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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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Computer program contains mathematical model which provides relationship between engine gas dynamics and combustion processes. Mathematically simulated explosions initiate gas disturbances. Design methods for damping disturbances can be studied to prevent future engine shutdown or destruction.
User manual for computer programs to determine high frequency instability in baffled annular liquid propellant rocket engines - Vol. 2
High frequency nonlinear combustion instability in baffled annular liquid propellant rocket engines - Vol. 1
Payload/spent rocket engine case separation system
Comparison of solid propellant nozzle heat transfer coefficients with predicted data
Omnidirectional flexible, rubber-steel seal design, fabrication, and performance testing for solid propellant rocket engine thrust vector control
Analysis of chemical, physical, and mechanical problems imposed by heat sterilization for demonstration of sterilizable rocket engine system
Design approach for solid propellant rocket igniters
Mathematical models of nonlinear combustion instabilities in liquid propellant rocket engine
Closed loop servosystem for variable speed tape recorders on board spacecraft
Evaluation of selected low-cost ablative materials for large solid rocket engine nozzle design
Solid propellant engine structural analysis, examining transient thermal loading and internal pressure effects
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A parametric study of ballistic modifications to the 120 inch diameter solid propellant rocket engine which forms part of the Air Force Titan 3 system is presented. 576 separate designs were defined and 24 were selected for detailed analysis. Detailed design descriptions, ballistic performance, and mass property data were prepared for each design. It was determined that a relatively simple change in design parameters could provide a wide range of solid propellant rocket engine ballistic characteristics for future launch vehicle applications.
For abstract, see N72-14799.
Current design practices are reviewed and assessed, and guidance is established for achieving greater consistency in design, reliability in the end product, and efficiency in the design effort. The total problem is discussed, and design elements involved in successful design are identified. Design criteria are described, and the rule, guide, limitation, or standard which must be imposed on each essential design element is given. Recommended practices are presented for satisfying each of the criteria.
Technical emphasis was placed on characterization of a scaled-up batch of the improved propellant formulation and determination of the effects of dry heat sterilization on propellant integrity and structural response. The grain stress analysis was directed toward tailoring a fully-bonded grain to the calculated propellant allowable stresses and investigating various bond release concepts to relieve stresses incurred in thermal shrinkage following sterilization.