University of Florida Rocket Team Preliminary Design Review

Transcription

1 University of Florida Rocket Team Preliminary Design Review

2 Agenda Overview Mission Statement Concept of Operations Summary Vehicle Subsystems Motor Choice Flight Dynamics and Simulations Payloads Target Detection Project Plan Verification Safety Verification Educational Engagements Budget and Funding Schedule Future Work

3 Mission Statement The UF Rocket Team will develop a payload that will be flown to an altitude of 5,280 feet. All components will be safely recovered after each flight. By doing so the team hopes to gain experience in a research-based, competitive, and experiential exploration project while also providing relevant and cost effective research and development. During the process, the UF Rocket Team will focus on developing an interest in STEM fields and STEM education in the local area.

4 Concept of Operations The launch vehicle shall reach a target apogee altitude of 5,280 ft. At apogee, the launch vehicle shall separate and release the target detection payload. At apogee, both the launch vehicle and payload will release parachutes (drogue for launch vehicle, singular parachute for payload). The launch vehicle and the target detection payload shall not follow a ballistic trajectory.

5 Concept of Operations The target detection camera shall observe the area beneath the launch vehicle and analyze it to determine the color of the tarps. At an altitude of 600 ft. the launch vehicle will again separate and release the main parachute; it will land using this parachute. The launch vehicle and payload shall transmit its location to the ground station via GPS.

6 Agenda Overview Mission Statement Concept of Operations Summary Vehicle Subsystems Motor Choice Flight Dynamics and Simulations Payloads Target Detection Project Plan Verification Safety Verification Educational Engagements Budget and Funding Schedule Future Work

7 Component Overview

8 Dimensions, Materials and Justification Airframes G12 Fiberglass Yield Strength: 41 ksi Bulkheads/Centering Rings Type 2 PVC Shear Modulus: 145 ksi Nosecone Polypropylene Plastic Weight: 10.5 oz Total Length 102 inches Total Weight lbs

9 Forward Section Dimensions Body Tube: 15.0 in. OD: in. ID: in. Coupler: 12.0 in. OD: in. ID: in. Purpose 1. Aerodynamics 2. Houses payload 3. Contains payload drogue

10 Avionics Bay Dimensions Body Tube: 17.5 in. OD: in. ID: in. Coupler: 10.0 in. OD: in. ID: in. Purpose 1. Ejection charges 2. Houses Avionics Bay 3. Contains drogue chute

11 Aft Section Dimensions Body Tube: 49.4 in. OD: in. ID: 3.90 in. Inner Tube: 24.0 in. OD: in. ID: in. Motor Centering 2 centering rings, 1 in. thick each Motor Retention Screw-on engine retainer Fin Integration Through-the-wall fin attachment

12 Composite Fins Fin Manufacturing Wet Layup Process CNC Milled Aluminum Molds Parchment Paper Mold Release C-clamp Compression E-class Fiberglass Added for Mass at Reduced Cost Carbon Fiber/fiberglass 45 and 90 weave orientations

13 Avionics and Recovery Avionics Electronics PerfectFlite Stratologger CF x2 BigRedBee BRB900 GPS Ejection Charges 2 Grams Black Powder Deployment Scheme Apogee - 36 Drogue Housed in mid fuselage 600 Feet - 48 Main Housed in aft fuselage

14 Avionics and Recovery

15 Motor Selection Motor Selection: Cesaroni K635-RL-17 Chosen based on a plethora of decision criteria, including thrust curve performance, total impulse, max thrust, and burn time. TOTAL IMPULSE: MAX THRUST: AVERAGE THRUST: ISP: BURN TIME: PROPELLANT MASS: DRY MASS: TOTAL MASS: MOTOR DIAMETER: Ns ( lb.s) N ( lb) N ( lb) s s 1115 g (39.33 oz) 649 g (22.89 oz) 1768 g (62.35 oz) 54 mm (2.13 in)

16 Propulsion System & Motor Selection

17 Flight Dynamics and Simulation The simulations were run in OpenRocket, a 6 degree of freedom software used to predict rocket flight. The simulations were run using flight conditions predicted for the month of April in Huntsville, Alabama. Simulations were run to predict: Apogee Velocity Acceleration Stability Margin

18 Velocity vs. Time

19 Acceleration vs. Time

20 Stability Margin Static Stability Margin: SM =(Xcp-Xcg)/d 3.47 Higher static stability margin to ensure stability during the beginning of flight Stability margin of 2.12 off the rod

21 Drift Radius

22 Kinetic Energy Kinetic energy During Descent: Main parachute: lbm*ft 2 /s 2 Drogue parachute: lbm*ft 2 /s 2 Calculated using the average velocity between time when parachute was employed and the time the rocket touched the ground.

23 Agenda Overview Mission Statement Concept of Operations Summary Vehicle Subsystems Motor Choice Flight Dynamics and Simulations Payloads Target Detection Project Plan Verification Safety Verification Educational Engagements Budget and Funding Schedule Future Work

24 Payload Summary Payload subsystem will be ejected at apogee. Payload subsystem will use one 12 parachute for recovery. There will be a primary and redundant altimeter for recovery. A raspberry pi zero will process the images.

25 Alternative Designs

26 Payload Electronics

27 Camera Slot

28 Payload Dimensions

29 Payload Wiring

30 Agenda Overview Mission Statement Concept of Operations Summary Vehicle Subsystems Motor Choice Flight Dynamics and Simulations Payloads Target Detection Project Plan Verification Safety Verification Educational Engagements Budget and Funding Schedule Future Work

31 Verification and Test Plan Subsystem Tests Requirements Payloads Target Detection Test Structures Airframe Material Test Avionics Bay Material Test Drop Test Recovery Charge Ejection Test Parachute Packing Test Ground Main and Drogue Deployment Test

32 Verification and Test Plan Subsystem Tests Requirements Avionics Transmission Test Battery Life Check GPS Range Test Propulsion Static Motor Test Full Scale Launch Subscale Launch Aerodynamics Subscale Wind Tunnel Test Boattail Wind Tunnel Test Miscellaneous Subscale Launch Launch Rehearsal Full Scale Launch

33 Safety Verification Each team shall use a launch and safety checklist created by the team. The safety officer will attend team activities to monitor, emphasize safety and develop hazard analyses, failure modes analyses, and procedures. The team mentor, Jimmy Yawn, will be also be responsible for team safety during any processes that require his involvement. A Launch Operations Risk, Hazards Analysis, Failure Modes, and Vehicle Environmental Concerns assessments have been carried out to emphasize the criticality of potential occurrences that would affect the team s safety or the safety of the surrounding environment and how to best to handle them.

34 Safety Verification Cont. The UF Rocket Team will conduct a majority of all manufacturing, composites, propulsion, and testing work at the UF MAE Student Design Center (SDC) in the Rocket Team bay. All members will abide by the rules of the MAE SDC and safety protocol are obeyed. ensure all Qualified members of the UF Rocket Team will be given tests to become certified as Safety Stewards, if desired, which gives them access to all machines and equipment in the SDC. Safety Stewards have a list of responsibilities that they must follow when conducting work in the SDC. All members that are not certified as Safety Stewards must perform all activities with the guidance of a Safety Steward.

35 Educational Engagement Engagement at local schools Engaging Presentation on STEM geared toward Rocketry Live rocket launch demonstrations, hands-on kits and activities Coordination with Alachua County Public Schools Volunteer Office 3 Elementary School Events Station based hands-on activities

36 Budget and Funding

37 Schedule Event Dates Subscale Work 11/6 12/6 Subscale Launch 12/9 Final Material Ordered 1/1 Full Scale Manufacturing 1/8 2/8 Full Scale Launch 2/10

38 Agenda Overview Mission Statement Concept of Operations Summary Vehicle Design Methodology Subsystems Motor Choice Flight Dynamics and Simulations Vehicle Verifications Plan Payloads Target Detection Project Plan Verification Safety Verification Educational Engagements Budget and Funding Schedule Future Work

39 Future Work Develop detailed, final design Manufacture subscale Component Testing Order all materials Subscale Launch, Dec. 9th

40 Questions