Virginia Tech NASA USLI CDR Presentation Ishan Arora, Nicholas - - PowerPoint PPT Presentation
Virginia Tech NASA USLI CDR Presentation Ishan Arora, Nicholas Corbin, William Dillingham, Valerie Hernley, Joseph Lakkis, Max Reynolds, Angelo Said January 24, 1:30 PM CST Content Mission Overview Final Vehicle Design
Ishan Arora, Nicholas Corbin, William Dillingham, Valerie Hernley, Joseph Lakkis, Max Reynolds, Angelo Said
January 24, 1:30 PM CST
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Mission Statement:
“Our vehicle will reach apogee at 4,500 feet and separate into two independent sections, each of which have both a drogue and main recovery parachute. After landing, the booster section will deploy an autonomous UAV with backup RC that delivers a navigational beacon to a Future Excursion Area.”
0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery
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0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery
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0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery
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0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery
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0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery
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Overview and Relative Locations
Airframe Materials
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○ Birch plywood composite with fiberglass lamination ○ External mounting system for easy replacement
○ Density: 0.751 oz/in³ ○ Peak Loading: 1548.9 lbf
○ COTS; Metal Tipped; Fiberglass; Von - Karman
○ Carbon Fiber / Soric LRC Foam Laminate ○ Wall thickness: 0.14 inches ○ Density: 0.193 oz/in³ ○ Matrix Material: FibreGlast System 2000 Epoxy ○ Peak strength: 3270 lbf
Advanced Recovery Release Device (ARRD) 1. Black powder containment area 2. Pin utilized for paracord attachment, held in place by shear pin 3. Mounting plate that will attach to centering ring 4. Final resting area for pin post ignition of black powder charge 5. Pressure relief port
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Outboard Shock Cord Retention System
cord “stopper” design
○ Additional sewn loop sits in shock cord guide ○ Then wrapped around metal link that sits on a pin
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Aerotech K-1000T
Works
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Motor Ignition Motor Burnout Average Thrust-to-Weight: Ratio 9.1
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* The Recovery Bay weight shown does not include the mass of the nose cone. ** The Nose Cone weight shown includes the added mass for stability purposes. Total Weight: 26.3 lbf Causes of Error/Variability
us (weight from manufacturer)
(density/dimension in simulation is not representative of actual unit)
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○ Descent under drogue and main parachute ○ Total mass of Booster Bay and Recovery Bay ○ 0, 5, 10, 15, and 20 mph wind cases
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Chute Release:
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ARRD:
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1. 2000 mAh Battery 2. Adafruit 500 Power Boost Battery Shield 3. Arduino Uno Microcontroller 4. Adafruit Ultimate GPS Logger Shield 5. XBee-Pro 900HP 6. SparkFun XBee Shield 7. Adafruit BMP280 Barometric/Altitude Sensor 8. Adafruit ADXL345 Triple-Axis Accelerometer Booster Bay Electronics
1. 2. 3. 4. 8. 7. 5. 6.
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Vehicle/Recovery:
T1.1 Airframe Compression Testing T1.2 Vehicle Electronics: XBee Communication T1.3 Vehicle Electronics: GPS Orientation/Placement T1.4 Vehicle Electronics: Test for Interference T1.5 Fin Bending Test D1.1 Sub-Scale Separation Demonstration D1.2. Sub-Scale Test Flight D1.3 ARRD System Demonstration D1.4 Vehicle Electronics: XBee/GPS/Altimeter/Accelerometer Data Transfer D1.5 Vehicle Electronics: Cable Cutter E-match Activation D1.6 Vehicle Electronics: Battery Life D1.7 Final Assembly Demonstration D1.8 Full-Scale Separation Demonstration D1.9 Vehicle Demonstration Flight D1.10/2.5 Payload Demonstration Flight
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Payload:
T2.1 Range of Flight - Battery Limited T2.2 Range of RF Connectivity and Video Transmission T2.3 Accuracy and Precision of GPS navigation T2.4 Passive Battery Bleed T2.5 Shaker Table Test D2.1a Deployment Electronics: Powering on the UAV D2.1b Deployment Mechanics: Powering on the UAV D2.1c Deployment Mechanics: Payload Cover Flip D2.1d Deployment Software Demonstration D2.1e Deployment Demonstration from Booster Bay D2.2 Beacon Release Electronics - Buzzer Trigger D2.3 In-flight Beacon Release Demonstration D2.4 Manual Override Safety Demonstration D1.10/2.5 Payload Demonstration Flight
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2.975 inch outer diameter
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recovery design
○ Shock cord length critical ○ Parachute sizing critical ○ Energy upon landing critical ○ Parachute fire retardant critical
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SADI - Superior Autonomous Delivery Instrument
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Electronics Horizontal Retaining Cable Cutters Payload Protection Cover Black Powder Reservoir UAV
and RC navigation enabled
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* Assuming 7 mph wind
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Canopy Properties
components
reproducible
vertical force retention system
propeller clearance
Nav Beacon
volume
battery
until ready for deploy
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GPS
For autonomous travel Receiver For RC back-up
VTX and Camera
For video feed and reassurance Microswitch For keeping UAV powered off during flight Flight Controller Flight controls, stability, gyroscopic ability and the “brain”
“OMNIBUS Betaflight F3”
arrival at the FEA
switch designated to the cube release
and release the cube
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○ GPS coordinates ○ iNav open-source software
○ Transmitter has switch to activate in case of autonomous malfunction ○ Video with manual control can be used to fine-tune navigation/delivery
cubic inch navigational beacon to the FEA
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Navigation
The fail-safe retention system provides both vertical and horizontal load support while doubling as a bay to protect the payload during separation, guiding it
Vertical Retention: Guide rods running through holes in the UAV Horizontal Retention: Cables holding down the UAV are taut until cut by cable cutters Bulkheads: Plates at the ends protect the payload during separation and from black powder charges
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○ Constant wind speed ○ Constant thrust ○ CD & A estimated from lit review
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Theoretical results will be validated by extensive testing to improve performance predictions
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○ Do not have to disassemble permanent components to access assembly.
○ Designed to remove and reload in minimal time
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retain the UAV in the horizontal direction, hold down the spring loaded protective cover
terephthalate
environment during descent and separation
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○ Fins can be easily replaced
○ Multiple contact points for fastening via centering rings ○ Clamps onto fin surface to increase rigidity
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factoring in wind speeds and launch angles
and provide integrity to our design
○ Autonomous navigation to FEA ○ RF control possible for fine-tuned delivery as needed ○ Cable cutter used for cube release upon arrival