USA flag logo/image

An Official Website of the United States Government

Rocket Nozzle Thrust Diverter

Award Information

Agency:
Department of Defense
Branch:
N/A
Award ID:
Program Year/Program:
2012 / SBIR
Agency Tracking Number:
F112-181-0501
Solicitation Year:
2011
Solicitation Topic Code:
AF112-181
Solicitation Number:
2011.2
Small Business Information
Exquadrum, Inc
12130 Rancho Road Adelanto, CA 92301
View profile »
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No
 
Phase 1
Fiscal Year: 2012
Title: Rocket Nozzle Thrust Diverter
Agency: DOD
Contract: FA9300-12-M-1005
Award Amount: $149,983.00
 

Abstract:

ABSTRACT: Exquadrum proposes a rocket nozzle thrust diverter to achieve an additional 2:1 throttle reduction above and beyond the throttle capability of the engine. The innovative thrust diverter operates separate from the engine and engine cycle, and therefore has no performance effect on the turbomachinery, thrust chamber, or nozzle. It is stowed away from the engine exhaust stream for re-usability and long-life, and is deployed using a single actuator, synchronization ring, and linkages. In Phase I, Exquadrum will document the requirements, use modeling and simulation to conduct design trade studies, generate a general arrangement drawing to document the resulting configuration, and perform a proof-of-concept sub-scale hot fire demonstration test. This test will also generate the initial data regarding loads, temperatures, and performance that will be useful in identifying risks for the modeling, simulation, and development efforts planned for Phase II. BENEFIT: Anticipated benefits of this research includes the successful demonstration of the rocket nozzle thrust diverter system through a proof-of-concept hot fire test conducted at the completion of Phase I. This test will demonstrate the ability of the rocket nozzle thrust diverter to reduce the measured thrust 50 percent, hence demonstrating the 2:1 throttle requirement. Additional benefits of the rocket nozzle thrust diverter include using it as an uncooled nozzle extension for increased performance, as well as using its actuation capability to provide altitude compensation for improved off-design performance. These performance improvements have the potential to offset the added weight of the thrust diverter system. The rocket nozzle thrust diverter enables greater throttle range beyond the rocket engine throttle capability. Moving the throttling capability from the engine to the diverter reduces the operating range of the engine, which improves performance and reliability. Having an overall increased throttle range enables significantly lower thrust during stage separation for a booster engine and provides deeper throttling capability for upper stage engines. The technology is applicable to booster and upperstage with either bell, conical, or aerospike nozzles for Air Force, NASA, and the growing commercial space launch industry.

Principal Investigator:

Philip Pelfrey
Executive Vice President
(760) 246-0279
phil.pelfrey@exquadrum.com

Business Contact:

Eric E. Schmidt
Vice President&COO
(760) 246-0279
eric.schmidt@exquadrum.com
Small Business Information at Submission:

Exquadrum, Inc
12130 Rancho Road Adelanto, CA -

EIN/Tax ID: 383667286
DUNS: N/A
Number of Employees:
Woman-Owned: No
Minority-Owned: No
HUBZone-Owned: No