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Analytical characterization of AOTV perigee aerothermodynamic regimeIn preliminary design studies of AOTV (Aeroassisted Orbital Transfer Vehicle) configurations, it is desirable to have a simple analytical method for characterizing the aerothermodynamic regime at skip trajectory perigee as a function of vehicle L/D and m/CDA (ballistic coefficient). The present study derives an approximate perigee solution from the generalized equations of motion. For a prescribed entry velocity vector, the solution determines a Zeta function (proportional to density divided by m/CDA) at perigee as a parametric function of the exit velocity vector and (constant) L/D. The perigee Zeta function then determines perigee density (or altitude) as a parametric function of m/CDA. The solution allows the following classic aerothermodynamic parameters to be determined at perigee as parametric functions of m/CDA, L/D, and the exit velocity vector: Reynolds Number (viscous effects), Mach Number (compressibility effects), Knudsen Number (rarefaction effects), sphere and disk bow shock standoff distance, Damkohler Number (relaxation effects), viscous correlation parameter (viscid-inviscid interactions), and Stanton Number (convective heat transfer). Results of the analysis are given for low L/D and mid L/D AOTV configurations on return from geosynchronous and L5 orbits. It is concluded the method successfully provides preliminary estimates of the aerothermodynamic parameters through the use of simple algebraic equations and plots.
Document ID
19840056588
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Desautel, D.
(San Jose State University San Jose, CA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1984
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 84-1713
Accession Number
84A39375
Funding Number(s)
CONTRACT_GRANT: NCA2-OR-675-401
Distribution Limits
Public
Copyright
Other

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