Results 1 to 10 of about 11,111 (215)
The transfer functions of rocket nozzles [PDF]
Journal of the American Rocket Society, 1952 The transfer function is defined as the fractional oscillating mass flow rate divided by the fractional sinusoidal pressure oscillation in the rocket combustion chamber. This is calculated as a function of the frequency of oscillation.
Tsien, H. S.
core +4 more sources
Effect of Nozzle Contour on Flow Separation in Overexpanded Rocket Nozzles
TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B, 2005 In the present paper, parametric numerical analyses of the separated transonic flows in overexpanded rocket nozzles are conducted. Several types of nozzles are examined numerically to clarify the detailed mechanisms of the occurrence of restricted shock separation (RSS) in compressed truncated perfect (CTP) nozzles.
Yoshinobu Tsujimoto +4 more
openaire +7 more sources
Inverse Design of Highly Deformable Mechanical Metamaterial Based on Partitional Semi-Random Optimization. [PDF]
Adv Sci (Weinh)This research presents a novel optimization method for the inverse design of flexible mechanical metamaterials, enhancing traditional strategies by evaluating deformation in subregions. Combining simulated annealing with a genetic algorithm, it improves design efficiency and enables customizable deformation paths.
Cao X, Zhao Z, Wang P, Duan S, Lei H.
europepmc +2 more sources
Effect of High-Mass Fraction of Aluminum on Catalytic Hybrid Rocket Motor
Applied Sciences, 2022 Catalytic hybrid rocket motors using hydrogen peroxide (HP) are easy and efficient to achieve multiple starts and stops, and hydroxyl-terminated polybutadiene (HTPB) grains are commonly used due to their excellent mechanical properties.
Hui Tian +5 more
doaj +1 more source
International Journal of Aerospace Engineering, 2022 Multi-interface is a typical feature of solid rocket motor nozzles, and the interface evolution law is an important aspect to analyze the thermo-structural response of solid rocket motor nozzles.
Lin Sun +4 more
doaj +1 more source
Film Cooling in Rocket Nozzles [PDF]
, 2020 Abstract In this project supersonic, tangential film cooling in the expansion part of a nozzle with rocket-engine like hot gas conditions was investigated. Therefore, a parametric study in a conical nozzle was conducted revealing the most important influencing parameter on film cooling for the presented setup.
Ludescher, Sandra Christine +1 more
openaire +3 more sources
Design and analysis of rocket nozzle
Materials Today: Proceedings, 2021 Abstract This paper is about the design and analysis of two different rocket nozzle configurations. First configuration is without any fillets and curved surfaces and second configuration is with fillets and curved surfaces. Second configuration is used since stress concentration will be more at the corners if we don’t have an optimized geometry ...
Bhaskara Rao Lokavarapu, R. Harikrishnan
openaire +2 more sources
Impacts of Micro-Deviations of Aperture on the Characteristics of Collision Atomization Field
Applied Sciences, 2022 As the final flow channel of the liquid rocket engine, the manufacturing of impinging atomization nozzles has become a critical link in the manufacture of impinging atomization components. At present, the high-precision machining of millimeter nozzles in
Yarui Ma +3 more
doaj +1 more source
Ablation performance of 3D C/SiC composite nozzles under double-component liquid power environment
Cailiao gongcheng, 2022 In order to explore the ablation characteristics of C/SiC ceramic composite nozzles in the working environment of liquid rocket engines, 3D C/SiC composite nozzle was prepared by the precursor impregnation pyrolysis(PIP) process, and the ablation test of
BAI Longteng +4 more
doaj +1 more source
Propulsion tests on ultra-high-temperature ceramic matrix composites for reusable rocket nozzles
Journal of Advanced Ceramics, 2023 Ultra-high-temperature ceramic matrix composites (UHTCMCs) based on a ZrB2/SiC matrix have been investigated for the fabrication of reusable nozzles for propulsion.
Diletta Sciti +8 more
doaj +1 more source