Double-hole-shaped segmented rotary powder charging solid-liquid rocket engine thrust chamber

Abstract

The invention discloses a scheme of a double-hole-shaped segmented rotary powder charging solid-liquid rocket engine thrust chamber. The double-hole-shaped segmented rotary powder charging solid-liquid rocket engine thrust chamber comprises a front combustion chamber assembly, a front-segment solid fuel grain, a middle cavity assembly, a back-segment solid fuel grain, a back combustion chamber assembly, a spray pipe assembly and a combustion chamber shell body. The fuel grains are the two segments of double-hole-shaped grains which are the same in geometric shape. The two segments of grains are charged by being rotated at the angle of 30-60 degrees. A middle cavity is formed between the two segments of grains and made of ablation-resistant high-silicon oxygen. The outer wall surface of the middle cavity is bonded with the inner wall surface of the combustion chamber shell body of an engine. When the engine works, the two segments of grains are rotationally charged, and thus the strokes of oxidizers and fuel in combustion chamber bodies are prolonged; and meanwhile, the oxidizers and the fuel can be mixed and combusted more sufficiently due to the existence of the middle cavity and the hindering effect of the end surface of the back-segment grain, so that the combustion rate and the combustion efficiency of the solid-liquid rocket engine are effectively improved.

Description

technical field [0001] The invention relates to the technical field of solid-liquid rocket motors, in particular to a thrust chamber of a solid-liquid rocket motor with double-hole-shaped segmented rotary charges. Background technique [0002] Solid-liquid rocket engine is a new type of rocket propulsion system that uses liquid oxidizer and solid fuel as propellant combination. Because the fuel and oxidant of the solid-liquid engine are stored separately, it has unique characteristics different from solid or liquid engines, and has the advantages of good economy, good safety, good environmental protection, and easy thrust adjustment. It is expected to have broad development prospects in the aerospace field, especially in small and medium-sized sounding rockets, suborbital vehicles and high-altitude high-speed cruise vehicles. [0003] However, since the oxidant and fuel of solid-liquid rocket motors are out-of-phase and non-premixed, the combustion in the combustion chamber...

AI Technical Summary

Problems solved by technology

[0003] However, since the oxidant and fuel of solid-liquid rocket motors are out-of-phase and non-premixed, the combustion in the combustion chamber is a typical diffusion combustion process, which causes the solid-liquid rocket motor's solid fuel grain to burn at a relatively high rate. lower disadvantage

Also, combustion is generally less efficient than both liquid and solid rocket motors due to poor mixing of the oxidizer and fuel

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