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

A solid-liquid rocket and engine technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as low combustion efficiency, poor mixing degree of oxidant and fuel, and low burning rate of solid fuel grains, and achieves improved Combustion efficiency, improvement of combustion efficiency, and high loading rate

Active Publication Date: 2017-06-20
BEIHANG UNIV
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  • Abstract
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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-liq

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

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[0019] The present invention will be further described in detail below with reference to the drawings and embodiments.

[0020] The invention is a double-hole-shaped segmented rotating charge solid-liquid rocket engine thrust chamber, such as figure 1 , figure 2 As shown, the front combustion chamber assembly 1, the front solid fuel grain 2, the intermediate cavity assembly 3, the rear solid fuel grain 4, the after combustion chamber assembly 5, the nozzle assembly 6, and the combustion chamber shell 7.

[0021] The solid fuel grains are filled into the engine combustion chamber shell, and the outer wall surface of the intermediate cavity and the inner wall surface of the engine combustion chamber shell are matched by bonding. The engine nozzle assembly, the after-combustion chamber assembly and the rear end of the combustion chamber shell are connected by long bolts, and an O-ring seal is used to ensure airtightness.

[0022] The front-stage solid fuel grain 2 and the rear-stage so...

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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...

Claims

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Application Information

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IPC IPC(8): F02K9/72
CPCF02K9/72
Inventor 田辉朱浩何凌飞张源俊于瑞鹏
Owner BEIHANG UNIV
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