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Hypervelocity Missile Stage Separation
- Small Business Information
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Woman-Owned: NoMinority-Owned: NoHUBZone-Owned: No
- Phase 1
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Fiscal Year: 2003Title: Hypervelocity Missile Stage SeparationAgency / Branch: DOD / ARMYContract: DAAH01-03-C-R13Award Amount: $119,957.00
Abstract:
Hypervelocity kinetic energy missiles such as the CKEM are being designed utilizing multistage Booster-Sustainer configurations. Concepts entail different methods to separate booster and sustainer stages including passive drag, pyrotechnically-assisted,and, sustainer-motor-ignition-assisted separation. Stage separation is a highly transient process whose simulation requires utilizing 3D, transient CFD and modeling multiphase (particulate) effects as well as afterburning chemistry. Aerodynamic forces andmoments on each body must be accurately accounted for and frictional and normal contact forces between the embedded stages must be determined. This problem is significantly more complex than ?traditional? separation problems where only aerodynamic forcesand moments are considered. A 6DOF analysis is required which predicts the resulting motion of these two stages which must be coupled to the CFD analysis in a time accurate manner, while accounting for the complex physical processes present. Theinnovation is the extension of current, advanced CFD methodology to deal with the many additional intricacies of this complex separation problem. Phase I will serve to scope out the overall problem and demonstrate the ability to analyze the CKEM separationscenario for a simplified geometry. In addition to paving the path for supporting design/development activities for tactical systems and relevant separation events, this activity will lead to our ability to simulate very complex stage separation events forother types of systems with fully coupled CFD/6DOF and plume chemistry and multi-phase effects. This has significant commercial potential as related to a variety of design and systems studies which include:(1) Separation analysis of the X-37 Space Shuttle;(2) Separation analysis of the X-43 Hyper-X scramjet research vehicle;(3) TBM separation event simulations supporting IR detection (IR spike); and,(4) Launcher analyses and flyout with application to both Army and Naval missile launcher designs.This effort will expand the types of problems we can support and will enhance the commercialization of the specialized CFD codes we now license.Small Business Information at Submission:COMBUSTION RESEARCH & FLOW TECHNOLOGY, I
174 North Main Street, P.O. Box 1150 Dublin, PA 18917EIN/Tax ID: 232759059DUNS: N/ANumber of Employees:Woman-Owned: NoMinority-Owned: NoHUBZone-Owned: No
Award Information
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Agency: Department of Defense |
Branch: Army |
Award ID: 63062 |
Program Year/Program: 2003 / SBIR |
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Agency Tracking Number: A022-1256 |
Solicitation Year: N/A |
Solicitation Topic Code: N/A |
Solicitation Number: N/A |