University of Minnesota NASA USLI Presentation 10-29-2012 - PowerPoint PPT Presentation

University of Minnesota NASA USLI Presentation 10-29-2012 University of Minnesota: 2012-2013 USLI 1 Preliminary Design Review

Objectives • Design a rocket to reach apogee at 1 mile • Deploy a drogue and main chute • Deploy a payload on the ground • Remain Subsonic • Design a Re-usable Modular system University of Minnesota: 2012-2013 USLI 2 Preliminary Design Review

Rocket Design • Key Components  Payload bay section  Pressure tank section  Air-pressure airbrakes  Modular fin system  Modular motor mount system University of Minnesota: 2012-2013 USLI 3 Preliminary Design Review

Vehicle Dimensions • Length 122.75 inches • Diameter 6.160 inches • Weight 48.378 lbs • Clipped delta fins with 8 inch span • Static Margin: 2.87(coasting) and 2.23(launch) University of Minnesota: 2012-2013 USLI 4 Preliminary Design Review

Vehicle Material • G-10 fiberglass: Avionics bay, bulkheads, electronics mount tube, fins • Carbon fiber: Main body tubes, pressure tank University of Minnesota: 2012-2013 USLI 5 Preliminary Design Review

Components that will be stress tested • Body Tubes • Piston • Pressure Vessel Mount • Motor mount • Bulkheads • Fins • Shear pins University of Minnesota: 2012-2013 USLI 6 Preliminary Design Review

Systems That will be Tested • Payload deployment • Payload: Functionlity of payload • Airbrakes: Wind tunnel and actual flight test on half scale University of Minnesota: 2012-2013 USLI 7 Preliminary Design Review

Motor Selection • Motor Size constraints: 75mm motor • Need motor to slightly overshoot 5,280 ft • Cessaroni Pro75 4-Grain L : 4687.94 N-s • Exit rail velocity: 71.9076 ft/s • Stability out of the railing • Thrust to weight: 11.247 University of Minnesota: 2012-2013 USLI 8 Preliminary Design Review

Vehicle Verification University of Minnesota: 2012-2013 USLI 9 Preliminary Design Review

Performance Characteristics University of Minnesota: 2012-2013 USLI 10 Preliminary Design Review

Performance Characteristics University of Minnesota: 2012-2013 USLI 11 Preliminary Design Review

Performance Summary Characteristic Value Max Altitude 5674 feet (Without Airbrakes) Max Mach Number 0.602 Static Margin 2.87 (After Burnout) Corrective Moment Coefficient 4250 (After Burnout) Damping Moment Coefficient 28 (After Burnout) Exit Rail Velocity 71.9076 ft/s Thrust to Weight Ratio 11.247 University of Minnesota: 2012-2013 USLI 12 Preliminary Design Review

Half Scale Testing  Examine manufacturing and assembly process  Verify Simulation with results  Confirm Recovery System  Confirm Effectiveness of airbrake system University of Minnesota: 2012-2013 USLI 13 Preliminary Design Review

Avionics and Control Components Quantity Raven3 Featherweight Altimeter 3 1 Redundant altimeter Entacore AIM USB (front avionics bay) Redundant altimeter Entacore AIM XTRA. 1 The AIM EXTRA also doubles as GPS tracker for Recovery (aft avionics bay) 9 Volt Battery 4 Screw Switch 4 Avionics Bay 2 University of Minnesota: 2012-2013 USLI 14 Preliminary Design Review

Avionics and Control • Altimeters:  Raven 3  Aim USC  Aim Xtra • Orientation • Wiring University of Minnesota: 2012-2013 USLI 15 Preliminary Design Review

Avionics and Control • ArduMega Microcontroller : Closed loop • Ninja Paintball tank  90 in 3  4500 psi storage  850 psi discharge  N 2 gas University of Minnesota: 2012-2013 USLI 16 Preliminary Design Review

Recovery • Deploy drogue and main chute • Safely collect the payload • Meet requirement of keeping max Kinetic Energy less than or equal to 75ft-lbf • Governing equation for black powder mass calculation: 𝑂 = 𝕎𝕎 𝑆𝑆 ∗ 454 University of Minnesota: 2012-2013 USLI 17 Preliminary Design Review

Recovery Recovery Setup Charge Assembly University of Minnesota: 2012-2013 USLI 18 Preliminary Design Review

Recovery Recovery Summary Component Model Size Deploy Altitude Terminal Velocity Drogue Rocketman Mach II 36” Apogee 65.97 ft/s Main Fruity Chutes Iris Ultra 120 120” 800 ft 14.92 ft/s Black Powder • FFFg black powder charge used 1.14 grams for drogue • • 2.19 grams for main University of Minnesota: 2012-2013 USLI 19 Preliminary Design Review

University of Minnesota: 2012-2013 USLI 20 Preliminary Design Review

Payload Mission Overview • Simulate deployment of extraterrestrial body • Receive inputs from a ground controller and to move according to the controllers command • To execute certain autonomous comands University of Minnesota: 2012-2013 USLI 21 Preliminary Design Review

Payload Design • Major Components:  Hitec HSR-5980SG Digital HMI High Torque Servo  2.4 GHZ First Person Camera System  ArduIMU Micrcontoller  MediaTek MT3329 GPS  RC Receiver and Transmitter • Dimensions: University of Minnesota: 2012-2013 USLI 22 Preliminary Design Review

Payload Verification • Electronics testing • Ground Testing • Deployment Testing University of Minnesota: 2012-2013 USLI 23 Preliminary Design Review

Payload Test Plan Overview Payload requirement Design feature to verify Verification of completion requirement Payload must not sustain any The rover will have a By inspection of the rover it will be clear whether the damage upon landing or casing around itself during rover sustained any damage. Also if the rover is not deployment from the rocket flight and upon landing. performing certain functions in real time such as the live itself. The chassis will be built feed video to a computer, damage could be potentially such that the rover will be verified. able to experience up to 20 G in the rocket. Successful deployment from the The casing will protect the The verification can be seen by inspection whether the rocket upon landing. rover until it is deployed rover was successfully deployed. As there will be an out in which the casing will electronic switch to turn the black powder off in case of it fall off helping in the not deploying, data will be sent back to see if was successful deployment. deployed or not. Black power will be used to deploy the rover safely from the rocket. University of Minnesota: 2012-2013 USLI 24 Preliminary Design Review

Payload Test Plan Overview Payload requirement Design feature to verify Verification of completion requirement The rover is required to perform Two high torque servos By inspection if the rover has moved in the desired path. certain maneuvers during its will be used independently time on the surface of the on each wheel to earth. It will have to move 10 maneuver the rover. A feet forward, rotate 180̊ and receiver will obtain the move forward 10 feet again. functions from the RC controller and the ArduIMU+V3 will interpret these maneuvers to make the rover move its servos to inevitably move the rover. If no command is sent to rover The autonomous function If the rover has moved, by inspection it will be shown if it upon deployment for five will be programmed into functioned autonomously. minutes move to autonomous the ArduIMU such that if a functions of moving the rover signal is not received from 10 feet forward, rotating 180̊ the RC controller, it will and moving forward 10 feet. perform the autonomous functions. University of Minnesota: 2012-2013 USLI 25 Preliminary Design Review

Payload Test Plan Overview Payload requirement Design feature to verify Verification of completion requirement There will be a live video feed A CCD Camera will be If there is camera visual on the team member’s from the rover to a team mounted on the rover that computer, it will be known that the requirement was member’s computer , is able to transmit its video successfully accomplished. to a team member’s computer via a receiver and patch antenna. A GPS unit will transmit the GPS ArduIMU shield. If there are transmissions from the rover back to a team rover’s location back to a team member’s computer, the requirement will be verified. member. University of Minnesota: 2012-2013 USLI 26 Preliminary Design Review