Proposals justification to combined rocket engines application as a part of aerospace system
- Paper number
IAC-08.C4.5.7
- Author
Dr. Olexiy Shynkarenko, Dniepropetrovsk National University, Ukraine
- Coauthor
Dr. Valeriy Buchars'kyy, Dniepropetrovsk National University, Ukraine
- Coauthor
Prof. Olexandr Petrenko, Dniepropetrovsk National University, Ukraine
- Coauthor
Prof. Olexiy Sichevoy, Dniepropetrovsk National University, Ukraine
- Year
2008
- Abstract
Last years the economic aspect of space launches has essentially amplified - ascent cost of 1kg payload into an orbit becomes a defining criterion for the launch system selection. Thereupon in Ukraine the national aerospace system (ASS) creation problem is actual both from an economy position, and from the point of national prestige view. In this work the formulation and a justification proposals of different type engines (rocket, propulsion jet and other drives) as a part of aerospace system for launch, acceleration and returning from an orbit of the aerospace plane are conducted. The given paper is logical prolongation of previous researches in numerical modeling of processes in rocket engines. Obviously, the problem of the propulsion system creation with indicated requirements is one of the central problems of ASS creation. Redundancies of classical engines (working on liquid or solid fuel) are practically exhausted now; therefore actual is use of new design approaches. In the presented work of preliminary studies the perspective approach to a question of an increasing propulsion system efficiency using ASS is conducted - air oxygen usage as an additional oxidizer for giving an additional impulse to the second stage of rocket. It means using of a new propulsion system - a combined rocket engine (CRE). Altitudes reached by ASS comparison that uses various engine types conducted the estimation of ASS engine configurations efficiency. The mathematical model was constructed for processes simulation in CRE; it allows receiving a stationary distribution picture of parameters in engine’s internal area. There is a capability of random shape of axisymmetrical engine calculation with central body of any shape. Design technique of CRE was built using method of numerical modeling. The received distribution of the traction increase has given the chance to evaluate approximately an increase of a total traction impulse for flight time. As a result of the theoretical research it is possible to make a conclusion that using of air oxygen in CRE increases drive efficiency. Heightening of the engine efficiency occurs not only by atmospheric air ejection, but also by afterburning of rocket engine’s combustion products. Potentially, the last presumes can give the ability to reduce an oxidizer-to-fuel ratio in LRE and, thereby, to increase its resource and reliability. The received results approve advantages for using CRE as accelerating drives for a first stage of rocket.
- Abstract document
- Manuscript document
IAC-08.C4.5.7.pdf (🔒 authorized access only).
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