0
0
7
G2
1842
3947.056
8400.8429
283.2
0
0
6
G3
1843
3947.0526
8400.8363
258
0
0
6
G1
1844
3947.0509
8400.8474
306.4
0
0
6
G2
1845
3947.0473
8400.8399
299.9
0
0
6
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G3
1846
3947.0534
8400.8358
259.2
0
0
6
G1
1847
3947.0512
8400.8473
287.6
0
0
6
G2
1848
3947.0588
8400.8391
306.1
0
0
5
G3
1849
3947.0561
8400.8784
154.7
0
0
5
G1
1850
3947.0532
8400.8480
285.3
0
0
5
G2
1851
3947.0596
8400.8418
303.4
0
0
5
G3
1852
3947.0445
8400.8106
251.4
1.5
1
5
G1
1853
3947.0535
8400.8462
289.8
0
0
5
G2
1854
3947.0636
8400.8372
310.3
0
0
5
G3
1855
3947.1658
8400.8785
254
5.9
5
5
G1
1856
3947.0534
8400.8464
299.7
0
0
4
G2
1857
3947.0548
8400.8403
289.4
0
0
4
G3
1858
3947.1629
8400.8722
204.3
1.3
1
4
G1
1859
3947.0537
8400.8463
295.3
0
0
4
G2
1901
3947.0585
8400.8413
295.2
0
0
4
G3
1902
3947.0542
8400.7913
297.7
0.6
0
4
G1
1903
3947.0539
8400.8465
-33
0
0
4
G2
1904
3947.0553
8400.8403
300
0
0
3
G3
1905
3946.8711
8400.7488
309.7
2.6
2
3
G1
1906
3947.0539
8400.8466
288.4
0
0
3
G2
1907
3947.0555
8400.8296
301.1
0
0
3
G3
1908
3947.1486
8400.8503
309.8
7.5
9
3
G1
1909
3947.0539
8400.8469
280.2
0
0
3
G2
1910
3947.0455
8400.8385
289.5
0
0
3
G3
1911
3947.1146
8400.8343
311.3
1.1
1
3
G1
1912
3947.0469
8400.8456
298.8
0
0
3
G2
1913
3947.0518
8400.8435
284.2
0
0
3
G3
1914
3947.1146
8400.8343
311.3
1.1
1
2
G1
1915
3947.0467
8400.8496
-33
0
0
2
G2
1916
3947.0535
8400.8414
290.8
0
0
2
G3
1917
3947.1146
8400.8343
311.3
1.1
1
2
G1
1918
3947.0484
8400.8492
290.7
0
0
2
G2
1919
3947.0409
8400.8378
302.3
0
0
2
G3
1920
3947.0378
8400.8312
310.2
11.7
11
2
G1
1921
3947.0531
8400.8497
268.6
0
0
2
G3
1923
3946.9431
8400.7843
309.8
1.8
1
2
G1
1924
3947.0423
8400.8467
296.8
0
0
2
G2
1925
3947.0482
8400.8423
294.9
0
0
2
G3
1926
3946.8400
8400.7513
307.8
1.2
1
2
G1
1927
3947.0562
8400.8626
258.5
0
0
1
G3
1928
3946.8812
8400.8003
307.1
4.2
4
1
G1
1929
3947.0487
8400.8480
290.3
0
0
1
G2
1930
3947.0514
8400.8408
287.9
0
0
1
G3
1931
3946.9818
8400.7980
307.5
0
0
1
G1
1932
3947.0486
8400.8487
295.5
0
0
1
G2
1933
3947.0540
8400.8438
281.2
0
0
1
G3
1934
3947.0525
8400.8236
307
0.4
0
1
G1
1935
3947.0484
8400.8491
271.8
0
0
1
G2
1936
3947.0517
8400.8398
292.4
0
0
1
G3
1937
3947.0531
8400.8272
290.8
1.3
1
1
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G3
1846
3947.0534
8400.8358
259.2
0
0
6
G1
1847
3947.0512
8400.8473
287.6
0
0
6
G2
1848
3947.0588
8400.8391
306.1
0
0
5
G3
1849
3947.0561
8400.8784
154.7
0
0
5
G1
1850
3947.0532
8400.8480
285.3
0
0
5
G2
1851
3947.0596
8400.8418
303.4
0
0
5
G3
1852
3947.0445
8400.8106
251.4
1.5
1
5
G1
1853
3947.0535
8400.8462
289.8
0
0
5
G2
1854
3947.0636
8400.8372
310.3
0
0
5
G3
1855
3947.1658
8400.8785
254
5.9
5
5
G1
1856
3947.0534
8400.8464
299.7
0
0
4
G2
1857
3947.0548
8400.8403
289.4
0
0
4
G3
1858
3947.1629
8400.8722
204.3
1.3
1
4
G1
1859
3947.0537
8400.8463
295.3
0
0
4
G2
1901
3947.0585
8400.8413
295.2
0
0
4
G3
1902
3947.0542
8400.7913
297.7
0.6
0
4
G1
1903
3947.0539
8400.8465
-33
0
0
4
G2
1904
3947.0553
8400.8403
300
0
0
3
G3
1905
3946.8711
8400.7488
309.7
2.6
2
3
G1
1906
3947.0539
8400.8466
288.4
0
0
3
G2
1907
3947.0555
8400.8296
301.1
0
0
3
G3
1908
3947.1486
8400.8503
309.8
7.5
9
3
G1
1909
3947.0539
8400.8469
280.2
0
0
3
G2
1910
3947.0455
8400.8385
289.5
0
0
3
G3
1911
3947.1146
8400.8343
311.3
1.1
1
3
G1
1912
3947.0469
8400.8456
298.8
0
0
3
G2
1913
3947.0518
8400.8435
284.2
0
0
3
G3
1914
3947.1146
8400.8343
311.3
1.1
1
2
G1
1915
3947.0467
8400.8496
-33
0
0
2
G2
1916
3947.0535
8400.8414
290.8
0
0
2
G3
1917
3947.1146
8400.8343
311.3
1.1
1
2
G1
1918
3947.0484
8400.8492
290.7
0
0
2
G2
1919
3947.0409
8400.8378
302.3
0
0
2
G3
1920
3947.0378
8400.8312
310.2
11.7
11
2
G1
1921
3947.0531
8400.8497
268.6
0
0
2
G3
1923
3946.9431
8400.7843
309.8
1.8
1
2
G1
1924
3947.0423
8400.8467
296.8
0
0
2
G2
1925
3947.0482
8400.8423
294.9
0
0
2
G3
1926
3946.84
8400.7513
307.8
1.2
1
2
G1
1927
3947.0562
8400.8626
258.5
0
0
1
G3
1928
3946.8812
8400.8003
307.1
4.2
4
1
G1
1929
3947.0487
8400.8480
290.3
0
0
1
G2
1930
3947.0514
8400.8408
287.9
0
0
1
G3
1931
3946.9818
8400.7980
307.5
0
0
1
G1
1932
3947.0486
8400.8487
295.5
0
0
1
G2
1933
3947.054
8400.8438
281.2
0
0
1
G3
1934
3947.0525
8400.8236
307
0.4
0
1
G1
1935
3947.0484
8400.8491
271.8
0
0
1
G2
1936
3947.0517
8400.8398
292.4
0
0
1
G3
1937
3947.0531
8400.8272
290.8
1.3
1
1
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1938
3947.0387
8400.8443
313.8
0
0
1
G2
1939
3947.0519
8400.8443
289.3
0
0
1
G3
1940
3947.0522
8400.8276
278.4
0
0
0
G1
1941
3947.0522
8400.8535
267.1
0
0
0
G2
1942
3947.0538
8400.8450
287.1
0
0
0
G3
1943
3947.0611
8400.8307
260.4
0
0
0
G1
1945
3947.0486
8400.8514
291.6
0
0
0
G2
1946
3947.0517
8400.8431
287.4
0
0
0
G3
1947
3947.0559
8400.8266
249.7
0
0
0
G1
1948
3947.0491
8400.8500
311.5
0
0
0
G2
1949
3947.0540
8400.8407
273.9
0
0
0
G3
1950
3947.0523
8400.8225
272
0.1
0
0
G1
1951
3947.0493
8400.8494
-33
0
0
0
G2
1952
3947.0562
8400.8412
282.4
0
0
0
G3
1953
3947.0504
8400.8126
271
0
0
0
G1
1954
3947.0534
8400.8574
265.5
0
0
0
G2
1955
3947.0562
8400.8387
267.4
0
0
0
G3
1956
3947.0626
8400.7847
323.7
0.9
0
0
G1
1957
3947.0518
8400.8526
274.7
0
0
-1
G2
1958
3947.0515
8400.8402
287.2
0
0
-1
G3
1959
3947.0480
8400.8156
297.4
0
0
-1
G1
2000
3947.0509
8400.8514
283.3
0
0
-1
G2
2001
3947.0522
8400.8411
284.9
0
0
-1
G3
2002
3947.0492
8400.8098
317.8
0
0
-1
G1
2003
3947.0505
8400.8506
304
0
0
-1
G2
2004
3947.0498
8400.8398
298.8
0
0
-1
G3
2005
3947.0508
8400.8099
317.3
0
0
-1
G1
2007
3947.0501
8400.8500
278.1
0
0
-1
G2
2008
3947.0504
8400.8389
289.4
0
0
-1
G3
2009
3947.0452
8400.8041
301.7
0
1
-1
G1
2010
3947.0501
8400.8497
287.2
0
0
-1
G2
2011
3947.0510
8400.8390
300.8
0
0
-1
G3
2012
3947.0484
8400.8280
240
0
0
-1
G1
2013
3947.0502
8400.8493
-33
0
0
-1
G2
2014
3947.0451
8400.8372
353.3
0
0
-1
G3
2015
3947.0530
8400.8350
227.8
0
0
-1
G1
2016
3947.0502
8400.8489
286.7
0
0
-1
G2
2017
3947.0497
8400.8375
305.9
0
0
-2
G3
2018
3947.0500
8400.8378
220.9
0
0
-2
G1
2019
3947.0502
8400.8487
301.2
0
0
-2
G2
2020
3947.0533
8400.8405
261.4
0
0
-2
G3
2021
3947.0539
8400.8384
219.4
0
0
-2
G1
2022
3947.0500
8400.8484
311.8
0
0
-2
G2
2023
3947.0509
8400.8366
303.2
0
0
-2
G3
2024
3947.0513
8400.8245
230.7
0.9
0
-2
G1
2025
3947.0500
8400.8481
306.9
0
0
-2
G2
2026
3947.0528
8400.8402
270.7
0
0
-2
Maximum
3947.1658
8400.9683
550.3
Minimum
3946.8119
8400.7488
-33.0
3 hours, 18 minutes
Mean
3947.0568
8400.8451
278.6
GPS UTC time DDMM.mmmm DDDMM.mmmm Altitude Speed Heading Box temp
G1
1938
3947.0387
8400.8443
313.8
0
0
1
G2
1939
3947.0519
8400.8443
289.3
0
0
0
G3
1940
3947.0522
8400.8276
278.4
0
0
0
G1
1941
3947.0522
8400.8535
267.1
0
0
0
G2
1942
3947.0538
8400.8450
287.1
0
0
0
G3
1943
3947.0611
8400.8307
260.4
0
0
0
G1
1945
3947.0486
8400.8514
291.6
0
0
0
G2
1946
3947.0517
8400.8431
287.4
0
0
0
G3
1947
3947.0559
8400.8266
249.7
0
0
0
G1
1948
3947.0491
8400.8500
311.5
0
0
0
G2
1949
3947.054
8400.8407
273.9
0
0
0
G3
1950
3947.0523
8400.8225
272
0.1
0
0
G1
1951
3947.0493
8400.8494
-33
0
0
0
G2
1952
3947.0562
8400.8412
282.4
0
0
0
G3
1953
3947.0504
8400.8126
271
0
0
0
G1
1954
3947.0534
8400.8574
265.5
0
0
Maximum
Minimum
Mean
3947.1658
3946.8119
3947.0579
8400.9683
8400.7488
8400.8468
550.3
-33.0
224.7
first 2 hours, 52 minutes
Ansys Procedure to Analyze High Altitude Balloon Payload
1.Preferences --> Thermal
2.Preprocessor-->Element Type--> Add/Edit/Delete
a) Add...
i. Thermal Solid: Brick 20 Node 90
ii. Ok
b) Close
3.Preprocessor --> Material Properties --> Material Models
a) Select Material Model 1
b) Double Click Thermal
c) Double Click Conductivity
d) Double Click Isotropic
i. kxx: .15152 --> Ok
e) Menu --> Material--> Exit
4.Preprocessor --> Modeling --> Create --> Keypoints --> In Active CS
a) Enter node numbers and locations (hit apply after each entry)
Point #
1
2
3
4
5
6
x
4.5
4.5
0
0
5
5
y
0
4.5
4.5
5
5
0
b) Ok
5.Preprocessor --> Modeling --> Create --> Lines --> Lines --> Straight Lines
a) Join Nodes: (1,2), (2,3), (3,4), (4,5), (5,6), and (6,1)
b) Ok
6.Preprocessor --> Modeling --> Create --> Areas--> Arbitrary --> By Lines
a) Choose all lines created in step 5
b) Ok
7.Preprocessor--> Modeling --> Operate --> Extrude --> Areas --> Along Normal
a) Select Area --> Ok
b) DIST: 4.5
c) Ok
8.Preprocessor --> Modeling --> Create --> Volumes --> Block --> By 2 Corners and Z
a) Pick top left corner of volume made in steps 4 through 7 and drag to the
bottom right corner of the volume
b) Set Depth = .5
c) Ok
9.Plot Ctrls --> View Settings --> Viewing Direction
a) Coords of View Point: 1, 1, 1
b) Ok
10.Preprocessor --> Modeling --> Operate --> Booleans --> Add --> Volumes
a) Select Both Volumes
b) Ok
11.Preprocessor --> Modeling --> Operate--> Booleans --> Add --> Areas
a) Select faces that are made up of 2 areas and combine them (along sides)
b) Select Ok
c) Repeat this step until all faces divided into two areas have been combined
12.Plot Ctrls --> View Settings --> Viewing Direction
a) Coords of View Point: -1, -1, -1
b) Ok
13.Preprocessor --> Modeling --> Operate --> Booleans --> Add --> Areas
a) Select faces that are made up of 2 areas and combine them (along edges)
b) Select Ok
c) Repeat this step for the other edge containing two areas
14.Preprocessor --> Meshing --> Mesh Attributes --> All Volumes
a) TYPE: 1 Solid 90
b) Ok
15.Preprocessor --> Meshing --> Size Ctrls --> Manual Size --> Global --> Size
a) Pick different sizes between .175 (Fine) and 2 (Coarse) to test different
meshes
b) Ok
16.Preprocessor --> Meshing --> Mesh --> Volumes --> Free
a) Pick Volume
b) Ok
17.Preprocessor --> Loads --> Define Loads --> Apply --> Thermal --> Convection -->
On Areas
a) Select the 2 large faces nearest to the bottom of the screen
i. Vali Film Coefficient: .0075968
b) Ok
18.Preprocessor --> Loads --> Define Loads --> Apply --> Thermal --> Convection -->
On Areas
a) Select the large face near the top of the screen
i.Vali Film Coefficient: .0079648
b) Ok
19.Preprocessor --> Define Loads --> Apply --> Thermal --> Heat Flux --> On Area
a) Select all edges
b) VALUE: 0
20.Plot Ctrls --> View Settings --> Viewing Direction
a) Coords of Viewpoint: 1, 1, 1
21.Preprocessor --> Loads --> Define Loads --> Apply --> Thermal --> Convection -->
On Areas
a) Select both sides (not the top)
b) Ok
c) Vali Film Coefficient: .007342
d) VAL2I Bulk Temp: -94
e) Ok
22.Preprocessor --> Loads --> Define Loads --> Apply --> Thermal --> Convection -->
On Areas
a) Select top area
b) Ok
c) Vali Film Coefficient: .00769779
d) VAL2I Bulk Temp: -94
23,Solution --> Solve --> Current LS --> Ok
24.Close
25.Close Status Window
26.General Postprocessor --> Plot Results --> Contour Plot --> Nodal Solutions
a) Select DOF Solution --> Temperature --> Ok
BASIC Stamp Program Source Code
' bigmemread.bsp
' This program dumps the contents of the memory to the DEBUG terminal window.
' Copy it from there for post-processing.
' {$STAMP BS2p}
' {$PBASIC 2.5}
beginning VAR
Word
ending
VAR
Word
slot
lastslot
char
i
counter
j
VAR
VAR
VAR
VAR
VAR
CON
Byte
Byte
Byte
Word
Byte
45
STORE 1
READ 4, lastslot
information
' first address containing information in current
' slot
' last address containing information in current
' slot
' current program slot number
' last program slot with information
' working character
' counter
' number of sentences stored in current slot
' number of characters per sentence
' look in slot 1 to start
' read in the slot number of last slot with
Main:
DEBUG "Starting Memory Dump...", CR
FOR slot = 1 TO lastslot
STORE slot
GOSUB Reading
NEXT
DEBUG CR, "Done Reading EEPROM!!"
END
Reading:
READ 0, Word beginning
READ 2, Word ending
READ 5, counter
DEBUG CR, CR, "Slot: ", DEC slot, "
counter=", DEC counter
IF ending = 10 THEN RETURN
FOR i = beginning TO (ending - 1)
'IF (i-beginning) // j = 0 THEN DEBUG CR
READ i, char
IF char = "G" THEN DEBUG CR
DEBUG char
NEXT
RETURN
' -reset.bsp
' This program resets the memory writing location information.
' {$STAMP BS2p}
' {$PBASIC 2.5}
addr
counter
slot
othernum
VAR
VAR
VAR
VAR
Word
Byte
Byte
Word
STORE 1
addr = 10
slot = 1
WRITE 4, slot
'
FOR counter = 1 TO 7
STORE counter
WRITE 0, Word addr
'
WRITE 2, Word addr
'
WRITE 5, 0
'
FOR othernum = 10 TO 2047
WRITE othernum, 0
NEXT
NEXT
DEBUG "Done clearing memory!"
' current memory address (in EEPROM)
' number of sentences stored in current slot
' current program slot number
set starting slot number to slot 1
set slot address start to 10
set slot current write address to 10
set slot sentence counter to 0
'
'
'
'
'
'
-fulltest.bsp
This program is the first attempt at being able to read in
data from multiple GPS receivers and multiple sensors and
store them in EEPROM. It also formats the data into custom
data packets for transmission over HAM frequencies and sends
those packets to the radio's TNC.
' Sentence Structure
' KD8CKD-1>G1hhmmDDMM.mmmmNDDDMM.mmmmW12345.6999.9360+90
' {$STAMP BS2p}
' {$PBASIC 2.5}
' Pin assignments
P_TOTNC
CON
TNC)
P_FROMTNC
CON
DQ
PIN
SkipROM
CON
CvrtTmp
CON
RdSP
CON
j
CON
10
8
13
$CC
$44
$BE
45
' Useful variables
current
VAR
addr
VAR
chars
VAR
char
VAR
i
VAR
tempIn
VAR
sign
VAR
tLo
VAR
tHi
VAR
idx
VAR
counter
VAR
Byte
Word
Byte(10)
Byte
Word
Word
tempIn.BIT11
tempIn.BYTE0
tempIn.BYTE1
Nib
Byte
slot
Byte
VAR
' Stamp TX/TNC RX (16 for PC, 10 for
'
'
'
'
'
'
Stamp RX/TNC TX
Temperature pin
ignore device S/N
start temperature conversion
read DS1822 scratch pad
number of characters per string
'
'
'
'
'
'
'
current GPS
current memory address (in EEPROM)
read in array variable
read in character variable
counter
temperature
1 = negative temperature
' number of sentences stored in
' current slot
' current program slot number
Initilize:
STORE 1
' look in slot 1 to start
READ 4, slot
' read in the current writing slot number
STORE slot
' go to appropriate slot
READ 2, Word addr
' load starting write address
READ 5, counter
' get counter position
PAUSE 500
' delay start by 0.5 seconds
SEROUT P_TOTNC, 16624, ["HBAUD 9600", 13]
' sending TNC commands
SEROUT P_TOTNC, 16624, ["CONNECT KD8CKD-2", 13]
PAUSE 5000
' allow 10 seconds to connect
Main:
First:
current = 49
' ASCII value "1"
SERIN 1, 16624, 3000, Second, [WAIT ("MC,"), STR chars\4]
GOSUB Write1
SERIN 1, 16624, 3000, Second, [WAIT ("MC,"), WAIT (","), WAIT (","),
chars\9, WAIT (","), char]
GOSUB Write2
SERIN 1, 16624, 3000, Second, [WAIT ("MC,"), WAIT (","), WAIT (","),
(","), WAIT (","), STR chars\10, WAIT (","), char]
GOSUB Write3
SERIN 1, 16624, 3000, Second, [WAIT ("GA,"), WAIT (","), WAIT (","),
(","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), STR
STR
WAIT
WAIT
chars\7]
GOSUB Write4
SERIN 1, 16624, 3000, Second, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\5]
GOSUB Write5
SERIN 1, 16624, 3000, Second, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\3]
GOSUB Write6
Second:
current = 50
' ASCII value "2"
SERIN 2, 16624, 3000, Third, [WAIT ("MC,"), STR chars\4]
GOSUB Write1
SERIN 2, 16624, 3000, Third, [WAIT ("MC,"), WAIT (","), WAIT (","), STR
chars\9, WAIT (","), char]
GOSUB Write2
SERIN 2, 16624, 3000, Third, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), STR chars\10, WAIT (","), char]
GOSUB Write3
SERIN 2, 16624, 3000, Third, [WAIT ("GA,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), STR chars\7]
GOSUB Write4
SERIN 2, 16624, 3000, Third, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\5]
GOSUB Write5
SERIN 2, 16624, 3000, Third, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\3]
GOSUB Write6
Third:
current = 51
' ASCII value "3"
SERIN 3, 16624, 3000, Fourth, [WAIT ("MC,"), STR chars\4]
GOSUB Write1
SERIN 3, 16624, 3000, Fourth, [WAIT ("MC,"), WAIT (","), WAIT (","), STR
chars\9, WAIT (","), char]
GOSUB Write2
SERIN 3, 16624, 3000, Fourth, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), STR chars\10, WAIT (","), char]
GOSUB Write3
SERIN 3, 16624, 3000, Fourth, [WAIT ("GA,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), STR chars\7]
GOSUB Write4
SERIN 3, 16624, 3000, Fourth, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\5]
GOSUB Write5
SERIN 3, 16624, 3000, Fourth, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\3]
GOSUB Write6
Fourth:
current = 52
' ASCII value "4"
SERIN 7, 16624, 3000, After, [WAIT ("MC,"), STR chars\4]
GOSUB Write1
SERIN 7, 16624, 3000, After, [WAIT ("MC,"), WAIT (","), WAIT (","), STR
chars\9, WAIT (","), char]
GOSUB Write2
SERIN 7, 16624, 3000, After, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), STR chars\10, WAIT (","), char]
GOSUB Write3
SERIN 7, 16624, 3000, After, [WAIT ("GA,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), WAIT (","), STR chars\7]
GOSUB Write4
SERIN 7, 16624, 3000, After, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\5]
GOSUB Write5
SERIN 7, 16624, 3000, After, [WAIT ("MC,"), WAIT (","), WAIT (","), WAIT
(","), WAIT (","), WAIT (","), WAIT (","), STR chars\3]
GOSUB Write6
After:
GOTO Main
Write1: '"G1hhmm" - GPS receiver number and UTC time
IF counter > 41 AND slot = 7 THEN
' checking status of current slot
END
ELSEIF counter > 41 THEN
slot = slot + 1
STORE 1
WRITE 4, slot
STORE slot
READ 2, Word addr
READ 5, counter
ENDIF
WRITE addr, "G", current, chars(0), chars(1), chars(2), chars(3)
addr = addr + 6
RETURN
Write2: '"DDMM.mmmmN" - Latitude
WRITE addr, chars(0), chars(1), chars(2), chars(3), chars(4), chars(5),
chars(6), chars(7), chars(8), char
addr = addr + 10
RETURN
Write3: '"DDDMM.mmmmW" - Longitude
WRITE addr, chars(0), chars(1), chars(2), chars(3), chars(4), chars(5),
chars(6), chars(7), chars(8), chars(9), char
addr = addr + 11
RETURN
Write4: '"#####.#" - Altitude (meters)
WRITE addr, chars(0), chars(1), chars(2), chars(3), chars(4), chars(5),
chars(6)
addr = addr + 7
RETURN
Write5: '"###.#" - Speed (knots)
WRITE addr, chars(0), chars(1), chars(2), chars(3), chars(4)
addr = addr + 5
RETURN
Write6: '"###" - Direction (degrees)
OWOUT DQ, 1, [SkipROM, CvrtTmp]
' send convert temperature command
DO
' wait on conversion
PAUSE 25
' small loop pad
OWIN DQ, 4, [tempIn]
' check status (bit transfer)
LOOP UNTIL (tempIn)
' 1 when complete
OWOUT DQ, 1, [SkipROM, RdSP]
' read DS1822 scratch pad
OWIN DQ, 2, [tLo, tHi]
' get raw temp data
tempIn = tempIn >> 4
' round to whole degrees
tHi = $FF * sign
' correct twos complement bits
IF sign = 0 THEN char = "+" ELSE char = "-"
chars(8) = tempIn DIG 1 + 48
chars(9) = tempIn DIG 0 + 48
WRITE addr, chars(0), chars(1), chars(2), char, chars(8), chars(9)
addr = addr + 6
counter = counter + 1
WRITE 2, Word addr
' save next memory address
WRITE 5, counter
' save counter total
SEROUT P_TOTNC, 16624, ["KD8CKD->"]
FOR i = (addr - j) TO (addr - 1)
READ i, char
SEROUT P_TOTNC, 16624, [char]
NEXT
SEROUT P_TOTNC, 16624, [13]
PAUSE 56000
RETURN
PREPARATORY CHECKLIST
Preflight Planning
___Weather Checks Completed
___BalloonTrack Prediction Okay
___Launch Site Confirmed
___Launch Team & Chase Team Personnel Totals
___Gas Cylinder Transport Arranged
___FAA Contacted
___Airport Contacted
Preflight Systems
___Gas Fill Team
___Balloon Available
___Full Helium Cylinders***QTY___
___Fill Valve Ready
___Equipment Ready
___Flight Crew Available
___Imaging/Cameras
___Camera(s) Functioning
___Memory Available
___Batteries Charged
___Flight Crew Available
___Communications
___Radios & GPS Functioning
___Screamer Functioning
___Laptop Functioning & Power System Ready
___Batteries Charged
___All Wires Securely Connected
___Flight Crew Available
___Payload
___All Flight Boxes in Good Condition
___Experiment in Working Order
___Experiment Data Collection Working
___Connections Between Modules Secure
___Flight Crew Available
PARTS CHECKLIST
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
□
Ground cloth/tarp
Weights for ground cloth
Table
Handling gloves
“Big hands”
Helium (in secure transport structure)
Helium regulator
Balloon hose and filler assembly
Filler assembly hose clamp
Fish scale/counterweight
Balloon
Parachute
Kite string cut to length
Caribiners
Knitting hoop
Handheld GPS tracker
Notebook and pen
Video camera and battery
Video camera cassettes
Digital camera and batteries
Snacks and beverage
Mobile HAM (with car battery)
Laptop
o Power cable
o Floppy drive
o CD-ROM drive
o Drive cable
o HAMÆPC cable
o HOBO Cable
o Wireless card
o USB flash drive
o Camera card reader
□ Communication module
o GPS receiver
o GPS antenna
o Battery pack (for GPS) – 4 AA batteries
o Handheld HAM radio with battery pack
o HAM antenna
o Screamer circuit
o 9V battery for screamer
o Camera
o Camera batteries
o Camera flash memory card
o HOBO logger
o Thermocouple
o Box lid
o Nylon bag
o Bag label card – harmless radio device; contact info
□ Experiment module
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
o _______________________________
□ Tool kit
o Multimeter
o Screwdrivers
o Pliers
o Wire cutters
o Wire
o Electrical tape
o Duct tape
o Spare AA batteries
o Battery charger
o Spare 9V batteries
o Zip ties
o Kite string
o Pocketknife
o Scissors
o Extra caribiners
Launch Preparation Procedure
1.
2.
3.
4.
Payload and parachute weight:
____________________ lbs
Desired lift: 1.2(#1 + mballoon ) − mballoon = ____________________ lbs
Check gas level in cylinders to be used
At launch site
a. Place ground cloth on ground with no sharp objects (weight down corners)
b. Attach regulator to cylinder #1
c. Make sure regulator output closed
d. Note Initial pressure of cylinder #1: _______________psi
e. Put on handling gloves
f. Place balloon on ground cloth, inspect for damages
g. Tape lift gauge loop to filler assembly
h. Place balloon nozzle over filler assembly
i. Clamp or tape balloon nozzle onto filler assembly
j. One person should be holding the balloon nozzle, one person operating the
regulator, others guarding the balloon with “big hands”
k. Begin inflation (use regulator to begin slowly and increase fill rate as
balloon takes shape)
l. When cylinder #1 reaches ~100 psi close regulator output
m. Record cylinder #1 pressure: _____________ psi
n. Shut off in-line valve
o. Shut off cylinder #1 valve
p. Move regulator to cylinder #2
q. Open cylinder #2 valve
r. Record cylinder #2 initial pressure: _______________ psi
s. Open regulator
t. Open in-line valve, continue inflation
u. When appropriate, connect fish scale to loop
v. Carefully let go of balloon nozzle while someone holds fish scale
w. Take several readings and roughly average in your head
x. When desired lift achieved, close in-line valve and regulator
y. Record final pressure of cylinder #2: _____________ psi
z. Close cylinder
aa. Tape load loop to balloon nozzle with small piece of tape
bb. Pinch off balloon nozzle
cc. Twist balloon nozzle
dd. Tie balloon nozzle with kite string (CAUTION: not too tight or it will tear
through)
ee. Fold nozzle material
ff. Tie again
gg. Duct tape balloon nozzle
5. Check connections
a. Flight GPS antenna to GPS unit (before power-up)
b. Flight GPS to flight HAM radio (Kenwood TH-D7)
c. Batteries to GPS unit
d. Flight HAM radio to HAM antenna
e. HAM radio battery pack
f. Camera batteries
g. Camera timer circuit
h. Camera timer circuit switch
i. Screamer speaker
j. Screamer circuit
k. Screamer battery
l. Screamer switch
m. HOBO thermocouple
6. Prepare laptop/mobile HAM radio
a. Power on laptop
b. Power on HAM radio
c. Connect to mobile HAM radio
d. Set HAM frequency to 144.390 MHz
e. Check TNC mode
f. Check APRS mode
g. Load Xastir
7. Check settings
a. Power on HAM radio
b. Set frequency to 144.390 MHz
c. Check TNC mode
d. Check Beacon mode
e. Lock keypad (hold F for >1s)
f. Confirm receiving signals in Xastir
g. Move communication module around, checking that Xastir updates
location
8. HOBO launch
a. Close Xastir (serial port is needed to launch HOBO)
b. Connect HOBO cable
c. Launch HOBO logger
d. Delete log file in Xastir log folder
e. Reopen Xastir
f. Reconfirm data reception
g. Start trace on callsign
h. Confirm that coordinates are reasonable by comparing with handheld GPS
9. Check experiment module operation
a. _______________________________
b. _______________________________
c. _______________________________
d. _______________________________
e. _______________________________
f. _______________________________
10. Camera
a. Turn on camera
b. Turn on timer
c. Confirm pictures are being taken
d. Make sure the display is off
11. Switch on screamer circuit
12. Final check of APRS packet reception
13. Begin APRS packet logging
14. Connect parachute to balloon (redundant strings)
15. Connect parachute to hoop
16. Connect hoop to communications module
17. Connect communications module to experiment module
18. Launch
CONTACT SHEET AND DIRECTIONS
Contact Names and Phone Numbers:
Wright State University
High Altitude Balloon Program
Flight No.: ____________________
Flight Date: _____/_____/________
LAUNCH DESCRIPTION AND PURPOSE
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
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______________________________________________________________________________
Recorded by: _______________________
Wright State University
High Altitude Balloon Program
Flight No.: ____________________
Flight Date: _____/_____/________
WEATHER FORECAST & FLIGHT PREDICTIONS
Launch Site: __________________________
_____ ____.____N, _____ ____.____W
Launch Time Window: _______:__________ ± ___________ minutes
Launch Site Forecast (at launch time):
High Altitude Wind Direction:
___________ knt
Temp:
High/Low:
________/_______°F
Surface Wind: ______/________mph
Clouds:
__________________
Precipitation: _______________%
UV Index:
__________________
Sunrise:
Other:
__________________
_______________F
_______________
_____ (direction)
Balloon Flight Simulation:
Ascent Rate:
________________ft/min
Burst Altitude:
________________ft
Descent Rate:
________________ft/min
Estimated Flight Duration:
________________minutes
Landings Site Bearing:
________________degrees
Landing Site Range:
________________miles
Latitude:
_____ ____.____N, _____ ____.____W
Longitude:
_____ ____.____N, _____ ____.____W
Landing Site Forecast:
Temp:
_______________F
High/Low:
________/_______°F
Winds:
______/________mph
Clouds:
_________________
Precip:
_______________%
UVI:
_________________
Expected Terrain: ________________________________________________________
Predicted Recovery Route:
_____________________________________________________
_______________________________________________________________________
Recorded by: _______________________
Wright State University
High Altitude Balloon Program
Flight No.: ____________________
Flight Date: _____/_____/________
ACTUAL FLIGHT
Launch Site: ________________________
_____ ____.____N, _____ ____.____W
Launch Site Conditions: ________________________________________________________
_______________________________________________________________________
Contents:
1. Command module:
□ TH-D7/GPS tracking
□ Camera
□ Screamer Circuit
□ Temperature logger
□ Other: _____________________
2. Experiment module: ________________________________________________________
_______________________________________________________________________
Balloon Flight:
Launch Time:
_____________________
Recovery Time:
_____________________
Ascent Rate (initial average):
_____________________ft/min
Ascent Rate (before burst average):
_____________________ft/min
Burst Altitude (Last GPS coordinate):
_____________________ft
Landing Site Bearing:
_____________________degrees
Landing Site Range:
_____________________miles
Landing Site Latitude:
_____ ____.____N, _____ ____.____W
Landing Site Longitude:
_____ ____.____N, _____ ____.____W
Flight Duration:
_____________________minutes
Landing Site Weather/Terrain Conditions: __________________________________________
_______________________________________________________________________
Additional Notes: ______________________________________________________________
_______________________________________________________________________
_______________________________________________________________________
Recorded by: _______________________
Wright State University
High Altitude Balloon Program
Flight No.: ____________________
Flight Date: _____/_____/________
POST-LAUNCH SYNOPSIS
______________________________________________________________________________
______________________________________________________________________________
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______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
______________________________________________________________________________
Recorded by: _______________________