A Space Bicomponent Orbit Control Engine Based on Two-way Single-Nozzle Centrifugal Injector

Abstract

The invention discloses a space bipropellant orbit-control engine based on a two-way single-nozzle centrifugal injector. The space bipropellant orbit-control engine is suitable for meeting the task requirements of orbital maneuver, orbital transfer and the like of aerospace crafts. The space bipropellant orbit-control engine comprises a mounting connection plate, a heating device, a control valve,screws, a body structure, an inner nozzle, an outer nozzle, a temperature measuring sensor, a combustion chamber and a jet pipe. After the control valve is started, the two propellants of an oxidizing agent and a combustion agent enter a swirling cavity of the outer nozzle and a swirling cavity of the inner nozzle of the centrifugal injector correspondingly to rotate at a high speed, rotational flow fog cones are formed on the nozzles and are further atomized and sprayed out according to a certain mass flow proportion, the two propellants are mixed for combusting in the combustion chamber coated with a high-temperature resistant and oxidation resistant coating, high-temperature fuel gas is formed ultimately and is further expanded and accelerated in the Laval jet pipe and accordingly thrust is formed.

Description

technical field [0001] The invention relates to a space dual-component orbit control engine based on a dual-channel single-nozzle centrifugal injector and a molybdenum silicide composite coating thrust chamber, which is suitable for mission requirements such as orbital maneuvering and orbital transfer of aerospace vehicles. Background technique [0002] The two-way single-nozzle centrifugal engine adopts a nested structure of two-way centrifugal nozzles to realize the injection of oxygen and fuel two-way propellant. Through the pressure drop potential energy and swirl effect, the propellant is ejected in a high-speed rotating jet state. Under the disturbance of internal and external forces, part of the droplets are atomized and evaporated to participate in the spontaneous combustion reaction. [0003] The space orbit control engine based on the centrifugal single-nozzle injection scheme has the characteristics of high performance, long life, good combustion stability and rep...

AI Technical Summary

Problems solved by technology

[0004] However, unlike high-chamber pressure engines, the space propulsion system can provide limited working pressure, and it is difficult to improve the injection effect of the nozzle under low pressure drop

Especially for centrifugal engines, under the condition of low pressure drop, it is difficult to obtain ideal injection speed and angle, which affects the quality of atomization

[0005] In addition, the injection form of the centrifugal injector and the design state of the combustion chamber will have a crucial impact on combustion and cooling, and there is a serious coupling relationship

If the atomization and mixing are insufficient, the performance of the engine will be greatly reduced. If the combustion temperature distribution is unreasonable or the cooling is insufficient, it will lead to local high temperature in the combustion chamber, which will affect the working life.

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