A dual-channel centrifugal injector structure for a variable-thrust solid-liquid rocket engine

Abstract

The invention discloses a variable thrust solid-liquid rocket engine two-way centrifugal injector structure. The structure includes a spray cap, a liquid separator, a nozzle and a shell. When injected into a primary channel, an oxidizing agent vertically enters a liquid accumulation chamber at the lower end of the spray cap from the spray cap, is divided into three parts to pass through the liquid separator, and is sprayed into a cyclone chamber in the internally tangent direction of the nozzle; when injected into a secondary channel, the oxidizing agent obliquely enters a liquid accumulation chamber in the middle of the liquid separator from the spray cap and is divided into three parts to be sprayed into the cyclone chamber in the internally tangent direction of the liquid separator; the cyclone chamber is formed by being surrounded by the liquid separator and the nozzle; Under the condition of the large flow rate, the oxidizing agent is injected into the primary channel and the secondary channel at the same time, under the condition of the small flow rate, the oxidizing agent is only injected into the primary channel, and high efficiency combustion under the condition of the large flow regulating ratio is thus achieved. The structure is used for spaying and atomization of the variable thrust solid-liquid rocket engine oxidizing agent, and under the condition of the large flow regulating ratio, the combustion efficiency is higher.

Description

Technical field [0001] The invention belongs to the field of solid-liquid rocket engines, and particularly relates to a double-path centrifugal injector structure of a variable-thrust solid-liquid rocket engine. Background technique [0002] Rocket engines with thrust control capabilities have technical advantages in many situations of space transportation and space maneuvering, and can achieve the best thrust control, thereby maximizing the carrying capacity. [0003] The active phase of manned spaceflight uses variable thrust engines for propulsion, which can strictly control the overload of astronauts and ensure the safety of astronauts; for spacecraft rendezvous and docking and orbital maneuvers, variable thrust engines can improve the flexibility of control and control. If the missile system uses variable thrust engines for propulsion, the maneuverability of the missile's flight trajectory can be improved, thereby enhancing the penetration capability of the missile weapon. In...

AI Technical Summary

Problems solved by technology

In the process of large-scale thrust adjustment of the variable thrust solid-liquid rocket engine, the oxidant flow rate of the engine changes greatly, and it is difficult to ensure the injection pressure drop and engine performance during the entire working process by using conventional injectors

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