Acoustic Analysis of Solid Rocket Motor Cavities by a Finite Element Method
Adaptation of NASTRAN program to solve acoustic mode problems of solid rocket motor cavities by finite element method
Herting, D. N.↗
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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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Evaluation of SNAP-8 liquid NaK pump-motor (NaK PMA) following vibration and shock testing
Vibration and shock testing of SNAP 8 liquid NaK pump motor assembly
Nelson, R. B.↗
Low-cost molded plastic sounding rocket motors
Sounding rockets motors with integrally molded plastic case and nozzle, discussing cost effectiveness and demonstration tests
Ward, J. C., Jr.↗
Base thermal environment of the Delta launch vehicle with six strap-on solid propellant motors
In-flight base heating and thermal environment measurements from Thor Delta launch vehicle using six strap-on solid propellant motors
Greenwald, G. F.↗
Formulating propellants for fully case-bonded end-burning motors
Low modulus solid propellants family for low thrust-to-mass ratio fully case bonded end-burning motors, using polymer network theory for binder formulation
Marsh, H. E., Jr.↗
Research on combustion instability and application to solid propellant rocket motors
Combustion instability with wave motion coupling in solid propellant rocket motors due to energy gain and loss mechanisms within chamber
Culick, F. E. C.↗
Motor starting techniques for the 2-to-15 kW Brayton space power system
Motor starting techniques for 2-15 kW Brayton space power system with turbine driven radial flow compressor and Lundell type alternator
Cantoni, D. A.↗
Solid-propellant motors for high-incremental velocity low-acceleration maneuvers in space
Low thrust long burning solid rocket propellant motor for orbit insertion maneuvers, discussing design, static tests, nozzle composition, igniter and performance
Shafer, J. I.↗
Stem clutch for motor driven valve
Development of mechanical device to reduce possibility of damage to motor driven needle valve is discussed. Mechanical clutch is employed to allow slippage when needle valve reaches limit of travel. Operation of system for various conditions is described.
Blum, D. E.↗
DC motor proportional control system for orthotic devices
Multi-channel proportional control system for operation of dc motors for use with externally-powered orthotic arm braces is described. Components of circuitry and principles of operation are described. Schematic diagram of control circuit is provided.
Blaise, H. T.↗
Design criteria monograph on solid rocket motor igniters
Summary of large and loosely organized body of existing successful design techniques and practices for solid rocket motor igniters is presented.
Source record↗
Design of a three-phase, 15-kilovolt-ampere static inverter for motor-starting a Brayton space power system
The design of a three-phase, 400-Hz, 15-kVA static inverter for motor-starting the 2- to 15-kWe Brayton electrical space power system is described. The inverter operates from a nominal 56-V dc source to provide a 28-V, rms, quasi-square-wave output. The inverter is capable of supplying a 200-A peak current. Integrated circuitry is used to generate the three-phase, 400-Hz reference signals. Performance data for a drive stage that improves switching speed and provides efficient operation over a range of output current and drive supply voltage are presented. A transformerless, transistor output stage is used.
Frye, R. J.↗
Solid-propellant motors for high-incremental-velocity low-acceleration maneuvers in space
The applicability of solid-propellant rockets into a regime of high-performance long-burning tasks beyond the capability of existing motors is discussed. Successful static test firings have demonstrated the feasibility of: (1) utilizing fully case-bonded end-burning propellant charges without mechanical stress relief; (2) using an all-carbon radiative nozzle markedly lighter than the flight-weight ablative nozzle it replaces, and (3) producing low spacecraft acceleration rates during the thrust transient through a controlled-flow igniter that promotes operation below the previous combustion limit.
Shafer, J. I.↗
Application of the Galerkin Method in the Design of Stable Liquid Rocket Motors
A brief description of results obtained in the continuing investigations is presented. The following areas are covered: (1) the development of the third-order, multimode theory to study the behavior of large amplitude transverse instabilities, (2) nonlinear axial mode instability, and (3) the influence of the functional form of the unsteady combustion response function upon the stability characteristics of rocket motors. Also a study was begun to improve the second order potential theory in order to provide a better approximation to the nozzle boundary condition.
Zinn, B. T.↗
Vacuum stability testing of Apollo 15 Scientific Instrument Module (SIM) non-metallic materials and reversion of silicone rubber in a motor switch
Vacuum stability screening tests were performed on the Apollo 15 Scientific Instrument Module (SIM) bay nonmetallic materials in accordance with the NASA document SP-R-0022. The testing was necessary to support the evaluation to determine the effect material outgassing contamination would have on the SIM bay optical lenses and sensing devices. The Apollo 15 SIM experiments were highly successful, therefore, it is assumed that contamination due to the outgassing of nonmetallic materials did not affect equipment operation. A related problem, the reversion of a silicone rubber grommet which affected an electrical motor switch operation is also reported.
Clancy, H. M.↗
Study of solid rocket motors for a space shuttle booster. Volume 2 book 2: Supporting research and technology
The baseline SRM design for the space shuttle employs proven technology based on actual motor firings. Supporting research and technology are therefore required only to address system technology that is specific to the shuttle requirements, and that is needed for optimization of design features. Eight programs are recommended to meet these requirements.
Vonderesch, A. H.↗
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 3: Program acquisition planning
Plans for conducting Phase C/D for a solid rocket motor booster vehicle are presented. Methods for conducting this program with details of scheduling, testing, and program management and control are included. The requirements of the space shuttle program to deliver a minimum cost/maximum reliability booster vehicle are examined.
Vonderesch, A. H.↗