Power-On Missile Stage Separation Simulation
Our proposal involves the formulation and development of innovative technical approaches for accurately simulating the transient power-on separation event for a multi stage, supersonic/hypersonic missile. As part of this Phase II effort we will undertake the development and validation of a time dependent, self adaptive, overset mesh approach for handling the complex grids needed for missile stage separation. We will incorporate and validate the necessary modeling terms to account for the volumetric contributions of heavy particulate loadings and upgrade and validate the solid wall boundary conditions to allow for particle reflections as well as the potential formation and build up of a molten slag layer. Ultimately we will demonstrate the ability of the improved model to analyze transient power-on missile stage separation over a broad range of flight scenarios of interest. This will include comparisons of a hypersonic power-on stage separation case for which detailed flowfield data will become available which will serve to demonstrate and validate the advanced capabilities of the software and also serve to identify any deficiencies in the model.
Small Business Information at Submission:
Combustion Research and Flow Technology,
6210 Kellers Church Road Pipersville, PA -
Number of Employees: