Gimbaled, partially submerged rocket nozzle Patent
Gimbaled partially submerged nozzle for solid propellant rocket engines for providing directional control
Brown, R. L.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Spherically-shaped rocket motor Patent
Spherical solid propellant rocket engine having abrupt burnout
Odonnell, T. J.↗
Propellant grain for rocket motors Patent
Grain configuration for solid propellant rocket engines
Pierce, R. M.↗
Demonstration of a sterilizable solid propellant rocket motor Final report, Feb. 1969 - Jul. 1970
Demonstration of solid propellant rocket engine for unmanned planetary landers to withstand dry heat sterilization
Weinberg, L.↗
Application of nuclear solid-core rockets to interplanetary orbital launch by multiorbit injection
Nuclear solid core rocket engine performance for interplanetary orbital launch of spacecraft by multiorbit injection
Funk, J.↗
Design, fabrication, and test of omnidirectional flexible seals for thrust vector control of large solid rocket motors Final report
Omnidirectional flexible, rubber-steel seal design, fabrication, and performance testing for solid propellant rocket engine thrust vector control
Wong, E. Y.↗
Design criteria monograph for pressurized metal cases
Organiation and presentation of data pertaining to design of solid propellant rocket engine cases are discussed. Design criteria are presented in form of monograph based on accumulated experience and knowledge. Improvements in reliability, cost effectiveness, and engine efficiency are stressed.
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Study of solid rocket motor for a space shuttle booster. Appendix A: SRM water entry loads
An analysis of the water entry loads imposed on the reusable solid propellant rocket engine of the space shuttle following parachute descent is presented. The cases discussed are vertical motion, horizontal motion, and motion after penetration. Mathematical models, diagrams, and charts are included to support the theoretical considerations.
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Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary
The factors affecting the choice of the 156 inch diameter, parallel burn, solid propellant rocket engine for use with the space shuttle booster are presented. Primary considerations leading to the selection are: (1) low booster vehicle cost, (2) the largest proven transportable system, (3) a demonstrated design, (4) recovery/reuse is feasible, (5) abort can be easily accomplished, and (6) ecological effects are minor.
Vonderesch, A. H.↗
Study of solid rocket motors for a space shuttle booster. Volume 2, book 1: Analysis and design
An analysis of the factors which determined the selection of the solid rocket propellant engines for the space shuttle booster is presented. The 156 inch diameter, parallel burn engine was selected because of its transportability, cost effectiveness, and reliability. Other factors which caused favorable consideration are: (1) recovery and reuse are feasible and offer substantial cost savings, (2) abort can be easily accomplished. and (3) ecological effects are acceptable.
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Study of solid rocket motors for a space shuttle booster. Volume 2, book 3: Cost estimating data
Cost estimating data for the 156 inch diameter, parallel burn solid rocket propellant engine selected for the space shuttle booster are presented. The costing aspects on the baseline motor are initially considered. From the baseline, sufficient data is obtained to provide cost estimates of alternate approaches.
Vanderesch, A. H.↗
Study of solid rocket motors for a space shuttle booster. Volume 2, book 3, addendum 1: Cost estimating data
A second iteration of the program baseline configuration and cost for the solid propellant rocket engines used with the space shuttle booster system is presented. The purpose of the study was to ensure that total program costs were complete and to review areas where costs might be overly conservative and could be reduced. Labor and material were analyzed in more depth, more definition was prepared to separate recurring from nonrecurring costs, and the operations portions of the engine and stage were separated into more identifiable activities.
Vonderesch, A. H.↗
Study of solid rocket motors for a space shuttle booster. Volume 4: Mass properties report
Mass properties data for the 156 inch diameter, parallel burn, solid propellant rocket engine for the space shuttle booster are presented. Design ground rules and assumptions applicable to generation of the mass properties data are described, together with pertinent data sources.
Vonderesch, A. H.↗
Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary
The design, development, production, and launch support analysis for determining the solid propellant rocket engine to be used with the space shuttle are discussed. Specific program objectives considered were: (1) definition of engine designs to satisfy the performance and configuration requirements of the various vehicle/booster concepts, (2) definition of requirements to produce booster stages at rates of 60, 40, 20, and 10 launches per year in a man-rated system, and (3) estimation of costs for the defined SRM booster stages.
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Study of solid rocket motors for a space shuttle booster. Appendix E: Environmental impact statement, solid rocket motor, space shuttle booster
An analysis of the combustion products resulting from the solid propellant rocket engines of the space shuttle booster is presented. Calculation of the degree of pollution indicates that the only potentially harmful pollutants, carbon monoxide and hydrochloric acid, will be too diluted to constitute a hazard. The mass of products ejected during a launch within the troposphere is insignificant in terms of similar materials that enter the atmosphere from other sources. Noise pollution will not exceed that obtained from the Saturn 5 launch vehicle.
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Factors affecting the thermal shock behavior of yttria stabilized hafnia based graphite and tungsten composites.
Hafnia-based composites containing either graphite or tungsten were investigated as rocket nozzle throat inserts in solid propellant rocket engines. The thermal shock resistance of these materials is considered in terms of macroscopic thermal conductivity, thermal expansion, modulus of elasticity, and compressive fracture stress. The effect of degree of hafnia stabilization, density, and graphite or tungsten content upon these parameters is discussed. The variation of the ratio of elastic modulus to compressive fracture stress with density and its effect upon thermal shock resistance of these materials are discussed in detail.
Lineback, L. D.↗
Analysis of advanced programs (Study 2.3). Volume 1: Executive summary
An analysis of advanced programs for space missions is presented. The subjects discussed are (1) alternate space shuttle configurations, (2) space transportation systems, (3) computer programs and methodology to estimate program cost implications of space vehicle program uncertainties, (4) vehicle synthesis program, (5) relative effectiveness of various proposals for space vehicles, and (6) cost analysis of solid propellant rocket engine program to support space shuttle vehicle.
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Study of solid rocket motor for space shuttle booster, volume 2, book 3, appendix A
A systems requirements analysis for the solid propellant rocket engine to be used with the space shuttle was conducted. The systems analysis was developed to define the physical and functional requirements for the systems and subsystems. The operations analysis was performed to identify the requirements of the various launch operations, mission operations, ground operations, and logistic and flight support concepts.
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