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Analysis and test for space shuttle propellant dynamics : 1/60th scale model test results

Author
Berry, R. L.
Published
Mar 1, 1978.
Physical Description
1 electronic document
Additional Creators
Tegart, J. R.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
During the abort sequence, the ET and orbiter separate under aerodynamic loading, with propellant remaining in the ET. The separation event included a seven second decelerating coast period during which the residual propellant accelerates relative to the ET/orbiter. At separation, ET clearance was primarily provided by aerodynamics acting on the ET to move it away. The motion of the propellant, primarily LOX, significantly influenced the resulting ET motion and could cause the ET to recontact the orbiter. A test program was conducted involving thirty-two drops with 1/60th scale models of the ET LOX tank. The objective was to acquire data on the nature of low g propellant reorientation, in the ET LOX tank, and to measure the forces exerted on the tank by the moving propellant.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19780013358.
Accession ID: 78N21301.
MCR-78-523.
NASA-CR-151681.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15729244