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Design and performance verification of a passive propellant management systemThis paper describes the design and verification testing of a reusable passive propellant management system. The system was designed to acquire propellant in low- or zero-g environments and also retain this propellant under high axially directed accelerations that may be experienced during launch and orbit-to-orbit transfer. The system design requirements were established to satisfy generally the requirements for a large number of potential NASA and military applications, such as orbit-to-orbit shuttles and satellite vehicles. The resulting concept was a multicompartmented tank with independent surface tension acquisition channels in each compartment. The tank was designed to provide a minimum expulsion efficiency of 98 percent when subjected to the simultaneous conditions of acceleration, vibration, and outflow. The system design has the unique capability to demonstrate low-g performance in a 1-g test environment, and the test program summarized was structured around this capability.
Document ID
19780059650
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hess, D. A.
(McDonnell-Douglas Astronautics Co. Saint Louis, MO, United States)
Regnier, W. W.
(McDonnell Douglas Astronautics Co. St. Louis, Mo., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 78-1029
Meeting Information
Meeting: Joint Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: July 25, 1978
End Date: July 27, 1978
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
78A43559
Funding Number(s)
CONTRACT_GRANT: NAS8-31808
Distribution Limits
Public
Copyright
Other

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