University of Florida Rocket Team Critical Design Review
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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
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.
Component Overview Aft airframe Avionics Bay airframe Payload Section Aft Airframe 47 inches Avionics Bay Airframe 26 inches Payload Section 47 inches
Mass Statement and Margin Rocket has a projected mass of approx. 18.34 lbs excluding motor mass With the addition of the 5% margin, the mission vehicle will have a mass of 19.25 lb. also excluding motor mass
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
Final Dimensions and Materials Overall Dimensions Length: 120 inches Outer Diameter: 4.02 inches Weight: 19.25 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
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
Forward Section Dimensions Body Tube: Coupler: 24.0 in. 12.0 in. Purpose 1. Aerodynamics 2. Houses payload 3. Contains payload chutes OD: 4.024 in. OD: 3.867 in. ID: 3.900 in. ID: 3.722 in.
Mid Section Dimensions Body Tube: Coupler: 22.5 in. 10.0 in. Purpose 1. Ejection charges 2. Houses Avionics Bay 3. Contains drogue chute OD: 4.024 in. OD: 3.867 in. ID: 3.900 in. ID: 3.722 in.
Aft Section Dimensions Body Tube: Inner Tube: 53.4 in. 25.0 in. Fin Integration Through-the-wall fin attachment OD: 4.024 in. OD: 2.311 in. ID: 3.900 in. ID: 2.142 in.
Aft Section Motor Centering 2 centering rings, 1 in. thick each Motor Retention Screw-on engine retainer
Sections Integrate with Rivets 4 total each withstand 75 lbf
Manufactured Parts: Thrust Bulkhead
Manufactured Parts: Centering Ring
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
Propulsion System & Motor Selection
Propulsion System & Motor Selection
Propulsion System & Motor Selection
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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
Altitude vs Time The predicted altitude for the rocket at apogee is 5312 feet.
Velocity vs Time
Acceleration vs Time
Stability of Rocket The center of gravity (blue) and center of pressure (red) are labeled below: For the predicted conditions, the stability of the rocket off the rod is 3.92 stability margin calipers. The static stability margin for the rocket is 5.7
Stability Cont.
Flight Dynamics & Simulation
Flight Dynamics & Simulation
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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 - 72 Main Housed in aft fuselage Terminal Velocities Launch Vehicle: Drogue 75.73 fps - Main 23.27 fps Payload: Drogue 77.24 fps - Main 28.11 fps
Avionics and Recovery Kinetic Energy Payload Parachute Section 1 (367 grams) Section 2 (1283.3 grams) Drogue (12 inches) 75.02 foot-pounds 262.31 foot-pounds Main (30 inches) 9.94 foot-pounds 34.74 foot-pounds Launch Vehicle Drogue Parachute Section 1 (6347.2 grams) Launch Vehicle Main Parachute Section 1 (2029 grams) Section 2 (3953.1 grams) Main (72 inches) 37.64 foot-pounds 73.34 foot-pounds Drogue (36 inches) 1247.14 foot-pounds
Avionics and Recovery
Avionics and Recovery
Drift Radius
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
Payloads
Payloads
Payload Wiring
Payloads Source: https://www.apogeerockets.com/electronics-payloads/dual-deployment/chute-release?cpath=52_159&
Payload Drift
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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 4.4.1 4.4.2 3.1 3.2
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 2.2 2.10 2.11 2.13 2.18 2.19 2.18 2.19
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 subscale rocket. Will further test for full-scale. Verify all parts remain usable after experiencing high deceleration similar to that of landing The subscale rocket landed successfully with no damage. Will further test with full-scale rocket. Target Detection Test Black Powder Charge Ejection Test Component Shock Test
Vehicle Verifications Plan: Overview of Major Tests Test Subscale Launch Criterion Launch subscale rocket to verify models for rocket dynamics using predicted and real apogee values Status/Report Real apogee reached at 2675 feet (models predicted ~2805 feet for apogee) 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 Subscale 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. Both motors were 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 Parachute Packing and Deployment Test
Vehicle Verifications Plan: Overview of Major Tests Test Criterion Status/Report Boattail Heat Test Verify the rocket boattail can withstand motor exhaust heat temperatures without deforming using a heat gun and infrared thermometer Pending Epoxy Fin Joint Test Verify the fin connections are capable of withstanding shear stresses equal to those created by aerodynamic pressure during launch using weights and fin clamps Pending 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 Pending
Boattail Wind Tunnel Test 3D printed concave, convex and straight tube boattails were tested at different wind speeds Convex limited the drag the most, then concave then straight tube
Static Motor Similar shape graph and maximum thrust between manufacturers thrust curve and the tested thrust curve Disparities may have risen from ununiform burn of grains
Black Powder Testing Black powder separation system testing 1.5 grams of black powder proved to be a sufficient amount for both separation events in the rocket
Subscale Flight Test Apogee: 2765 ft
Sub-Scale Flight Analysis
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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.
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.
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
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 2 Elementary School Events Station based hands-on activities
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
Budget and Funding
Agenda Overview Concept of Operations Launch Vehicle Dimensions Mass Statement and mass margin Launch Vehicle Key Design Features Motor Choice Stability and Flight Dynamics Recovery Avionics Subsystem Parachute Design Kinetic Energy Calculations Predicted Drift Payload Design Final Design and Dimensions Verification Testing Test Plans and Procedures Scale Model Test Flight Project Plan Safety Verification Educational Engagement Budget and Funding Schedule Future Work Questions
Schedule Event Dates Final Materials Ordered 1/8 Full Scale Manufacturing 1/9-1/30 Full Scale Assembly and Testing 1/31-2/7 Full Scale Launch 2/10 Payload Manufacturing 1/9-1/30 Payload Testing Complete 2/7
Future Work Full Scale Manufacturing and Assembly Payload Testing and Verification Full Scale Test Launch Complete component material testing Educational Engagements
Questions