Preliminary Design Review Agenda Mission Success Criteria - PowerPoint PPT Presentation

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

Agenda ● Mission Success Criteria ● Launch Vehicle ○ Recovery ● Payload ○ Primary Payload - Unmanned Aerial System ○ Mid-air and Ground Deployment ○ Retention ○ Secondary Payload - Computer Vision ● Safety ● Project Plan The University of North Carolina at Charlotte 2 - 49er Rocketry Team

Vehicle Mission Success Criteria Item Criteria VMSC 1 The launch vehicle must successfully house the payload until deployment. VMSC 2 The launch vehicle will reach the target altitude within 100 ft. VMSC 3 During ascent, the computer vision (CV) will successfully track the location of the sample recovery area VMSC 6 Each altimeter will have its own dedicated power supply VMSC 7 Drogue parachutes will deploy no later than 2 sec. after apogee. VMSC 8 All pieces of the launch vehicle will land within 90 sec. Complete vehicle success requirements are located in Sections 3.1.2 The University of North Carolina at Charlotte 3 - 49er Rocketry Team

Launch Vehicle Specifications Values Length 106.7 in. Weight 63 lbs Max velocity 600 ft/s Loaded Stability 2.55 ● Booster section ○ Will house: motor, modular fin can, recovery system ● Payload section ○ Will house: payload, payload deployment, ground orientation and stabilization, computer vision, and recovery system The University of North Carolina at Charlotte 4 - 49er Rocketry Team

Nosecone ● LD-Haack series ○ Low drag coefficient ○ Reduced pressure and wave drag ● Length to diameter ratio of 1.5 ● Additively manufactured from ABS The University of North Carolina at Charlotte 5 - 49er Rocketry Team

Payload Section ● Payload airframe will be constructed of 6 in. ID carbon fiber tube with 1/16th in. wall thickness ● Total weight of 38lbs. ● Clearance holes for cameras to recess into airframe and for passage of wiring. ● The recovery system will utilize dual deployment from the parachute bay located above the avionics bay. The University of North Carolina at Charlotte 6 - 49er Rocketry Team

Booster Section ● Comprised of motor, motor retainer, modular fin can, and recovery system ● Loaded weight : 24.7 lbs ● Unloaded weight : 14.2 lbs ● Utilizes reloadable motor casing capable to fitting primary and secondary motors ● 5 in. carbon fiber tube used for its high strength to weight ratio The University of North Carolina at Charlotte 7 - 49er Rocketry Team

Booster Recovery ● Booster transitions from 5 to 6 in. ID with 1/16 in. wall thickness ● Separation occurs just above and below the recovery section ● Altimeter Bay ○ High strength to weight ratio ○ Shields altimeters from stray interference The University of North Carolina at Charlotte 8 - 49er Rocketry Team

Modular Fin Can ● Fins are able to be modified or replaced quickly and with minimal tooling ● Modular fin design allows for more control over the stability of the rocket ● Consists of modular fins and fin retainer ● Fins will be polycarbonate for dimensional stability and high strength to weight ratio The University of North Carolina at Charlotte 9 - 49er Rocketry Team

Motor Retention ● 75 mm motor chosen for thrust performance compared to projected vehicle weight ● Quick turnaround time ● Aero Pack RB75P motor casing ● Boattail threads into retainer cap to fully secure motor ○ Boattail and retainer cap are printed from ULTEM due to relative location to extreme heat The University of North Carolina at Charlotte 10 - 49er Rocketry Team

Camera Vision Mounts ● Four externally mounted cameras collect visual data during launch ● Cameras angled at 35 degrees from vertical ● Cameras recessed into airframe to reduce protrusion ● Verification of flight dynamics to ensure minimal impact to vehicle center of pressure or stability The University of North Carolina at Charlotte 11 - 49er Rocketry Team

Stability Margin Stability margin was calculated using OpenRocket and Barrowmans equations Handbook Criteria: ● Minimum Static Stability - 2.0 No Computer Vision ● OpenRocket - 3.06 ● Calculated - 2.95 With Computer Vision ● OpenRocket - 2.62 ● Calculated - 2.55 Motor Burnout ● OpenRocket - 3.23 ● Calculated - 3.16 The University of North Carolina at Charlotte 12 - 49er Rocketry Team

Motor Selection Handbook Criteria ● Maximum Impulse: 5120 N-s (L-Class) ● Minimum Velocity at Rail Exit: 52 ft/s Simulated Data: Primary : Aerotech L2200 Average Rail Exit Max. Thrust to Max. Velocity Motor Apogee Velocity Acceleration Weight (ft/s) (ft) (ft/s) (ft/s²) L2200 4135 7.88 66.3 529 338 L2375 3949 8.77 63.6 526 284 Secondary : Cesaroni L2375 The University of North Carolina at Charlotte 13 - 49er Rocketry Team

Flight Simulations Simulation Results ● Table is comprised of data averaged from 5 simulations ● Assumed rail cant of 7.5 degrees ● Mass distribution was simulated in OpenRocket to increase accuracy of simulations Wind Speed (mph) 0 5 10 15 20 Apogee (ft) 4256 4214 4161 4086 4032 16.8 16.7 16.6 16.4 16.2 Time to Apogee (s) Rail Velocity (ft/s) 67.1 67.1 67.1 67.1 67.1 Max. Velocity (ft/s) 529 529 529 528 527 Max. Acceleration 337 338 338 338 338 (ft/s²) The University of North Carolina at Charlotte 14 - 49er Rocketry Team

Recovery Overview 1. Initial separation. 2. Booster section drogue deployment. 3. Payload section drogue deployment with bagged main parachute. 4a. Booster main parachute release at 500 ft. 4b. Payload main parachute release at 500 ft. 5. The UAS deployment upon RSO approval. 6. Landing The University of North Carolina at Charlotte 15 - 49er Rocketry Team

Parachute Selection Drogue Parachutes Classic Elliptical Type Diameter (in) 15 Cd 1.5 Main Parachutes Section Booster Payload Type Iris Ultra Compact Iris Ultra Compact Diameter (in) 96 144 Cd 2.2 2.2 The University of North Carolina at Charlotte 16 - 49er Rocketry Team

Altimeter Bay Hardware Both Altimeter bays will include: ● Two PerfectFlite StratologgerCFs ● Aluminum Charge Wells ○ 4 for booster, 2 for payload ● 9V Batteries ● Altimeter Sled ● Carbon Fiber Bulkhead Payload specific additions include: ● Aluminum Bulkhead ● Tender Descender ● Deployment Bag ● Altus Metrum TeleMega Booster Recovery Altimeter Bay The University of North Carolina at Charlotte 17 - 49er Rocketry Team

Vehicle Separation Section Booster Main Booster Drogue Payload Main Black Powder Charge Size (g) 1.2 .4 1.0 Full ejection charge calculations are located in Section 3.4.2 The University of North Carolina at Charlotte 18 - 49er Rocketry Team

Drift Calculations Wind Speed Booster (ft) Payload with Payload (mph) UAS deploying UAS (ft) (ft) 0 0 0 0 5 508.9 539.1 565.5 10 1017.9 1078.2 1131.1 15 1526.8 1617.3 1696.6 20 2035.7 2156.4 2262.2 Full drift calculations are located in Section 3.5.4 The University of North Carolina at Charlotte 19 - 49er Rocketry Team

Descent Times and KE Section Mass (lbm) KE (ft-lb f ) Section Times (s) Nosecone 3 .47 Booster 69.4 Payload 35.1 64.77 Payload with UAS 73.51 Payload deploying UAS 29.1 44.52 Payload Deploying UAS 77.12 Booster Recovery 11.2 14.86 Booster 13.5 21.53 Complete calculations are located in Sections 5.4.4-5 The University of North Carolina at Charlotte 20 - 49er Rocketry Team

Requirement Verifications Item Requirement Verification Method Verification Plan 3.8 Each altimeter will have its own Inspection & Each altimeter will be wired dedicated power supply. Demonstration to its own 9V battery housed within the altimeter bay. 3.1.2 Drogue parachutes will be Demonstration The drogues will be set to deployed no more than two deploy 1 sec. and 2 sec. seconds after apogee. after apogee for the booster and payload sections respectively. 3.11 Descent time will be no more Test The booster section will land than 90 sec. in 69.4 sec. and the payload section will land in 77.1 sec. Complete Recovery verifications are located in Sections 7.1.3 The University of North Carolina at Charlotte 21 - 49er Rocketry Team

Team Derived Recovery Requirements Item Requirement Verification Verification Plan Method TDVR 9 The recovery system must allow for Inspection The recovery system of the option of mid-flight deployment the payload section will of payload be designed to allow for one side of the payload bay to be accessible during descent. TDVR 10 Altimeters must be able to be armed Inspection & The altimeter switches and disarmed without disassembly Demonstration will be designed to be of the launch vehicle accessible through the vehicle airframe. Complete Team Derived Recovery tables are located in section 5.4 The University of North Carolina at Charlotte 22 - 49er Rocketry Team