Maverick Rocket
PDR Presentation
4 NOV 16
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Team and Mission Selection
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Team Members
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Nicholas Ramzi: Team Lead (Aerospace Engineering, Class of 2017)
Tate Turner: Team Co-Lead, Sub-Scale Lead (Aerospace Engineering, Class of 2017)
August Uecker: Avionics and ATDLS Lead (Electrical Engineering, Class of 2017)
Jeremiah Robbins: Structures Officer (Mechanical Engineering, Class of 2017)
Brian Kennedy: Safety Officer (Aerospace Engineering, Class of 2017)
Austin Jomp: Propulsion Officer (Aerospace Engineering, Class of 2017)
Jon Pullum: Recovery Officer (Aerospace Engineering, Class of 2017)
Lorenzo Armstrong: Avionics and Design Testing Officer (General Engineering, Class of 2017)
Mentor: CAPT Trip Barber, USN (ret) NAR Level 3
Faculty Rep: Major Kristen Castonguay, USAF
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Mission and Charter
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The vision of Navy Rockets is to:
• Supplement academic material in both the aerospace and engineering fields
• Expand each midshipmen’s knowledge and experience to become more proficient and
well- rounded members of the engineering community
• Provide leadership opportunities in a technical environment to better serve midshipmen
as future leaders in today’s Navy
As a team we strive to:
• Seek out projects that can benefit the aerospace community and reinforce our own
educational objectives
• Deliver quality research and products on time, based on sound engineering and
business practices, and operate to a level above client expectation
As representatives of the armed services we will:
• Conduct ourselves in a professional manner and bring credit to both the United States
Naval Academy and the United States Naval service.
We are committed to excellence in practice, delivery, and conduct.
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Chosen Mission
3.2. Target detection and upright landing
3.2.1. Teams shall design an onboard camera system capable of identifying and differentiating
between 3 randomly placed targets.
3.2.1.1. Each target shall be represented by a different colored ground tarp located on the
field.
3.2.1.2. Target samples shall be provided to teams upon acceptance and prior to PDR.
3.2.1.3. All targets shall be approximately 40’X40’ in size.
3.2.1.4. The three targets will be adjacent to each other, and that group shall be within 300
ft. of the launch pads.
3.2.2. After identifying and differentiating between the three targets, the launch vehicle
section housing the cameras shall land upright, and provide proof of a successful
controlled landing.
3.2.3. Data from the camera system shall be analyzed in real time by a custom designed onboard software package that shall identify and differentiate between the three targets.
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Flight Plan
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CP 1, Maverick Launch
CP 2, at apogee, lower motor section separates
CP 3, the lower section of Maverick will fall under
drogue parachute until an altitude of 1000 ft.
AGL.
CP 4, the lower section main chute will deploy
and will control the descent to 0 ft. AGL.
CP 5, 3 seconds after apogee, the middle and
upper sections will separate.
CP 6, the upper section of Maverick will fall
under drogue parachute until an altitude of 1000
ft. AGL.
CP 7, the upper section main chute will deploy
and will control the descent to 0 ft. AGL.
CP 8, the Drone section of Maverick will fall
under drogue parachute until an altitude of 1000
ft. AGL.
CP 9, at 1000ft AGL, the Drone Section main
chute will deploy. This will carry the drone down
to 500ft AGL while the drone arms are deployed
and initial power is applied. With confirmation of
deployment and the RSO’s approval we will
separate the Drone Section main chute, and the
Drone Section will have a controlled descent by
Drone Power to 0ft AGL. The Drone Section
Parachutes will fall by itself to 0ft AGL after
separation from the Drone Section.
CP 10, the detached parachute will descend and
land
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Maverick Design
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• Carbon fiber
Body
- 6” inner diameter
- 6.15” outer diameter
SEP 1
• 3 distinct body sections
• Stability Margin: 2.08
CG
SEP 2
CP
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Fin Sleeve
• 3D Printed Ultem
• Fins will be 90⁰ apart
• Secured using 8 1.5” galvanized
steel bolts
• Allows for quick replacement and
lowest weight margin
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Propulsion
• Cessaroni K1440 (Primary)
• Cessaroni K660 (Secondary)
• Alternatives: Aerotech K700
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RockSim Simulations
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Recovery
• Drogue parachutes: 30” Fruity Chute
• Main parachutes: 72” Fruity Chute
• Descent rate for a 10 lb section of the
rocket: Approximately 12 ft /sec
• NOMEX parachute
liners
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Recovery
-Material:
-3D Printed Ultem
-Mechanics:
- Will house all parachutes, drogues, and
tubular nylon for deployment
-Pushed flush with drone to prevent collision
forces
-Testing:
- Ground ejection testing will be used to
mitigate potential tangling during separation
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Control Avionics
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Flight separation
Chute deployment
Altimeters
GPS
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Avionics Bay
• Must be able to be inserted and
removed quickly
• Must be able to be turned on
from an external switch
• Must be able to be quickly
replaced for re-build
requirement
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Automatic Target Detection and Landing System
ATDLS Design
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Launch Configuration
ATDLS
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Apogee Configuration
- At apogee the rocket will
split into 3 sections
- Each section will have a
drogue that will deploy
immediately after separation
- At 1000 ft AGL the main will
deploy
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Descent and Landing Configuration
- Middle section of Maverick Rocket will
perform landing
- Bottom (motor) section will land under
a main parachute with GPS tracking
- Top (nose cone) section will land under a main
parachute with GPS tracking
- After target detection, the ATDLS will
descend to the ground for an upright landing
- Will not be separated from section’s main
parachute unless given explicit permission
from the RSO
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Arms
-Material:
-machine cut aluminum to ensure
maximum strength with lowest weight
fraction
-Mechanics:
-Arms rotate 90⁰ from vertical to a
position of 90 degrees off Z-axis
-Arms will stop through use of a pawl
-Testing:
-drop tested to ensure pawl is secure in
the forces of flight.
-Ground separation testing will be done
to ensure consistent deployment free of
tangling
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Legs
Materials:
- Legs will be made out of machine cut
aluminum
Deployment:
- Legs will rotate 30 degrees off the vertical
to stop 150 degrees of the z-axis
- Legs will rotate 30 degrees off the vertical
to stop 150 degrees of the z-axis
- Legs will stop via the use of a McMaster
Carr spring piston with a ½” stroke
- Legs will be made with a 30 degree cut on
bottom to ensure upright landing
Testing:
- Legs will be drop tested to ensure the spring
piston can withstand the forces of flight and
landing maneuvers
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UAV Design Components
-Spider SP2212 Motors
-ZTW Flash 30a ESC
-Turnigy 3300mAh Battery
Pack
-Multirotor Carbon Fiber
Props
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UAV Control Hardware
• Lumenier Lux Quad Mixer
• Raspberry Pi 3B Main Processor
• Mobius Wide Angle Action Camera
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ATDLS PROGRAM LOGIC
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Material and Experimental Tests
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Wind Tunnel Testing
• Testing will be conducted on a subscale
design
• The scale model testing will take place
inside the Open Circuit Wind Tunnel in
Rickover Hall.
• Rocket will be mounted to the sting
balance, with pressure ports longitudinally
along the rocket’s nose cone to measure
pressure distribution .
• The objective of this experiment is to
analyze the aerodynamic stability of the
rocket used and measure coefficient of
drag
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Avionics Testing
• Communication system will be tested by doing signal test at 3 miles with
rocket in launch pad and recovery configurations
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Testing different ground station antennas for best orientation
• Drone Flight characteristics will be tested using Drone section
controlled by radio controller
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Test to determine max climb rate, controllability of drone
Results used for control laws
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Ground Ejection Testing
• In order to ensure the proper separation at apogee the separation charges
will be deployed on a ground test stand
• Success Standards:
1. Proper and consistent deployment
2. Tangle free deployment with ATDLS protruding components
3. Ability to reset the test within 1 hour to simulate competition timing
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Sub-Scale Launch
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Purpose: To test leading design in an actual launch to test feasibility at the full scale level
Completion and Success thresholds:
1. Separate at apogee into three sections mimicking the separation in the full scale
design
2. Deploy the landing legs into landing configuration in accordance with the full scale
flight plan determined altitude
3. Deploy all drogue parachutes at apogee
4. Successfully use the tender descender to initiate deployment of the main parachute
at 1000 ft. AGL
5. Successfully deploy main parachute and land all three sections under main
parachute
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Safety
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Operational Risk Management Matrix
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Major Risks
• Stage Separation Failure – Risk Assessment: 1E
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Redundant separation charges
• Technological Failure in Raspberry Pi – Risk Assessment: 1E
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Redundancies in programming
Power supply checks
• Quadcopter Spin-up Failure – Risk Assessment: 3C
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Parachute de-coupler will not detach until quadcopter achieves full power
Worst Case: all components will descend under parachute
• Parachute Deployment Failure – Risk Assessment: 1D
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Multiple tests in code and subscale launches will be carried out to ensure it is properly
functioning
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Major Dates and Milestones
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18 NOV- Sub Scale Due
18 NOV- Sub Scale Review with Mentor
19 NOV- Sub Scale Launch*
16 DEC- CDR Draft
13 JAN- CDR Final
13 FEB- Full Scale Due
17 FEB- Full Scale Review with Mentor
18 FEB- Full Scale Launch*
*Tentative on feedback from Mentor review
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Questions?
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