Flight Readiness Review 1 Agenda Launch Vehicle Recovery - - PowerPoint PPT Presentation
49er Rocketry Team The University of North Carolina at Charlotte Flight Readiness Review 1 Agenda Launch Vehicle Recovery Payload Primary Payload: UAS Retention and Deployment Camera Vision Safety
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○ Booster (ID) : 5 in. ○ Payload (ID) : 6 in. ○ Thickness : 1/16 in.
○ Total Length: 111 in. ○ Loaded Mass: 67.7 lbm.
○ 4000 ft. AGL
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○ Length: 9 in. ○ Aft Diameter: 6 in. ○ Material: ABS
○ Length: 46 in. ○ Inner Diameter: 6 in. ○ Material: Quasi-isotropic Carbon Fiber
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○ Loacates SRA locations on ascent
○ Camera (4x) ○ Computer ○ Battery
○ Inner mount - 5.5 in. length ○ camera mount - angles camera 30 deg ○ camera shield - teardrop shape ○ All hardware 3D printed from PETG
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○ Quasi-isotropic Carbon Fiber ○ 56 in.
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Booster Section Component Mass (lbm) Booster Recovery 5.90 Transition 1.77 Modular Fin Can 3.63 Motor And Retention 15.9 Booster Airframe 1.70 Total 28.9 Payload Section Component Mass (lbm) Nose Cone 2.15 Payload Recovery 7 GSOS 9.5 Computer Vision 3.53 Primary Payload 14.05 Payload Airframe 2.57 Total 38.8
Launch Vehicle Section Mass (lbm) Payload 38.8 Booster 28.9 Total 67.7
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2.3 (s)
10.5 (lbm)
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Total Mass (lbm) Ballasted Mass (lbm) Static Stability Post-Burnout Stability 67.7 0.0 3.0 3.73
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Wind Speed (mph) Simulated (ft) Calculated (ft) Percent Difference
3766 3875 2.81 5 3740 3854 2.96 10 3723 3797 1.95 15 3659 3711 1.40 20 3621 3604 0.47
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1. Initial separation at apogee with booster drogue deployment.
ft-lbf of kinetic energy
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○ Size: 96 in. ○ Cd: 2.2 ○ Shape: Annular ○ Descent Rate: 12.12 ft/s
○ Size: 144 in ○ Cd: 2.2 ○ Shape: Annular ○ Descent Rate: 10.53 ft/s
○ Size: 15 in. ○ Cd: 1.5 ○ Booster Descent Rate: 93.94 ft/s ○ Payload Descent Rate: 133.2 ft/s
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○ 45 ft total
○ 3/16 in. Quick Links ○ 1/4 in. Quick Links ○ 1/4 in. Stainless Steel Eyebolt ○ 3/8 in. Stainless Steel Eyebolt ○ Tender Descender Level 3
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○ 30 ft total
○ 3/16 in. Quick Links ○ 1/4 in. Stainless Steel Eyebolt ○ 3/8 in. Stainless Steel Eyebolt
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Full details of the recovery system are located in Section 3.3.
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Parachute deployment bag Tender Descender L3
Component Payload Section Booster Section Deployment Bag 1 Stratologger CF 2 2 Telemega 1 B.P. Charge Wells 2 4 Nomex Blankets 1 2 CF Bulkhead 2 AL Bulkhead 1 1
PerfectFlite StratologgerCF
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Wind Speed (mph) Booster Drift (ft) Payload Drift With UAS (ft) Payload Drift Without UAS (ft) 5 476.9 518.2 540.7 10 953.8 1036.5 1081.4 15 1430.6 1554.7 1662.0 20 1907.5 2073.0 2162.7
Within NASA requirement of 2,500 ft.
Full drift calculations are located in Section 3.4.9.
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Section Landing KE (ft-lbf ) Booster 25.56 Booster Recovery 8.95 Payload with UAS 67.38 Payload without UAS 46.69 Nosecone .47
Full calculations are located in Section 3.4.7 and 3.4.8.
Within NASA requirement of 75 ft-lbf
Booster (s) Payload with UAS (s) Payload without UAS (s) 65.03 70.67 73.73
Within NASA requirement of 90 sec.
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Tracker Frequency Location Comm Specialists, Inc RC-MP 222.330 MHz Booster Shock Cord Comm Specialists, Inc RC-MP 223.010 MHz Payload Shock Cord
Full specifications are located in Section 3.3.10.
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Launch Day Conditions - 02/22/2020
Onboard Equipment
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Apogee (ft) Time to Apogee (s) Velocity (ft/s) Acceleration (ft/s^2) 4098 16.7 920 308
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Payload Section
Apogee: 4180 ft.
Booster Section
Apogee: 4099 ft
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Payload Section ~2190 ft. drift Booster Section ~1850 ft. drift
Full results are located in Section 5.1.2.
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Full analysis of the flight is Located in Section 5.1.2. Vehicle Section Landing Velocity (ft/s) Payload 83.2 Booster 14.1 Vehicle Section Landing Kinetic Energy (ft-lbf) Nosecone 332.6 Payload 678.5 Booster 45.4 Booster Recovery 26.8
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Full vehicle test plans are located in Section 7.1.
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Full Vehicle Verification Requirements Located in Section 8.4.
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Full Vehicle Verification Requirements Located in Section 8.4.
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1. UAS travels to flight altitude of 25 ft. 2. UAS navigates towards SRA GPS coordinate. 3. UAS implements CV
SRA. 4. UAS arrives at SRA. 5. UAS lands outside and waits for sample collection signal. 6. UAS receives sample collection signal, lands in SRA, and collects sample. 7. UAS transports sample 10 ft away from SRA.
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○ Thrust-to-weight ratio: 3.1
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1.00 in. 1.25 in. 16.0 in. 5.43 in. 4.79 in. 5.43 in.
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12.1 in. 14.4 in. 5.86 in. 16.6 in. With Propellers Width = 28.6 in. Length = 26.4 in. Height = 5.86 in. Diagonal = 33.9 in.
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○ 0.0625 in. thick ○ High Modulus Twill Weave
Aluminum Standoffs
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1. Swivel Camera Mount 2. NanoPi Neo Core 2 3. LiDAR Sensor 4. 11000 mAh LiPo Battery 5. Sample Collection and Storage 6. EJ501a Quick Disconnects 7. LM2596 Power Converters 8. FrSky Taranis Receiver 9. Airbot 200 A PDB 10. Pixhawk 4 11. Grayson Hobby 50A ESCs 12. STM32 Blue Pill 13. Pixhawk 4 GPS 14. Maxbotix MB1240 Ultrasonic Sensor
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Standoffs and fixtures used
to carbon fiber frame plates.
using velcro tape.
plate using dampening foam strip.
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Pixhawk 4 GPS LiDAR & NanoPi Ultrasonic Sensor Quick Disconnect
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tube supports load
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○ 12 in. diameter ○ 5 in. pitch
○ 770 W maximum continuous power ○ Weight: 5.89 oz.
○ 50 A maximum continuous current draw ○ 55 A peak current draw (<30 seconds) ○ Input voltage: 11.1 V, 3S
○ Additively manufactured from PETG ○ Strength successfully verified through testing
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sample
manufactured from PETG
theoretically ○ 32 mL collected in testing
○ 170 oz/in torque at 6 V ○ 1:1000 gearbox ○ Weighs 0.257 oz. ○ 360 degrees of rotation
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○ Main flight controller ○ Supports UART and I2C protocols ○ Supports autonomous flying and mission planning
○ Companion computer ○ Sends autonomous control commands to Pixhawk 4 ○ Sends microcontroller when to start sample collection
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UART
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○ UBLOX M8N GPS unit ○ IST8310 Compass unit ○ Primary sensor for navigation
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○ Used for Stereovision ○ Detects obstacles and SRA site
○ Backup sensor for object avoidance
○ Handled by NanoPi Neo Core 2 ○ Uses OpenCV library
○ Actuated using MG90s micro servo
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○ 10 Hz sample rate ○ Range: 0.7-25 ft. ○ 0.4 in. resolution
○ 600 Hz sample rate ○ Range: 45.9 ft. ○ 1.57 in. resolution
○ Processed by NanoPi SBC ○ Used to construct autonomous commands
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○ 2.4 GHz ○ 16 Channels
○ 2.4 GHz ○ 8 Channels ○ 16 Channels with SBUS
○ Three position switch ‘SE’ for autonomous flight, UAS hover, and manual flight ○ Two position switch ‘SF’ for UAS SRA landing ○ Two position switch ‘SH’ for sample collection
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SE SF SH
FrSky X8R Receiver FrSky Taranis X9D Transmitter
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flight
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SE SF SH
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○ 11000 mAh ○ 3 cell ○ 11.1 V ○ 40C discharge rate
○ Adjustable output by potentiometer ○ Converts 11.1 V to 5 V ○ Converts 11.1 V to 3.3 V
○ 16 AWG for 50A ○ 8 & 10 AWG for 200A
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11.1 V LiPo Battery Airbot 200A PDB LM2596 DC-DC Converter
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supply from launch vehicle battery to the UAS battery at launch
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○ 902 - 928 MHz @ 250 mW ○ 200 Kbps up to 4 miles ○ Used for both transmitter and receiver
○ Altitude receiving antenna ○ Deployment transmitting antenna ○ Connects to GCS
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○ 900 MHz @ 250 mW ○ Deployment receiving antenna ○ Located inside sealant cap
TeraWave 900 MHz 15 dBi Yagi Antenna ArcAntenna Dipole Whip Antenna in Sealant Cap
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○ Graphs real-time altitude of payload section ○ Generates deployment signal ○ Generates reset commands
○ Transmits signal from laptop to payload section ○ Receives signal from payload section
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○ Single board computer ○ Sends SRA GPS location to UAS over CAN bus ○ Sends Telemega altimeter data to deployment microcontroller to be sent to GCS
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Coordinate
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ODROID-N2 ELP USB Camera
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Four Subsystems:
Orientation (GSOS)
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CAD Rendering Bulkhead and Lead Screw UAS Interference
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brushless DC motor
○ 3 mm pitch ○ Additively Manufactured PETG Belt Clamp
○ 4.71:1 gear ratio ○ Park brake mechanism with MG90s micro servo ○ Additively manufactured from PETG
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door for stabilization
rotation for orientation ○ 2678 oz.-in. torque ○ GT2 Belt, 5 mm pitch ○ Additively manufactured belt clamp
determine orientation
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1 2 3 4 5
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○ 611 oz. - in. of torque
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Payload Demonstration Flight can be found in Section 5.2
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Testing of Payload Systems can be found in Section 7.2
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Unique ID Verification Plan Verification Status and Progress Report Location SOW 4.2 A system will be designed capable of being launched in a high-powered rocket, deploying safely, and recovering simulated lunar ice from one of several locations on the surface
safe by NAR, FAA, and NASA as well as will
adhere to the intent of the challenge. Additional experiments will be documented appropriately and will not contribute to scoring. In Progress The design, analysis, construction, and testing
verification flight remaining. Section 4 SOW 4.3.1 The launch vehicle will be launched from the NASA-designated launch area using provided launch pad. All hardware utilized during the mission must be launched within the launch vehicle. Complete Payload systems have not been designed to use hardware besides that included within the launch vehicle and to be launched from a NASA-designated launch area using provided launch pad. Section 4
Requirements Verification can be found in Section 8.4
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Team Derived Payload Requirements can be found in Section 8.3
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○ Updated list items ○ Payload preparation
○ Troubleshooting
○ Finalized verifications
○ Finalized assembly manual
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○ Packing List ○ Component Inspection
○ Recovery ○ Payload ○ Vehicle
○ Setup on pad ○ Igniter Installation
○ Component Inspection
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Full Scale Launch Checklists can be found in section 6.1
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Personnel Hazard Analysis can be found in section 6.2.2
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Vehicle FMEA can be found in section 6.2.3
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Payload FMEA can be found in section 6.2.4
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Environmental Hazard Analysis can be found in section 6.2.5
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Verification of Requirements can be found in section 8.4
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○ Vehicle Demonstration Flight - February 22, 2020 ○ Payload Demonstration Flight - March 7, 2020
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Project Plan can be found in Section 9.5, Appendix D
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Events Date
Charlotte Kid’s Fest 10/12 314 Freshman Learning Community 9/9 400 J.M. Robinson Middle School 10/7-10/8 150 Weddington High School 10/21 60 TARC Team Mentoring Recurring 8 Explore! 10/12 200; 200 UNCC Athletics 2/8 150 Mallard Creek Elementary 12/17, 2/4-2/24 75 Discovery Day Takeover 2/21 400 Total 1,965
Educational Engagement can be found in Section 8.7
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Source Amount Niner Nation Gives $7,103.00 NC Space Grant $6,000.00 Crowdfunding $11,497.00 Bridge Tournament $1,700.00 ISL Department/College $4,000.00 Total: $30,300.00 Category Amount Vehicle $12,478.19 Payload $4,274.78 Testing $1,000.00 Outreach $500.00 Travel $6,104.00 Shipping $211.34 Total: $24,568.31
Budget and Funding Plan can be found in Sections 8.6 and 8.7
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General NASA Requirements can be found in Section 8.4
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