University of Florida Rocket Team Flight Readiness Review

Transcription

1 University of Florida Rocket Team Flight Readiness Review

2 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

3 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. The launch vehicle and the target detection payload shall not follow a ballistic trajectory. The target detection payload shall come down under a drogue parachute until an altitude of 500 ft, at which point a main parachute is released

4 Concept of Operations The target detection camera shall observe the area beneath the launch vehicle and analyze it for the color of the tarps At an altitude of 500 ft. the launch vehicle will again separate and release the main parachute; it will land using this parachute. The launch vehicle and target detection payload shall both land in a way that they can be reused for launch within the same day. The launch vehicle and payload shall transmit its location to the ground station via GPS.

5 Mass Statement and Margin Rocket has a projected mass of approx lbs excluding motor mass With the addition of the 5% margin, the mission vehicle will have a mass of lbs also excluding motor mass

6 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

7 Final Dimensions and Materials Overall Dimensions Length: inches Outer Diameter: 4.02 inches Weight: pounds without motor (with 5% margin) Motor weighs 4.3 pounds Material Selection Airframes: G12 Fiberglass Tubes Fins: Carbon Fiber Bulkheads/Centering Rings: Strengthened PVC Coupler Tube: G12 Fiberglass Tubes

8 Material Selection Airframes G12 Fiberglass Yield Strength: 41 ksi Bulkheads/Centering Rings Type 2 PVC Shear Modulus: 145 ksi Nosecone Polypropylene Plastic Weight: 10.5 oz

9 Forward Section Dimensions Body Tube: Coupler: 24.0 in in. Purpose 1. Aerodynamics 2. Houses payload 3. Contains payload chutes OD: in. OD: in. ID: in. ID: in.

10 Mid Section Dimensions Body Tube: Coupler: 22.5 in in. Purpose 1. Ejection charges 2. Houses Avionics Bay 3. Contains drogue chute OD: in. OD: in. ID: in. ID: in.

11 Aft Section Dimensions Body Tube: Inner Tube: 53.4 in in. Fin Integration Through-the-wall fin attachment OD: in. OD: in. ID: in. ID: in.

12 Rear View

13 Aft Section Motor Centering 2 centering rings, 1 in. thick each Motor Retention Screw-on engine retainer

14 Manufactured Parts: Thrust Bulkhead

15 Manufactured Parts: Centering Ring

16 Vehicle Integration Aft Fuselage Mid-Section Fuselage Payload Section

17 Vehicle Integration (cont.) 4 total each withstand 75 lbf

18 Assembly Overview 1. Cutting Airframes 2. Drilling Rivet & Shear Pin Holes 3. Sanding Surfaces 4. Starting Construction of Motor Retention 5. Attaching Fins 6. Completing Motor Retention

19 Propulsion System & Motor Selection CESARONI TECH 2437 K660-CL-A DESCRIPTION VALUE DESCRIPTION VALUE TOTAL IMPULSE Ns ( lb.s) LOADED WEIGHT g (68.22 oz) MAX THRUST N ( lb) PROPELLANT WEIGHT g (41.20 oz) AVERAGE THRUST N ( lb) BURNOUT WEIGHT g (25.69 oz) BURN TIME 3.69 s MOTOR DIMENSIONS D x L mm (D x L in) ISP s PROPELLANT TYPE Cesaroni Classic Solid Propellant

20 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

21 Altitude vs Time The predicted altitude for the rocket at apogee is 5312 feet.

22 Velocity and Acceleration Simulated Velocity vs Time Simulated Acceleration vs Time

23 Stability of Rocket The center of gravity (blue) and center of pressure (red) are labeled below:

24 Stability Cont. For the predicted conditions, the stability of the rocket off the rod is 6.22 stability margin calipers. The static stability margin for the rocket is 7.99

25 Stability Cont.

26 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

27 Avionics and Recovery

28 Avionics and Recovery

29 Avionics and Recovery

30 Avionics and Recovery Avionics Electronics PerfectFlite Stratologger CF x2 BigRedBee BRB900 GPS Ejection Charges 2.5 Grams Black Powder (Backup 3 Grams) Deployment Scheme Apogee - 24 Drogue Housed in mid fuselage 500 Feet - 48 Main Housed in aft fuselage Terminal Velocities Launch Vehicle: Drogue fps - Main fps Payload: Drogue fps - Main fps

31 Avionics and Recovery Kinetic Energy Payload Parachute Section 1 (1.45 lbs) Section 2 (4.04 lbs) Drogue (12 inches) foot-pounds foot-pounds Main (24 inches) foot-pounds foot-pounds Launch Vehicle Drogue Parachute Section 1 (14.35 lbs) Launch Vehicle Main Parachute Section 1 (3.92 lbs) Section 2 (8.55 lbs) Main (48 inches) foot-pounds foot-pounds Drogue (24 inches) foot-pounds

32 Drift Radius

33 Payload Drift Radius

34 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

35 Payload Dimensions

36 Payload General Diagram

37 Payload Electronics Raspberry Pi Camera Stratologger 9V Battery Switch Pi Battery Raven

38 Payload Main Chute Source:

39 Payload Code

40 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

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

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

43 Test Plans and Procedures Test Criterion Status/Report Boattail Wind Tunnel Determine which boattail design will limit drag forces, using 3D printed, scaled-down models and a calibrated wind tunnel. Convex > Concave > No boattail Test the ability of the target acquisition software to select appropriate landing areas using a picture to simulate the landing zone Successfully tested software. Will test further with final camera. Test the ability of the black powder to separate the airframe without burning the parachute The airframe successfully separated for the full scale rocket. Verify all parts remain usable after experiencing high deceleration similar to that of landing The full scale rocket successfully landed after test launch with no damage done to the rocket. Target Detection Test Black Powder Charge Ejection Test Component Shock Test

44 Vehicle Verifications Plan: Overview of Major Tests Test Full scale Launch Criterion Launch subscale rocket to verify models for rocket dynamics using predicted and real apogee values Status/Report During the fullscale rocket launch, issues with the recovery events were experienced. Verify that the parachutes fit without tangling and fully deploy once ejected by verifying that each of the parachute s cords are taut during landing Full scale launch shows that the packing and ejection methods used result in an untangled configuration and slow the rocket sufficiently enough to avoid damage. Static Motor Test and record data using a load cell for the selected subscale and full-scale motors. Compare thrust curves with those from the manufacturer. The fullscale motor was tested successfully. A calibrated load cell collected data and produced thrust curves with similar shape and timing of events to those of the manufacturer. Material Compressive Stress Test Use and Instron test machine to find the stress-strain curves of rocket materials to insure the rocket can handle the forces endured during flight. Pending. Will complete for future rocket team activities. Parachute Packing and Deployment Test

45 Vehicle Verifications Plan: Overview of Major Tests Test Criterion Status/Report GPS Range Test Physically move the GPS receiver and transmitter to the maximum drift location to verify adequate signal strength at the expected maximum range required for transmissions Completed. The GPS performed as expected when moved from reciever.

46 Static Motor Test Cesaroni K660 Static Test Manufacturer Provided Data Burn Time (s) Total Impulse (Ns) Average Thrust (N) Maximum Thrust (N)

47 Black Powder Testing Aft Section: 2.0 grams Payload Bay: 1.5 grams Forward Section: 1.5 grams In all three tests, the rocket sections were successfully separated without damage to the internal components

48 Altimeter Connection Tests Avionics Bay Main Altimeter (StratoLoggerCF) 9.0 V Avionics Bay Backup Altimeter (StratoLoggerCF) 9.1 V Payload Bay Main Altimeter (Raven3) V Payload Bay Backup Altimeter (StratoLoggerCF) 8.9 V All four altimeters (two in Avionics Bay, two in Payload Bay) were properly connect and able to successfully ignite an electric match

49 Static Motor Test The variation in thrust curves are within the standard 5% margin of error

50 Flight Dynamics FULL SCALE ROCKET TEST LAUNCH RESULTS

51 Flight Dynamics FULL SCALE ROCKET TEST LAUNCH ACTUAL (15.8 DEGREE LAUNCH ANGLE) 4710 ft

52 Flight Dynamics FULL SCALE ROCKET TEST LAUNCH EXPECTED (0 DEGREE LAUNCH ANGLE) 5150 ft

53 Agenda Overview Concept of Operations Mass Statement and Margin Launch Vehicle Launch Vehicle Dimensions Key Design Features Vehicle Integration Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Summary of Requirements Verification Test Plans and Procedures Full Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions

54 Safety Verification Each team shall use a launch and safety checklist created by the teams safety officer, Christopher Thomas. 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.

55 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 ensure all safety protocol are obeyed. All qualified members of the UF Rocket Team will be given tests to become certified as Safety Stewards, 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.

56 Safety Verification Cont. During pre-flight routines, the team will utilize the published checklists to ensure the rocket is assembled and prepared safely and in the proper manner. While working with the rocket, the team will use use the Personal Hazard Tables and utilize any necessary PPE in order to safely assemble the rocket. All process will be supervised by the Safety Officer, the Project Manager, Systems Lead, and Team Mentor.

57 Educational Engagement STEM outreach at local schools Engaging presentation and activity geared toward Rocketry Coordination with Alachua County Public Schools Volunteer Office Engagement with 3 schools Collaboration with University of Florida student organizations 295 students engaged in direct education

58 Treasury

59 Project Schedule The team planned a re-flight test launch on 3/10/18 with a backup launch on 3/17/18 Preparations are being made for the trip to Huntsville with regards to travel.

60 Questions