Materials for Solid Rocket Engines

The internal structure of heavy-calibre rocket engines, as used in army ordnance, is a multi-interface bonding structure. The bonding quality between layers has an important impact on safety when shooting, so it must be tested before use in the field. In this paper, the progress of research into ultrasonic testing (UT) technology for the interface bonding of solid rocket motors is reviewed from the two aspects of testing methods and signal processing technology. Future work is also discussed.

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Reliability evaluation of large solid rocket engines during engineering development

Planetary and Space Science ◽

10.1016/0032-0633(61)90302-6 ◽

1961 ◽

Vol 7 ◽

pp. 217-229

Author(s):

M. Lipow ◽

D.K. Lloyd

Keyword(s):

Reliability Evaluation ◽

Rocket Engines ◽

Engineering Development ◽

Solid Rocket

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Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

Open Chemistry ◽

10.1515/chem-2020-0182 ◽

2020 ◽

Vol 18 (1) ◽

pp. 1452-1467

Author(s):

Javier Carlos Quagliano Amado ◽

Pablo Germán Ross ◽

Natália Beck Sanches ◽

Juliano Ribeiro Aguiar Pinto ◽

Jorge Carlos Narciso Dutra

Keyword(s):

High Performance ◽

Short Review ◽

Rocket Engines ◽

Solid Rocket Motor ◽

Composite Propellant ◽

Rocket Motors ◽

Polyhedral Oligosilsesquioxane ◽

Combustion Gases ◽

Solid Rocket ◽

Heat Shielding

AbstractThis review addresses a comparison, based on the literature, among nitrile rubber (NBR), ethylene-propylene-diene-monomer rubber (EPDM), and polyurethane (PU) elastomeric heat shielding materials (EHSM). Currently, these are utilized for the insulation of rocket engines to prevent catastrophic breakdown if combustion gases from propellant reaches the motor case. The objective of this review is to evaluate the performance of PU–EHSM, NBR–EHSM, and EPDM–EHSM as insulators, the latter being the current state of the art in solid rocket motor (SRM) internal insulation. From our review, PU–EHSM emerged as an alternative to EPDM–EHSM because of their easier processability and compatibility with composite propellant. With the appropriate reinforcement and concentration in the rubber, they could replace EPDM in certain applications such as rocket motors filled with composite propellant. A critical assessment and future trends are included. Rubber composites novelties as EHSM employs specialty fillers, such as carbon nanotubes, graphene, polyhedral oligosilsesquioxane (POSS), nanofibers, nanoparticles, and high-performance engineering polymers such as polyetherimide and polyphosphazenes.

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Transient Induced Delay in the Check Injector of the ADDA Combined Rocket Motor

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.436.3 ◽

2013 ◽

Vol 436 ◽

pp. 3-9

Author(s):

Radu Dan Rugescu ◽

Gabriel Calcisca ◽

Dragos Ronald Rugescu

Keyword(s):

Check Valve ◽

Transient Behavior ◽

Fast Response ◽

Surface Finishing ◽

Rocket Engines ◽

Line System ◽

Rocket Motors ◽

Basic Parameters ◽

Efficient Alternative ◽

Solid Rocket

Conceived as simple, cheap and highly efficient alternative to solid rocket motors, the compound rocket engines include a liquid feed line system, within which at least the minimal components are involved, like the liquid tank, the dislocation augmenter, the main release valve, the in-line check valve (ICV) and the injector head. Simplicity and reliability are the main requirements in designing and manufacturing the components and, in order to accomplish these requirements, the dynamics and transient behavior of the devices become the key features of the entire design. The transient of the ICV required primary attention as it needs to cut the reversed flow of the liquid in a definitely short amount of time, determined from the condition of a given liquid return delay stop into the internal feed duct (IFD) of the engine. This delay was also set to cover the condition of partial vaporization of the liquid within the ICV and the IFD of the system. Numerical simulations were performed under rational assumptions regarding the mechanical behavior of ICV parts, limited to a number of minimal elements that secure a smooth work of the device and a fast response to upwind and downwind liquid pressure variations. The basic parameters considered are the size of the parts, their densities, closely connected to the manufacturing materials involved, sealing and surface finishing technology used that outputs the viscous and friction properties of the device parts considered for simulation. The ORVEAL research is granted by Romanian UEFISCDI.

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Intricacy of the Transit Manifold Concept Paid-off by Computational Accuracy

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.325-326.142 ◽

2013 ◽

Vol 325-326 ◽

pp. 142-147

Author(s):

Radu D. Rugescu ◽

Alina Bogoi ◽

Radu Cirligeanu

Keyword(s):

Power Plants ◽

Cfd Simulation ◽

Green Energy ◽

Rocket Engines ◽

Computational Accuracy ◽

Thrust Chamber ◽

Isentropic Flow ◽

Unsteady Simulation ◽

Isentropic Flows ◽

Solid Rocket

Despite its intricacy the numerical method applied within the TRANSIT code proved successful in describing discontinuous, non-isentropic flows in rocket engines and solar-gravitational towers for green energy. A number of 0-D approaches are known to render some results in demonstrating the feasibility of the solar tower concept, or in unsteady simulation of transient phases in rocket engines. Computational efficiency is demonstrated by CFD simulation of the starting transients in ADDA solid rocket engines and in the SEATTLER solar mirror tower. The code is exclusively directed to unsteady flow simulations in slender channels. The wave front model scheme covers the dual behavior of fully non-isentropic flow with mass addition and mixing in the thrust chamber or blunt heat addition in a heater and fully isentropic through the exhaust nozzle or gravity draught in a tall tower. Along the tower of the solar-gravity draught power plants small perturbation discontinuous flows are covered. Code robustness is demonstrated during runs on the PC.

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