Results 221 to 230 of about 13,247 (287)

Optimal design of solid rocket motor nozzle under two-phase flow

Xinhui Tian, Zhensheng Sun, Z.Q. Zhang, Yin Zhang, Zhi‐Hui Zhang, Liangwei Fu   +5 more
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Annular rocket motor and nozzle configuration Patent

, 1962
John F. Connors
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Development of a Reusable Aerospike Nozzle for Hybrid Rocket Motors

, 2009
Patrick Lemieux
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Advanced Rocket Nozzles

Journal of Propulsion and Power, 1998
Several nozzle concepts that promise a gain in performance over existing conventional nozzles are discussed in this paper. It is shown that signie cant performance gains result from the adaptation of the exhaust e ow to the ambient pressure. Special attention is then given to altitude-adaptive nozzle concepts, which have recently received new interest ...
Hagemann, G., Immich, H., Nguyen, T. van, Dumnov, G.   +3 more
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Scaling of Rocket Nozzle Admittances

AIAA Journal, 1974
To apply the admittance data measured experimentally for small-scale nozzles, the necessary scaling criteria must be established. The results of an investigation undertaken to determine these criteria are presented and the data indicate that under cold-flow conditions the damping of axial instabilities provided by full-scale nozzles can be determined ...
B. JANARDAN, B. DANIEL, B. ZINN
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Multiphase Effects on Solid Rocket Nozzle Performance

Journal of Propulsion and Power, 2023
In the present work, we discuss the employment of a computational fluid dynamics approach to evaluate the specific impulse of solid rocket motors. Particular care is focused on two-phase flow and divergence losses, which represent the most important contributions to the overall nozzle performance loss.
Marco Grossi, Alessio Sereno, Daniele Bianchi, Bernardo Favini   +3 more
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Flow phenomena in advanced rocket nozzles - The plug nozzle

34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
In recent years, plug nozzles have gained a renewed interest in space business. In principle, this nozzle concept offers a continuous altitude adaptation up to its design pressure ratio. But, the flow adaptation achieved with this advanced rocket nozzle concept induces shocks and expansion waves resulting in exit profiles far away from idealized one ...
Hagemann, G., Immich, H., Terhardt, M.
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FREE VIBRATIONS OF ROCKET NOZZLES

Symposium on Structural Dynamics and Aeroelasticity, 1965
Fig. 4 Flowfield of a parallel flow nozzle exhausting normal to a concave surface in a vacuum (h/re = 10, RJh = 1.1, R = 60 ft/°R, Me = 4.0, 6e = 0°, 7 = 1.2, Bs = 1.0). 2 Roberts, L., "The action of a hypersonic jet on a dust layer/' IAS Paper 63-50 (1963). 3 Van Dyke, M. and Gordon, H. D., "Supersonic flow past a family of blunt axisymmetric bodies,"
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High-Performance Rocket Nozzle Concept

Journal of Propulsion and Power, 2010
An innovative technical solution that overcomes the limitation induced by flow separation phenomena and allows increasing the vacuum-specific impulse of a main stage rocket engine is presented. After reviewing the open technical literature on flow separation and advance nozzles design, the newly proposed concept is extensively presented.
Luca Boccaletto, Jean-Paul Dussauge
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