Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
NSPO SMART PHONE AND PERSONAL SATELLITE CUBESAT
PLATFORMS: YAMSAT-2 &3
Chen-Joe Fong1＊, Albert Lin1, Ming-Shong Chang1, Yu-Lin Kuo1, Anson Tai2, Bo-Kai Huang1,
Randson Huang3, Henry Chen1, Hsiu-Ching Cheng1, Chian-Chian Liou1, Ching-Horng Lee1,
Vicky Wen1, Alex Wang2, Sen-Miao Chen2, 4, and Kevin Lee1
1
National Space Organization (NSPO), HsinChu, Taiwan
MoGaMe Mobile Entertainment Co. Ltd, Taipei, Taiwan
3
Chinese Taipei Amateur Radio League, Taipei, Taiwan
4
Dep. of Bio-Industrial Mechanics Engineering, National Taiwan University, Taipei, Taiwan
*
Email: [email protected]
2
ABSTRACT
The YamSat-1 was the first developed
picosatellite class CubeSat development
program in National Space Organization,
Taiwan. Since the YamSat-1 program, the
follow-on NSPO-built CubeSat program named
“YamSat-2 & 3” are 2U & 3U CubeSat
engineering development model platforms,
respectively, and all built from
commercial-off-the-shelf parts for advanced
technology demonstration and academically
educational purpose. The YamSat’s mission
objective is to develop a 2U CubeSat bus
platform for smart phone and ship traffic
tracking applications. And the YamSat-3
mission objective is to develop a personal
satellite 3U CubeSat platform for remote
sensing and GNSS-RO applications. The
candidate payloads of YamSat-2 & 3 include
Automatic Identification System, Automatic
Packet Reporting System, Remote Sensing, and
GNSS-RO payloads, high power LED/LD array,
and CMOS-based Tiny Remote Sensing
Instrument module with narrow and 360-degree
wide Field-of-View cameras, where image and
video data are downlinked through a dedicated
5.84 GHz high speed link. The programs also
include an amateur radio frequency band
YamSat ground station, a DIY software-defined
radio received-only 70 cm band ground station;
and a 5.84 GHz high-speed downlink ground
station. The spacecraft bus platform will consist
of the required subsystems to support the
mission. YamSat’s new experience gave fruitful
lessons learned and had opened up an
innovative avenue for conducting new
academic, educational, and low-cost space
research experiment to the follow-on CubeSat
satellites built in Taiwan’s universities. In this
paper we will describe the two-year follow-on
NSPO-built YamSat-2 & 3 CubeSat program of
its current status.
KEYWORDS: YamSat-2, YamSat-3,
CubeSat, Systems Engineering
1. INTRODUCTION
The first CubeSat design in the world (satellite
weight less than 1 kilogram, called picosatellite)
was proposed in 1999 by Jordi Puig-Suari of
California State Polytechnic University and
Bob Twiggs of Stanford University. The goal
of CubeSat was to enable graduate students to
be able to design, build, test and operate in
space. The first batch of CubeSats was
launched in June 2003 on a Russian Eurockot.
Since then it opened a new era of pico-satellite
development. (Heidt, 2000)
YamSat-1 is the first picosatellite class satellite
developed by National Space Organization,
A1
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
payload module, automatic packet reporting
system, and camera functions. In this paper, we
will describe the development of the YamSat-2
and YamSat-3 satellite program status. (Fong,
2014a-c, 2016a-d)
Taiwan. Different from the traditional system
engineering development, NSPO developed a
new satellite system engineering development
model and also opened a new rapid prototyping
system engineering method. At the time,
YamSat’s new experience gave fruitful lessons
learned and had opened up an innovative
channel for conducting new academic,
educational, and low-cost space research
experiment to the Pico and Nano satellites built
in Taiwan’s universities and research institutes.
(Lin, 2001; Fong, 2002; Hu, 2002)
2.YAMSAT MISSION
2.1 Satellite Mission Objectives
The main objectives of this YamSat-2 & 3
mission development are (Fong, 2014a-c):
- Complete technology demonstration of the
prototype model. After appropriate system
environmental tests (such as radiation,
thermal vacuum testing and the dynamic
testing), the prototypes can be changed into
a flight model and to be launched into space.
- The development of educational experiment
payload, scientific payload and engineering
payload will be combined with the
cooperation of industry, academia and
research to promote the space industry of
Taiwan's CubeSat satellite.
- Manufactured parts, components, assemblies,
or subsystems can be verified on the
engineering development model for further
use on different mission CubeSats.
Since 1999 after 17 years from the academy to
the promotion of the industry, CubeSats have
crossed over Death-of-Valley of technological
development the cost of a CubeSat is
significantly less and are easier to launch than
larger satellite. Scientific experiment can be
scaled down to a sizeable volume for a CubeSat
mission. And nontraditional satellite users in
academia, industry, and government agencies
now have options for accessing space. the
National Academies of Sciences, Engineering
and Medicine (in US) conclude that CubeSats
are already producing high value science, are
enabling new kinds of targeted measurements,
and can augment – but not replace – the
capabilities of large satellite missions and
ground-based facilities. (Jones, 2014; National
Academies, 2016)
2.2 YamSat Mission Trade-Off Analysis
The YamSat satellite program is to develop a
2U and 3U CubeSat engineering development
platform consisting of COTS components to
demonstrate the integration of advanced
technologies and to provide space applications
for academic education in universities. The
design standard for CubeSats is generally to use
the open hardware and software, and many
related technologies are available on the
Internet. Because the mission life is about a few
months, it is possible to combine with
commercial or automotive electronic
components. Table 1 shows the results of the
system trade-off update for the YamSat-3
satellite mission. (Fong, 2014a-c, 2016a-d)
After the development of the first YamSat (1A,
1B, 1C) in Taiwan, YamSat-2 & 3 are the two
R&D projects in the “NSPO Satellite Key
Technology Development Program.” Internal
R&D subproject, YamSat-2 is a smart phone
satellite R&D / verification sub-program,
YamSat-3 is a personal satellite R&D
sub-program. These two subprograms will
develop 2U and 3U CubeSat engineering
development platform consisting of COTS
components to demonstrate the integration of
advanced technologies and provide space
applications for academic education in
universities. The current candidate payloads for
YamSat-2 & 3 consists of self-developed
mobile phones and personal satellite
development platforms with smart phones, AIS
(Automatic Identification System) receiver
2.3 YamSat Satellite Characteristics
NSPO-developed YamSat-2 & 3 satellites will
establish a 5.84 GHz high-speed transmission
engineering development model and its ground
system. The future will be in a technical way to
A2
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
show the further development of multi-purpose
2U & 3U CubeSat flight prototype model.
Table 2 is the major characteristics of the
YamSat-2 & 3 satellite. (Fong, 2014a-c,
2016a-d)
ArduSat opens to the ground users to write a
variety of flight software and personal
experiments. So it is very suitable for
educational experiments. As for the Raspberry
Pi, which can be equipped with Linux OS,
more like the CubeSat enthusiasts. Space
improved version of the Raspberry Pie referred
to as AstroPi. Our program follows the current
international trends and transforms the Arduino
payload module into the AstroPi payload
module.
AstroPi has a class-6063 of aviation standard
aluminum shell, equipped with an 8-level color
LED matrix and 5 control button joystick.
There are a large number of sensors including
gyroscope, accelerometer, magnetometer,
temperature Sensors, atmospheric pressure
sensors, and humidity sensors. In addition, the
program’s AstroPi payload is equipped with a
visible light camera and a far-infrared camera.
The upper right corner of Figure 2 is the
sensing and control component that the AstroPi
payload instrument may be put in the program.
Figure 6 shows the AstroPi payload module.
2.4 YamSat Satellite System Architecture
Figure 1 and Figure 2 show the YamSat-2 & 3
satellite bus electrical system block diagram,
respectively. YamSat-3 satellite bus mechanical
structure is shown in Figure 3. Figure 4 & 5
show the YamSat-2 & 3 satellite engineering
model, respectively. (Fong, 2014a-c, 2016a-d)
3. SATELLITE PAYLOAD
The YamSat-2 & 3 program extends the
handset and personal satellite research to
develop space experiments and applications.
YamSat-2 candidate payload will include
self-developed smart phones, AIS payload
module, auto-packet reporting system (APRS)
and with the camera function of the mobile
phone CubeSat research and development
platform. The YamSat-3 candidate payload will
consist of a Tiny Remote Sensing Instrument
(TRSI) with a CMOS camera. The TRSI
contains an optical telescope system. The
captured image and video data from the TRSI
module is downlinked to the ground via a
high-speed 5.84 GHz transmitter. A set of open
source AstroPi payload modules that can
accommodate a variety of space sensors and a
set of high-brightness high-power LED/LD
(Laser Diode) array modules are adopted for
optical communication. A brief introduction is
described as follows. (Fong, 2014a-c, 2016a-d)
3.2 Tiny Remote Sensing Instruments (TRSI)
PC-104 Module
NSPO developed the TRSI (Tiny Remote
Sensing Instruments) shown in Figure 7. By
use of RPi dual CMOS Camera interface and
self-made space lens, with Omnivision 5647
500 million pixels, supports 1080P (maximum
resolution QSXVGA) powerful photographic
capability. Combine 5.8 GHz RF and data rate
up to 4Mbps through this telemetry module to
take photographs and photography that one can
be connected with the ground station image
data back. Using Pi4J program development
framework shown in Figure 8, the design
process to deal with multi-threaded scheduling,
receiving XML commands from the ground
station, and analysis. XML processing analysis
module, after analysis, we can see the type and
type of service to be executed (real-time
command / regular work services). NSPO XML
development framework used for the JAXB,
pre-designed XML Schema related through the
Binding Compiler generate the relevant
categories and interfaces. Then directly through
3.1 Arduino/AstroPi Payload Instrument
Module
NSPO develops with the open source systems
Arduino/Raspberry Pi payload module for a
variety of space sensors. Due to the open
source feature of Arduino that is the open
source systems including open hardware and
software, and a considerable number of sensing
and control module for its design. Arduino is
also the first to be used in the International
Space Station, a variety of space applications,
and later by ArduSat selection. After the launch,
A3
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
444.5 mm, occupying 2.5 U of the CubeSat.
Figure 12 shows the CubeSat structure frame
and telescope system design. In addition, we
must consider the diffraction phenomenon of
the telescope system. For the light through the
optical system imaging will produce the
phenomenon of diffraction in the focus of the
spot. This spot is called Airy Disk. The Airy
spot diameter must match the Pixel Size of the
CMOS sensor, otherwise the image is blurred.
From the formula (2), we can see that the
spatial diameter of the CIE system is about 7.83
μm, which is 5 times of the Pixel Size of the
CMOS sensor. Therefore, the imaging may be
slightly blurred and need to be analyzed by
optical simulation software.
the JAXB API Marshal / Unmarshal related
documents. In this way, in accordance with the
RF received from the xml command, the
dynamic generation of relevant XML file
instructions, designed to achieve
standardization. It is easy to expand and
ensure that the subsequent generation of
documents to meet the original XML
definition.
3.3 Tiny Remote Sensing Instruments (TRSI)
Optical Telescope Design
The CubeSat is planned to work in the 400 km
altitude orbit and the ground resolution of 2 m
to use Ov5647 series of CMOS sensor (see
Table 3). The Pixel Size is 1.4 μm. As for the
mirror selection, the aspheric mirror compared
to spherical mirror has a better set of light.
Because there is no domestically manufactured
aspherical mirror of the optical plant we chose
commercial Edmund reflector lens as a
CubeSat engineering telescope mirror group.
Based on the above requirements and
specifications, we design a suitable telescope
system for CubeSat. (Fong, 2016a-d)
(2)
By means of optical software simulation, we
can obtain the important performance indexes
of the system as shown in Table 6. The optical
modulation transfer function (MTF) is about
30% at 1/2 cut-off frequency. From formula (3),
we can calculate that the cut-off frequency is
about 357.14 lp/mm. From the image
simulation, we can observe to produce slightly
lattice-like image blur effect as shown in Figure
11.
The telescope system designed by a Cassegrain
telescope which is a reflective system
consisting of two sets of axisymmetric mirrors.
The design has the advantage of reducing the
long focal length system to a shorter
accommodation space. Figure 9 shows the
telescope system of the 3D architecture.
Based on the telescope requirement that the
orbit height is 400 km, the ground resolution is
2 m, the CMOS sensor Pixel Size is 1.4 μm and
the formula (1), the effective focal length of the
telescope system must be greater than 280 mm.
(3)
3.4 High Brightness and High Power LED /
LD Array Module
Manufactured by domestic academic
institutions as the experimental payload
mechanical configuration that mainly equipped
with high-brightness and high-power LED / LD
arrays and Laser Retro Reflector (LRR). In
addition to allowing the surface through the
surface of the receiver to see the surface of the
satellite’s LED light in the future, but also can
be transmitted Moss password based on its high
brightness characteristics. Its high-power laser
diode and LRR can be used for laser
communication and other academic education
experimental purposes.
(1)
For the selection of the lens, the primary mirror
is a parabolic mirror with a diameter of 76.1
mm and a radius of curvature of -889 mm. The
reflecting surface is aluminum-plated. The
secondary mirror is a plane mirror with a
diameter of 50 mm and a reflective surface of
aluminum (See Figure 10, Table 4 and Table 5).
The effective focal length of the lens group is
A4
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
5.84 GHz band. For ground station video
transmission system, the ground receiving
station includes 5.84 GHz high-speed system,
the receiving antenna feed head and RF
low-frequency signal down-converter circuit
low noise block (LNB) development.
3.5 Custom AIS Payload
Currently the reason to select AIS Receiver
communication is as follows:
- Monitoring of marine vessels in accordance
with Taiwan needs
- Users of the public, with business
opportunities
- Domestic manufacturers AIS receiver,
technology is mature
- Familiar with AIS system and data
processing
- Wide range of antenna transmission and
reception, low requirement for satellite
attitude control that is available with B dot
magnetic control
Table 7 shows the specifications of the AIS
receiver verification version. (Fong, 2016cd)
5.2 Self-Developed 70 cm Band Software
Radio Receiver Ground Station
The self-developed 70 cm band software radio
receiver ground station system consists of a
70-cm (430 MHz) 8-Elements linear
polarization Yagi antenna, a low-noise linear
amplifier (LNA), a FunCube Dongle Pro +
software radio receiver, or a Realtek radio
receiver RTL SDR TV Stick, Raspberry Pi open
source personal computer. The system block
diagram of the software radio receiver ground
station for the entire 70 cm (430 MHz) band is
shown in Figure 14.
4 SATELLITE BUS
YamSat-2 & 3 program satellite bus will
include the required subsystems to support this
task, including the Power Subsystem (EPS), the
Attitude Control Subsystem (AOCS) with
high-speed transmission links and 430 MHz
Frequency band of the amateur radio
communication subsystem (COMM), a satellite
data processing subsystem (OBDH) with a
smart phone as a backup, an engineering
structure mechanical subsystem (SMS) for 3D
printing and a flight software subsystem (FSW).
Please refer to the detailed system design
references. (Fong, 2014a-c, 2016a-d)
5.3 YamSat Ground System
Figure 15 is the NSPO YamSat satellite ground
station system. This project will require the
system to work with the independent
development of the second generation of
intelligent mobile phone functionality of the
personal satellite experimental engineering
body and open source system ground station to
process the software operating system and
application upgrades.
5. YAMSAT GROUND SYSTEM
6. CONCLUSION
The YamSat satellite program Ground System
includes: (Fong, 2014a-c, 2016a-d)
• A 5.84 GHz band high-speed ground
receiving station system,
• Self-made 70 cm amateur radio frequency
band for the software radio receiver ground
station system, as well
• YamSat amateur radio ground station system
update.
In this paper, we describe the origin of the
satellite mission of the YamSat series satellite,
and the main objectives of its future
development. Also we describes possible
satellite payloads for the tasks of YamSat-2 & 3.
This paper describes the design of small-scale
CMOS remote sensing camera (TRSI) PC-104
module and optical telescope. NSPO's
self-developed satellite experimental
engineering model and open source system
ground station. Hoping to make the relevant
development of educational experiment
payload, scientific payload and engineering
payload will combine the industry and
5.1 Remote Sensing Instruments High Speed Receiving Ground Station System
Figure 13 shows a high-speed ground receiving
station system with a diameter of 1 meter in the
A5
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
CubeSat Platform for Remote Sensing &
GNSS-RO Mission,” ICEO&SI 2016, PW-4,
Keelung, Taiwan, 26-28 Jun. 2016.
academia research and mutual cooperation to
promote the future of Taiwan’s personal
satellite space industry.
Fong, C.-J., Lin, A., Chang, M.-S., Kuo, Y.-L. ,
Tai, A., Huang, B.-K., Huang, R., Chen, H.,
Cheng, H.-C., Liou, C.-C., Lee, C.-H., Wen, V.,
Wang, A., and Lee, K. 2016c. “NSPO
YamSat-2 & 3 CubeSat Platforms,” INSPIRE
Workshop, Chongli, Taiwan, 20-22 Jul. 2016.
7. REFERENCES:
Fong, C.-J., Lin, A., Shie, A., Yeh, M., Chiou,
W.-C., Tsai M.-H., Ho, P.-Y., Liu, C.-W., Chang,
M.-S., Pan, H.-P., Tsai, S., Hsiao, C., Hwang
C.-H., Chang-Liao K.-S., and Wang L.-K.,
2002. “Lessons
Learned of NSPO’s
Picosatellite Mission: YamSat - 1A, 1B & 1C”,
The 16th Annual AIAA/USU Conference on
Small Satellites, Aug. 2002.
Fong, C.-J., Chang, M.-S., Lin, A., Kuo, Y.-L.,
Chen, H., Huang, B.-K., Cheng, H.-C., and Lee,
C.-H. 2016d. “YamSat-2 & 3: NSPO Smart
Phone and Personal Satellite CubeSat
Platforms,” Vol. 17-04, Kangshan Kaohsiung, 5
Nov. 2016.
Fong, C.-J., Chang, M.-S., Chen, H., Cheng,
H.-C., Kuo, Y.-L., Liou, C.-C., and Yang, E.
2014a. “NSPO CubeSat Personal Satellite
Development for Space Application”, 2014
AASRC, E13, Tainan, Taiwan, 15 Nov. 2014.
Heidt, H., Puig-Suari, J., Moore, A.S.,
Nakasuka, S., Twiggs, R. J. 2000.“CubeSat: A
new Generation of Picosatellite for Education
and
Industry
Low-Cost
Space
Experimentation”, Proceedings of the 14th
Annual AIAA/USU Conference on Small
Satellites, Logan, Utah, USA, 13-16 Aug. 2000.
Fong, C.-J., Chang, M.-S., Chen, H., Cheng,
H.-C., Kuo, Y.-L., Liou, C.-C., and Yang, E.
2014b. “Personal Satellite Research and
Development for Space Experiment and
Application (PSRDSEA),” RSSTW 2014,
Hsicchu, Taiwan, 20 Nov. 2014.
Lin, A., Chang, Chang, C.-L., Tsai, S., Fong,
C.-J., Chang, C.-P., Lin R., Liu, C.W., Yeh, M.,
Chung, M.-H., Pan, H.-P., and Hwang, C.-H.
2001. YamSat: the First Picosatellite being
Developed
in
Taiwan,
SSC01-VIIIb-8,
Proceedings of the 15th Annual AIAA/USU
Conference on Small Satellites, Logan, Utah,
USA, 13-16 Aug. 2001.
Fong, C.-J. Chang, M.-S., Chen, H., Cheng,
H.-C., Kuo, Y.-L. Liou, C.-C., and Chang, G.-S.
2014c. “NSPO Personal Satellite Engineering
Development
Model
for
Technology
Demonstration and Education Application,”
2014 Taiwan-Russia Joint Symposium, Taiwan,
22 Dec. 2014.
Jones, N. 2014. “Mini satellites prove their
scientific power,” Nature, Vol. 508, 17 Apr.
2014, pp. 300~301.
Fong, C.-J. Lin, A., Chang, M.-S., Kuo, Y.-L. ,
Tai, A., Huang, B.-K., Huang, R., Chen, H.,
Cheng, H.-C., Liou, C.-C., Lee, C.-H., Wen, V.,
Wang, A., and Lee, K. 2016a. “YamSat-2 & 3
CubeSat Engineering Development Model of
Technology Demonstration for Remote Sensing
& GNSS-RO Mission,” ICGPSRO 2016,
F0014, Taipei, Taiwan, 9-11 Mar. 2016.
National Academies of Sciences, Engineering,
and Medicine. 2016. Achieving Science with
CubeSats: Thinking Inside the Box.
Washington, DC: The National Academies
Press. doi:10.17226/23503.
Fong, C.-J. Lin, A., Chang, M.-S., Kuo, Y.-L. ,
Tai, A., Huang, B.-K., Huang, R., Chen, H.,
Cheng, H.-C., Liou, C.-C., Lee, C.-H., Wen, V.,
Wang, A., and Lee, K. 2016b. “YamSat-2 & 3
Table 1. System Trade-Off for the YamSat-3
satellite mission (Trade-Off)
A6
Remote Sensing Satellite Technology Workshop 2016
Mission
Payload
Orbit
Mission Life
Weight
Model
Arduino payload
Instrument Module
400km x 60 deg
1 month
1 kg
EDM (Engineering
Development
Model)
High brightness / pow er
LED/LD array
800 km x 97 deg
3 month
2 kg
FM (Flight
Model)
CubeSat
Tiny remote sensing
instrument (TRSI) module
300 km
6 month
3 kg
PocketQube
Smart Phone
Design Life
Solar Cell
Battery
3 month
GaAs
Triple-junction
Li-Ion
AX.25
1 month
Si
Ni-H2
CCSDS
Structure
Ground
Aluminum
6061-T6
Aluminum
7075-T6
Stacks of PCBs
follow ing PC/104
standard
Upgraded YamSat
ground station
70 cm DIY SDR
ground station
PSRDSEA
(Personal Satellite
Research &
Development
Experiment &
Application)
Nov. 28, 2016
Table 5. 25mm Diameter, Enhanced Aluminum,
Flat Mirror
PFM (Proto
Flight Model)
QM (Qulification
Model)
TubeSat
Method
DIY
DIT (Do-It-Together)
Crow d Sourcing
Volume
1U
(10cm x 10cm x 10cm)
2U
(10cm x 10cm x 20cm)
3U
(10cm x 10cm x 30cm)
Communication
Si-Zn
Communication (DL)
Communication (UL)
AOCS
On Board Computer
DL: 5.84GHz
UL: 1.28 GHz
GPS Receiver
Open systems
DL: ~ 430MHz
UL: ~ 430MHz
IMU
RaspBerry Pi 2.0
DL: 144 MHz
UL: 144 MHz
Magnetometer
Smart Phone
Magnetic Torquer
3D-Printing
5.84GHz high-speed
DL ground station
1.28 GHz UL Ground
Station
Reaction Wheel
Table 6. Key performance indicators of
CubeSat telescope system
Start Tracker
Sun Sensor
Requirement of Telescope
Table 2. The major characteristics of the
YamSat-2 & 3 satellite
Orbit (km)
400
GSD (m)
2
EFL (mm)
444.5
MTF (%)
30 % @ ½ Cutoff frequency
(Cutoff frequency = 357.14)
Specification of Sensor
Pixel Size (um)
1.4 x 1.4
Active Array Size
2592 x 1944
Image Area (um2 )
3673.6 x 2738.4
Specification of Mirror
M1
M2
R (mm)
-889.0
Inf
D (mm)
76.2
50
K
-1
－
Substrate
BOROFLOAT®
Coating
Enhanced Aluminum
Table 7. Custom AIS receiver function
verification version specification
Table 3. CMOS sensors dominant performance
indicators
Table 4. 3 Diameter x 17.5 FL, Enhanced
Aluminum, Parabolic Mirror
Figure 1. YamSat-2 satellite bus electronic
system block diagram
A7
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
Figure 2. YamSat-3 satellite bus electronic
system block diagram
Figure 5. YamSat-3 satellite engineering model
platform
Figure 3. YamSat-3 satellite bus mechanical
configuration
Figure 6. AstroPi payload instrument module
Figure 7. Tiny Remote Sensing Instrument
(TRSI) PC-104 Module
Figure 4. YamSat-2 satellite engineering model
platform
Figure 8. TRSI Service framework
A8
Remote Sensing Satellite Technology Workshop 2016
Nov. 28, 2016
Figure 13. High-speed receiver ground-station
system
Figure 9. YamSat-3 satellite telescope system
3D architecture
Figure 10. YamSat-3 satellite telescope system
2D architecture
Figure 14. 70cm band software radio receiver
ground station system
Figure 15. NSPO YamSat ground station
Figure 11. Optical simulation software analysis
results
Figure 12. Design of YamSat-3 satellite
structure frame and telescope system
A9