High performance Earth Storable Rocket Engine

1995 ◽  
Author(s):  
John Campbell ◽  
Joseph Riccio
Keyword(s):  
High Performance ◽  
Rocket Engine

A study into the feasibility of using the oxygen-hydrocarbon engine 11D58M as a basis for development of a high-performance multifunctional gas-generatorless rocket engine with oxygen cooling

2019 ◽  
pp. 67-80
Author(s):  
Boris A. Sokolov ◽  
Nikolay N. Tupitsyn
Keyword(s):  
Film Cooling ◽  
High Performance ◽  
Rocket Engine ◽  
Hydrocarbon Fuel ◽  
Gas Generator ◽  
Automatic Equipment ◽  
The Us ◽  
Upper Stage ◽  
Pump Assembly ◽  
Turbo Pump

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.

Characterization of Rotating Cavitation in a High Speed Inducer of Liquid Rocket Engine

2011 ◽  
Vol 320 ◽  
pp. 196-201
Author(s):  
Fei Tang ◽  
Li Jia Wen
Keyword(s):  
High Speed ◽  
High Performance ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Blade Surface ◽  
Cavitation Phenomenon ◽  
Flow Fluctuations ◽  
Blade Cascade ◽  
Liquid Rocket

Rotating cavitation is one of the most important problems in the development of modern high performance rocket pump inducers. In this paper, a numerical simulation of rotating cavitation phenomenon in a 2D blade cascade of liquid rocket engine inducer was carried out using a mixture model based on Rayleigh-Plesset equation. The purpose is to investigate the characterization of rotating cavitation in a high speed inducer. The results show that when sub-synchronous rotating cavitation occurs, the speed for the length of the blade surface cavitation is lower than the speed frequency of rotation shaft with the same direction. The external aspect is that the pressure at the upstream of blades changes synchronous. Thus, the generation of sub-synchronous rotating cavitation is closely related to the changes of flow angel which caused by the flow fluctuations. Hence, elimination of the flow rate redistribution among the flow channel can effectively suppress the occurrence of this phenomenon.

scholarly journals Development of improved performance electromagnetic valve for liquid rocket engine

2020 ◽  
Vol 19 (4) ◽  
pp. 30-42
Author(s):  
A. A. Igolkin ◽  
T. A. Chubenko ◽  
A. D. Maksimov
Keyword(s):  
Magnetic Induction ◽  
High Performance ◽  
Rocket Engine ◽  
Mathematic Model ◽  
Liquid Rocket Engine ◽  
Electromagnetic Valve ◽  
Magnetic Induction Distribution ◽  
Improved Performance ◽  
Liquid Rocket ◽  
Distribution Field

The problem of developing optimal-design electromagnetic valves is relevant for many industries. The development of technology is characterized by increased power and pressures used for actuator mechanisms, as well as by reducing the dimensions and mass of automatic units. The goal of this article is to develop an advanced electromagnetic valve that would ensure optimal combination of high performance, reliability, technological effectiveness and minimal cost. On the basis of standard dependences for electromagnetic phenomena a mathematic model of a SU.1 valve was developed. It was calculated in several special-purpose software packages: NISA, FEMM, ANSYS Maxwell. Parametric analysis was implemented in ANSYS Maxwell for variable working gap settings and values of current force in the solenoid. As a result, the magnetic induction distribution field was obtained. The results of modeling the operation of the electromagnetic valve and the magnetic induction distribution field are presented for variable working gap settings and different values of current force in the solenoid. The model of an advanced electromagnetic valve for a liquid rocket engine was developed on the basis of the dependences obtained. The duration of single engine firing obtained is 40 msec. The results obtained make it possible to create a valve with hold-open time of 800msec, which is considered sufficient for application in electromagnetic direct current valves.

Fuzzy Damage Mitigating Control of Mechanical Structures

1998 ◽  
Vol 120 (2) ◽  
pp. 249-256 ◽  
Author(s):  
M. S. Holmes ◽  
Asok Ray
Keyword(s):  
Control System ◽  
High Performance ◽  
Rocket Engine ◽  
Reference Trajectory ◽  
Sampled Data ◽  
Simulation Experiments ◽  
Trade Off ◽  
Synthesis Procedure ◽  
Critical Components ◽  
Data Controller

This paper presents the architecture and synthesis of a damage mitigating control system for mechanical structures where the objective is to achieve high performance with increased reliability, availability, component durability, and maintainability. The proposed control system has a two-tier structure. In the lower tier a linear sampled-data controller tracks a reference trajectory vector while the upper tier contains a fuzzy-logic-based damage controller which makes a trade-off between system performance and the damage in critical components. The synthesis procedure is demonstrated by simulation experiments on the model of a reusable rocket engine. The simulation results explore the feasibility of automatically regulating the damage/performance trade-off in a real-time setting.

A high performance liquid rocket engine for satellite main propulsion

2000 ◽  
Author(s):  
Carl Stechman ◽  
Peter Woll ◽  
Raymond Fuller ◽  
Anthony Colette
Keyword(s):  
High Performance ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Liquid Rocket

scholarly journals Progress in Fabrication of Silicon Nitride Structural Components for Turbomachinery Applications

1996 ◽  
Author(s):  
John P. Pollinger
Keyword(s):  
Silicon Nitride ◽  
High Performance ◽  
Rocket Engine ◽  
Ceramic Materials ◽  
Department Of Energy ◽  
Structural Components ◽  
Technology Program ◽  
Ceramic Components ◽  
Nozzle Blade

The development and refinement of high performance silicon nitride structural ceramic materials over the last five years is leading to evaluation and implementation of components in aircraft, space, industrial, and automotive turbomachinery applications. Current material properties, status of component fabrication technologies, and status of applications being evaluated and commercialized at AlliedSignal Ceramic Components is discussed. Currently achievable properties of in-situ reinforced monolithic silicon nitride materials are presented. The development and status of component forming processes is also discussed, including their potential as manufacturing processes. The processes discussed include slipcasting, green machining, gelcasting, and injection molding. Finally, status of silicon nitride component fabrication and evaluation in a number of applications is discussed, including nozzle, blade, and wheel components for the U.S. Department of Energy (DOE) automotive turbine technology programs, the DOE Advanced Turbine Systems industrial turbine technology program, and a NASA-funded program to develop advanced rocket engine turbopumps.

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