Preliminary Design Review 1 Agenda Mission Success Criteria - PowerPoint PPT Presentation

49er Rocketry Team University of North Carolina at Charlotte Preliminary Design Review 1

Agenda ● Mission Success Criteria ● Vehicle ● Recovery ● Payload - UAV ● Payload - UAV Housing ● Payload - Load Cell ● Safety ● Project Plan 2

Vehicle Mission Statement and Success Criteria ● The launch vehicle mission will be considered a success when: ○ MSV1 - Delivers a UAV within 250 ft. of our target apogee of 4,200 ft. above ground level. ○ Returns to ground within 90 sec., a 2,500 ft. radius, and under 75 ft-lb f of kinetic energy. ○ MSV2 - All payloads remain secured and protected from all elements of the flight. ○ MSV4 - No safety hazard posed to bystanders 3 Complete Mission Statement and Success Criteria is located in Section 3.1

Vehicle Dimensions • Total length of ~95.6 in. 4

Static Stability • Loaded Stability of 2.1 caliber • Stability at rail exit of 2.2 caliber • Unloaded Stability of 2.6 caliber 5

Motor Selection Overview ● L800 is the leading design choice for an overall weight between 41 lb m and 43 lb m ● L1050 is the leading design choice if weight is between 43 lb m and 44 lb m ● Meets Competition requirements for velocity off the rail and impulse ● Readily obtainable for purchase 6

Motor Justification Max acceleration of 145 ft/sec 2 Cesaroni L800 Motor Justification ● ● Maximum Rail Cant of 10° ● Minimum Apogee of 4039 ft ● Velocity off the rail of 59.1 ft/sec ● Thrust to weight ratio of 5.5:1 7

Vehicle Material Options Carbon Fiber PETG Aluminum 6061-T6 Fiberglass 8 Complete Testing Plan is located in Section 6.5

Payload Section and Nose Cone - Payload section airframe will be 4.5” ID 0.06” wall thickness fiberglass - LD-Haack nose cone shape - AM PETG with an aluminum tip 9

Booster Section Overview • 4.5 in. ID with 0.06 in. wall thickness carbon fiber tubing will be used for the airframe • Two piece PETG and aluminum curved boat tail • Flat plate carbon fiber fins with 5° chamfer on the leading and trailing edges 10

Booster Section Fins Fin Shape Flat Plate ● Drag coefficient increase of 25% ● Frontal area decrease by 32% ● Overall drag force decreases by 11% 11

Booster Section - Boat Tail Boat Tail Shape ● Aluminum adapter with a composite shell ● Curved design offered ~15% of drag reduction shown in comparative CFD simulation 12

Motor Retention • Lateral deflection prevented by carbon fiber motor tube, centering rings, and fin tabs • Axial deflection prevented by attaching to load cell and a retaining lip on the boat tail 13

Leading Vehicle Design • LD Haack PETG 3D printed nose cone with • Flat carbon fiber fin with 5° bevel on leading aluminum tip and trailing edges • Fiberglass payload section airframe • Aluminum base with composite shell curved • Carbon fiber booster and recovery airframes boat tail as well as the fins. 14

Vehicle - Requirements Verification 15 Complete Vehicle Requirement Verification Plan is located in Section 7.1.1

Vehicle - Team Derived Requirements 16 Team Derived Requirements for Vehicle are located in Section 7.1.2

Vehicle - Testing Plan 17 Complete Testing Plan is located in Section 6.5

Recovery Success Criteria ● Recovery of the launch vehicle will be considered successful if: ○ MSR1 - The booster and payload sections will separate into independent recovery sections at apogee. ○ MSR2 - The drogue parachutes will fully deploy and the main parachutes will partially deploy during initial descent. ○ MSR3 - The main parachutes for the booster and payload sections will fully open at 500 ft. ○ MSR4 - The separate sections will reach the ground within 90 sec. of apogee, within the 2,500 ft. landing radius, and within 75 ft − lb f of kinetic energy. 18 Complete Mission Statement and Success Criteria is located in Section 3.1

Recovery - Overview 1. Initial separation at apogee. 2. 2 sec. after apogee, deployment of drogue parachute with partial deployment of main parachute. 3. Full deployment of main parachute at 500 ft. 4. Touchdown within 90 sec, 2,500 ft. radius, and 75 ft-lb f of kinetic energy. 5. Main parachute is released for UAV deployment. 19

Recovery - Overview ● The parachutes will be released via single deployment of both the drogue and main parachutes. ● Jolly Logic Chute Releases will keep the main parachute closed until 500 ft. ● Tender Descender will release payload main parachute line. 20

Recovery - Deployment Booster just after apogee separation Drogue Parachute Main Parachute (closed) Nomex Blanket Booster Section Booster Recovery Section Kevlar Tether Line 21

Recovery - Deployment Main Parachute (open) Nomex Blanket Drogue Parachute Booster Section Kevlar Tether Line Booster Recovery Section 22

Recovery - Parachutes Iris Ultra Light Booster Payload Section Section Main Iris Ultra Light Iris Ultra Light Parachute Diameter 72 in. 96 in. C d 2.2 2.2 30.3 in 3 50.2 in 3 Packing Volume Classic Elliptical Drogue Classic Elliptical Classic Elliptical Parachute Diameter 12 in. 12 in. C d 1.5 1.5 7.4 in 3 7.4 in 3 Packing Volume 23

Recovery - Altimeter Bay 1. Perfectflite Stratologger CF 2. Black Powder Charge Blocks 3. 9 V Batteries 4. Eyebolt for Tether Connection 5. Altimeter Sled 6. Carbon Fiber Bulkhead * Carbon fiber outer shell, arming switches, pressure relief holes not shown. 24

Recovery - Booster Section ● One altimeter used for initial separation (primary or secondary) ● Two altimeters used for booster separation (primary and secondary) ● Three independent 9V batteries ● Dual e-match wiring ● Dual Jolly Logic Chute Release 25

Recovery - Payload Section ● Same procedure as previously listed for booster recovery section ● MCU, IMU, LiPo for main parachute release located in payload section 26

Recovery - Performance 27

Recovery - Requirement Verification 28 Complete Recovery Requirement Verification Plan is located in Section 7.1.1

Recovery - Team Derived Requirements 29 Team Derived Requirements for Recovery are located in Section 7.1.2

Recovery - Testing Plan 30 Complete Testing Plan is located in Section 6.5

Payload Success Criteria ● Payload mission will be considered successful if: ○ MPS3 - The nose cone and airframe successfully separate. ○ MPS5 - The UAV is successfully lifted above the airframe prior to take off. ○ MPS10 - Camera vision successfully locates and positions UAV above the FEA for beacon deployment. ○ MPS11 - UAV successfully avoids encounters with objects via object detection system. ○ MPS12 - UAV successfully delivers navigational beacon. ○ MPS13 - Load cell successfully logs motor thrust data. 31 Complete Mission Statement and Success Criteria is located in Section 5.1

Payload Overview Property Payload Section Nose Cone Length 25 in. 22.5 in. Overall Weight 21 lbs. (including payload recovery) UAV Weight 1.75 lbs. 32

UAV - System Overview 33

UAV - Flight Control System Objective: To autonomously control the UAV flight characteristics during operation. ● Raspberry Pi Zero W ○ Open source Linux-based Operating System ○ Can be programmed with Python and C ● 3DR Pixhawk PX4 2.4.8 Flight Controller ○ Open source flight stack ○ Supports extra peripherals via I2C ○ Supports autonomous flying and Mission Planner 34

UAV - FEA Detection System Objective: To use machine vision technologies to locate the FEA and initiate beacon delivery behavior. ● Will detect an FEA and interrupt the FCS then direct UAV movement towards the center of the FEA, and trigger beacon drop ● Jevois A33 Camera ○ features built-in CPU and GPU ○ Communicates with Flight Control system via serial 35

UAV - Beacon Retention and Deployment Objective: To retain the navigational beacon on-board the UAV until signaled to release. ● Beacon assembly will be secured to airframe with a PETG mount. Servo horn will hold beacon in place ● HS-40 Nano Servo Motor ○ 8.4 oz/in at 4.8V; 10.5 oz/in at 6V ○ Weighs 0.17 ounces 36

UAV - Object Detection and Avoidance Objective: To locate and respond appropriately to any obstructions encountered during operation. ● MaxBotix MB1240 ○ 10 Hz sample rate ○ Range of 8 to 300 inches ○ 0.4 inch resolution ● MakerFocus Lidar Range Finder ○ 100 Hz sample rate ○ Range of 12 to 472 inches ○ 0.4 inch resolution 37

UAV - Drive System ● DJI 8331 folding propellers ○ 8.3 inch diameter ○ 3.1 inch pitch ● Edge R2304 High Performance F3P 3D Foamy Motor ○ 1480 KV (RPM/Volt) ○ 125W Maximum Continuous Power ○ Approximately 24.5 ounces of thrust ● Four EMAX 20A electronic speed controllers (ESC) ○ Max continuous current draw: 20A ○ Max peak current draw: 30A ○ Input voltage: 7.4V - 14.8V ○ Weighs only 0.12 ounces 38