Add to ORKGThe characteristics and performance of the orbit maneuvering engine for the space shuttle are discussed. Emphasis is placed on the regeneratively cooled thrust chamber of the engine. Tests were conducted to determine engine operating parameters during the start, shutdown, and restart. Characteristics of the integrated thrust chamber and the performance and thermal conditions for blowdown operation without supplementary boundary layer cooling were investigated. The results of the test program are presented
The combustion stability characteristics of engines applicable to the Space Shuttle Orbit Maneuverin...
This paper describes Rocketdyne's successful analysis and demonstration of the Space Shuttle Main En...
Analysis, design, fabrication, and test efforts were performed for the existing OF2/B2H6 regenerativ...
Data on the performance, stability, and thermal characteristics of an OME operating with an alternat...
The test program conducted to characterize the steady state stability, thermal, and performance char...
Analyses and preliminary designs of candidate OME propellant combinations and corresponding engine d...
An analytical and design study was conducted to compare the high and low contraction ratio thrust ch...
The stability characteristics of the like-doublet injector were defined over the range of OME chambe...
An evaluation of reusable thrust chambers for the space shuttle orbit maneuvering engine was conduct...
Descriptions are given of the test hardware, facility, procedures, and results of electrically heate...
The performance and heat transfer characteristics of a doublet element type injector for the space s...
A subscale injector test program conducted with a ten-inch diameter like-doublet injector to determi...
Test hardware, facilities, and procedures are described along with results of electrically heated tu...
An abbreviated program was conducted to investigate igniter, injector, and thrust chamber technology...
The current Space Shuttle Orbital Maneuvering Engine (OME) is pressure fed, utilizing storable prope...
The combustion stability characteristics of engines applicable to the Space Shuttle Orbit Maneuverin...
This paper describes Rocketdyne's successful analysis and demonstration of the Space Shuttle Main En...
Analysis, design, fabrication, and test efforts were performed for the existing OF2/B2H6 regenerativ...
Data on the performance, stability, and thermal characteristics of an OME operating with an alternat...
The test program conducted to characterize the steady state stability, thermal, and performance char...
Analyses and preliminary designs of candidate OME propellant combinations and corresponding engine d...
An analytical and design study was conducted to compare the high and low contraction ratio thrust ch...
The stability characteristics of the like-doublet injector were defined over the range of OME chambe...
An evaluation of reusable thrust chambers for the space shuttle orbit maneuvering engine was conduct...
Descriptions are given of the test hardware, facility, procedures, and results of electrically heate...
The performance and heat transfer characteristics of a doublet element type injector for the space s...
A subscale injector test program conducted with a ten-inch diameter like-doublet injector to determi...
Test hardware, facilities, and procedures are described along with results of electrically heated tu...
An abbreviated program was conducted to investigate igniter, injector, and thrust chamber technology...
The current Space Shuttle Orbital Maneuvering Engine (OME) is pressure fed, utilizing storable prope...
The combustion stability characteristics of engines applicable to the Space Shuttle Orbit Maneuverin...
This paper describes Rocketdyne's successful analysis and demonstration of the Space Shuttle Main En...
Analysis, design, fabrication, and test efforts were performed for the existing OF2/B2H6 regenerativ...