A thrust chamber of a liquid-film-cooled orbital attitude control engine

Abstract

The invention discloses a thrust chamber of a liquid film cooling rail attitude control engine. A first propellant chamber is arranged on the outside of the head of the thrust chamber, and a second propellant chamber is arranged on the outside of the body of the thrust chamber and is located outside the middle position; the thrust chamber The shell wall of the head is provided with a plurality of first injection holes communicating with the first propellant chamber; the shell wall of the thrust chamber body is evenly provided with a plurality of combustion injection holes and a plurality of liquid film injection holes along the circumferential direction ; The second propellant is sprayed to the head and throat of the thrust chamber through the combustion injection hole and a plurality of liquid film injection holes, because the liquid film injection is directed towards the throat of the thrust chamber, and the tangential liquid inlet method is adopted , so it can reduce the loss of the liquid film and give full play to the cooling performance of the liquid film; at the same time, the combustion injection hole faces the head of the thrust chamber, and adopts a tangential liquid inlet method, which can exert the cooling performance of the liquid film. The reaction of the first propellant not only reduces the proportion of liquid film to propellant, but also realizes the whole body cooling of the thrust chamber.

Description

technical field [0001] The invention relates to an engine thrust chamber, in particular to a liquid film cooling rail attitude control engine thrust chamber. Background technique [0002] The improvement of the specific impulse performance of the orbit attitude control engine can effectively prolong the working life of the spacecraft or increase the quality of the payload, which can bring very significant economic and military benefits. The main factors restricting the improvement of the specific impulse performance of the orbit attitude control engine are: high-performance injector technology, high-temperature resistant material technology and inefficient use of liquid film. Among them, the inefficient use of liquid film has become the primary restrictive factor leading to the reduction of engine specific impulse. [0003] In traditional orbital attitude control engines, there are two ways of liquid film cooling: [0004] One is that the propellant is sprayed to the wall ...

AI Technical Summary

Problems solved by technology

[0010] In order to solve the problem in the background technology that the proportion of liquid film in the thrust chamber of the existing orbital attitude control engine remains high, resulting in a decrease in the specific impulse performance of the engine, the present invention provides a liquid film cooling orbital attitude control engine thrust chamber

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