Spacecraft launch depressurization loads

Sanz Andres, Angel Pedro and Santiago Prowald, Julián B. and Ayuso Barea, A. (1997). Spacecraft launch depressurization loads. "Journal of Spacecraft and Rockets", v. 34 (n. 6); pp. 805-810. ISSN 0022-4650.


Title: Spacecraft launch depressurization loads
  • Sanz Andres, Angel Pedro
  • Santiago Prowald, Julián B.
  • Ayuso Barea, A.
Item Type: Article
Título de Revista/Publicación: Journal of Spacecraft and Rockets
Date: December 1997
Volume: 34
Faculty: E.T.S.I. Aeronáuticos (UPM)
Department: Vehículos Aeroespaciales [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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The pressure variation inside the launch vehicle fairing during climb through the atmosphere induces structural loads on the walls of closed-type spacecrafts or equipment boxes. If the evacuation of the air is not fast enough, excessive pressure loading can result in damage of elements exposed to the rising pressure jump, which depends mainly on the geometry of venting holes, the effective volume of air to be evacuated, and the characteristic time of pressure variation under the fairing. A theoretical study of the reservoir discharge forced by the fairing time-dependent pressure variation is presented. The basic mathematical model developed can yield both a numerical solution for the pressure jump and an asymptotic solution for the most relevant case, the small-prcssurc-jump limit, showing the dependence on a single nondimensional parameter: the ratio of the reservoir discharge to the fairing pressure profile characteristic times. The asymptotic solution validity range upper limit, obtained by comparison with the numerical solution, is determined by the starting of choked operation. Very high sensitivity of the maximum pressure jump to the ratio of characteristic times has been observed. Another relevant finding is that the pressure profiles for different launchers can be considered similar when rewritten in appropriate form and only their characteristic times are required for the analysis. The simple expressions of the asymptotic solution are a useful tool for preliminarily sizing the reservoir discharge geometry and estimating depressurization loads

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Item ID: 40032
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Deposited by: Biblioteca ETSI Aeronauticos
Deposited on: 25 Apr 2016 13:45
Last Modified: 25 Apr 2016 13:45
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