An Integrated Thrust Control Solution

Period of Performance: 01/06/2005 - 09/30/2005

$115K

Phase 1 SBIR

Recipient Firm

Ghkn Engineering, LLC
P.O. Box 258516307 NE 83rd Street
Redmond, WA 98073
Principal Investigator

Abstract

This proposal describes a feasibility study to evaluate several concepts for integrated thrust vector control of a tactical missile. The proposed designs include a moveable aeropintle capable of moving laterally as well as axially and a fluidic gas injection system with the goal of provide both thrust variation and thrust vector control. The variable thrust aeropintle can be mechanized to move in the appropriate direction, on command, to achieve the desired flight path. The fluidic approach evaluated will include fluidic control injection utilizing chamber bleed gas or a third component pressure fed gas into the exhaust stream of the variable thrust aeropintle concept. Another approach to be examined is a gimbaled aeropintle with an axial position actuator. The objective of this study is to develop a baseline design offering a substantial improvement in flight path control such that the vehicle flight can be altered as much as a reversal in direction ("U" turn). The baseline design recommended as a result of this study will be evaluated for cost/schedule benefits and applicability to current missile designs.