CDR - Critical Design Review 1 Agenda Launch Vehicle Recovery - - PowerPoint PPT Presentation
49er Rocketry Team The University of North Carolina at Charlotte CDR - Critical Design Review 1 Agenda Launch Vehicle Recovery Overview Subscale Flight Analysis Payload Safety Project Plan The University of
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Airframe Dimensions Booster (ID) 5 in. Payload (ID) 6 in. Wall Thickness 1/16 in. Vehicle Summary Total Length 110 in. Loaded Mass 63 lbm Target Altitude 4000 ft
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LD Haack Nosecone
Length 9 in. Length:Diameter 1.5 Material ABS
Airframe
Material Quasi-isotropic Carbon Fiber Inner Diameter 6 in. Length 64 in.
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Computer Vision (CV)
Components
Mounting
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Component Material Fins Polycarbonate Fin Retainer ULTEM 9085 Boattail ULTEM 9085
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Airframe
Material Quasi-isotropic Carbon Fiber Inner Diameter 5 in. Length 30.5 in. Transition 4 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 16.5 Booster Airframe 1.70 Total 29.5 Payload Section Component Mass (lbm) Nose Cone 2.15 Payload Recovery 7 GSOS 7 Computer Vision 3.53 Primary Payload 11.25 Payload Airframe 2.57 Total 33.5
Launch Vehicle Section Mass (lbm) Payload 33.5 Booster 29.5 Total 63
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Total Impulse (lbf/s) 1147 Maximum Thrust (lbf) 697 Average Thrust (lbf) 495 Burn Time (s) 2.3 Total Mass (lbm) 10.5 Propellant Mass (lbm) 5.5
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Total Mass (lbm) 63.0 63.5 64.0 64.5 65.0 65.5 66.0 Ballast Mass (lbm) 0.0 0.5 1.0 1.5 2.0 2.5 3.0 Static Stability 2.61 2.68 2.75 2.82 2.89 2.96 3.02 Post-Burnout Stability 3.20 3.27 3.35 3.42 3.49 3.56 3.63
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Wind Speed (mph) Simulated Calculated Percent Difference
4221 4268 1.10 5 4177 4244 1.57 10 4116 4178 1.48 15 4077 4078 0.02 20 3986 3955 0.78
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1. Initial separation at apogee with booster drogue deployment.
ft-lbf of kinetic energy
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Size 15 in. Cd 1.5 Shape Elliptical Booster Descent Rate 93.94 ft/s Payload Descent Rate 133.2 ft/s 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 Booster Main Parachute Payload Main Parachute Drogue Parachutes
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○ 30 ft. total
○ 3/16 in. Quick Links ○ ¼ in. Stainless Steel Eyebolt ○ ⅜ 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 3.4.
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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) 5 575.7 512.7 535.2 10 1151.5 1025.5 1070.4 15 1727.2 1538.2 1605.5 20 2303.0 2051.0 2140.7
Within NASA requirement of 2,500 ft.
Full drift calculations are located in Section 3.5.10.
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Section Landing KE (ft-lbf ) Booster 23.58 Booster Recovery 3.17 Payload with UAS 69.28 Payload without UAS 48.27 Nosecone .33
Full calculations are located in Section 3.5.8 and 3.5.9.
Within NASA requirement of 75 ft-lbf
Booster (s) Payload with UAS (s) Payload without UAS (s) 78.51 72.98 69.92
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
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First Subscale Flight
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Component Recorded Simulated Percent Difference Apogee (ft) 1605 1670 3.9%
(ft/s) 330 340 2.9% Time to Apogee (s) 10.5 10.6 0.94%
Second Subscale Flight
Component Recorded Simulated Percent Difference Apogee (ft) 1662 1672 0.6%
(ft/s) 335 328 2.1% Time to Apogee (s) 10.5 10.5 0%
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Third Subscale Flight
Component Recorded Simulated Percent Difference Apogee (ft) 1600 1662 3.7%
(ft/s) 342 329 3.8% Time to Apogee (s) 10.5 10.6
0.94%
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Second Flight
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Value Recorded Theoretical Percent Difference Apogee (ft) 1605 1670 3.9% Descent Time (s) 38 36.5 3.9% Landing KE (ft-lbf) 62 52 16.0% Value Recorded Theoretical Percent Difference Apogee (ft) 1662 1672 0.6% Descent Time (s) 37.2 40.2 7.5% Landing KE (ft-lbf) 60 50 16.7%
First Flight
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Third Flight
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Full analysis of subscale flights is Located in Section 3.3.
Value Recorded Theoretical Percent Difference Apogee (ft) 1600 1662 3.7% Descent Time (s) 36 39.4 8.6% Landing KE (ft-lbf) 60 50 16.7%
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1. UAS travels to flight altitude of 25 ft 2. UAS navigates towards SRA GPS coordinate. 3. UAS implements CV once within 50 ft of 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
○ Additively manufactured electronics mounts
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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
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PETG Standoffs and fixtures used
component orientation important.
electronics to carbon fiber frame plates.
fiber plate using velcro tape.
carbon fiber plate using dampening foam strip.
Ultrasonic Sensor Mounting Fixture EJ501a Quick Disconnect Mounting Fixture LM2596 Mounted to Carbon Fiber Using PETG Standoffs LiDAR and NanoPi Mounting Fixture
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carbon fiber tube supports load
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6061 T6 aluminum.
each arm in place.
unfolding.
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maneuvering.
streamlined carbon fiber tube.
rotation into ACS rotation.
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sample.
manufactured from PETG.
○ 170 oz/in torque at 6 V ○ weighs 0.257 oz. ○ 360 degrees of rotation
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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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○ 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
○ PETG ○ Strength successfully verified through testing
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Turnigy Aerodrive Sk3 on Thrust Test Stand with Additively Manufactured PETG Propeller Adaptor
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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 ○ Will detect and avoid obstacles ○ Will detect SRA site
○ Backup sensor for object avoidance
○ Handled by NanoPi Neo Core 2 ○ OpenCV library ○ Hardware optimizations
○ Rotates swivel mount 90 degrees.
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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
○ Done by NanoPi ○ Used to construct autonomous commands
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○ 902 - 928 MHz @ 250 mW ○ 200 Kbps up to 4 miles ○ Used for both transmitter and receiver
○ Altitude signalling antenna ○ Deployment receiving antenna ○ Located inside sealant cap
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○ Altitude receiving antenna ○ Deployment transmitting antenna ○ Connects to GCS
TeraWave 900 MHz 15 dBi Yagi Antenna TE Connectivity AMP Connector 1513168-1
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○ Receives and graphs altitude ○ Initiates deployment ○ Initiates reset commands
○ Transmit signal from laptop to payload section. ○ Receives signal from payload section
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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 ○ Discharge rate: 40C
○ Adjustable by potentiometer ○ 11.1 V to 5 V ○ 11.1 V to 3.3 V
○ 12 AWG for 50 A ○ 8-10 AWG for 200 A ○ Airbot 200 A PDB
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LM2596 DC-DC Converter Airbot 200A PDB 11.1 V LiPo Battery
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○ Single board computer ○ Sends SRA’s GPS location to UAS over CAN bus ○ Sends altimeter data to deployment microcontroller to be sent to the GCS
ODROID-N2 ELP USB Camera
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Subsystems:
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for axial and radial loads
with slots for torsional and radial loads
prevents backdriving of the leadscrew
transfer force to a carbon fiber bulkhead
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the telescoping slides
used to increase torque for midair deployment
decrease speed for ground deployment
during midair deployment.
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Deployment Motor and Gearbox Telescoping Slides
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gearmotors drive the doors for stabilization
drives rotation for
○ 2678 oz-in torque ○ Belt drive
determine orientation
and disengage park gears
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in two halves from PETG
Motors ○ 333.4 oz-in. Torque
○ Two 0.125 in. Thick 6061 T6 Bars
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○ David Clifton
○ Tyler Watkins
○ “Living documents” to be updated after each launch
○ Personnel ○ Environmental ○ FMEA
○ Updated with current applicable regulatory information, hazard analyses, and MSDSs for team reference
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○ Recovery Systems ○ Motor
○ Launch Vehicle
○ Setup on Launch Pad ○ Igniter Installation
○ Disarm ○ Disassembly
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Complete Testing Plan is located in Section 6.1.
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Complete Testing Plan is located in Section 6.2.
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Full General Requirements Verifications are Located in Section 7.4.
Unique ID Verification Plan Verification Status and Progress Report Location SOW 1.1 A team mentor will be designated to handle all aspects of the ejection charges and installation of e-matches. In Progress Verification of this requirement will be conducted throughout the project. N/A SOW 1.2 The project manager will be assigned to update and revise the project plan throughout the project. In Progress The project lead and manager will communicate with the team to ensure necessary progress is being made. N/A SOW 1.3 Foreign National (FN) team members must be identified prior to submission of the PDR. Complete N/A SOW 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. Complete N/A
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Full Vehicle Requirements Verifications are Located in Section 7.4.
Unique ID Verification Plan Verification Status and Progress Report Location SOW 2.1 The launch vehicle will reach a called altitude through a combination of design elements. Incomplete The Target altitude was declared and will be verified at the competition launch. Section 3.2 SOW 2.2 The team has designated a target apogee of 4,000 ft. Complete N/A SOW 2.3 An Altus Metrum TeleMega altimeter will be housed in the payload altimeter bay and used to record the official altitude on launch date. In Progress An Altus Metrum Telemega will be used as the scoring altimeter and will be confirmed in the LRR. Section 3.4.2 SOW 2.4 The rocket is designed using high strength materials such as carbon fiber to prevent damage to the vehicle. In Progress The launch vehicle will use repackable chutes and robust design to ensure relaunch on the same day. Section 3.5.11
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Full Recovery Requirements Verifications are Located in Section 7.4.
Unique ID Verification Plan Verification Status and Progress Report Location SOW 3.1 The launch vehicle recovery system will deploy the drogue parachute no later than 2 \textit{sec} after apogee and deploy the main parachute no lower than 500 \textit{ft}. Incomplete The full-scale recovery system will be tested at full-scale launches. Section 6.1.10 SOW 3.2 Ground testing will be done to test parachute ejection prior to launch. In Progress Ground testing of subscale has been completed and the recovery officer and safety officer will conduct future full-scale tests. Section 6.1.9 SOW 3.3 Minimum parachute sizes were calculated to meet kinetic energy landing requirements. In Progress Requirement will be further verified in full-scale test launches. Section 3.5.8 SOW 3.4 Each main altimeter will have a matching redundant backup. Complete All avionics bays have been designed to include a full set of redundant altimeters. Section 3.4.4
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Full Payload Requirements Verifications are Located in Section 7.4.
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 and analysis of all payload systems are finalized with some subsystems undergoing testing and others undergoing fabrication before testing can occur. 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
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Full Safety Requirements Verifications are Located in Section 7.4.
Unique ID Verification Plan Verification Status and Progress Report Location SOW 5.1 The Safety Officer will be required to compile all safety checklists for launch day activities prior to the CDR. In Progress Section 5.2 SOW 5.2 David Clifton has been identified as the primary safety officer for the 49er rocketry team with Tyler Watkins acting as the backup safety officer. Complete Section 5.1 SOW 5.3 The safety officer will be present at all of the
atmosphere of safety. In Progress Section 5.2 SOW 5.4 The safety officer must have a detailed knowledge of all range safety rules and be able to convey those rules to all members attending the launch day events. In Progress Section 5.3
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Full Team Derived Requirements Verifications are Located in Section 7.2.
Unique ID Verification Plan Verification Status and Progress Report Location TDVR 1 Calculations will be done to ensure that CV housing does not significantly impact the launch vehicle CP. Complete Section 3.2.3 TDVR 2 The deployment stabilization system will be tested on a variety of terrains to confirm its usability on the launch field. Incomplete The stabilization system will be ground tested and this requirement verified upon completion
Section 3.2.4 TDVR 3 CFD and simulation software will be used to simulate launch vehicle flight and confirm predicted stability. Subscale flights will verify construction methods ensuring a safe launch vehicle. Complete Section 3.5.1 TDVR 4 Calculations will be done on different fin shapes to assess changes to CP. In Progress Section 3.2
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Full Team Derived Payload Requirements Verifications are Located in Section 7.3.
Unique ID Verification Plan Verification Status and Progress Report Location TDPR 1 The supplier specifications will be used for purchased components and CAD mass analysis used for manufactured components to acquire the estimated weight. The actual weight will be verified using a scale In progress All components of the UAS have been weighed individually with exception of the leadscrew retention assembly, which was estimated using CAD and material selection, for a weight of 5.80
the constructed UAS is weighed. Section 4.11.5 TDPR 2 Simulation software will be used for an estimate of flight time. Ground testing will verify the flight time In Progress The flightime of the UAS has been estimated to be 11.2 mins. using ECALC software. Flight testing of the UAS will fully verify this requirement. Section 4.3.5 & Section 6.2.3 TDPR 3 Each requirement will be individually tested
verified in conjunction with each other through the full-scale launch. In Progress Control systems used for autonomous
Integration of all autonomous systems in UAS test flight will fully verify this requirement. Section 6.2.6
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Category Amount Launch Vehicle $10,268.65 Payload $5,192.65 Testing $1,000.00 Outreach $500.00 Travel $9,000.00 Shipping $211.34 Total $26,172.64
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