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CSU RocketSAT

CSU RocketSAT. Colorado State University Project Advisor: Dr. Azer Yalin Graduate Advisor: Grant Rhoads Matt Lyon Wesley Munoz Ryan Sullenberger Kenny Vogel October 14, 2009. Conceptual Design Review. Mission Overview. Objective

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CSU RocketSAT

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  1. CSU RocketSAT Colorado State University Project Advisor: Dr. AzerYalin Graduate Advisor: Grant Rhoads Matt Lyon Wesley Munoz Ryan Sullenberger Kenny Vogel October 14, 2009 Conceptual Design Review

  2. Mission Overview • Objective • Space exploration missions are challenged with the ability to measure the amount of fluid (specifically a cryogenic fluid) that remains in a tank without the assistance of gravity. The RocketSat payload will consist of an optical mass gauging system that will demonstrate accurate measurements of the amount of fluid in a tank exposed to any gravitational environment. Two tanks with different volumes of liquid will be independently opened and closed from the system to show the volume difference between the two, simulating the loss (or usage) of liquids.

  3. Mission Overview The overall goal of the CSU RocketSat Team for the 2009 – 2010 academic year is to design and flight test a system that could be used as a mass gauge for cryogenic (liquid) fuel systems.  The team will develop a methodology for measuring the change in volume of a liquid sample due to the change in density of an enclosed gas. This system is designed to measure fluid volumes in any gravitational environment, but has specific application to orbital rockets and space vehicles. An interferometer will be used to obtain the fringe pattern of an enclosed gas.

  4. Mission Overview • Previous Research: • A mass gauging demonstrator for any gravitational conditions was studied and constructed by Bill Witherow, Kevin Pedersen and ValentinKorman in the 2006 IRAD Review. • The objectives of this experiment was to develop a sensor and measurement technique to accurately determine liquid volume in a tank in any gravitational environment, and demonstrate its accuracy and reliability in a relevant cryogenic environment. • The mass gauging system used a modified Michelson interferometer to detect subtle changes via the index of refraction.

  5. Mission Overview • Michelson Interferometer used for IRAD 2006.

  6. Mission Overview Mission Overview Mission Overview • Working laboratory experiment at MSFC; limit of successful data Fringe Count Optics Tank 1 Tank 2

  7. Mission Requirements

  8. Success Criteria • Minimum: • To construct a functional Optical Mass Gage within the size and weight constraints • Accurately and precisely measure differences in liquid volumes while on the earth (1G levels) • Pass all of Wallops’ testing requirements and be eligible to fly on launch day • Stay under budget • Maximum: • Accurately and precisely measure differences in liquid volumes throughout the entire flight envelope • Have all data be successfully recorded to the micro-SD card throughout the entire flight envelope • All minimum criteria

  9. Scientific Benefits • Future space missions are severely limited by the inability to determine the amount of fluid that remains in a tank without the assistance of gravity. • The sensor would enable future mission concepts dependant on mass gauging. • The sensor design is simple with minimal intrusion or modification to the tank. • Optical mass gauging system with piston would only require a compression device of a few cubic centimeters to determine volumes of 100 liter tanks. The same system would require a compression of roughly the same size of 1/3 of a soda can to allow for complete detection of 1000 liter volumes. This result far exceeds any current compression system. Ref: W. Witherow, Kevin Pedersen. Mass Gauging Demonstrator for Any Gravitational Conditions. IRAD 2006.

  10. Design • Design will consist of a Michelson-Morley or Mach-Zehnderinterferometer, two liquid tanks containing different volumes of water, and a piston for compression. • Interference from the laser beam will be recorded by a data logger. Mach-Zehdner Interferometer Conceptual Payload Design

  11. Expected Results It is expected that the Mach-Zehnder Interferometer will detect the change in the index of refraction for a noble gas (argon) within a contained volume during a launch on a sounding rocket, due to the difference in volume of a contained fluid.

  12. Payload Canister User’s Guide Compliance • Mass and Volume • Expected to require ½ of a full-size can (9.3in dia. x 4.75in height) • Mass is expected to be under 7 lb • Payload activation • Playload will be activated by a G-switch • All power and electronics will be provided by a power source and electronics system flown on the CSU RocketSat project in July 2009. • G-switch will be redesigned from last year to prevent accidental triggering during integration • Rocket Interface • Shorting wires and interface with the rocket will be that same as those from 2009.

  13. Shared Can Logistics Plan • Canister is shared with University of Northern Colorado • Northern Colorado Mission: • Studying the dynamics of a vessel containing a known liquid to study slosh affects that could be applicable to payloads attached to the spend final stage of a booster. • Colorado State Mission: • Innovative method for measuring gas volume with possible application to cryogenics using fringe patterns. • The CSU RocketSAT team would STRONGLY prefer to occupy the bottom half of the can due to the nature of vibrations on the experiment • The bottom bulkhead will be mounted to using the standard 5-bolt pattern, but it is preferable to use a different mounting pattern to UNC that does not have a standoff directly in the center

  14. Management • Team Members: • Matt Lyon • Wesley Munoz • Ryan Sullenberger • Kenny Vogel

  15. Budget

  16. Conclusions • The apparatus will be a functioning Mach-Zehnder Optical Mass Gauging system capable of measuring the change in volume of water between two separate tanks, to simulate a loss in mass. The most challenging endeavors involved with this project will be maintaining optical alignment throughout the mission, especially due to severe vibrations and accelerations, as well as the limited budget. Limited resources force us to design around looser tolerances that could be achieved with higher quality parts. Another challenge will be miniaturizing the device to fit within half a RocketSat canister. Our device will require an innovative approach to problem solving.

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