Results 11 to 20 of about 838 (233)

Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher [PDF]

Journal of Aerospace Technology and Management, 2022
The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of a turbo-pumped liquid propellant rocket engine. This system is the most complex and expensive in a medium-size launch vehicle, after the engine.
Yurii Mitikov, Olexiy Shynkarenko
doaj   +3 more sources

Comparison of Optimization Techniques and Objective Functions Using Gas Generator and Staged Combustion LPRE Cycles

Applied Sciences, 2022
This paper compares various optimization techniques and objective functions to obtain optimum rocket engine performances. This research proposes a modular optimization framework that provides an optimum design for Gas Generator (GG) and Staged Combustion
Suniya Sadullah Khan, Ihtzaz Qamar, Muhammad Umer Sohail, Raees Fida Swati, Muhammad Azeem Ahmad, Saad Riffat Qureshi   +5 more
doaj   +1 more source

The concept of reducing the man-made impact of launches of the promising Irtysh launch vehicle in the impact areas of the Baikonur cosmodrome [PDF]

Омский научный вестник: Серия "Авиационно-ракетное и энергетическое машиностроение", 2019
Scientific and methodological approaches to minimizing the man-made impact of launches of promising carrier rockets of the «Irtysh» type by oxygen-kerosene main liquid-propellant rocket engines of the Baiterek rocket complex in areas of falling of the ...
B. T. Suimenbayev, V. I. Trushlyakov, G. T. Yermoldina, Zh. B. Suimenbayeva, A. M. Bapyshev   +4 more
doaj   +1 more source

Multi-Scenario Trajectory Optimization for Vertical Takeoff and Vertical Landing Vehicles Using the Gauss Pseudospectral Method

Aerospace, 2022
Vertical takeoff and vertical landing (VTVL) vehicles, based on throttling liquid rocket engines, are attracting increasing attention for their validation of guidance and control techniques during landing.
Yang Liu, Chenyang Li, Xiongfeng Zhu, Qiulong Han, Peng Cui, Dongdong Zhang   +5 more
doaj   +1 more source

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Aerospace, 2023
To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber,
Bo Xu, Bing Chen, Jian Peng, Wenyuan Zhou, Xu Xu   +4 more
doaj   +1 more source

Influence of surface roughness on the heat transfer coefficient of fluids in an additively manufactured supercharger

Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2022
The supercharger is intended for heating a fluid (gaseous helium or gaseous nitrogen) used for the pressurization of fuel tanks of oxidizer and propellant of a rocket engine. The fluid is heated with the generator gas downstream the turbine.
A. S. Smekalkin, A. V. Ivanov
doaj   +1 more source

Dynamic interaction between clustered liquid propellant rocket engines under their asynchronous start-ups

Propulsion and Power Research, 2021
A nonlinear mathematical model of the low-frequency dynamics of the clustered multi-engine rocket propulsion system has been developed and the computations of the engine transient processes during the start-ups of the four-engine propulsion system with a
Sergey I. Dolgopolov, Olexiy D. Nikolayev, Nataliia V. Khoriak   +2 more
doaj   +1 more source

Research Progress of Decommissioned Solid Rocket Motor Charge Emptying and Recycling Technology [PDF]

Hangkong bingqi
As the service life of solid rocket engines comes to an end, their operational reliability and performance stability gradually decline. Effectively disposing of large numbers of retired solid rocket engines has become a critical issue.
Zhou Yaping, Lin Zhihui, Wang Maoyu, Dong Jun, Liu Tiansheng, Qiao Haitao
doaj   +1 more source

Analysis of a Stator-Rotor-Stator Spinning Disk Reactor in Single-Phase and Two-Phase Boiling Conditions Using a Thermo-Fluid Flow Network and CFD

Fluids, 2022
Cryogenic liquid propellants are used in liquid rocket engines to obtain high specific impulse. The flow rates are controlled by turbopumps that deliver liquid propellant to the engine at high pressure levels.
Lorenzo Mazzei, Francesco Maria Marin, Cosimo Bianchini, Riccardo Da Soghe, Cristina Bertani, Dario Pastrone, Maddalena Angelucci, Giuseppe Caggiano, Michiel de Beer   +8 more
doaj   +1 more source

Limits of Fluid Modeling for High Pressure Flow Simulations

Aerospace, 2022
Flows in liquid propellant rocket engines (LRE) are characterized by high pressures and extreme temperature ranges, resulting in complex fluid behavior that requires elaborate thermo-physical models.
Nelson P. Longmire, Daniel T. Banuti
doaj   +1 more source