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Solid-liquid-solid co-combustion chamber combined propulsion rocket engine and aircraft

A rocket engine and combined power technology, applied in the aerospace field, can solve problems such as low packing density and small thrust weight

Active Publication Date: 2021-04-09
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the deficiencies in the prior art, the application provides a solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft to solve the problems of low packing density and small thrust-to-weight ratio of the solid-liquid hybrid rocket engine in the prior art. question

Method used

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  • Solid-liquid-solid co-combustion chamber combined propulsion rocket engine and aircraft
  • Solid-liquid-solid co-combustion chamber combined propulsion rocket engine and aircraft
  • Solid-liquid-solid co-combustion chamber combined propulsion rocket engine and aircraft

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Embodiment 1

[0049] see figure 1 and figure 2 , a solid-liquid-solid co-combustion chamber combined power rocket engine provided in this embodiment, hereinafter referred to as the rocket engine, wherein, the filling density of the combustion chamber 100 in the rocket engine is large, and the solid propellant grain and the solid-liquid fuel are fully utilized The advantage of the grain 121 improves the thrust-to-weight ratio of the rocket engine. Rocket motors can be applied to aircraft to provide long endurance and maneuverability for the aircraft.

[0050] It can be understood that the above-mentioned solid propellant grains can be understood as the first solid propellant grains 122 in this embodiment.

[0051] The rocket engine provided in this embodiment includes a combustion chamber 100. The combustion chamber 100 includes a body 110 and a grain filling chamber 120 disposed on the body 110. The grain filling chamber 120 is used to fill combustible fuel grains.

[0052] In this embo...

Embodiment 2

[0068] see figure 1 and figure 2 , a rocket engine provided in this embodiment can be applied to an aircraft to provide long endurance and maneuverability for the aircraft. This embodiment is an improvement made on the technical basis of the above-mentioned embodiment 1. Compared with the above-mentioned embodiment 1, the difference lies in:

[0069] Please refer to figure 1 and Figure 5 , in this embodiment, a detachable first heat insulating layer 123 is provided between the first solid propellant grain 122 and the solid-liquid fuel grain 121 . That is to say, the first heat insulating layer 123 is arranged inside the column cavity 1210 of the solid-liquid fuel grain 121, and is used to separate the first solid propellant grain 122 from the solid-liquid fuel grain 121, and its purpose is to prevent The high temperature of the first solid propellant grain 122 during combustion causes pyrolysis or cracks in the solid-liquid fuel grain 121 .

[0070] It can be understood...

Embodiment 3

[0103] see figure 1 , figure 2 as well as image 3 , a rocket engine provided in this embodiment can be applied to an aircraft to provide long endurance and maneuverability for the aircraft. This embodiment is an improvement made on the technical basis of the above-mentioned embodiment 1 or embodiment 2. Compared with the above-mentioned embodiment 1 or embodiment 2, the difference lies in:

[0104] Please refer to figure 2 , the rocket engine provided in this embodiment includes a thrust chamber 200 , an oxidant storage chamber 300 and a combustion chamber 100 .

[0105] The thrust chamber 200 is connected to the oxidant storage chamber 300 , the oxidant storage chamber 300 is connected to the combustion chamber 100 , and the end of the combustion chamber 100 away from the oxidant storage chamber 300 is also connected to the tail nozzle 150 .

[0106] In the initial state of the tail nozzle 150, the end of the tail nozzle 150 away from the combustion chamber 100 is prov...

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Abstract

The invention provides a solid-liquid-solid co-combustion chamber combined power rocket engine and an aircraft, which relate to the technical field of aerospace. The solid-liquid-solid co-combustion chamber combined power rocket engine includes a combustion chamber, and the combustion chamber includes a body and a grain filling chamber arranged on the body; the grain filling chamber is filled with a first solid propellant grain and a solid-liquid fuel grain; wherein , the solid-liquid fuel grain is provided with at least one column cavity along the axis direction, and the first solid propellant grain is disposed in the column cavity. The solid-liquid-solid co-combustion chamber combination power rocket engine provided by the invention rationally utilizes the effective space of the combustion chamber, has high filling density and compact structure. In addition, the advantages of the first solid propellant grain and the solid-liquid fuel grain are fully utilized, and the thrust-to-weight ratio of the rocket engine is further improved by combining the first solid propellant grain and the solid-liquid fuel grain.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a solid-liquid-solid co-combustion chamber combined power rocket engine and an aircraft. Background technique [0002] As the main source of power for spacecraft and missiles, rocket engines have always been a hot research topic in various countries. [0003] At present, chemical rocket motors with more practical applications can be divided into three categories: solid rocket motors, liquid rocket motors, and solid-liquid hybrid rocket motors. Among them, the solid-liquid hybrid rocket engine has been the focus of research in recent years because it has the advantages of high specific impulse, adjustable thrust, multiple shutdown and startup of liquid rocket engines, and easy storage, simple structure, and high reliability of solid rocket engines. However, solid-liquid hybrid rocket engines also have defects such as low packing density and small thrust-to-weight ratio, which ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/10F02K9/36F02K9/32
CPCF02K9/10F02K9/32F02K9/36
Inventor 蔡国飙李睿智田辉朱浩谢彬于睿鹏
Owner BEIHANG UNIV