Preliminary Design Review Agenda Mission Success Criteria - - PowerPoint PPT Presentation
49er Rocketry Team The University of North Carolina at Charlotte Preliminary Design Review Agenda Mission Success Criteria Launch Vehicle Recovery Payload Primary Payload - Unmanned Aerial System Mid-air and
The University of North Carolina at Charlotte
○ Recovery
○ Primary Payload - Unmanned Aerial System ○ Mid-air and Ground Deployment ○ Retention
○
Secondary Payload - Computer Vision
2
The University of North Carolina at Charlotte
3
Item Criteria VMSC 1 The launch vehicle must successfully house the payload until deployment. VMSC 2 The launch vehicle will reach the target altitude within 100 ft. VMSC 3 During ascent, the computer vision (CV) will successfully track the location of the sample recovery area VMSC 6 Each altimeter will have its own dedicated power supply VMSC 7 Drogue parachutes will deploy no later than 2 sec. after apogee. VMSC 8 All pieces of the launch vehicle will land within 90 sec.
Complete vehicle success requirements are located in Sections 3.1.2
The University of North Carolina at Charlotte
○ Will house: motor, modular fin can, recovery system
○ Will house: payload, payload deployment, ground orientation and stabilization, computer vision, and recovery system
4
Specifications Values
Length 106.7 in. Weight 63 lbs Max velocity 600 ft/s Loaded Stability 2.55
The University of North Carolina at Charlotte
○ Low drag coefficient ○ Reduced pressure and wave drag
5
The University of North Carolina at Charlotte
the avionics bay.
6
The University of North Carolina at Charlotte
and recovery system
primary and secondary motors
weight ratio
7
The University of North Carolina at Charlotte
○ High strength to weight ratio ○ Shields altimeters from stray interference
8
The University of North Carolina at Charlotte
9
and with minimal tooling
stability of the rocket
and high strength to weight ratio
The University of North Carolina at Charlotte
projected vehicle weight
○ Boattail and retainer cap are printed from ULTEM due to relative location to extreme heat
10
The University of North Carolina at Charlotte
during launch
vehicle center of pressure or stability
11
The University of North Carolina at Charlotte
Stability margin was calculated using OpenRocket and Barrowmans equations Handbook Criteria:
No Computer Vision
With Computer Vision
Motor Burnout
12
The University of North Carolina at Charlotte
Handbook Criteria
Simulated Data:
13
Primary: Aerotech L2200 Secondary: Cesaroni L2375 Motor Average Apogee (ft) Thrust to Weight Rail Exit Velocity (ft/s)
(ft/s) Max. Acceleration (ft/s²) L2200 4135 7.88 66.3 529 338 L2375 3949 8.77 63.6 526 284
The University of North Carolina at Charlotte
Simulation Results
14
Wind Speed (mph) 5 10 15 20 Apogee (ft) 4256 4214 4161 4086 4032 Time to Apogee (s) 16.8 16.7 16.6 16.4 16.2 Rail Velocity (ft/s) 67.1 67.1 67.1 67.1 67.1
529 529 529 528 527
(ft/s²) 337 338 338 338 338
The University of North Carolina at Charlotte
1. Initial separation. 2. Booster section drogue deployment. 3. Payload section drogue deployment with bagged main parachute.
5. The UAS deployment upon RSO approval. 6. Landing
15
The University of North Carolina at Charlotte
Drogue Parachutes Main Parachutes
16
Type Classic Elliptical Diameter (in) 15 Cd 1.5 Section Booster Payload Type Iris Ultra Compact Iris Ultra Compact Diameter (in) 96 144 Cd 2.2 2.2
The University of North Carolina at Charlotte
Both Altimeter bays will include:
○ 4 for booster, 2 for payload
Payload specific additions include:
17
Booster Recovery Altimeter Bay
The University of North Carolina at Charlotte
18
Section Booster Main Booster Drogue Payload Main Black Powder Charge Size (g) 1.2 .4 1.0
Full ejection charge calculations are located in Section 3.4.2
The University of North Carolina at Charlotte
19
Wind Speed (mph) Booster (ft) Payload with UAS (ft) Payload deploying UAS (ft) 5 508.9 539.1 565.5 10 1017.9 1078.2 1131.1 15 1526.8 1617.3 1696.6 20 2035.7 2156.4 2262.2
Full drift calculations are located in Section 3.5.4
The University of North Carolina at Charlotte
20
Section Times (s) Booster 69.4 Payload with UAS 73.51 Payload Deploying UAS 77.12 Section Mass (lbm) KE (ft-lbf) Nosecone 3 .47 Payload 35.1 64.77 Payload deploying UAS 29.1 44.52 Booster Recovery 11.2 14.86 Booster 13.5 21.53
Complete calculations are located in Sections 5.4.4-5
The University of North Carolina at Charlotte
21
Item Requirement Verification Method Verification Plan 3.8 Each altimeter will have its own dedicated power supply. Inspection & Demonstration Each altimeter will be wired to its own 9V battery housed within the altimeter bay. 3.1.2 Drogue parachutes will be deployed no more than two seconds after apogee. Demonstration The drogues will be set to deploy 1 sec. and 2 sec. after apogee for the booster and payload sections respectively. 3.11 Descent time will be no more than 90 sec. Test The booster section will land in 69.4 sec. and the payload section will land in 77.1 sec.
Complete Recovery verifications are located in Sections 7.1.3
The University of North Carolina at Charlotte
22
Item Requirement Verification Method Verification Plan TDVR 9 The recovery system must allow for the option of mid-flight deployment
Inspection The recovery system of the payload section will be designed to allow for
bay to be accessible during descent. TDVR 10 Altimeters must be able to be armed and disarmed without disassembly
Inspection & Demonstration The altimeter switches will be designed to be accessible through the vehicle airframe.
Complete Team Derived Recovery tables are located in section 5.4
The University of North Carolina at Charlotte
Complete Mission Success Criteria is located in section 4.1.2
23
Item Criteria PMSC 1 The UAS travels autonomously to the SRA using a combination of GPS coordinates and CV. PMSC 2 The UAS autonomously avoids objects and collisions using onboard sensors and CV. PMSC 4 Flight and control of the UAS is assisted using the ACS. PMSC 6 The UAS and deployment system will be capable of both mid-air deployment and ground deployment. PMSC 7 The ground deployment stabilization system orients the UAS within ±5 degrees normal to the ground. PMSC 9 A minimum of 15 mL of ice simulant sample is collected and retained during the mission.
The University of North Carolina at Charlotte
24
The University of North Carolina at Charlotte
25
○ Auxiliary control surfaces ○ Folding propellers ○ Hinged camera mount ○ Autonomous flight with manual override
The University of North Carolina at Charlotte
26
The University of North Carolina at Charlotte
27
The University of North Carolina at Charlotte
28
The University of North Carolina at Charlotte
following mid-air deployment
without pitching the airframe
29
The University of North Carolina at Charlotte
30
Stabilization Doors Sealant Cap Deployment Rail
The University of North Carolina at Charlotte
31
3. 1. 2. 4. 1. Initial 1. Stabilization 1. Ground Clearance 1. Deployed
The University of North Carolina at Charlotte
32
1. 3. 2. 4. 1. Main Parachute Opens 1. Sealant Cap Opens 1. Ejection 1. Deployed
The University of North Carolina at Charlotte
○ Lead screw threaded into rear of UAS
○ Rollers mounted to bottom plate, slotted into payload bay, prevents UAS motion off of the plate
○ Servo actuated pin to prevent lead screw rotation ○ Payload bay lid will retain UAS in case of critical retention failure ○ Shift of UAS location in payload bay disconnects deployment control, defaults to ground deployment
33
The University of North Carolina at Charlotte
simulant
○ Semi-cylinder will rotate 180 degrees and scoop the collected sample ○ Powered by a micro spur gear motor
34
The University of North Carolina at Charlotte
35
The University of North Carolina at Charlotte
○ 5 lbs of thrust per motor
○ 1000 KV ○ Max current of 47 A ○ 5.47 oz
○ 50 A max continuous current ○ 55 A max < 30 sec ○ 7.2 V to 11.1 V input ○ 1.7 oz
36
The University of North Carolina at Charlotte
○ Runs Linux OS ○ Run programs and scripts written in Python and C/C++
○ Control UAS motors ○ Control Auxiliary Control Surfaces (ACS) ○ Runs ArduPilot flight stack ○ Supports autonomous flight through MAVLink protocol
37
The University of North Carolina at Charlotte
by a color camera
locate SRA site
markings
faster processing
38
25 ft
The University of North Carolina at Charlotte
stereoscopic vision algorithm
creates depth map
avoid them
39
The University of North Carolina at Charlotte
○ 2.4 GHz ○ 16 channels ○ Programmable switches ○ For manual control of UAS
○ 2.4 GHz ○ 8 Channels ○ SBus compatible ○ .59 oz
40
The University of North Carolina at Charlotte
○ 902-928 MHz ○ 200 Kbps up to 4 miles ○ 250 mW transmit power ○ Used for both transmitter and receiver
○ Deployment receiving antenna ○ 902 - 928 MHz ○ 0 dBi gain ○ 10 W max power
41
The University of North Carolina at Charlotte
○ Handheld for deployment signal ○ 902-928 MHz ○ 15 dBi ○ 50 W max output power ○ 2.54 lbs ○ Connects to XBee-Pro
42
The University of North Carolina at Charlotte
43
Component Current Draw (mA) Quantity Operation Time (min) Current Consumed (mA) Motors 12000 4 8 9000.00 Control Surface Servo 250 4 2 167.00 Flight Controller 3000 2 10 500.00 NanoPi SBC 2000 1 8 334.00 STM32 Blue Pill microcontroller 100 1 10 100.00 Cameras 185 2 8 62.00 Sample Collection Servo 250 1 2 9.00 Total Current (mAh) 10,172
Complete calculations are located in Sections 4.6.3
The University of North Carolina at Charlotte
voltages for seperate systems
○ UAS will be in low-power mode until deployment ○ UAS siphons power from battery on Vehicle until deployment ○ Microcontroller switches between the two batteries
44
Device Power rail requirement NanoPi SBC 5V / 2A rail STM32 Blue Pill 3V / 0.5A rail Servos for stereo vision 5V / 0.5A rail Motors for propulsion 11.1V / 50A rail
The University of North Carolina at Charlotte
apogee
launch site
ground location
45
The University of North Carolina at Charlotte
46
Item Requirement Verification Method Verification Plan 4.3.2 A sample recovery site will be located
Demonstration, Test The UAS will utilize sensors and computer vision to determine the sample recovery site. A secondary payload will assist in location of recover sites using computer vision. The autonomous navigation to sample recovery sites will be tested prior to and in the full scale test launch. 4.3.7.4 Shear pins will not exclusively be used for retention. Demonstration The retention system will not use shear pins.
Complete Payload Requirements located in section 6.1.3
The University of North Carolina at Charlotte
47
Item Requirement Verification Method Verification Plan TDPR 1 UAS weight will be less than 7 lbs. Analysis CAD design for estimate, measure using scale for actual. TDPR 5 UAS control surfaces will be able to rotate ±30 degrees normal of the axis
Test Ground and full-scale testing. TDPR 8 The payload bay will protect the UAS and deployment system from recovery charges. Test Ground and full-scale testing.
Complete Team Derived Payload Requirements located in section 6.1.2
The University of North Carolina at Charlotte
○ Primary: David Clifton ○ Backup: Samantha McKinney
○ Team Safety Briefing ■ UNCC Safety Handbook ■ Safety Checklists ○ Safety Verification ■ Signature approval ○ Hazard analysis ■ FMEAs
Probability Severity 1 2 3 4 Catastrophic Critical Marginal Negligible A - Frequent 1A 2A 3A 4A B - Probable 1B 2B 3B 4B C - Occasional 1C 2C 3C 4C D - Remote 1D 2D 3D 4D E - Improbable 1E 2E 3E 4E
48
Risk Assessment Codes located in section 5.2
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC Injury from catastrophic on take-
Disregard of required withdrawal distances for high power rockets Severe bodily injury from expelled material 1C All team members will strictly adhere to a withdrawal distance of 300 ft Procedure 1E Injury in machine shop Lack of attention to work Serious bodily injury 1C All team members must take required safety tests and adhere to all posted machine shop rules Procedure 1E
49
Complete Personnel Hazard Analysis located in section 5.2
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC CATO Manufacturer preparation and handling guidelines not followed Loss of launch vehicle 1A Motor preparations will be supervised and signed by the safety officer to ensure guidelines are followed Procedure 1E Motor retainer failure Motor retainer not secured Severe damage to or loss of vehicle 1C Motor retainer will be securely inserted into the booster section using epoxy Design, Analysis, Testing 1E
50
Complete Vehicle FMEA table located in section 5.3.1
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC Parachute is tangled upon deployment Poor packing of parachute allows for catching upon recovery deployment Parachute does not fully inflate 1C Packing of the parachutes will be inspected prior to launch Procedure 1E Tender descender fails to open Ejection charge not large enough to deploy Parachute cannot fully inflate 3C Ejection charge size will be calculated Analysis, Testing 3E
51
Complete Recovery FMEA table located in section 5.3.1
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC Damage to payload due to ejection charge ignition Payload bay sealant cap cannot withstand pressure generated during recovery events
sealant cap
payload components 1A Ground testing of the effects of energetics on the sealant cap will be conducted to validate structural integrity Analysis, Testing 3E Loss of power
to initialise upon deployment
to complete mission
UAS
mission requirements 1C
connections will be checked prior to any launch day operations
be charged and checked prior to arriving at the launch site Procedure 1E
52
Complete Payload FMEA table located in section 5.3.2
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC Aerial deployment not permitted by Federal Aviation Administration (FAA) FAA does not permit the competition site a waiver for 14 CFR part 107: Small Unmanned Aircraft Systems Payload will be restricted to a 400ft maximum deployment altitude or default to a ground deployment 1B The payload will be retained within the payload bay until below 400 ft to remain compliant with regulations 14 CFR part 107 and 49 U.S. Code 44809 Design, Procedure 1E NAR certified personnel cannot attend launch Schedules do not work for NAR certified personnel Launch must be postponed 1B Schedules will be discussed and launch days planned in advance to ensure all required personnel are present Procedure 1E
53
Complete Launch operations hazards table located in section 5.3.3
The University of North Carolina at Charlotte
Hazard Cause Effect Pre-RAC Mitigation Mitigation Type Post-RAC High winds at launch High pressure cell in area
change vehicle flight dynamics
1C Team will check all weather forecasts prior to launch day to determine if launch conditions are met Procedure 1E Rain Storm fronts in the area
critical electronics
launch 1C Critical electronics will be kept in waterproof containers until ready to be installed in launch vehicle Procedure 1E
54
Complete Environmental Hazards table located in section 5.4
The University of North Carolina at Charlotte
Hazard Impact Probability Quantification Mitigation Lack of funding High High Team members will participate in fundraisers, crowdfunding efforts, and additional work opportunities Inability to achieve necessary funding will require allocating
delays and inability in
Critical damage to sub- scale or full-scale launch vehicle High High New components will need to be constructed increasing project costs and delaying project deadlines Vehicle components and recovery systems will be tested prior to launch
55
Complete Risks to Project Completion table located in section 5.5
The University of North Carolina at Charlotte
56
Milestone Date Proposal September 18, 2019 Preliminary Design Review November 1, 2019 Conceptual Design Review January 10, 2020 Flight Readiness Review March 2, 2020 Vehicle Demonstration Flight March 2, 2020 Payload Demonstration Flight March 23, 2020 Launch Date April 4, 2020
Complete Project plan located in Section 7.3
The University of North Carolina at Charlotte
57
Category Amount Launch Vehicle $12,478.19 Payload $4,274.78 Testing $1,000.00 Outreach $500.00 Travel $9,000.00 Total $27,252.97
Complete budget is located in Section 7.3.2
The University of North Carolina at Charlotte
58
Funding Source Amount Niner Nation Gives $7,103 NC Space Grant $5,000 Crowdfunding $10,000 Bridge Tournament $1,000 Department and College $4,000 Senior Design $2,000 Total $29,103
Complete Funding plan can be located in section 6.2.1
○ On campus outreach to garner interest in the team ○ Maintain workspace and resources for future teams
The University of North Carolina at Charlotte
○ Charlotte Kids’ Fest - 6500 attendees ○ J.M. Robinson Middle School - 150 attendees ○ Explore! - 200 attendees
○ Johnston YMCA ○ UNCC Athletics/Baseball Event
59
Complete Educational outreach event list is located in section 7.3.3
The University of North Carolina at Charlotte
60
Item Requirement Verification Method Verification Plan 1.1 The 2019-2020 49er Rocketry Team will be responsible for completing all tasks associated with the project except for handling of any ejection charges, preparation of ejection charges,
Inspection A team mentor will be designated to handle all aspects of the ejection charges and installation of electronic matches. 1.4 All team members attending the launch week activities must be submit by the CDR including students, a mentor, and no more than two adult educators. Inspection The project lead will compile and submit team information and forms to NASA. 1.7 All necessary forms and submissions to NASA project management will be submit by the team in a timely manner, in advance of deadlines. Inspection The project plan will be maintained to reflect necessary submissions to
compile and submit all information and forms for submission to the NASA project management team. Complete General Requirements located in section 6.1.3
The University of North Carolina at Charlotte
61