MODEL DEVELOPMENT FOR EXHAUST PLUME EFFECTS ON LAUNCH STAND DESIGN

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$499,860.00
Award Year:
1990
Program:
SBIR
Phase:
Phase II
Contract:
n/a
Award Id:
10545
Agency Tracking Number:
10545
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
3311 Bob Wallace Ave #203, Huntsville, AL, 35805
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
S D Smith
() -
Business Contact:
() -
Research Institute:
n/a
Abstract
EXISTING MODELS FOR DETERMINING PLUME INDUCED LAUNCH STAND PRESSURE AND THERMAL EFFECTS ARE TOO LABOR AND COMPUTATIONALLY EXPENSIVE TO ROUTINELY APPLY TO DESIGN LAUNCH STANDS AND MISSILE LAUNCHERS. THE TYPES OF CODES UTILIZED DURING THE DESIGN OF THE KENNEDY LAUNCH STAND INCLUDED; AN INVISCID TWO PHASE FLOW CODE, A VISCOUS MIXING CODE, A PARTICLE/SHOCK LAYER INTERACTION MODEL, A GASEOUS IMPINGEMENT MODEL AND A THERMAL ANALYSIS CODE WHICH INCLUDEDPARTICLE/SURFACE INTERACTIONS. THESE MODELS REQUIRED CONSIDERABLE MANUAL INTERVENTION FOR A SINGLE CALCULATION. A UNIFIED DESIGN MODEL WILL BE DEVELOPED THAT CAN TREAT ARBITRARY LAUNCH STAND GEOMETRIES WITH LITTLE OR NO USER INTERACTION FROM INPUT TO OUTPUT: IMPACT PRESSURE, HEATING RATE AND RESULTANT TEMPERATURE DISTRIBUTIONS THROUGH AND OVER THE LAUNCH STAND/DEFLECTOR HARDWARE. THE PHASE I CODE WILL INCLUDE A COMBINED INVISCID AND VISCOUS TWO DIMENSIONAL/AXISYMETRIC FLOW CODE COMBINED WITH A PLUME IMPINGEMENT MODEL. THIS MODEL WILL INCLUDE REAL, REACTING GAS, TWO PHASE AND VISCOUS MIXING EFFECTS. THE OUTPUT OF THIS STUDY WILL BE A VALIDATED EFFICIENT TOOL FOR PREDICTINGPLUME INDUCED PRESSURE AND THERMAL EFFECTS TO LAUNCH STANDS AND LAUNCHERS FOR BOTH LIQUID AND SOLID ROCKET LAUNCH VEHICLES AND MISSILES.

* information listed above is at the time of submission.

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