THRUST VECTOR CONTROL USING MOVEABLE STRUTS

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$487,000.00
Program:
SBIR
Contract:
N/A
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
N/A
Award Year:
1988
Phase:
Phase II
Agency Tracking Number:
5078
Solicitation Topic Code:
N/A
Small Business Information
Applied Technology Associates
P.o. Box 19343, Orlando, FL, 32814
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
N/A
Principal Investigator
 () -
Business Contact
 DR. ROBERT CAVALLERI
Title: INVESTIGATOR
Phone: () -
Research Institution
N/A
Abstract
THRUST VECTOR CONTROL OF SOLID PROPELLANT ROCKET NOZZLES CANBE OBTAINED WITH THE USE OF EITHER FLUID DYNAMIC MEANS OR MECHANICAL MEANS. THE FLUID DYNAMIC TECHNIQUES EMPLOY INJECTION OF GAS OR LIQUID INTO THE EXHAUST NOZZLE THROUGH THE NOZZLE WALL. THE MECHANICAL TECHNIQUES EMPLOY MOVING THE NOZZLE EXHAUST BELL BY GIMBALLING AT THE NOZZLE THROAT OR THE USE OF JET TABS AT THE NOZZLE EXHAUST PLANE. INSERTION OF A SOLID BODY INTO THE EXHAUST NOZZLE CAN HAVE THE SAME EFFECT AS THE FLUID DYNAMIC TECHNIQUE BUT REQUIRES THE USE HIGH TEMPERATURE MATERIALS. AN ALTERNATIVE IS TO EMPLOY A TRANSPIRATION COOLED BODY THAT IS PROJECTED THROUGH THE NOZZLE WALL. THE EFFECTIVENESS OF THIS TECHNIQUE AND THE COOLING REQUIREMENTS FOR THE STRUT CAN BE DETERMINED THROUGH THE USE OF COMPUTATIONAL FLUID DYNAMIC TECHNIQUES AND ANALYTICAL HEAT TRANSFER TECHNIQUES. A PARAMETRIC STUDY WILL BE PERFORMED FOR AN CONICAL INTERNAL SUBSCALE AXISYMMETRIC NOZZLE THAT WILL DETERMINE THRUST VECTOR CONTROL (TVC) EFFECTIVENESS FOR VARIOUS NOZZLE AXIAL LOCATIONS AND STRUT CONFIGURATIONS. POTENTIAL PASSIVE MATERIALS AND ACTIVELY COOLED CONFIGURATIONS WILL BE EVALUATED FOR THE STRUT APPLICATION. CANDIDATE MATERIAL WILL BE TABULATED.

* information listed above is at the time of submission.

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