1 / 34

Preliminary Design Review

Preliminary Design Review. University of Colorado Boulder NASA Student Launch 2013-14. Overview. Launch Vehicle & Subsystems Recovery System Communications Systems HazCam Hazard Detection Liquid Sloshing Experiment Aerodynamic Analysis Payload. Vehicle Summary.

newton
Download Presentation

Preliminary Design Review

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Preliminary Design Review University of Colorado Boulder NASA Student Launch 2013-14

  2. Overview • Launch Vehicle & Subsystems • Recovery System • Communications Systems • HazCam Hazard Detection • Liquid Sloshing Experiment • Aerodynamic Analysis Payload

  3. Vehicle Summary • 168 inches long, 3.9 inch inside diameter • Carbon fiber body • High strength-to-weight ratio • Fiberglass nosecone • RF transparent

  4. Vehicle Sections Aerodynamic Analysis Drogue Parachute Electronics Bay Main Parachute Motor Section HazCam& GPS Liquid Sloshing

  5. Stability • Static stability margin

  6. Stability (cont.) • Stability: 15 calibers • Center of Gravity location: • 69 inches from tip of the nose • Center of Pressure location: • 130 inches from tip of the nose Center of Gravity Center of Pressure

  7. Vehicle Safety Verification Plan • Summary of Verification Plan • Structural Testing • Subscale Flights • Dual Deployment & Ejection Testing • Full Scale Flights

  8. Motor • Cesaroni L-1720 White Thunder • Total impulse: 823 lbf-s • Average thrust: 398 lbf • Max thrust: 437 lbf • Burn time: 2.1 s

  9. Motor Justification • Target altitude: 4,000 feet • Preliminary simulations predict 4,595 feet • Actual altitude will be lower due to mass increasing as design matures, added ballasts • Subsonic speeds (for aerodynamic analysis) • Maximum Mach number: 0.5 • Adequate payload experiment time during descent

  10. Performance Summary • T:W ratio = 10 • Rail exit velocity = 103 ft/s • Max velocity = 562 ft/s • Max acceleration = 296 ft/s2

  11. Launch Vehicle Verification Plan • Summary of Verification Plan • 1.1The vehicle shall deliver the research payload to an altitude of 4,000 above ground level • Satisfied by motor, ballasts; verified by analysis, test • 1.2 The vehicle shall carry one commercially available barometric altimeter for recording the official altitude for competition • Satisfied by altimeter; verified by analysis, test • 1.3 The launch vehicle shall be designed to be recoverable and reusable • Satisfied by recovery system, verified by analysis • 1.4 The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours, from the time the FAA waiver opens • Satisfied by demonstrated team ability, verified by test

  12. Launch Vehicle Verification Plan cont. • Summary of Verification Plan cont. • 1.5The launch vehicle shall be capable of remaining in launch-ready configuration at the pad for a minimum of one hour without losing functionality of critical components. • Satisfied by battery-operated electronics; verified by test • 1.6The launch vehicle shall be capable of being launched by a standard firing system. The firing system will be provided by the NASA-designated Range Services Provider. • Satisfied by motor; verified by inspection

  13. Launch Vehicle Verification Plan cont. • Summary of Verification Plan cont. • 1.7The launch vehicle shall require no external circuitry or special ground support equipment to initiate launch (other than what is provided by Range Services). • Satisfied by motor; verified by inspection • 1.8The launch vehicle shall use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the NAR • Satisfied by motor; verified by inspection

  14. Recovery System - Overview • Parachute Design • Elliptical Cupped • 15 ft. main parachute • 6 ft. drogue parachute • Parachute Material • 1.9 oz. rip-stop nylon • 1 in. woven nylon cord Elliptical Cupped Parachute —Source: http://www.the-rocketman.com/chutes.html Subscale Parachute

  15. Recovery System - Parachute Placement/Deployment • Two elliptical cupped parachutes with dual deployment • Drogue Parachute • Apogee (target altitude: 4,000 feet AGL) • Main Parachute • 1,000 feet AGL Drogue Parachute Electronics Bay Main Parachute Motor Section

  16. Recovery System - Hardware • Recovery Attachments • Long sections of shock cord attached by quick links to bulkhead coupler tube assemblies • Bulkheads made from wood with U-bolts attached • Shock cords attached to U-bolts Previous Electronics Bay

  17. Recovery System- Avionics • Raven Featherweight altimeters • 1st event (drogue deployment) at apogee • 2nd event (main deployment) at 1,000 feet AGL • Redundant altimeter is Raven Featherweight Wiring for Raven3 Featherweight

  18. Communication Systems - Overview • Wireless downlink to ground station • HazCam data • GPS data • Located in RF transparent fiberglass nosecone

  19. Hazard Camera (HazCam) Payload - Overview • Scans ground looking for Hazards • Image is taken and sent to Raspberry Pi • Raspberry Pi analyzes image and looks for Hazard • When hazard is found, it is transmitted to ground station • All footage is saved onboard for post-launch analysis Drawing of Nosecone-HazCam Assembly

  20. HazCam Payload - Block Diagram • HazCam connects to Comm System via USB to Arduino Board • Uses cost effective and easy-to-use Raspberry Pi hardware

  21. HazCam Payload - Design • Used to process image • Handles transmission to Xbee transmitter • Built by makers of Raspberry Pi, comes with fully built library • Capable of HD video

  22. HazCam Algorithm - Current State

  23. HazCam Algorithm - Future Work • Increase Speed • Translate to C • Reduce False Positives

  24. Liquid Sloshing Experiment - Overview • Innovative method of microgravity liquid fuel transport • Liquid fuel starts in pressurized tank • AIM USB altimeter opens solenoid valve at motor burn-out • Fuel forced from pressurized tank through valve to unpressurized tank • Valve closes at apogee (drogue deployment, end of microgravity phase)

  25. Liquid Sloshing Experiment - Design • Solenoid switch activated by electrical pulse from altimeter • Compatible with PVC tubing • Programmable to send signal at peak velocity (burn-out) and apogee • High flight heritage and cost-effective Sprinkler Valve AIM USB Altimeter

  26. Liquid Sloshing Experiment -Additional Design Considerations • PVC selected for sturdiness, availability, ability to be pressurized safely • Pressurized tank includes depressurizing ball valve for safety First Prototype of Liquid Sloshing Apparatus

  27. Liquid Sloshing Experiment - Block Diagram • Pressure Sensor and Data Logger activated prior to launch, record data during entire flight • Altimeter activates Sprinkler Valve at motor burnout, deactivates at apogee • On-board systems do not interface with ground station in real time to save cost and space AIM USB Altimeter Pressure Sensor Sprinkler Valve Data Logger

  28. Liquid Sloshing Experiment - Interface and Testing Plan • Interface With Rocket • Located in upper payload bay below nosecone • Payload supported and connected to rocket body by wooden bulkheads • Electronics sled in payload bay contains altimeter, data logger • Testing • Pressure testing for PVC to ensure 4:1 pressurization safety factor • Drop test to ensure payload survival in case of parachute failure • Operational testing on ground and during subscale launches • Electronics test pre-launch to ensure functionality

  29. Aerodynamic Analysis Payload - Overview • The payload will measure aerodynamic flow over the side of the rocket • Will compare pressures over protuberances in two different types of flow • Compared against CFD results

  30. Aerodynamic Analysis Payload Design - Structure • Protuberances with pressure ports constructed at and around payload • Pressure ports drilled at • Vortex generators ahead of one protuberance

  31. Aerodynamic Analysis Payload Design – Pressure Measurement System • Pressure ports will be connected by vinyl tubing to pressure sensors • Four pressure ports per protuberance • (Increased/decreased as budget allows) • Microcontroller will read digital pressure sensor and velocity data • Store data to SD card • Downlink payload status to COM unit

  32. Aerodynamic Analysis Payload Design – Test and Verification Plan • CFD will provide preliminary estimates of the effects of the protuberances on the flow • A subscale of the upper body tube will be constructed and tested in the wind tunnel on campus

  33. Aerodynamic Analysis Payload - Data Analysis • Six sets of pressure data will be generated • Turbulent flow over protuberance • Laminar flow over protuberance • Control flow (no protuberance) • Pressure data from CFD simulations for each of the conditions listed above • This data will be compared numerically as well as qualitatively to see how the different flows compare • This will give insight as to how the protuberances affected the flight of the rocket and flow patterns around the rocket.

  34. Questions? University of Colorado Boulder NASA Student Launch 2013-14

More Related