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RocketSat 8 Conceptual Design Review

RocketSat 8 Conceptual Design Review. University of Colorado Boulder 10/4/11. Mission Statements.

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RocketSat 8 Conceptual Design Review

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  1. RocketSat 8 Conceptual Design Review University of Colorado Boulder 10/4/11

  2. Mission Statements • RocketSat 8 shall integrate and validate the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD). This shall provide a means to de-orbit future small satellites. • RocketSat8 shall validate an attitude determination system for future RockSatmissions

  3. Theory and Background • 23 small satellites (10kg-500kg) launched every year by the United States • Growth of small satellites in space exponentially increases the likelihood of collisions • The rise in the number of satellites in orbit has led to an increasing need for a cost effective and lightweight means to de-orbit small satellites. • The RocketSat VII attitude determination system was successful, but the accuracy of the system couldn’t be verified since there was no known solution for the attitude of the rocket.

  4. Requirements

  5. Requirements (cont.)

  6. Requirements (cont.)

  7. Requirements (cont.)

  8. Minimum Success Criteria • Mission success depends on the image capture of the deployed RODEO device. • Secondary mission success is determined by the validation of the RocketSat8 attitude determination system

  9. Mission overview: Concept of Operations Deploy RTS RTS data collection Send Data from RTS to payload Apogee Altitude: ≈160 km Initialize Camera Begin Rodeo Deployment Continue Telemetry Splash Down End Telemetry Pre-Launch -Begin Telemetry -Begin attitude data collection Chute Deployment Continue Telemetry

  10. Mission overview: Expected Results We expect: • the RODEO system to be fully extended while attached to the rocket • to capture an image of the extended RODEO system • the RTS to detatch from the rocket canister • to measure deceleration from the RTS • to transmit the deceleration data from the RTS • We expect to characterize the rockets attitude and verify it with a known solution

  11. Design Overview

  12. User Guide Compliance: Structures • The payload shall fit into the allotted 12 in diameter base and 11 in height and weigh less than 30 +- 1 lb. • The center of gravity shall be within 1 square inch of the RockSat-X deck. • Materials with a high resistance to stress corrosion and cracking, and a low outgassing index will be used. • The deployable shall conform to all standards to safely eject from the canister.

  13. Payload Layout: Structures • The structure thus far will be composed of two plates. • The bottom plate will include the RTS containing the deployable given to us by Composite Technology Development, as well as the ejection system. • The electronics boards and the ADS(Attitude Determination System) will all be utilized on the top plate with the cameras.

  14. Payload Layout: Structures Top Plate Bottom Plate ADS Ejection System Deployable Electronics Board Keep Out Zone Camera on bottom of top plate

  15. RODEO Test Structure (RTS) Layout: rough diagram RTS RODEO Note: Drawing not drawn to scale

  16. Mission Requirements • The payload shall conform to the requirements set forth in the 2011 RockSat-X User Guide • The system shall successfully deploy the hardware manufactured by Composite Technology Development. • The structure will interface with RockSat-X through provided mounting surfaces.

  17. Mission Requirements: Electronics Integration • All electronic interfaces will be held in place throughout the duration of the flight with the exception of the deployable. • The structure will withstand the forces of launch and protect the scientific and electrical systems. • The structure will thermally protect the electronics for as long as reasonable data can be collected. • The system shall successfully take at least one photo of the deployable as it leaves the canister, and house the cameras securely during launch.

  18. Mission Requirements: Ejection System • The ejection system shall be durable enough to survive the forces of launch. • The structure shall allow exposure to an open air environment while still protecting electronics and instruments from harm.

  19. Electrical Subsystem Electrical Subsystems: • Power • Memory • Radio Communications (Comm) • Mechatronics • Imaging

  20. Conceptual Electrical Configuration Main Structure Power line Digital line Analog Line Note: Not actual layout Power Comm RTS Radio Comm ADS Sail Deploy MCU Charging (before deploy) MCU Imaging Sensors Memory Power RTS Deploy

  21. User Guide Compliance: Electrical • The GSE Controlled power lines shall carry a total current of less than 1.85 A. • The Timer Controlled power lines shall carry a total current of less than 3.75 A. • All telemetry lines shall operate in the range of 0 – 5 V. • All components shall operate at 28 V or less. Higher voltages shall be used only with express written permission. • All components shall be conformal coated to protect from the space environment.

  22. State Chart: Software State 2 Launch State 1 Pre-Launch State 3 Apogee State 4 Post-Apogee State 5 Splash Down Power On Telemetry • Apogee Code • Initialize Camera • Delay 30 seconds G Switch Telemetry • Main Code • Store Data • Check Timed Sequence One Telemetry Yes • Initial Code • Initialize Devices • Check G Switch • Deploy Code • Deploy RTS • Get Data RTS Camera • Final Code • Check Time Sequence Two • Stop Recording Yes No RTS

  23. Design Overview: RockSat-X 2012 User’s Guide Compliance

  24. Management Andrew Broucek Project Manager Wheeler Gans Systems Lead Nate Keyek-Franssen Structures Lead Emma Young Science Lead Andrew Thomas Electrical Lead Ethan Long Software Lead Devin Mackenzie Structures Eric Lobato Science ShreyankAmartya Electrical Long Tat Software Kameron Medina Structures Aram Podolski Science Brendan Lee Electrical

  25. Preliminary Schedule- Important Dates

  26. Preliminary Schedule- Weekly Schedule

  27. Budget

  28. Additional Support • We will be working in conjunction with Composite Technology Development (CTD). Our main advisors from CTD are still to be determined

  29. Conclusions Mission Statement To integrate and validate the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD) and test the attitude determination system from RocketSat VII Next Steps • Prepare for PDR • Finalize Design

  30. Questions

  31. Refrences 1"The Bright Future of Small Satellite Technology :: Via Satellite." Guest Edition :: Satellite Today. Web. 04 Oct. 2011. <http://www.satellitetoday.com/via/features/37150.html>. 2Carroll, Shawn, and Chris Koehler. Rocksat-X User Guide. 8 Feb. 2011. PDF.

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