Several accumulator designs and gas charge systems are considered in order to suppress POGO within the Ares I vehicle Upper Stage Liquid Ox ygen System. The thermodynamic and flow analysis completed to evaluat e candidate designs are presented and the results are used to evaluat e the ability of each concept to meet the levied suppression requirements. One annular accumulator design meets all suppression requirement s while also providing manufacturability and operability advantages. Of the two proposed charge systems to provide and maintain gas within the accumulator, a passive level control design meets the charge req uirements and maximizes reliability
Engine firing tests, using a full-scale flight-weight vehicle, were performed to evaluate a pressuri...
When the propellants in a liquid rocket engine burn, the rocket not only launches and moves in space...
A liquid oxygen / liquid methane 2,000 lbf thruster was designed and tested in conjuction with a noz...
A dynamic (frequency response) analysis was made of a liquid oxygen feed system consisting of a low-...
Analytical model for use in design of pump inlet accumulators for prevention of liquid rocket longit...
Waterflow tests of a heritage Space Shuttle Main Engine pogo suppressor were performed to experiment...
For single phase mechanically pumped fluid loops used for thermal control of spacecraft, a gas charg...
Topics covered include: (1) pogo suppression for main propulsion subsystem operation; (2) applicati...
The integration of the design features of the Shuttle elements into a cryogenic propellant managemen...
Two methods of active pogo suppression (stabilization) for the space shuttle vehicle were studied an...
AbstractProviding stability and dynamic quality of fuel systems is very important problem when devel...
Thermal conditioning systems for satisfying engine net positive suction pressure (NPSP) requirements...
Three designs were considered to satisfy the design objective. These designs were the current design...
The Low Profile Diffuser (LPD) project originated as an award from the Marshall Space Flight Center ...
With the advent of space exploration the demand for variable-thrust rocket engines grew appreciably....
Engine firing tests, using a full-scale flight-weight vehicle, were performed to evaluate a pressuri...
When the propellants in a liquid rocket engine burn, the rocket not only launches and moves in space...
A liquid oxygen / liquid methane 2,000 lbf thruster was designed and tested in conjuction with a noz...
A dynamic (frequency response) analysis was made of a liquid oxygen feed system consisting of a low-...
Analytical model for use in design of pump inlet accumulators for prevention of liquid rocket longit...
Waterflow tests of a heritage Space Shuttle Main Engine pogo suppressor were performed to experiment...
For single phase mechanically pumped fluid loops used for thermal control of spacecraft, a gas charg...
Topics covered include: (1) pogo suppression for main propulsion subsystem operation; (2) applicati...
The integration of the design features of the Shuttle elements into a cryogenic propellant managemen...
Two methods of active pogo suppression (stabilization) for the space shuttle vehicle were studied an...
AbstractProviding stability and dynamic quality of fuel systems is very important problem when devel...
Thermal conditioning systems for satisfying engine net positive suction pressure (NPSP) requirements...
Three designs were considered to satisfy the design objective. These designs were the current design...
The Low Profile Diffuser (LPD) project originated as an award from the Marshall Space Flight Center ...
With the advent of space exploration the demand for variable-thrust rocket engines grew appreciably....
Engine firing tests, using a full-scale flight-weight vehicle, were performed to evaluate a pressuri...
When the propellants in a liquid rocket engine burn, the rocket not only launches and moves in space...
A liquid oxygen / liquid methane 2,000 lbf thruster was designed and tested in conjuction with a noz...