Results 201 to 210 of about 2,583,997 (256)

Advanced solid rocket motor

25th Joint Propulsion Conference, 1989
The Advanced Solid Rocket Motor (ASRM), a 150-in diameter segmented motor design that incorporates substantive design changes to improve the reliability and design safety margins of the Space Shuttle system, is discussed. The studies involved in the development of the ASRM are reviewed, and the ASRM design is summarized, including safety enhancement ...
KENNETH JONES, LOWELL ZOLLER
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Solid Propellant Rocket Motors

The Journal of the Royal Aeronautical Society, 1961
A solid propellant rocket motor consists essentially of a propellant charge in a container fitted with an expansion nozzle and igniter. Since, before a rocket motor can be designed, it is necessary to have some knowledge of the properties of the propellant to be used, a description will first be given of the propellants which are currently available.
W. R. Maxwell, G. H. S. Young
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Solid Rocket Motor Optimization

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008
A preliminary design of a solid rocket motor (SRM) is based on a multitude of design parameters (e.g., thrust profile, chamber pressure, burn time, etc.), whose values are difficult to determine initially, necessitating the design modeling and optimization for the specific mission.
Yair Kamm, Alon Gany
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Pulse-Triggered Instability in Solid Rocket Motors

AIAA Journal, 1982
This paper presents the results of a study to assess the ability of a recently developed comprehensive nonlinear combustion instability model to predict pulse-triggered instability in solid rocket motors. Performance models were developed to calculate the mass and energy flow rates produced by three laboratory pulsers (pyro, low brisance, and piston ...
J. BAUM, J. LEVINE, R. LOVINE
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Additional historical solid rocket motor burns

Acta Astronautica, 2006
Abstract The use of orbital solid rocket motors (SRM) is responsible for the release of a high number of slag and Al2O3 dust particles which contribute to the space debris environment. This contribution has been modeled for the ESA space debris model MASTER (Meteoroid and Space Debris Terrestrial Environment Reference).
Carsten Wiedemann, Maren Homeister, Michael Oswald, Sebastian Stabroth, Heiner Klinkrad, Peter Vörsmann   +5 more
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Combustion termination of solid rocket motors

Journal of Spacecraft and Rockets, 1965
To explore the feasibility of terminating combustion without the hazardous flame and debris associated with venting, a series of sixteen 5-in.-diam motors was fired. Two techniques were investigated: 1) injection of liquid into the combustion chamber, and 2) explosive discharge of coolants from a canister located inside the chamber.
H. J. TABACK, E. E. DAY, T. P. BROWNE
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The Advanced Solid Rocket Motor

Space Programs and Technologies Conference, 1992
The paper describes the Advanced Solid Rocket Motor (ASRM) that is being developed to replace, in 1997, the Redesigned Solid Rocket Motor which currently boosts the Space Shuttle. The ASRM will contain features to improve motor safety (fewer potential leak paths, improved seal materials, stronger case material, and fewer nozzle and case joints), an ...
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Analysis of Solid Rocket Motor Materials

2021 IEEE 12th International Conference on Mechanical and Intelligent Manufacturing Technologies (ICMIMT), 2021
The development of solid rocket engine has a long history. However, modern rocket technology and space flight developed until the end of the nineteenth century and the beginning of the twentieth century, and hence the gradual emergence of solid rocket, liquid rocket and hybrid rocket.
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Igniter performance in solid propellant rocket motors

2nd Propulsion Joint Specialist Conference, 1966
1 Robbins, J. H. and Rogers, A. C., Jr., "An analysis on predicting thermal stratification in liquid hydrogen," J. Spacecraft Rockets 3, 40-45 (1966). 2 Boudreaux, R. A., "Boundary layer thermodynamic and hydrodynamic characteristics of a flowing liquid hydrogen tank, with and without internal heat generation," Ph.D dissertation, Univ.
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Solid rocket motor temperature sensitivity

Journal of Propulsion and Power, 1994
The temperature sensitivity of the propellant and the solid rocket motor are described by several different temperature sensitivity coefficients. This enabled the derivation of three different relationships for the temperature sensitivity coefficient pi(sub K).
J. R. Osborn, S. D. Heister
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