Virginia Tech NASA USLI PDR Presentation Ishan Arora, Nicholas Corbin, William Dillingham, Valerie Hernley, Joseph Lakkis, Max Reynolds, Angelo Said 11/14/18 - 3:00 PM CST
Contents ● Team Overview ● Mission Overview ● Launch Vehicle a. Vehicle Layout b. Vehicle Specifications c. Airframe Materials d. Propulsion e. Recovery f. Electronics Bay g. Mission Performance Predictions h. Validity of Analyses 2
Contents ● Payload a. Mission Success Criteria b. Design Summary c. UAV Components d. Navigation e. Navigational Beacon Release f. Retention System g. Mission Performance Predictions 3
Contents ● Requirements Verification Plan a. General b. Launch Vehicle c. Recovery d. Payload e. Safety ● Project Management a. Budget b. Timeline c. Scrum ● Summary 4
Team Overview 5
Team Overview 6
Mission Overview 7
Mission Overview Mission Statement: “Our booster 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.” 8
ConOps 0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery 9
ConOps 0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery 10
ConOps 0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery 11
ConOps 0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery 12
ConOps 0) Launch 1) Booster/recovery bay separation 2) Main parachute deployment 3) Booster and recovery bay touchdown, payload deployment 4) Navigational Beacon delivery 13
Launch Vehicle 14
Launch Vehicle: Vehicle Layout Center of Center of Gravity Pressure 15
Launch Vehicle: Vehicle Layout Center of Center of Gravity Pressure 16
Launch Vehicle: Vehicle Layout 17
Launch Vehicle: Vehicle Layout Center of Center of Gravity Pressure 18
Launch Vehicle: Vehicle Specifications Vehicle Component Length (inches) CG Location 62.3 inches from tip of nose cone Booster Bay 36.75 CP Location 75.8 inches from tip of Recovery Bay 77.5 nose cone Von-Karman Nose Cone 34.5 Static Stability Margin 2.15 Boat Tail Transition 5 Thrust-to-weight Ratio 10.04 Total Length 100 Rail Exit Velocity 85.6 ft/sec 19
Launch Vehicle: Airframe Materials ● Fins: ● Body Tube: ○ Carbon Fiber / Soric LRC ○ Fabricated from aircraft grade birch plywood Foam Laminate ○ Expected wall thickness: 0.14 ○ External mounting system for easy replacement inches ○ Density: 0.23 oz/in^3 ○ Matrix Material: FibreGlast System 2000 Epoxy ● Nose Cone: ○ COTS Fiberglass Von - Karman ○ Peak strength: 3270 lbf Fiberglass Carbon Fiber 20
Launch Vehicle: Airframe Materials ● Design Criteria ○ Excellent performance in highly compressive loading scenarios ○ Lightweight materials ● Preliminary Airframe Material Selection: Carbon Fiber with sandwich core ○ High stiffness and strength to weight ratio ○ Allows for lightest possible construction ○ Application of sandwich core increases stiffness with minimal use of carbon fiber plys and increased weight 21
Launch Vehicle: Propulsion Motor Selection: Aerotech K-1000T Reloadable Motor Casing: Aerotech RMS-75 2560* Motor Retention: ● Centering rings ● Boat Tail Transition: Carbon fiber, Aluminum thrust ring, screw-cap retention system *Looking into borrowing to save money, may use comparable CTI casing (Pro75 3G) with AT Crossloads 22
Launch Vehicle: Propulsion Constraints: ● Mass ● Finances Aerotech produces reliable motors: ● Two team members are experienced with assemblies, RMS reloadable motors ● BATES grains using tubular core allow for linear thrust curve 23
Launch Vehicle: Recovery Parachutes: ● Rocketman Kevlar Skyangle ○ 1 ft for drogue chute ○ 5 ft for main chute Separation Method: ● Redundant Altimeters ○ Stratologger SL100 ○ Adafruit BMP280 ● Black Powder ○ FFFF black powder ○ BP weight determined based on volume and desired pressure 24
Launch Vehicle: Electronics Bay 1 1. Power for the system is a 6600 mAh Li-Po battery (2200 mAh for Recovery Bay) 2. Arduino Battery Shield 3. Arduino Uno microcontroller 4. Arduino Ultimate GPS Logger Shield 6 5. 900 MHz XBee Radio 6. Adafruit BMP280 Barometric/Altitude Sensor 5 2 3 4 25
Mission Performance Predictions ● Vehicle will maintain stability above 2.0 cal throughout its entire flight duration ● Vehicle will be within 100 ft of 4,500 ft target apogee ● Commercial altimeters will be used to verify official altitude ● Will deliver the payload safely to perform a successful beacon delivery ● Vehicle shall not exceed Mach 1 26
Mission Performance Predictions: Flight Data was reproduced from OpenRocket simulations. 27
Mission Performance Predictions: Recovery ● Descent under the main parachutes shall land the rocket sections below 75 lb-ft of energy ● Upon landing the vehicle shall be fully recoverable and reusable ● No damage shall be incurred to the vehicle or payload systems during flight or landing ● Accurately acquire data through the altimeters which are all consistent 28
Mission Performance Predictions: Drift Data was reproduced from OpenRocket simulations. 29
Launch Vehicle: Validity of Analyses ● OpenRocket ○ Designed for this specific purpose ○ Utilizes a 6-Degree Of Freedom Barrowman method for modeling ○ Supported by motor manufacturers within industry ○ Allows for customization and modeling of individual components ● MATLAB code ○ Developed based on peer approved research publications ○ Takes into account average drag coefficient, surface area, vehicle weight with and without motor, generalized thrust curve, air density, and launch rail angle 30
Payload 31
Payload: Mission Success Criteria ● Mission Success Criteria ○ Retained during flight using a fail-safe retention system ○ Shall autonomously deploy from the launch vehicle upon signal ○ UAV shall deliver a 1 inch cube (navigational beacon) to FEA ● Team-derived requirements ○ Small enough to fit within the 6 inch diameter launch vehicle ○ The UAV shall complete the mission using autonomous flight requiring less than 1 minute of manual input ○ Range must be great enough to be able to reach an FEA regardless of vehicle landing location within the launch site Launch field is about 1 square mile and will contain multiple FEA targets 32
Payload: Design Summary ● Quadcopter ● Autonomous (GPS) and RC navigation enabled ● Range: 1.4 miles* ● Flight Time: 1.7 minutes ● Weight: 0.53 lb ● Size: 5.71 x 6.10 x 2.45 (inches) ● Cube release mechanism * Assuming 7 mph wind 33
Payload: UAV Components 34
Payload: Navigation ● Autonomous ○ GPS coordinates ○ iNav open-source software ● RC Back-up ○ Transmitter has switch to activate in case of autonomous malfunction ○ Video with manual control can be used to fine-tune navigation/delivery ● Ultimate goal of UAV: Deploy a 1 cubic inch navigational beacon to the FEA 35
Payload: Navigational Beacon Release ● Video will be used to verify arrival at the FEA ● Transmitter will have auxiliary switch designated to the cube release ● Upon signal, cable cutter will fire and release the cube Cable Cutter 36
Payload: Retention System 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 out when it finally deploys. 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 37
Payload: Mission Performance Predictions ● Battery Capacity: 1000 mAh ● Range: 1 mile despite 20 mph wind ● Flight Time: 1.7 minutes ● Assumptions: ○ Constant wind speed ○ Constant thrust ○ C D & A estimated from lit review Theoretical results will be validated by extensive testing to improve performance predictions 38
Requirements Verification Plan 39
Recommend
More recommend
