Ordnance Research for Complex Dispensing Warheads

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8651-06-C-0125
Agency Tracking Number: F051-160-3514
Amount: $875,387.00
Phase: Phase II
Program: SBIR
Awards Year: 2006
Solicitation Year: 2005
Solicitation Topic Code: AF05-160
Solicitation Number: 2005.1
Small Business Information
891 Coldwater Creek Circle, Niceville, FL, 32578
DUNS: 006468131
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: Y
Principal Investigator
 Adam Wells
 Staff Aerodynamicist
 (850) 217-9938
 ajw@anyarinc.com
Business Contact
 Rayna McGlockton
Title: President
Phone: (850) 217-9938
Email: rmm@anyarinc.com
Research Institution
N/A
Abstract
To accurately model dispensing events in conceptual AF and Navy dispensing munitions, the simulation framework used to build the simulations must incorporate fast, accurate, scalable physics engine algorithms as well as robust interacting aerodynamic flow estimation. The Phase I SBIR effort demonstrated interfaces could be developed within Endgame Framework that supported an objected oriented physics engine capable of accurately and rapidly computing the response of several independent dispensed components reacting to simple uncoupled, noninteracting, aerodynamic loads. The Phase II effort will expand the development of the Phase I core capabilities to enable: 1) incorporation of sophisticated C++ framework that will enable rapid prototyping of symbolic algorithms planned for the physics engine, 2) simulation module development of an object oriented implementation that unifies constraint and collision response equations of motion based on using the mathematical framework, 3) engineering level aerodynamic coefficient estimation for dispensing components with the ability to support interacting or noninteracting flow fields, and 4) addition of convenient GUI and XML based access to parameters associated with munition properties, setup/configuration of the kinematics/physics algorithms, and setup/configuration of the aerodynamic load methodologies.

* Information listed above is at the time of submission. *

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