Computer Science – Performance
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.970h&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Performance
Scientific paper
operations, the Space Shuttle was designed to incur loss of thrust from one engine at liftoff and return safely to a runway. This is a very unusual capability in space launch vehicles and, if desired, must be designed into the system initially. For some extremely high value payloads on future expendable launch vehicles, this capability may be cost effective as well as for human space flights. Current designers may be inclined to design a "simple" emergency escape pod to resolve this issue. That may neither be the most effective nor the safest way to provide ascent failure tolerance. This paper discusses some real-world issues associated with this capability that the designers of the Space Shuttle did take into account that have become serious issues in real operations. paper discusses the affect of payload mass on abort capability. Issues related to abort modes can also be influence by other aspects of payload mass including center of gravity concerns. In a similar mode, consumables such as on-orbit attitude control propellant is a major factor in abort mode design. multiple engine failures during the powered ascent trajectory and have a happy outcome: landing on a runway. This paper discusses options and post-design fixes to the Space Shuttle to enhance multiple engine out capability. scenarios. include propellant underload on STS-61C, off nominal performance of engine clusters on STS-78 and STS-93, and other flights. Designers of these future human rated vehicles should consider the Space Shuttle experience in designing their systems. About the Authors: N. Wayne Hale, Jr. is currently the Deputy Chief for Shuttle of the NASA/JSC Flight Director Office. In 23 years with NASA at Houston's Johnson Space Center, he has served in the Mission Control Center for 41 Space Shuttle flights including 25 as Entry Flight Director. Mr. Hale received his Bachelor of Science Degree in Mechanical Engineering from Rice University in 1976 and his Master of Science Degree in Mechanical Engineering from Purdue University in 1976 based on his thesis research in heat and mass transfer. During the late 1970's and early 1980's Mr. Hale was co-author on several papers dealing with problems in heat and mass transfer. Barbara A. Conte is a 1986 graduate of Rice University with a Bachelor of Science in Mechanical Engineering. Currently the lead of the Mission Operation Directorate's Ascent Analysis Group at NASA/JSC, she has 15 years of experience in the ascent performance analysis of Space Shuttle flights.
Conte B. A.
Hale W. Jr. N.
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