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Hypervelocity Missile Stage Separation

Award Information

Agency:
Department of Defense
Branch:
Army
Award ID:
63062
Program Year/Program:
2003 / SBIR
Agency Tracking Number:
A022-1256
Solicitation Year:
N/A
Solicitation Topic Code:
N/A
Solicitation Number:
N/A
Small Business Information
Combustion Research and Flow Technology, Inc.
6210 Kellers Church Road Pipersville, PA 18947-1020
View profile »
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 2
Fiscal Year: 2003
Title: Hypervelocity Missile Stage Separation
Agency / Branch: DOD / ARMY
Contract: W31P4Q-04-C-R020
Award Amount: $729,998.00
 

Abstract:

The innovation is the inclusion of generalized 6DOF analysis methodology into advanced structured grid (CRAFT CFD) and unstructured grid (CRUNCH CFD), three-dimensional, time-accurate Navier-Stokes codes. This will permit the high fidelity simulation of abroad range of missile separation problems including the effects of plume interactions with both chemical kinetic and multiphase particulate effects. The codes can run in both time-accurate modes (for very high accuracy), and in more conventional modeswhere the aerodynamic forces are updated at prescribed time intervals. The coupled 6DOF/CFD codes will be applied to the CKEM stage separation problem where present designs are based on using passive drag concepts to separate the booster and sustainerstages. During the early stages of separation, the analysis requires considering a unified booster/sustainer configuration with variable center of gravity and moments of inertia; while at later stages the analysis transitions to a more conventionaltwo-body problem. The new code will be used to support CKEM separation design and evaluation studies including simulating separation tests at the CUBRC shock tunnel facility as well as planned flight tests. In addition, the new code will be used toanalyze seeker window shroud separation and submunition-dispense problems.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 simulatevery complex stage separation events for other 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.

Principal Investigator:

Brian York
Principal Scientist & Tre
2152499780
york@craft-tech.com

Business Contact:

Brian York
Principal Scientist & Tre
2152499780
york@craft-tech.com
Small Business Information at Submission:

COMBUSTION RESEARCH & FLOW TECHNOLOGY
174 North Main Street, P.O. Box 1150 Dublin, PA 18917

EIN/Tax ID: 232759059
DUNS: N/A
Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No