The objectives of this task were to measure and compare the combustion response characteristics of the selected propellant formulation for the Space Shuttle Advanced Solid Rocket Motor (ASRM) with those of the current Redesigned Solid Rocket Motor (RSRM) formulation. Tests were also carried out to characterize the combustion response of the selected propellant formulation for the ASRM igniter motor.
ASRM Combustion Instability Studies
1992
34 pages
Report
Keine Angabe
Englisch
Physical & Theoretical Chemistry , Advanced solid rocket motor (Sts) , Burning rate , Combustion stability , Pressure oscillations , Solid propellant combustion , Solid propellant ignition , Solid propellant rocket engines , Solid rocket propellants , Frequency ranges , Heat flux , Igniters , Pressure effects , Pressure measurement , Signal to noise ratios , Space shuttles
ASRM combustion instability studies
NTRS | 1992
|AIAA | 1993
|ASRM Case Insulation development
NTRS | 1993
|ASRM nozzle design and development
AIAA | 1991
|ASRM Case Insulation development
AIAA | 1993
|