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University of
Alabama in
Huntsville
NASA SL
Critical Design
Review
University of Alabama in Huntsville
USLI CDR11/16/2018
LAUNCH VEHICLE
University of Alabama in Huntsville
USLI CDR21/16/2018
University of Alabama in Huntsville
USLI CDR31/16/2018
Vehicle Summary
• Launch Vehicle Dimensions– Fairing Diameter: 6 in.– Body Tube Diameter: 4 in.– Mass at lift off: 43.8 lbm. – Length: 103 in.
• Concept– L-Class Solid Commercial Motor– Rover Delivery– Electronic Dual Deployment– Fiberglass Airframe
Vehicle CONOPS
11/3/2017University of Alabama in Huntsville
USLI PDR4
Powered Ascent:
0 – 3.3 seconds
0 – 1,190 ft.
Deploy Drogue:
19 seconds
5,429 ft.
Deploy Main:
62 seconds
600 ft.
Landing:
121 seconds
0 ft. Deploy Rover:
Team Command
University of Alabama in Huntsville
USLI CDR51/16/2018
Vehicle Summary
Rover Piston Main
Parachute
Drogue
Parachute
Coupler
12 in.
Tracking/Rover
Deployment
Avionics
Fins (x4)
Recovery
Avionics
Forward
Airframe
30 in.
Aft
Airframe
42 in.
Payload
Fairing
36 in.
CG
56 in.
CP
69 in.
• Upper Airframe houses the rover, piston ejection system, and GPS tracker
Upper AirframeOverview
University of Alabama in Huntsville
USLI CDR61/16/2018
• 6 in. elliptical shape; 6.17 in. OD;
• ABS Plastic; 3-D printed in-house
• 1.75 in. shoulder; shear pinned to fairing
• 0.25 in. Aluminum bulkhead
Nose Cone
University of Alabama in Huntsville
USLI CDR71/16/2018
• Houses payload and deployment device
• Fiberglass; 6.17 in. OD, 6 in. ID
• Shear pinned to nose cone; 10-32 bolt connection to transition
Fairing
University of Alabama in Huntsville
USLI CDR81/14/2018
Transition
University of Alabama in Huntsville
USLI CDR9
• Three piece design, two 3D printed ABS plastic, one 0.5 in. thick aluminum bulkhead
• Each piece has holes for threaded inserts• Held together using ¼-20 and 10-32 bolts
Forward Insert Aft
1/16/2018
Transition
University of Alabama in Huntsville
USLI CDR10
• Three piece design allows for a 57% reduction in weight
• Max stress on aluminum bulkhead: 0.712 ksi• Yield stress: 42 ksi
1/16/2018
• Connects 4 in. body tube to the 6 in. fairing
• U-bolt for recovery harness attachment point
• Shear pins connect to 4 in. body tube
• Threaded rod with hex nuts for connection to fairing
Transition Coupler
University of Alabama in Huntsville
USLI CDR111/16/2018
• CO2 Powered – 12 gram cartridge
• Spring driven spike used to release stored gas
• 60 lbf. test monofilament fishing line used as arming tether for spring
• Hot wire cuts tether to release spring
• Two main components: piston head and CO2
housing
Piston Overview
University of Alabama in Huntsville
USLI CDR121/16/2018
• Ejects rover and nose cone
• Fiberglass coupler with aluminum bulkhead
Piston Head
University of Alabama in Huntsville
USLI CDR131/16/2018
• Houses CO2 cartridge and release mechanism
• 3D printed ABS Plastic
• Allows for easy and quick modification upon testing results
CO2 Housing
University of Alabama in Huntsville
USLI CDR141/16/2018
• CO2 housing positioned in transition shoulder
• Mounted to side using 3-D printed brackets and 4-40 bolts
• Keeps housing fixed during flight
Piston Configuration
University of Alabama in Huntsville
USLI CDR151/16/2018
• Aft Subsystem Components
Aft Subsystem Overview
University of Alabama in Huntsville
USLI CDR16
Recovery Bulkhead & U-Bolt
Fin(s)Fin Can Thrust Plate
Motor Retention RingMotor/Motor Case
1/16/2018
• Trapezoidal Fin Set (4)
– Maintain stability
• G10 Fiberglass
– Great strength/weight ratio
– 3/16” thickness
• Flutter Speed
– Calculated to be Mach 1.947 (2191.57 ft./sec)
Fins
University of Alabama in Huntsville
USLI CDR171/16/2018
• 4 bolts perpendicular to fin face
• 6 bolts normal to body tube to hold shape
– Also used to hold fin can in vehicle
• Entire assembly can
be removed
Fin Interface
University of Alabama in Huntsville
USLI CDR181/16/2018
Fin Can Assembly Overview
• Consists of: Fin Can, Motor Retention Ring, Thrust Plate, and Rail Button Press fit nut
University of Alabama in Huntsville
USLI CDR191/16/2018
Exploded View of the Fin Can Assembly
University of Alabama in Huntsville
USLI CDR201/16/2018
Fin Can
• 3D Printed in house
• Material: ABS plastic
• Purpose: Fin retention and centering of the motor
• Attached to the body tube using 4-40 bolts which maintain the shape of the Body tube
University of Alabama in Huntsville
USLI CDR211/16/2018
Fin Can Dimensions
University of Alabama in Huntsville
USLI CDR221/16/2018
Thrust Plate
• Machined in house
• Material: 6061 Aluminum
• Purpose: Transfer motor thrust to the airframe
• Attached to the fin can using the motor retention bolts
• Part was added due to concern of shearing the Fin Can while duringmotor burn
University of Alabama in Huntsville
USLI CDR231/16/2018
Thrust Plate Dimensions
University of Alabama in Huntsville
USLI CDR241/16/2018
Motor Retention Ring
• 3D printed in house
• Material: ABS plastic
• Purpose: Motor retention
• Attached to the fin can using the motor retention bolts
• Aft retention was chosen due to the difficulty of disassembling the forward retention system
University of Alabama in Huntsville
USLI CDR251/16/2018
Motor Retention Ring Dimensions
University of Alabama in Huntsville
USLI CDR261/16/2018
• Aerotech L1420R-PS
– Best met altitude target
• Avg. Thrust: 326.18 lbf.
• Burn Time: 3.2 sec
Motor Selection
27
Motor Altitude
Aerotech L2200 6107 ft.
Aerotech L1420 5429 ft.
Aerotech L1520 4329 ft.
1/16/2018University of Alabama in Huntsville
USLI CDR
• Dimensions
– Total length – 103 in.
– Wet mass – 43.80 lbm.
– CP location – 68.93 in.
– CG location – 55.60 in.
OpenRocket Flight Simulation
28
55.60 inches
68.93 inches
1/16/2018University of Alabama in Huntsville
USLI CDR
Stability Margin
29
Motor Burnout (3.28 cal.)
Initial Stability (2.22 cal.)
Apogee
1/16/2018University of Alabama in Huntsville
USLI CDR
OpenRocketFlight Simulation
11/3/2017University of Alabama in Huntsville
USLI PDR30
Attribute Value
Apogee (ft.) 5429
Length (in.) 103
Max. Mach Number 0.60
Rail Exit Velocity (ft./s) 60.6
Static Stability (cal.) 2.22
Motor Designation AT L1420R – P
Thrust-to-Weight Ratio 8.7
CG 56 in.
CP 69 in.
OpenRocket Flight Simulation
31
Motor Burnout (3.27 sec.)
Apogee (18.62 sec.)
Main Deploy (62.39 sec.)
1/16/2018University of Alabama in Huntsville
USLI CDR
• 1-D method used to verify OpenRocket sim
– Goal: Determine uncertainty in projected altitude
– Randomly varies conditions by a percentage
▪ drag coeff., vehicle mass, propellant mass, case mass
▪ Varied between ±6.25% and ±2.5%
– Use drag coefficient from subscale flight
▪ 𝐶𝑑 = 0.56
– 10,000 flights per simulation
Full Scale Monte Carlo Simulation
321/16/2018University of Alabama in Huntsville
USLI CDR
Full Scale Monte Carlo Simulation
33
Mean: 5626.31 feet
Median: 5617.45 feet
Std. Deviation: 192.29 feet
Max Altitude: 6463.91 feet
Min. Altitude: 5010.83 feet
1/16/2018University of Alabama in Huntsville
USLI CDR
• Central Subsystem responsibilities:
– Coupler between airframes
– Flight Avionics
– Ejection System
– Tracking and Ground Station
– Recovery System
Central Subsystem Overview
341/16/2018University of Alabama in Huntsville
USLI CDR
Drift Analysis
Vwind
35
• Monte Carlo Drift Model
– Assumes:
• Apogee is directly above the launch rail
• The parachute does not open immediately
• The drift distance stops once a component lands
• Horizontal acceleration is solely based on relative velocity
• Drogue parachute is negligible once the main is fully deployed
Vrelative
Wind Speed (mph) 0 5 10 15 20
OpenRocket Drift
Distance (ft)17.6 465.8 946.7 1461.9 1995.7
CRW Model Drift
Distance (ft)0 573.19 1148.9 1741.9 2311.8
1/16/2018University of Alabama in Huntsville
USLI CDR
• Requirement: No individual section will have a kinetic energy greater than 75 ft.-lbf. upon landing
• Terminal velocity under drogue: 112.7 ft./sec.
• Terminal velocity under main: 17.45 ft./sec.
Recovery System Calculations
36
Vehicle
Section
Mass (lbm.) KE (ft.-lbf.)
Fairing 14.35 67.85
Coupler 11.15 52.72
Aft 9.89 46.76
1/16/2018University of Alabama in Huntsville
USLI CDR
• Drogue Parachute Deployment:– Deployment at apogee– Fruity Chute CFC-18 (Cd = 1.5)– Shock Cords: 1 inch Nylon (50 ft)– Connected between forward motor
retention bulkhead in lower airframe and avionics bay housing.
– Descent speed under drogue: 112.7 ft/s
• Main Parachute Deployment:– Deployment at 600 ft above ground
level– Fruity Chute 96” Iris Ultra (Cd = 2.2)– Shock Cords: 1 inch Nylon (50 ft)– Connected between fairing
bulkhead and avionics bay housing. – Descent speed under main: 17.45
ft/s
Recovery System
371/16/2018University of Alabama in Huntsville
USLI CDR
Recovery Avionics Subsystem
• 2 PerfectFlite StratoLoggerCF altimeters; each with an independent 9V battery and pull pin + SPDT momentary activation switch
• 4 Safe Touch terminals, e-matches, and black powder charges
• Full redundancy in avionics and ignition
Avionics
381/16/2018University of Alabama in Huntsville
USLI CDR
Coupler
391/16/2018University of Alabama in Huntsville
USLI CDR
Charge Well
U-Bolt
Screw Terminal Strip
Flight Computer
Batteries
RBF Switches
12 in.
Recovery Deployment Avionics
40
• Normally Closed SPDT Pull Pin Microswitch– Prevents ignition during assembly– Helps preserve battery life
• Primary Drogue charge fired at apogee– Secondary fired one second after
• Primary Main charge fired at 600 ft.– Secondary fired at 550 ft.
• Primary charges contain 4 g. of black powder
• Secondary charges are 2 g. larger than primary
1/16/2018University of Alabama in Huntsville
USLI CDR
GPS Tracking & Rover Deployment Subsystem
41
System• CRW will use a custom PCB that contains an Xbee Pro-PRO
900HP RF module, Teensy LC, and MTK3339 GPS Chip
• Xbee transmits GPS coordinates to a receiver connected to the ground station laptop
• GPS sentences are parsed and written to file for flight data
• Rover Deployment Electronics operated via XBee
Structure Integration• 3D printed mount to secure tracker and deployment
electronics PCB within transition section of the rocket
• Three axis security and battery retention to ensure components are kept intact
1/16/2018University of Alabama in Huntsville
USLI CDR
Subscale Design
42
Scaling Factors:• Geometry of the design• Average Thrust of Motor and Thrust Curve• Kinetic Energy
1/16/2018University of Alabama in Huntsville
USLI CDR
• Successful recovery of all three subscale flights
• Altimeters ignited the black powder charges at the correct altitudes
Subscale FlightResults
431/16/2018University of Alabama in Huntsville
USLI CDR
• Flight 1- Apogee 2884 ft., some weathercocking
• Flight 2- Apogee 2323 ft., severe coning
• Flight 3- Apogee 3165 ft., vertical flight
Subscale FlightResults
441/16/2018University of Alabama in Huntsville
USLI CDR
• Using data gathered from the altimeters, the drag force and coefficient for the vehicle were found
• Using a weight of 6.33 lbs, an acceleration of 60.128 ft/s, an A of 0.0533 ft2, a 𝜌of 0.0751 lb/ft3, and a velocity of 396.55 ft/s:
– Cd = 0.56
SubscaleDrag Coefficient
451/16/2018University of Alabama in Huntsville
USLI CDR
▪ A = Area of the exposed section, ft2
▪ 𝜌 = density of the air, lbm/ft3
▪ Cd = Coefficient of Drag▪ u = Velocity, ft/s▪ m = mass, lbm▪ A = acceleration of the vehicle, ft/s2
▪ g = acceleration of gravity, ft/s2
• Diameter: Deployed 16.2 in., Integrated 5.7 in.
• Rover Length: 14.6 in., Chassis Length: 12 in.
Payload
461/16/2018University of Alabama in Huntsville
USLI CDR
• Rover fits inside the piston, which ejects it from the fairing
• CO2 cannister pushes rover through nose cone
Payload Integration
471/16/2018University of Alabama in Huntsville
USLI CDR
1. The rover is ejected from the rocket
2. Wheels deploy and rover moves 10 ft.
3. Rover stops and deploys solar panels
Payload CONOPS
481/16/2018University of Alabama in Huntsville
USLI CDR
1
3
2
• Stores and protects tray of rover electronics
• 12 in. x 4 in. x 3 in., Aluminum 6061-T6
• Machined from single Aluminum block
• Connects to motors, electronics tray, and solar panel lid
Chassis
491/16/2018University of Alabama in Huntsville
USLI CDR
• Spokes pulled by springs to expand wheel
• Wheel hub and spokes CNC milled aluminum
• Integrated Diameter: 5.7 in.
• Deployed Diameter: 16.2 in.
• Spoke 6 in. x 0.5 in. x 0.25 in.
Wheel
501/16/2018University of Alabama in Huntsville
USLI CDR
• Used to keep chassis upright during deployment
• 3D printed ABS
• 11 in. x 0.25 in. x 0.5 in.
• Mounts to chassis using a hinge
• Torsion spring pushes out after deployment
Stabilizing Arm
511/16/2018University of Alabama in Huntsville
USLI CDR
• This table details the normal load cases for each structural component
• The wheel hub is the weakest component but can withstand a 73% load increase
Strength Check Notes
52
Part Load Case Safety Margin
Chassis 210 lbf (sidewall) +2.45
Chassis 210 lbf (base) +1.37
Wheel Hub 210 lbf (sidewall) +0.73
Wheel Hinge 105 lbf (each) +5.11
Spoke 210 lbf (lengthwise force) +11.98
Spoke 7 lbf (Drive force) +6.42
1/16/2018University of Alabama in Huntsville
USLI CDR
• Rover electronics contained inside chassis
• Tray designed to wire and organize electronics outside chassis
• Tray lowered into top of chassis once assembled
Electronics Tray
531/16/2018University of Alabama in Huntsville
USLI CDR
• Designed to avoid interference with motors
• Tray Assembly: 11.6 in. x 3.8 in. x 2 in.
Electronics Tray
541/16/2018University of Alabama in Huntsville
USLI CDR
• Lid is closed during rover travel for protection
• Gear slides top lid out to reveal solar panel in chassis
• 3D printed ABS lid, gear bought from McMaster-Carr
• 12 in. x 4 in. x 0.375 in. when closed
• 12 in. x 7.25 in. x 0.5 in. when open
Rover Lid with Mechanism
551/16/2018University of Alabama in Huntsville
USLI CDR
• The mass of all components totaled 6.6 lbm.
• A 6% margin was added to the total weight to account for fasteners and adhesives
Rover Mass Budget
56
Component Mass (lbm.)
Chassis 2.0
Wheel Assembly 2.4
Lid/Solar Deployment 0.7
Tail 0.2
Electronics 1.3
6% Margin 0.4
Total 7.0
1/16/2018University of Alabama in Huntsville
USLI CDR
Payload Power Budget
571/16/2018University of Alabama in Huntsville
USLI CDR
Part Name Current
(mA)
Voltage (V) Adj Current Duty Cycle
(%)
Time (hr) Total (mWh)
Arduino Mega 0.17 5 0.0787 100 2.5 0.984
Camera 350 5 162.037 10 2.5 202.546
GPS 53 3.3 16.194 20 2.5 26.721
IMU 0.35 3 0.0972 100 2.5 0.729
Pressure/Temp 0.36 3.3 0.11 17 2.5 0.154
Wheel Motors 650 12 722.222 20 2.5 4333.333
Lid Motors 360 5 166.667 5 2.5 104.167
Radio transmit 229 3.3 69.972 10 2.5 57.727
Radio idle 44 3.3 13.444 90 2.5 99.825
Datalogger 100 3 27.778 10 2.5 20.833
Power
required
4847.01
Part Name Current
(mA)
Voltage (V) Adj Current Duty Cycle
(%)
Time (hr) Total (mWh)
Li-Ion Battery 2600 10.8 N/A 100 1 28080
Power
Supplied
28080
Power
Supplied
28080 mHr Power
required
28080 mHr Factor of
Safety
5.793 mHr
Electronics Block Diagram
581/16/2018University of Alabama in Huntsville
USLI CDR
Electronics Failure Path
59
• Emphasizes dependence of each lower level component on the component above it
1/16/2018University of Alabama in Huntsville
USLI CDR
SAFETY
601/16/2018University of Alabama in Huntsville
USLI CDR
• Training and communication are key to maintain safety and avoid mishaps
• Priorities in CRW safety program (in order of importance):1. Safety to personnel2. Safety to facilities & permanent systems3. Safety to flight hardware & objective success
• Established SOP and regulations to maintain safety practices
• Team is transitioning from designing to manufacturing and testing
Safety Overview
611/16/2018University of Alabama in Huntsville
USLI CDR
• CRW team meets twice weekly
• Safety briefings are held to update the team with pertinent information
• All conducted tests have documentation of results and lessons learned
• Documents and test results are recorded to the team’s server for ease of access
Communication
621/16/2018University of Alabama in Huntsville
USLI CDR
• Philosophy– Standardization of processes– Address risks and hazards with proper method
• Creation– Based on previous versions– In collaboration with team leads to adapt SOP steps to the features and
mission needs of the Vehicle and Payload
• Approval– Reviewed and approved by Red team members and faculty advisor
• Implementation:– Use latest version– Safety Monitor to ensure strict adherence to steps and safety aspects
Standard Operating Procedures
631/16/2018University of Alabama in Huntsville
USLI CDR
Launch and Assembly Procedures
• Final rocket assembly procedures for the Full Scale have been developed to fit the design concept
• Minimum assembly or modification of airframe at field
• Field operations are limited to subsystem integration and loading of energetics
• Simulated runs of launch procedures will take place at least one week prior to any launch
641/16/2018University of Alabama in Huntsville
USLI CDR
• Factors affecting launch vehicle and payload
– Sudden high winds
– Humidity
– Extreme temperatures
– Terrain
• Mitigations established:
– Minimum exposure to environment
– Constant monitor of the weather
Environmental Factors
651/16/2018University of Alabama in Huntsville
USLI CDR
• Factors affecting the Environment and Local communities– Hot exhaust
– Landing in trees, difficult terrains
– Landing on infrastructure and private properties
– Waste from manufacturing and launches
• Mitigations Established:– Inspection and understanding of launch field
– Waste collection and proper disposal
– Constant monitor of wind conditions
Environmental Factors
661/16/2018University of Alabama in Huntsville
USLI CDR
Training Activity Date
Red Cross First Aid CPR/AED/FA Completed
Basic Emergency Procedures Completed
Process Hazard Analysis Completed
Safe Testing Procedures Completed
Root-Cause Analysis Completed
Outreach Safety Procedures Completed
Sub-scale Launch Safety Procedures Completed
Hazardous Material Handling/Disposal Completed
Fire Extinguisher training Completed
Workshop Safety Briefings 1/23/2018
System Ground Tests Briefings 1/30/2018
TBD TBD
Upcoming Trainings
67
Safety Briefings are held based to relevant safety topics.
1/16/2018University of Alabama in Huntsville
USLI CDR
• Test Plan changes since PDR
– Completed tests includes the subscale launch and subscale charge test.
– New tests planned for Rover and Launch Vehicle fairing systems.
– GPS test is on going to ensure constant compatibility.
Test Plan
681/16/2018University of Alabama in Huntsville
USLI CDR
Test Plan
69
Test Number Test Type Test Status
T1 Subscale Ejection Charge Test ➢ Test has been conducted prior
to the subscale flight on 11-19-
2017
➢ Test shows that rocket has to
go drogue-less and use only
one shear pin on both main and
drogue for successful recovery.
T2 Subscale Flight ➢ Successful launch and recovery
➢ Vehicle did not reach initial
altitude prediction
T3 GPS tracker range and
capability/Telemetry
➢ Tracker currently Exhibit poor
performances.
➢ Team is currently learning how
to trouble shoot issues with
tracker.
➢ Telemetry test is planned for
Feb 10-11
T4 Fin Can Load Test ➢ Test will be planned for the end
of January to the early February
before the full scale launch.
1/16/2018University of Alabama in Huntsville
USLI CDR
T5 Rover Piston Deployment test ➢ Test will be scheduled in
February when the piston is
manufactured.
T6 Fairing Vibration Test ➢ Test is planned for middle to end
of February once test articles
arrive
T7 Faring Drop Test ➢ Test is planned for middle to end
of February once test articles
arrive
T8 Fairing Transition Compression test ➢ Test will be conducted once FEA
results shows doubts in the
structures.
T9 Rover Operational Test ➢ Test will be planned and carried
out when rover is constructed.
T10 Full Scale Charge Test ➢ Test will be conducted
approximately one week before
the first full scale launch date
T11 Full Scale Flight ➢ Flight will be held on Feb 17 and
18
Test Plan
701/16/2018University of Alabama in Huntsville
USLI CDR
TESTING AND REQUIREMENTS VERIFICATION
711/16/2018University of Alabama in Huntsville
USLI CDR
• Document template for tracking requirements verification
• Allows for all 4 methods to be tracked
• Place to record test procedures, personnel, and results
• Template is in Critical Design Review Appendix
Verification Reports
721/16/2018University of Alabama in Huntsville
USLI CDR
• Expected/In-Progress Verification Reports
– Review of project plan and procedures
– Review of all submitted documents, website, and teleconference setup
– Review of Educational Outreach Reports
– Demonstration of reusability through full-scale flight
General Requirements Verification
731/16/2018University of Alabama in Huntsville
USLI CDR
Test
Number
Test Type Description Test Status
T1 GPS tracker
range and
capability
o The GPS tracker of the launch vehicle and the
payload will be tested inside of their respective
fairing/compartment. This is to ensure that the GPS
can reliable transmit and receive signals.
o The test will also be conducted in obstacles such as
trees and buildings to reveal the limits of the GPS.
o The full test of GPS system performance and
reliability will be the subscale launch
o Single component tests (radio, GPS receiver), can
be done by a team member without supervision.
o Subscale launch tests will adhere to SOP.
➢ Tracker currently
Exhibit poor
performances.
➢ Team is currently
learning how to
trouble shoot
issues with tracker.
T2 Electrical Charge
on E-matches
o Spectrum analysis will be conducted to determine if
transmission waves will enter into the avionics
coupler and affect the electronic components
o The tracker can be placed inside the coupler to
determine how much transmission power exits. The
idea is if excessive power exits the coupler, an
excessive amount can enter.
o Shielding can then be implemented based on the
results.
o This test will require more than one team member.
However, Red team members and the mentor will
not be required for this type of test.
➢ Test is has not
been planned.
Test Plan
741/16/2018University of Alabama in Huntsville
USLI CDR
T3 Altimeter Test o The functionality of the altimeter will be evaluated with
the Charger Rocket Works’ altimeter testing container.
o Only applied for in-house made altimeters. Third party
altimeters like Statologger will not require testing.
➢ Test will be scheduled
when altimeter has
been created.
T4 Ejection Charge Test o This is to experimentally verify the correct
amount of black powder to be used in the
ejection of the drogue and main parachutes.
o An SOP has to be developed for this test
o This test is dangerous and only Red Team
with the presence of the mentor can conduct
the test.
➢ Test has been
conducted prior to the
subscale flight on 11-
19-2017
➢ Test shows that rocket
has to go drogue-less
and use only one shear
pin on both main and
drogue for successful
recovery.
T5 Rover Piston Deployment test o Experimentally verify the functionality of the
rover deployment mechanism.
o The test requires no pyrotechnics so anyone
in CRW can conduct the test.
➢ Test will be scheduled
in February when the
piston is manufactured.
T6 Fairing Transition Compression test o Experimentally verify the compression strength of the
fairing transition
o Only the section in doubt from the FEA results shall
printed for test.
o Currently planned to be a destructive test
➢ Test will be conducted
once FEA results
shows doubts in the
structures.
T7 Rover Terrain Test o The Rover, once constructed, shall be put through its
paces in different terrain conditions (except water and
mud).
o Test is to verify the spoke wheel design.
➢ Test will be planned
and carried out when
rover is constructed.
Test Plan
751/16/2018University of Alabama in Huntsville
USLI CDR
Full Scale Budget
Budget
Summary
Airframe $ 1763.11
Electronics $ 334.89
Recovery $ 899.09
Motors $ 1589.96
Rover Structure $ 438.97
Rover Electronics $ 682.34
Total Cost $ 5708.36
761/16/2018University of Alabama in Huntsville
USLI CDR
On the Pad Budget
Launch Vehicle
Airframe $ 997.81
Electronics $ 167.45
Recovery $ 621.09
Motor $ 259.99
Rover $ 621.00
Total $ 2046.34
771/16/2018University of Alabama in Huntsville
USLI CDR
11/3/2017University of Alabama in Huntsville
USLI PDR78