Add to ORKGThe Transient Cryogen Transfer Computer Program (TCTP) developed and verified for LOX systems by analyses of Skylab S-1B stage loading data from John F. Kennedy Space Center launches was extended to include hydrogen as the working fluid. The feasibility of incorporating TCTP into the space shuttle main engine dynamic model was studied. The program applications are documented
Cooperative efforts between the Lockheed-Huntsville Computational Mechanics Group and the NASA-MSFC ...
The basic issues concerning the physical chemical processes of the Space Shuttle Main Engine are dis...
Technical analyses and computer programs in support of optimization of liquid hydrogen thermal prote...
Computer simulation studies of liquid hydrogen fill and vent systems for the space shuttle are studi...
The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) hi...
The Director of the NASA Engineering and Safety Center (NESC), requested an independent assessment o...
A Space Shuttle Main Engine (SSME) test program was conducted between August 1995 and May 1996 using...
The Cryogenic Propellant Storage and Transfer (CPST) project has been a long-running program in the ...
The Director of the NASA Engineering and Safety Center (NESC), requested an independent assessment o...
Transient thermodynamic analyses were made of the LOX loading system proposed for the space shuttle ...
High-energy cryogenic propellant is an essential element in future space exploration programs. There...
To improve the Space Shuttle Main Engine (SSME) design and for future use in the development of gene...
A two-year feasibility and test program to solve the problem of unburned confined hydrogen at the Va...
Space Shuttle Main Engines (SSME) discharge a significant quantity of unburned hydrogen during norma...
Gasdynamic analysis for the turbine blades and nozzle vanes, HPFTP turbine analysis, and HPOTP turbi...
Cooperative efforts between the Lockheed-Huntsville Computational Mechanics Group and the NASA-MSFC ...
The basic issues concerning the physical chemical processes of the Space Shuttle Main Engine are dis...
Technical analyses and computer programs in support of optimization of liquid hydrogen thermal prote...
Computer simulation studies of liquid hydrogen fill and vent systems for the space shuttle are studi...
The objective is to provide improved analysis capability for the Space Shuttle Main Engine (SSME) hi...
The Director of the NASA Engineering and Safety Center (NESC), requested an independent assessment o...
A Space Shuttle Main Engine (SSME) test program was conducted between August 1995 and May 1996 using...
The Cryogenic Propellant Storage and Transfer (CPST) project has been a long-running program in the ...
The Director of the NASA Engineering and Safety Center (NESC), requested an independent assessment o...
Transient thermodynamic analyses were made of the LOX loading system proposed for the space shuttle ...
High-energy cryogenic propellant is an essential element in future space exploration programs. There...
To improve the Space Shuttle Main Engine (SSME) design and for future use in the development of gene...
A two-year feasibility and test program to solve the problem of unburned confined hydrogen at the Va...
Space Shuttle Main Engines (SSME) discharge a significant quantity of unburned hydrogen during norma...
Gasdynamic analysis for the turbine blades and nozzle vanes, HPFTP turbine analysis, and HPOTP turbi...
Cooperative efforts between the Lockheed-Huntsville Computational Mechanics Group and the NASA-MSFC ...
The basic issues concerning the physical chemical processes of the Space Shuttle Main Engine are dis...
Technical analyses and computer programs in support of optimization of liquid hydrogen thermal prote...