Engineering topics
Publications and source records attributed to Kirby, F. M..
Two injector types, either coaxial or impinging elements, for high pressure LOX/CH4 operation with an existing 40K chamber are examined. A comparison is presented. The detailed fabrication drawings and supporting analysis are presented.
The potential for converting the space shuttle main engine (SSME) to a dual-fuel, dual-mode engine using LOX/hydrocarbon propellants in mode 1 and LOX/H2 in mode 2 was examined. Various engine system concepts were formulated that included staged combustion and gas generator turbine power cycles, and LOX/RP-1, LOX/CH4, and LOX/C3H8 mode 1 propellants. Both oxidizer and fuel regenerative cooling were considered. All of the SSME major components were examined to determine their adaptability to the candidate dual-fuel engines.
Expendable launch vehicles will be phased out during the first years of shuttle operation and the payloads currently carried to orbit by these vehicles will be placed in low earth orbit by the reusable shuttle. In connection with limitations regarding the weight of the payload which can be launched by the Space Shuttle in its present form, approaches have been considered for increasing the payload capability of the Shuttle. Propulsion systems for Shuttle derived vehicles with larger payload capabilities have been studied. Such systems can potentially be obtained from modifications of the Space Shuttle Main Engine (SSME). Concepts based on modifications to the basic engine include an SSME-35 for low altitude operation with liquid rocket boosters and an SSME-150 for operation over the complete altitude range as might be required in a single-stage-to-orbit vehicle application. Another modification would provide operation with a hydrocarbon fuel instead of hydrogen.
Parametric data on split-combustor linear engine propulsion systems are presented for use in mixed-mode single-stage-to-orbit (SSTO) vehicle studies. Preliminary design data for two selected engine systems are included. The split combustor was investigated for mixed-mode operations with oxygen/hydrogen propellants used in the inner combustor in Mode 2, and in conjunction with either oxygen/RP-1, oxygen/RJ-5, O2/CH4, or O2/H2 propellants in the outer combustor for Mode 1. Both gas generator and staged combustion power cycles were analyzed for providing power to the turbopumps of the inner and outer combustors. Numerous cooling circuits and cooling fluids (propellants) were analyzed and hydrogen was selected as the preferred coolant for both combustors and the linear aerospike nozzle. The maximum operating chamber pressure was determined to be limited by the availability of hydrogen coolant pressure drop in the coolant circuit.
A description is presented of a dual-fuel modular split-combustor linear aerospike engine concept. The considered engine represents an approach to an integrated engine for a reusable single-stage-to-orbit (SSTO) vehicle. The engine burns two fuels (hydrogen and a hydrocarbon) with oxygen in separate combustors. Combustion gases expand on a linear aerospike nozzle. An engine preliminary design is discussed. Attention is given to the evaluation process for selecting the optimum number of modules or divisions of the engine, aspects of cooling and power cycle balance, and details of engine operation.
Performance, weight, and reusability of the Space Shuttle Main Engine, the next generation rocket engine, are important factors in achieving the Space Shuttle mission. The design features of the engine contributing to the achievement of these engine demands are discussed. Many new fabrication methods, material applications, and innovations incorporated into the engine are presented. The engine program is now in the second year of the 47 months development period. The current status of activities in engineering, manufacturing, and test are reviewed. The Design Verification Specification approach to engine development is compared to the development programs for Saturn/Apollo engines.
The Space Shuttle Main Engine and an Aerospike engine for the Space Tug illustrate the rocket engines of the future. This paper includes a description of design features leading to high performance, long life, and low cost. Computer control of the engine, turnaround maintenance plans, and engine development plans are also discussed.