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- W2043073922 abstract "Pressurization of the Space Shuttle solid rocket motor (SRM) nozzle boot cavity involves compressible gas flow along a duct with friction and a pressurizing volume with heat transfer at the boundaries. Numerical simulation of the process requires a solution of the simultaneous compressible flow, boot cavity conservation, and solid-conduction equations. Basic geometry consists of circular flow path connected to a plenum-free volume that is surrounded by a solid-conduction media (i.e., the cowl vent holes, boot cavity, and cavity insulation). An existing methodology is used to compute the compressible mass-flow rates through the vent hole. Boot cavity conditions are computed by the application of a finite-difference form of the conservation equations. In the boot cavity insulation (i.e., the solid-conduction regions), the finite-difference transient diffusion equation is applied. A conjugate solution is developed whereby the coupled first-order differential equations are solved simultaneously, along with a set of algebraic equations, by fully implicit successive point iteration. A model was constructed to simulate a boot cavity pressurization test, and a comparison of model response vs test data is given. The agreement is generally good." @default.
- W2043073922 created "2016-06-24" @default.
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- W2043073922 date "1989-09-01" @default.
- W2043073922 modified "2023-09-25" @default.
- W2043073922 title "Modeling of the Space Shuttle solid rocket motor nozzle boot cavity pressurization process" @default.
- W2043073922 doi "https://doi.org/10.2514/3.26083" @default.
- W2043073922 hasPublicationYear "1989" @default.
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