NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of...
Transcript of NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of...
![Page 1: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/1.jpg)
University of
Alabama in
Huntsville
NASA SL
Critical Design
Review
University of Alabama in Huntsville
USLI CDR11/16/2018
![Page 2: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/2.jpg)
LAUNCH VEHICLE
University of Alabama in Huntsville
USLI CDR21/16/2018
![Page 3: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/3.jpg)
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
![Page 4: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/4.jpg)
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
![Page 5: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/5.jpg)
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.
![Page 6: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/6.jpg)
• Upper Airframe houses the rover, piston ejection system, and GPS tracker
Upper AirframeOverview
University of Alabama in Huntsville
USLI CDR61/16/2018
![Page 7: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/7.jpg)
• 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
![Page 8: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/8.jpg)
• 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
![Page 9: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/9.jpg)
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
![Page 10: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/10.jpg)
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
![Page 11: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/11.jpg)
• 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
![Page 12: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/12.jpg)
• 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
![Page 13: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/13.jpg)
• Ejects rover and nose cone
• Fiberglass coupler with aluminum bulkhead
Piston Head
University of Alabama in Huntsville
USLI CDR131/16/2018
![Page 14: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/14.jpg)
• 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
![Page 15: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/15.jpg)
• 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
![Page 16: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/16.jpg)
• 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
![Page 17: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/17.jpg)
• 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
![Page 18: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/18.jpg)
• 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
![Page 19: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/19.jpg)
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
![Page 20: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/20.jpg)
Exploded View of the Fin Can Assembly
University of Alabama in Huntsville
USLI CDR201/16/2018
![Page 21: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/21.jpg)
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
![Page 22: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/22.jpg)
Fin Can Dimensions
University of Alabama in Huntsville
USLI CDR221/16/2018
![Page 23: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/23.jpg)
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
![Page 24: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/24.jpg)
Thrust Plate Dimensions
University of Alabama in Huntsville
USLI CDR241/16/2018
![Page 25: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/25.jpg)
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
![Page 26: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/26.jpg)
Motor Retention Ring Dimensions
University of Alabama in Huntsville
USLI CDR261/16/2018
![Page 27: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/27.jpg)
• 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
![Page 28: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/28.jpg)
• 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
![Page 29: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/29.jpg)
Stability Margin
29
Motor Burnout (3.28 cal.)
Initial Stability (2.22 cal.)
Apogee
1/16/2018University of Alabama in Huntsville
USLI CDR
![Page 30: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/30.jpg)
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.
![Page 31: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/31.jpg)
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
![Page 32: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/32.jpg)
• 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
![Page 33: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/33.jpg)
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
![Page 34: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/34.jpg)
• 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
![Page 35: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/35.jpg)
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
![Page 36: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/36.jpg)
• 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
![Page 37: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/37.jpg)
• 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
![Page 38: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/38.jpg)
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
![Page 39: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/39.jpg)
Coupler
391/16/2018University of Alabama in Huntsville
USLI CDR
Charge Well
U-Bolt
Screw Terminal Strip
Flight Computer
Batteries
RBF Switches
12 in.
![Page 40: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/40.jpg)
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
![Page 41: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/41.jpg)
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
![Page 42: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/42.jpg)
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
![Page 43: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/43.jpg)
• 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
![Page 44: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/44.jpg)
• 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
![Page 45: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/45.jpg)
• 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
![Page 46: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/46.jpg)
• 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
![Page 47: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/47.jpg)
• 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
![Page 48: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/48.jpg)
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
![Page 49: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/49.jpg)
• 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
![Page 50: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/50.jpg)
• 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
![Page 51: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/51.jpg)
• 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
![Page 52: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/52.jpg)
• 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
![Page 53: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/53.jpg)
• 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
![Page 54: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/54.jpg)
• 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
![Page 55: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/55.jpg)
• 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
![Page 56: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/56.jpg)
• 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
![Page 57: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/57.jpg)
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
![Page 58: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/58.jpg)
Electronics Block Diagram
581/16/2018University of Alabama in Huntsville
USLI CDR
![Page 59: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/59.jpg)
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
![Page 60: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/60.jpg)
SAFETY
601/16/2018University of Alabama in Huntsville
USLI CDR
![Page 61: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/61.jpg)
• 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
![Page 62: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/62.jpg)
• 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
![Page 63: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/63.jpg)
• 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
![Page 64: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/64.jpg)
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
![Page 65: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/65.jpg)
• 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
![Page 66: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/66.jpg)
• 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
![Page 67: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/67.jpg)
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
![Page 68: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/68.jpg)
• 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
![Page 69: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/69.jpg)
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
![Page 70: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/70.jpg)
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
![Page 71: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/71.jpg)
TESTING AND REQUIREMENTS VERIFICATION
711/16/2018University of Alabama in Huntsville
USLI CDR
![Page 72: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/72.jpg)
• 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
![Page 73: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/73.jpg)
• 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
![Page 74: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/74.jpg)
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
![Page 75: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/75.jpg)
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
![Page 76: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/76.jpg)
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
![Page 77: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/77.jpg)
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
![Page 78: NASA SL Critical Design Review · •Entire assembly can be removed Fin Interface University of Alabama in Huntsville USLI CDR 1/16/2018 18. Fin Can Assembly ... •3D printed in](https://reader034.fdocuments.us/reader034/viewer/2022052008/601d3932dab965042e400fcc/html5/thumbnails/78.jpg)
11/3/2017University of Alabama in Huntsville
USLI PDR78