Analytical Prediction Of Peak Pressure Transients Occurring During The Priming Of A Spacecraft Propulsion System

Abstract

The accurate prediction of the peak pressure transients that occur during the priming of a spacecraft propulsion system are vitally important as these transients can cause damage to components or even the auto detonation of some spacecraft propellants. This paper will focus on the accurate prediction of the peak pressure transients due to the reflected pressure wave. During the priming of a spacecraft propulsion system, pressure transients occur from the rapid deceleration of propellant from a pressurized manifold to an evacuated manifold downstream of an isolation valve. When the isolation valve is opened, propellant will flow essentially unrestrained until the fluid column impacts a surge suppression device. In the case of a straight edged orifice this will cause cavitation which will in turn slow down the fluid column. The propellant will continue to flow through the downstream piping until it hits a dead end. The initial impact of the fluid column with the dead end will cause a pressure transient. This transient will be referred to as "slug hammer". Once the line becomes liquid full, another pressure transient will occur which will cause a pressure wave to attenuate through all of the wetted lines. This transient will be referred to as the "reflected pressure wave". Surge suppression devices have the greatest effect on reducing the pressure transient due to slug hammer. Therefore it is important to accurately predict the pressure transient due to the reflected pressure wave, as this transient cannot be mitigated as effectively by simply adding additional margin. AFT Impulse, a surge/waterhammer modeling software, was shown to accurately predict the peak pressure transient due to the reflected pressure wave despite some of its modeling limitations, as long as the peak pressure transient is due to the reflected pressure wave.

Publication Date

1-1-2016

Publication Title

52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2016-4774

Socpus ID

85088060896 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85088060896

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