Flight Readiness Review March 16, Agenda. California State Polytechnic University, Pomona W. Temple Ave, Pomona, CA 91768

Transcription

1 Flight Readiness Review March 16, 2018 Agenda California State Polytechnic University, Pomona 3801 W. Temple Ave, Pomona, CA 91768

2 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

3 Changes Made Since CDR Vehicle Criteria Changes Criteria Changes Made Reason for Change Vehicle Size Vehicle Mass Overall length increased from 8.42 ft (101 in.) to 10 ft (120 in.) Overall mass increased from 43.7 lb to 46.2 lb (includes 4 lb ballast). Vehicle weight without ballast is 42.6 lb. Extra length needed to compensate for nose cone changes. Materials and dimensions were adjusted to improve design integrity during manufacturing and test flights; ballast used to decrease apogee altitude. 03/16/2018 California State Polytechnic University, Pomona FRR

4 Changes Made Since CDR Vehicle Criteria Changes Criteria Changes Made Reason for Change Payload Bay Nose Cone Fin Hollowed-bulkhead wood material changed to cast iron; hollowedbulkhead plug material changed from PLA to maple wood. Material changed from a PLA printed Von Karman to a fiberglass 5:1 Ogive Material changed from PLA to ½ in. plywood. Improved structural integrity; wood material failed load testing. Excessive manufacturing time needed for PLA printing; nose cone replacement was readily available and did not affect performance. Excessive manufacturing time needed for PLA printing; plywood was readily available and did not affect performance. 03/16/2018 California State Polytechnic University, Pomona FRR

5 Changes Made Since CDR Recovery System Criteria Changes Criteria Changes Made Reason for Change Recovery Avionics Terminal block added on each recovery bay bulkhead and placed adjacent to ejection charge canisters. Allows for much faster and organized e-match swap. Drogue Parachute No longer being manufactured inhouse; changed to Top Flight Recovery Ultra X-Type 30 in. Allowed for less manufacturing time and x-type is very inexpensive at $17.95 Main Parachute Fruity Chutes 120 in. Toroidal changed to Top Flight Recovery Crossfire 120 in. Fruity Chutes shroud lines were easily prone to tangling and had inconsistent results. Top Flight Recovery Crossfire simplified the recovery system and improved reliability. 03/16/2018 California State Polytechnic University, Pomona FRR

6 Changes Made Since CDR Payload Criteria Changes Criteria Changes Made Reason for Change Battery/power Payload Bay Switches Payload Electronics A 9-volt battery has been added to the rover to only power the Raspberry Pi CPU by use of a 5-volt regulator. The 5-volt, 2-amp (5000 mah) cell will only be used to power the servos, motor and GPS unit through the control circuit board. A power button has been added; small hole added to the body tube of the payload bay. A third Xbee transceiver added to the mesh network. Separate power was needed for the Raspberry Pi CPU; ensures servos and motor receive enough power and eliminates possibility of a back EMF damaging the RPi without use of a more complex circuit board. Allows access to initiating power to the rover prior to launch by switching on from the outside of the launch vehicle. Increased the range of communication between the ground station and the rover. 03/16/2018 California State Polytechnic University, Pomona FRR

7 Changes Made Since CDR Project Plan Changes Criteria Changes Made Reason for Change Full-Scale Flight Tests Tests scheduled for 2/3/18 and 2/10/18 were changed to 2/17/18, 2/14/18, and 3/3/18. 2/3/18 Manufacturing delays 2/10/18 & 3/3/18 cancelled due to poor weather conditions. Test Plan Dates Budget Several dates adjusted (details listed in section 7.1 of FRR report). Budget adjusted to meet project needs; Potential funding source added: California Space Grant Consortium Student-Led Hands-On Rocket Projects Manufacturing timeline varied according to materials purchasing and construction. Materials were changed for the recovery and payload systems. 03/16/2018 California State Polytechnic University, Pomona FRR

8 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

9 Overview of Launch Vehicle Design and Dimensions Final design length = 10 ft. Three independent sections (modules) 03/16/2018 California State Polytechnic University, Pomona FRR

10 Overview of Launch Vehicle Design and Dimensions Module 1 Nose cone Payload bay 03/16/2018 California State Polytechnic University, Pomona FRR

11 Overview of Launch Vehicle Design and Dimensions Module 2 Main parachute bay Recovery avionics bay Drogue parachute bay 03/16/2018 California State Polytechnic University, Pomona FRR

12 Overview of Launch Vehicle Design and Dimensions Module 3 Observation bay Motor bay 03/16/2018 California State Polytechnic University, Pomona FRR

13 Overview of Payload Design and Dimensions Full 6 in. diameter will be used to support the SPOC system 12 in. payload length will provide sufficient room for the DARIC rover A 4.7 in. payload bay opening will allow the rover to exit at landing 03/16/2018 California State Polytechnic University, Pomona FRR

14 Launch Vehicle Key Design Features: Hallow bulkhead Located at end of payload bay coupler Material changed from wood to cast iron OD: 5.75 in ID: 4.7 in. Material Allowable: 21.6 ksi Thickness: 0.5 in. Smallest gap: in. Max load allowable: 1350 lb. 03/16/2018 California State Polytechnic University, Pomona FRR

15 Launch Vehicle Key Design Features: Plug Material: Wood Purpose: Creates pressure seal during main parachute deployment Protects payload during main parachute deployment Pulled off from bulkhead during main parachute deployment using eye-bolt and ½ in. shock cord 03/16/2018 California State Polytechnic University, Pomona FRR

16 Key Design Features: Fin Integration Upper Centering Ring Upper Retention Ring Constructed with five centering rings cut to purpose. Center Fin Rings Lower Retention Ring Fins are screwed in to Lower and Upper Retention rings and located by Center Fin Rings Lower Retention Ring screws in to airframe and is responsible for transferring all motor forces to the airframe. Six stainless steel screws transfer load. Airframe Screws Fin Screws 03/16/2018 California State Polytechnic University, Pomona FRR

17 Key Design Features: Fin Integration Concern: Fin flutter in flight Solution: Fin slots cut wider than fin width. Space is filled with a stiff yet compressible rubber which resists small motions Rubber 0.51 Fin slots are cut to be 0.1 inches wider than fins. (Fin width = 0.5in) 03/16/2018 California State Polytechnic University, Pomona FRR

18 Motor Selection and Justification Aerotech L1420 Performance Parameters: Aerotech L1420 Thrust Curve Average Thrust: Maximum Thrust: Total Impulse: Burn Time: ISP: lb lb lb-s 3.2 s 183 s 03/16/2018 California State Polytechnic University, Pomona FRR

19 Mass Statement Total Mass of Launch vehicle Lift off weight: W = 46.2 lb (includes 4 lb ballast secured in observation bay (module 3) Ballast Criteria: A ballast weight has been implemented to reach a more desirable altitude Vehicle weight without ballast : W = 42.2 lb. Vehicle weight with ballast: W = 46.2 lb. 03/16/2018 California State Polytechnic University, Pomona FRR

20 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

21 Rocket Flight Stability in Static Margin Diagram Center of Gravity OpenRocket Inches Hand Calculations Measured Values Center of Pressure Stability Margin Inches 3.04 Caliber 67.0 Inches Inches 3.07 Caliber Percent Difference % 1.83 %.03% 03/16/2018 California State Polytechnic University, Pomona FRR

22 Rail Exit Velocity and T/W Ratio Rail Exit Velocity (12 ft rail): 71.7 ft/s Max T/W Ratio at MGLOW = lbs. T/W : /16/2018 California State Polytechnic University, Pomona FRR

23 OpenRocket Flight Simulation Results Wind Speed (MPH) Apogee (ft.) Time to Apogee (sec) Simulated Apogee (OpenRocket) (12 MPH winds) Full Scale Test Achieved Altitude (12 MPH winds) Percent Difference (relative to actual results) ft ft. 3.4% alt. = 5330 ft. at 0 mph winds /16/2018 California State Polytechnic University, Pomona FRR

24 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

25 Parachute Sizes: Drogue Ultra X-Type parachute from Top Flight Recovery Ripstop nylon 1.7 oz. with flat braided nylon lines Area of 4.4 ft 2 Mass of lbs. 03/16/2018 California State Polytechnic University, Pomona FRR

26 Parachute Sizes: Main Crossfire hemispherical parachute from Top Flight Recovery Ripstop nylon 1.7 oz. with flat braided nylon lines 10 ft. parachute Area of ft 2 Mass of 2 lbs. 03/16/2018 California State Polytechnic University, Pomona FRR

27 Descent Rates Event (altitude) Description Velocity 1 (5280 ft.) Apogee 0 ft/s 1-2 (5280 ft. to 500 ft.) 2-3 (500 ft. to 0 ft.) Drogue Parachute Deployment Main Parachute Deployment & Touch Down ft/s ft/s Total Descent Time = 84.8 s 03/16/2018 California State Polytechnic University, Pomona FRR

28 Kinetic Energy Phase Section and Weight Kinetic Energy (ft-lbf) Drogue Deployment (V=97.72 ft/s) Main Deployment (V=13.94 ft/s) Nose Cone and Payload Bay (10.7 lbs.) 1587 Main/Drogue Parachute and Recovery Bay (11.5 lbs.) 1705 Observation and Motor Bay (24.22 lbs.) Nose Cone and Payload Bay (10.7 lbs.) 32.1 Main/Drogue Parachute and Recovery Bay (11.5 lbs.) 34.7 Observation and Motor Bay (24.22 lbs.) 73.1 All rocket sections land under 75 ft-lb of kinetic energy to meet Requirement /16/2018 California State Polytechnic University, Pomona FRR

29 Drift Analysis Assumptions Instantaneous parachute deployment (conservative) Effective area of parachute is always perpendicular to wind Drogue deployment occurs exactly at apogee, and main at 500 ft. Only one parachute is effective during its respective phase Wind velocity (MPH) Drift Distance (ft.) When V drogue =97.72 ft/s V main =13.94 ft/s Requirement 3.9 is satisfied 03/16/2018 California State Polytechnic University, Pomona FRR

30 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

31 Recovery Systems Test Tested on 2/17/18 after recovery system criteria changes mades Main Drogue Old Parachutes Fruity Chutes Toroidal 10 ft. diameter A eff = sq. ft. C d = 2.2 Cruciform Manufactured In- House 48 in. diameter Surface area of 9 sq. ft. C d = 0.6 New Parachutes Top Flight Recovery 10 ft. diameter A eff = sq. ft. C d = 1.4 Top Flight Recovery Ultra X- Type 30 in. diameter Surface area of 4.4 sq. ft. C d = 0.98 Full scale launch used to confirm recovery reliability Full inflation of both parachutes Drogue deployment at apogee (5,454 ft.) Main deployment at 700 ft. with redundant charge set for 600 ft. 03/16/2018 California State Polytechnic University, Pomona FRR

32 Recovery Drop Tests Drogue parachute dropped from a height of 35 ft. Weight added to drogue: 0.5 lbs. C d provided by manufacturer: 0.98 C d calculated: 0.89 Descent Velocity using coefficient of drag Predicted: ft/s Verified from Full scale launch: 75 ft/s 03/16/2018 California State Polytechnic University, Pomona FRR

33 Recovery Drop Tests Main parachute dropped from a height of 35 ft. Weight added to main: 0.5 lbs. C d provided by manufacturer: 1.4 C d verified: 2.39 Descent Velocity using coefficient of drag Predicted: ft/s Verified from Full scale launch: ft/s 03/16/2018 California State Polytechnic University, Pomona FRR

34 Ejection Charge Test Procedure Ground test performed to determine necessary charge Conducted for both drogue and main parachutes Full scale tests completed on 17 February, 2018 and 24 February, 2018 Post ejection, lateral distance of each parachute measured to determine needed ejection charge size 03/16/2018 California State Polytechnic University, Pomona FRR

35 Ejection Charge Test Results Objective Ejection pulls out parachutes and shock cord completely Status Successfully discharged both main and drogue. Shock cord ejected completely. All shear pins broken All shear pins in recovery bay broken. No heat damage to recovery materials No damage body tube at recovery harness attachment location Minimal heat damage to main and drogue, reusable for flight. No damage to body and no damage to recovery electronics. 03/16/2018 California State Polytechnic University, Pomona FRR

36 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

37 S.P.O.C. Key Dimensions The S.P.O.C. systems outer diameter is constrained by the rockets diameter which drives its design. The length and width of the S.P.O.C. systems platform constrains the rovers length and width to ensure a the S.P.O.C. systems function. The S.P.O.C. systems inner pendulum radius constrains the overall possible height of the rover. All dimensions are in inches 03/16/2018 California State Polytechnic University, Pomona FRR

38 S.P.O.C. Key Features The locking pin mechanism keeps the S.P.O.C. system stagnant during flight. Once the parachute deploys it allows the S.P.O.C. system to self correct its orientation, ensuring the appropriate deployment of the rover. The hooking system secures the rover onto the platform during flight and landing. Once the rocket lands, the rotor servo placed on the rover rotates disengaging it from the hooking system. The ball bearings allows the S.P.O.C. system to rotate under the rovers CG. 03/16/2018 California State Polytechnic University, Pomona FRR

39 D.A.R.I.C. Key Dimensions The overall height, width and length of the rover is driven by the S.P.O.C. systems constraints. In order to fit all the electrical components into the rover, design changes were consistently made between the rover and S.P.O.C. system. All dimensions are in inches 03/16/2018 California State Polytechnic University, Pomona FRR

40 D.A.R.I.C. Key Features The 9V battery powers the main CPU while the main battery powers the remaining electrical components. This reduces the risk of not having enough power for our system which avoids having a failure during the mission. The rotor servos act as control surfaces. The rotor servo mounted on the rover secures it onto the S.P.O.C. system during flight. The main CPU controls all the electrical components that are mounted on the rover. 03/16/2018 California State Polytechnic University, Pomona FRR

41 S.P.D. Key Dimensions The S.P.D. system s width when closed is constrained by the inner pendulums diameter. The S.P.D. s overall height has to be taken into account when mounted on the rover to ensure there is no interference with the inner pendulum. The length of the S.P.D. system is constrained by the rovers design in order to ensure the best system integration. All dimensions are in inches 03/16/2018 California State Polytechnic University, Pomona FRR

42 S.P.D. Key Features There are four total solar panels, 2 are mounted to each deployable panel. The torsion springs provide the force to deploy the solar panels. The rotor servo is the control surface that holds the deployable panels closed until commanded to rotate out of contact with the deployable panels. 03/16/2018 California State Polytechnic University, Pomona FRR

43 Internal Interfaces Within Launch Vehicle 12 bolts hold S.P.O.C. system to Launch Vehicle Rotation Lock Pin is tethered to the Main Parachute via a steel cable 03/16/2018 California State Polytechnic University, Pomona FRR

44 Internal Interfaces Within Launch Vehicle Inside view demonstrating rover on SPOC platform 03/16/2018 California State Polytechnic University, Pomona FRR

45 D.A.R.I.C. to S.P.O.C. Interface Servo rotates tab into and out of locking position 03/16/2018 California State Polytechnic University, Pomona FRR

46 Payload Interfaces with Ground Systems Ground Station Xbee is mesh coordinator Router Xbee increases range by use of gain antenna Rover Xbee is mesh endpoint Interfaces with laptop at launch site Can easily receive a signal from the router due to close proximity 03/16/2018 California State Polytechnic University, Pomona FRR

47 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

48 Bulkhead Test Results Bulkheads capable of withstanding 1000 lbs. in compression. Hollow bulkhead capable of withstanding a maximum load of 150 lbs. U-bolt sheared from hollow bulkhead during testing. Status Completed: 1/17/18 Solid bulkhead: Pass Hollowed bulkhead: Fail 03/16/2018 California State Polytechnic University, Pomona FRR

49 Bulkhead Test Impact Test results allowed team to select stronger material for hollowed bulkhead. Material used in flight is cast iron. Procedure 1. The Safety Officer shall provide clearance for the test to be conducted after ensuring team members are aware of all safety hazards. 2. Ensure bulkhead is appropriately fixed to body tube and that all hardware has been attached. 3. Bulkhead component should resemble its launch configuration 4. Attach load to U-bolt location starting at 50 lbs., then increase weight gradually. 5. Continue previous step until bulkhead begins to yield. 6. Collect data and results. 03/16/2018 California State Polytechnic University, Pomona FRR

50 Parachute Drop Test Results Parachute with added weight came down with vertical flight path. 7.5 ounce weight used for testing was not damaged. Status Completed: 2/9/18 Pass 03/16/2018 California State Polytechnic University, Pomona FRR

51 Parachute Drop Test Impact Drop test proved inflation of both drogue and main parachute. Proved drogue and main parachute were ready for full-scale vehicle flight test. Procedure 1. Determine appropriate drop test area and measure the height of the drop distance. 2. Secure the video camera at an angle capable of recording the parachute s descent. 3. Attach a 7.5 oz. weight to the parachute. 4. Ensure that shroud lines are untangled and that parachute is correctly packed. 5. Begin video recording. 6. Drop the weight and packed parachute. 03/16/2018 California State Polytechnic University, Pomona FRR

52 Observation System Test Results Status Camera recorded video of launch vehicle flight for an hour and forty minutes. Completed: 2/17/18 2/24/18 Pass Impact Verified camera can record up to 2 hours of quality video of launch vehicle flight. Footage of launch vehicle performance. Procedure 1. Connect camera with Raspberry Pi Zero computer 2. Connect observation system to computer and download any required software 3. Program Raspberry Pi Zero to begin recording 4. Save and playback test recordings 03/16/2018 California State Polytechnic University, Pomona FRR

53 Ejection Charge Test Results Status 5 grams of black powder needed for drogue parachute ejection charge. 6 grams of black powder needed for main parachute ejection charge. Main parachute ejected 20 feet. Drogue parachute ejected 15 feet. Completed: 2/16/18 2/23/18 Pass 03/16/2018 California State Polytechnic University, Pomona FRR

54 Ejection Charge Test Impact Tests gave team knowledge of quantity of black powder needed for ejection charges. Proved ejection charges will successfully deploy main and drogue parachutes. Procedure 1. Administer all precautions to comply with safety regulations set forth by the Safety Officer. 2. Carefully pack each parachute and their shock cords into the body tubes while taking care to protect the recovery material with Nomex blankets. Make note of the parachute packing in order to simulate its setup during launch testing. 3. Place on the appropriate PPE as deemed by the SO. Measure the amount of ejection charge and prepare. 4. Setup the charge and then secure the bulkhead. Once the charge has been configured, the SO will ensure that the path ahead the nose cone is completely clear. 5. Secure the launch vehicle so that it is angled up into the air and not lying flat on the ground. The SO will ensure that the space around the launch vehicle is now clear. 6. Ignite the ejection charges and wait at least one minute before approaching the vehicle. 7. Assess the deployment distance achieved by inspecting the shock cord length and the parachute configuration. Document the inspection. 8. Re-size the charge appropriately to ensure sufficient deployment. 9. Repeat steps 1-8 until sufficient deployment is reached. 03/16/2018 California State Polytechnic University, Pomona FRR

55 Recovery Avionics Shielding Test Results Stratologger CF s successfully ignited the primary and redundant E-match and the GPS unit. Status Completed: 1/16/18 Pass Impact Proved RF shielding ensures no signal disconnections occur and signal strength is conserved. Proved launch vehicle avionics will function as planned. Procedure 1. The avionics bay component with the electronics sealed inside the bay will be lined with RF shielding. 2. As the test is conducted, the signal strength will be observed. 3. The test will be successful if signal disconnections do not occur. 03/16/2018 California State Polytechnic University, Pomona FRR

56 Payload Integration Test: Mount to Launch Vehicle Results S.P.O.C. system withstood loads experienced during launch vehicle flight. S.P.O.C. system was at proper orientation after launch vehicle landed. Status Completed: 1/20/18 Verified: 2/17/18 Pass 03/16/2018 California State Polytechnic University, Pomona FRR

57 Payload Integration Test: Mount to Launch Vehicle Impact Proved S.P.O.C. system can place rover in proper orientation after launch vehicle lands. Verified structural integrity of S.P.O.C. system. Procedure 1. The S.P.O.C. system will be mounted to launch vehicle using screws. 2. The S.P.O.C. system will contain a weight attached to simulate the rover. 3. The tube will have a snap cord of 40 feet attached. 4. When the tube is stopped, the impulse of a launch will be simulated. 5. The bolts and mounting locations of the S.P.O.C. system will be examined. 6. The S.P.O.C. system will also be tested in a full-scale flight test to ensure that the rover will be delivered at landing in the proper orientation to travel to its destination. 7. The flight test will also verify the structural integrity of the S.P.O.C. system once the loads analysis has been completed pre-flight. 03/16/2018 California State Polytechnic University, Pomona FRR

58 Payload Integration Test: Rover Mount to S.P.O.C. Platform Results Status Locking pin for the rover on the S.P.O.C. platform held for drop test. Completed: 1/20/2018 Pass 03/16/2018 California State Polytechnic University, Pomona FRR

59 Payload Integration Test: Rover Mount to S.P.O.C. Platform Impact Verified S.P.O.C. system will hold the rover in place for the duration of the flight so that it does not interrupt the flight trajectory of the launch vehicle and safely delivers the rover at landing. Verified S.P.O.C. system will remain stagnant during flight and allow the rover s platter to selfcorrect itself to the right orientation with respect to the ground. Vibration and impact tests showed the locking pin needed to be lengthened in order to remain in place during flight and to prevent rotation of the S.P.O.C. system before main shoot deployment Screw locations for the servo were lengthened, and longer screws were purchased as to provide more contact area to reduce the stress level the PLA experiences. Procedure 1. The launch vehicle tube will have the S.P.O.C. system mounted inside with a simulated weight representing the rover locked on the platform by the locking servo. 2. The tube will have a snap chord of 40 feet attached. 3. When the tube is stopped, the impulse of launch will be simulated. 4. The servo and locking mechanism will be examined. 03/16/2018 California State Polytechnic University, Pomona FRR

60 Raspberry Pi Test- Rover Operation Results Raspberry Pi performed all parts of the mission, including powering mechanisms and electronic components, and can idle for more than the required three hours. Status Completed: 2/2/18 Impact Confirmed the need for an additional 9V battery specifically for the CPU. Verified Raspberry Pi will operate rover as expected. Procedure Pass 1. The RPi will have the two servos, a motor, an Xbee and a GPS connected. 2. The run signal will be sent to the Xbee. 3. The functions of the two servos and motor will be watched and compared to their run schedule. 4. The GPS will also be watched to make sure it operates as intended. 5. The system will remain on standby for 3 hours to ensure that the battery will last. 03/16/2018 California State Polytechnic University, Pomona FRR

61 Xbee Test- Range Results The requirement of 3000 feet was not met as the only retrievable signal was made at 1500 feet. Status Completed: 2/19/18 Fail Rescheduled: 3/4/18 03/16/2018 California State Polytechnic University, Pomona FRR

62 Xbee Test- Range Impact Test shows that the antennas used will need to be replaced by larger antennas in order to get a better communication range. Analysis made after the failed Xbee test showed there were multiple interfaces in the path of the Xbee as it was conducted in a public area and had no direct path. Testing showed third Xbee with a gain antenna will ensure another added distance of 1500 feet, which will meet the requirement of 3000 feet total distance. Procedure 1. The Xbee dedicated to the rover will be connected to a laptop and placed inside a section of the launch vehicle tube; this will simulate how the signal could be impacted. 2. Another laptop with the ground station Xbee will be placed 3000 ft. away. 3. A message will be sent from the ground station to the rover Xbee. 4. A received message will be a successful test. 03/16/2018 California State Polytechnic University, Pomona FRR

63 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

64 Full-Scale Flight Tests First flight test on February 17, 2018 Friends of Amateur Rocketry, Randsburg, CA Apogee = 6,826 ft Second flight test on February 24, 2018 Mojave Desert Advanced Rocketry Society, Edwards, CA Apogee = 5454ft 03/16/2018 California State Polytechnic University, Pomona FRR

65 Apogee = 6823 feet First Full-Scale Flight Test Weight of full-scale launch vehicle not representative of intended final weight Payload not included in launch test Structural enhancements not yet completed Flight data not used for postflight simulations and drag coefficient calculations 03/16/2018 California State Polytechnic University, Pomona FRR

66 Second Full-Scale Flight Test Apogee reduced to 5460 feet Final weight of launch vehicle representative of intended final weight Slight tangling of main parachute Flight data used for post-flight simulations and drag coefficient calculations Drag coefficient of Percent error of 2.88% 03/16/2018 California State Polytechnic University, Pomona FRR

67 Drag coefficient of 0.59 obtained from subscale flight test data Predicted Flight Model Predicted apogee of feet Percent error of drag coefficient was 31.66% Percent error of predicted apogee was 8.82% 03/16/2018 California State Polytechnic University, Pomona FRR

68 Full-Scale Launch Test Results Launch vehicle was recovered in reusable condition. On-board camera footage revealed the successful, full deployment of the drogue parachute, which was deployed at apogee. The main parachute deployed at 700 feet using its primary ejection charge with no observable tangling of the shroud lines. No damages found on the payload bay. Recovery system allowed for the successful retrieval of the payload bay without any damages to the S.P.O.C. system. Recovery bay was recovered in perfect condition without any damages to the hollowed bulkhead. Structural integrity of the ½ in. thick cast iron bulkhead remained fully intact. Status Completed: 2/17/18 2/24/18 3/3/18 - Cancelled due to poor weather conditions Pass 03/16/2018 California State Polytechnic University, Pomona FRR

69 Full-Scale Launch Test Impact Testing proved that the recovery system could allow for the successful recovery of the payload. First flight test impacted the vehicle construction by promoting the need for structural. enhancements as a way to reduce the apogee and also further improve the overall structural integrity. Second test provided the confirmation that the 4 lb. ballast, its placement on-board the vehicle (in module 3), and the simulated payload mass significantly helped to reduce the altitude. Testing revealed that the launch vehicle and its payload integration components are competition ready. Procedure 1. The launch of the full-scale vehicle will incorporate all procedures outlined in Section The full-scale launch test includes a minimum of two flights deemed successful in recovery and reusability of the launch vehicle post-flight. 3. Any necessary changes shall be made to the launch vehicle pending launch test results, and the final, as-built configuration to be used in competition flight will be tested prior to the FRR milestone. 4. The first launch test will be used to test the changes made to the recovery system referenced in Section The second test will be used to test the integrity and safety of its design, and its stability, using a simulated payload mass and ballast within 10% of the vehicle s total weight. 6. The full-scale flight tests will also be used to ensure that the procedures in Section 6 are accurately outlined and competition ready. 03/16/2018 California State Polytechnic University, Pomona FRR

70 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

71 Verification Methods Nomenclature - 03/16/2018 California State Polytechnic University, Pomona FRR

72 Summary of Verifications Launch Vehicle NASA Launch Vehicle Compliance Matrix Vehicle Requirements Verification Method Status Design Requirements Section Verification Details REQ# Description T A D I V IP NV VR2.1 VR2.2 VR2.3 The vehicle will deliver the payload to an apogee altitude of 5,280 feet above ground level (AGL). The vehicle will carry one commercially available, barometric altimeter for recording An altimeter will be the official altitude used in determining the used to record flight altitude award winner. Teams will receive the data such as altitude maximum number of altitude points (5,280) if and temperature and to the official scoring altimeter reads a value of initiate parachute exactly 5280 feet AGL. The team will lose deployment at one point for every foot above or below the predetermined altitudes. required altitude. Each altimeter will be armed by a dedicated arming switch that is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad. The vehicle was found to deliver the payload to approximately 5,280 feet and meet the minimum rail exit velocity of 52 ft/s. Two 1/2 in. holes will be made on the recovery avionics bay to allow room for arming switches that may be accessed from the exterior & x x x x OpenRocket simulations of final design provide projected altitude, launch tests shall showcase altitude reached. The team shall review the launch vehicle system, subsystems and components design verifying at least one commercially available altimeter. Verify the dimensions are the appropriate size for the selected switches. 03/16/2018 California State Polytechnic University, Pomona FRR

73 Summary of Verifications Launch Vehicle Team-Derived Launch Vehicle Compliance Matrix Derived Requirements - Launch Vehicle Design Requirements Verification Method Status Derivation REQ# Description Verification Method Section T A D I V IP NV U Bolts must stay attached to bulkheads The U Bolts will have enough tensile, shear, and bearing strength x x x Observation Bay s camera can withstand forces during flight, parachute deployment, and landing The camera will be securely mounted with little to no space to move and isolated from contaminants x x x The plate inside of the recovery bay should not move so the e-match will not disconnect or go off early Plug will come out after main parachute deployment The epoxy is strong enough to withstand impulse forces experienced during parachute deployment The plate will securely attached in the bulkhead so it will not move or have anything that could potentially disrupt the e- match Plug will be able to disconnect from bulkhead once parachute deploys. Epoxy must be fully cured and then tested & & & x x x x x x x x x x 03/16/2018 California State Polytechnic University, Pomona FRR

74 Summary of Verifications Payload NASA Payload Compliance Matrix 03/16/2018 California State Polytechnic University, Pomona FRR

75 Summary of Verifications Payload NASA Payload Compliance Matrix ER4.5.3 ER4.5.4 After deployment, the rover will autonomously move at least 5 ft. (in any direction) from the launch vehicle. Once the rover has reached its final destination, it will deploy a set of foldable solar cell panels. The payload obective is to successfully deploy a rover from a safely landed rocket that will travel 5 feet from its landing site. The rover will deploy a set of foldable solar cell panels after reaching its final destination & & 4.5 x x x x x After moving at least 5 ft, deployment of solar panels will take place. The rover must also be tracking movement through the GPS system and the camera system. The deployable rover will be successfully able to navigate 5 feet away from the launch vehicle at landing and will be able to deploy solar panels. These panels will also have a very smooth and simple deployment as they will be held in a closed, face down position on top of the rover, by a servo. Notes Totals /16/2018 California State Polytechnic University, Pomona FRR

76 Summary of Verifications Payload Team-Derived Payload Compliance Matrix Derived Requirements - Payload Design Requirements Verification Method Status Derivation REQ# Description Verification Method Section T A D I V IP NV Battery drained and recharged to no more than2% Solar deployment system requires a maximum of 2% 4.5 X X solar pannels will then be battery life commanded to deploy Fastening system of rover to the pendulum system is required to retain stability throughout flight and ground impact (resist 10 G's) The CG of the rover is offset from the rockets by at least 40% of the length to achieve the pendulum system function Rover must be able to perform all mission functions and remain in standby for 3 hours using less than 5000 mwh of power Pendulum system will undergo series of drop tests to ensure bolt inside the launch vehicle will hold, and ensure hook will hold rover mass; test from 40 ft. Placement of the rover in launch vehicle will be varied and calculated until found to be 40% offset from launch vehicle CG. Rover will be given maximum of 5000 mwh of power and will be left in standby for 3 hours. It will then recieve commands to execute all functions. After moving at least 5 ft, solar panels will be deployed. Rover must perform tracking through GPS and camera. TBA X X TBA X X 4.5 X X 03/16/2018 California State Polytechnic University, Pomona FRR

77 Summary of Verifications Payload Team-Derived Payload Compliance Matrix Rover must be able to be remotely activated within a range of 3000 ft. Battery must be within dimension 1.1 inch diameter, 2.6 inch length GPS must begin sending data to ground station before rover deploys from launch vehicle. Create integrated electrical sys. powered through single battery so rover dimensions aren't increased past pendulum system dimesnions by addition of power source. Rasp Pi program must run as soon as system is turned on without opening terminal Rover will be placed 3000 ft from the computer and commands will be sent to begin movement and deployment. Battery measured and placed in rover frame with other electronics to ensure fitting. Start up time and time to reach nearby satellites tested at various ranges from ground station. Add 9V with a voltage to power the pi. Large battery will be used to power servos, motor, and GPS. Integrate system and try to run. Turn on system and iterate code until power-on is autonomous TBA X X 4.4 X X TBA X X 4.5 X X TBA X X 03/16/2018 California State Polytechnic University, Pomona FRR

78 Summary of Verifications Payload Payload Mission Requirements & Risk Matrix System Requirements (Derived Requirements) Verification Method Status Design Requirements & Risk Mitigation Section Verification Details REQ# Description T A D I V IP NV Risk Level DR1.0 Solar deployment system requires a maximum of 2% Battery drained and recharged to no more than 2% solar pannels will then be commanded to deploy. 4.5 x Conduct verifications by testing the exact battery intended for the mission. 1 1 DR2.0 Fastening system of rover to the pendulum system is required to retain stability throughout flight and ground impact (resist 10 G's) Pendulum system will undergo series of drop tests to ensure bolt inside the launch vehicle will hold, and ensure hook will hold rover mass; test from 40 ft x Pendulum system will have to endure many drop tests that may damage the model /16/2018 California State Polytechnic University, Pomona FRR

79 Summary of Verifications Payload Payload Mission Requirements & Risk Matrix DR3.0 The CG of the rover is offset within the SPOC system by at least 40% of the length to achieve the pendulum system function Placement of the rover in launch vehicle will be varied and calculated until found to be 40% offset from launch vehicle CG x Conduct verifications by collaborating with structures team for an accurate analysis. 1 DR4.0 Rover must be able to perform all mission functions and remain in standby for 3 hours using less than 5000 mwh of power Rover will be given maximum of 5000 mwh of power and will be left in standby for 3 hours. It will then recieve commands to execute all functions. After moving at least 5 ft, solar panels will be deployed. Rover must perform tracking through GPS and camera. 4.5 x Conduct a test to check if the rover in fact is able to perform these tasks. 1 1 DR5.0 Rover must be able to be remotely activated within a range of 3000 ft. Rover will be placed 3000 ft from the computer and commands will be sent to begin movement and deployment. 4.1 x Conduct a test to check if the rover in fact is able to perform the commanded tasks and responses. 1 03/16/2018 California State Polytechnic University, Pomona FRR

80 Summary of Verifications Payload Payload Mission Requirements & Risk Matrix DR6.0 DR7.0 DR8.0 DR9.0 Battery must be within dimension 1.1 inch diameter, 2.6 inch length GPS must begin sending data to ground station before rover deploys from launch vehicle. Create integrated electrical sys. powered through single battery so rover dimensions aren't increased past pendulum system dimensions by addition of power source. Rasp Pi program must run as soon as system is turned on without opening terminal Battery measured and placed in rover frame with other electronics to ensure fitting. Start up time and time to reach nearby satellites tested at various ranges from ground station. Add 9V with a voltage to power the pi. Large battery will be used to power servos, motor, and GPS. Integrate systems and try to run. Turn on system and iterate code until power-on is autonomous 4.4 x TBA x 4.5 x TBA x Visual inspection and checklists. Before a performance test can be conducted, it is necessary to inspect the battery for visual defects and adjustments. Visual inspection and checklists. Before a performance test can be conducted, it is necessary to ensure that the GPS is working regardless if the payload is integrated or not. Visual inspection and checklists to assess the value and quality of the vehicle. Visual inspection and checklists to assess the value and quality of the vehicle Notes Totals /16/2018 California State Polytechnic University, Pomona FRR

81 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission Performance 4.0 Recovery System 5.0 Recovery System Tests 6.0 Payload Design 7.0 Test Plans and Procedures 8.0 Full-Scale Flight Tests 9.0 Summary of Requirements Verifications 10.0 Educational Engagement 03/16/2018 California State Polytechnic University, Pomona FRR

82 Educational Engagement Timeline of Outreach Events: 03/16/2018 California State Polytechnic University, Pomona FRR

83 Educational Engagement Outreach Schedule and Details: Educational Outreach Date School Topic Education/Direct? Wednesday, January 31, 2018 Friday, February 2, 2018 Friday, February 9, 2018 Friday, February 16, 2018 Friday, February 23, 2018 Valley Oaks High School Suzanne Middle School Beckman High School Pioneer Middle School ipoly High School General Presentation - NASA Student Launch Programming's Role with Rocketry Presentation & C++ Coding Activity with Billy the Bronco Launch Vehicle Design and Build Presentation Programming's Role with Rocketry Presentation & C++ Coding Activity with Billy the Bronco Propulsion and Drag's Role with Rocketry & Paper Airplane Activity N Y N Y Y Student Attendance Total 825 Education/Direct 790 Required /16/2018 California State Polytechnic University, Pomona FRR

84 Educational Engagement Valley Oaks High School General Presentation 03/16/2018 California State Polytechnic University, Pomona FRR

85 Educational Engagement Suzanne Middle School Programming s Role with Rocketry Presentation & C++ Coding Activity with Billy the Bronco 03/16/2018 California State Polytechnic University, Pomona FRR

86 Educational Engagement Beckman High School Launch Vehicle Design and Build Presentation 03/16/2018 California State Polytechnic University, Pomona FRR

87 Educational Engagement Pioneer Middle School Programming s Role with Rocketry Presentation & C++ Coding Activity with Billy the Bronco 03/16/2018 California State Polytechnic University, Pomona FRR

88 Educational Engagement ipoly High School Propulsion and Drag s Role with Rocketry & Paper Airplane Activity 03/16/2018 California State Polytechnic University, Pomona FRR

89 Thank you! Questions? 03/16/2018 California State Polytechnic University, Pomona FRR