CN-121973958-A - Micro-miniature double-component partially premixed chemical thruster

CN121973958ACN 121973958 ACN121973958 ACN 121973958ACN-121973958-A

Abstract

The application discloses a microminiature double-component part premixing chemical thruster, which comprises an injector and a combustion chamber, wherein the injector is provided with a first component conveying channel, a second component conveying channel and a plurality of injection holes, the injection holes are arranged at intervals along the circumferential direction and are communicated with the second component conveying channel, a combustion chamber is formed in the combustion chamber, a buffer chamber and a plurality of premixing channels are formed between the combustion chamber and the injector, the buffer chamber is communicated with the first component conveying channel, the premixing channels are arranged at intervals along the circumferential direction and are communicated with the injection holes in a one-to-one correspondence manner, each premixing channel comprises an inlet section and an outlet section, the inlet section is directly communicated with the buffer chamber, the outlet section is communicated with the combustion chamber, and the sectional area of the inlet section is smaller than that of the outlet section. The microminiature bi-component part premixing chemical thruster can effectively prevent backfire, improve combustion stability, and provide stable driving force for satellite orbit lifting or attitude adjustment and the like.

Inventors

GONG JINGSONG
DONG KAILEI

Assignees

清华大学
曹妃甸区跨介质科学与系统研究院

Dates

Publication Date: 20260505
Application Date: 20260130

Claims (10)

1. A microminiature bi-component partially premixed chemical thruster comprising: The injector is provided with a first component conveying channel, a second component conveying channel and a plurality of injection holes, wherein the injection holes are arranged at intervals along the circumferential direction and are communicated with the second component conveying channel; A combustion chamber, in which a combustion chamber is formed; The combustion chamber is provided with a first component conveying channel, a first component spraying hole is formed in the first component spraying channel, a second component spraying channel is formed in the second component spraying channel, a buffer cavity and a plurality of premixing channels are formed between the combustion chamber and the spraying device, the buffer cavity is communicated with the first component conveying channel, the premixing channels are arranged at intervals along the circumferential direction and are communicated with the spraying holes in a one-to-one correspondence mode, each premixing channel comprises an inlet section and an outlet section, the inlet section is directly communicated with the buffer cavity, the outlet section is communicated with the combustion chamber, and the sectional area of the inlet section is smaller than that of the outlet section.
2. The microminiature two-component partially premixed chemical thruster according to claim 1, wherein a portion of the injector or the combustion chamber radially facing the inlet section is formed with a throttle portion.
3. The microminiature dual component part premix chemical thruster of claim 2, wherein the injector is formed with a buffer portion and a premix portion, the buffer portion being axially connected to the premix portion, the housing of the combustion chamber is formed with a first connection portion and a second connection portion, wherein, The buffer part is opposite to the first connecting part in the radial direction, the buffer cavity is formed between the buffer part and the first connecting part, the premixing part is opposite to the second connecting part in the radial direction, and a plurality of premixing channels are formed between the premixing part and the second connecting part.
4. A microminiature dual component part premix chemical thruster according to claim 3, wherein the premix is formed with a plurality of circumferentially spaced apart lobes, one premix channel being formed between each adjacent two of the lobes.
5. The microminiature two-component partially premixed chemical thruster according to claim 3, wherein the portion of the premixing portion radially protrudes to form the throttling portion, the throttling portion is in contact with the buffering portion, and an outer circumferential surface of the throttling portion is coplanar with an outer circumferential surface of the buffering portion.
6. The microminiature dual component part premix chemical thruster of claim 1, wherein the outlet of the injection orifice communicates with the outlet section of the premix passage and the outlet of the injection orifice is disposed proximate to the inlet section.
7. The microminiature two-component partially premixed chemical thruster of claim 1, wherein the premixing passage is configured as a direct flow passage or a swirl passage.
8. The microminiature dual component part premix chemical thruster of claim 7, wherein the angle between the extending direction of the premix channel and the axial direction of the injector is α, and satisfies 0 ° and 60 °.
9. The microminiature two-component partially premixed chemical thruster of claim 1, further comprising: A first component supply unit communicating with the first component delivery passage to be adapted to deliver a first component into the combustion chamber; A second component supply unit communicating with the second component delivery passage to be adapted to deliver a second component into the combustion chamber; the first component and the second component are adapted to be premixed within the premixing passage.
10. The microminiature two-component partially premixed chemical thruster of claim 1, further comprising: An igniter disposed on the housing of the combustion chamber adapted to ignite the mixed components within the combustion chamber; and the spray pipe is connected with the outlet of the combustion chamber so as to be suitable for gas spraying.

Description

Micro-miniature double-component partially premixed chemical thruster Technical Field The application relates to the technical field of microminiature chemical thrusters, in particular to a microminiature double-component part premixing chemical thruster. Background In the field of aerospace, the low orbit satellite runs with a plurality of challenges that the lower the ① orbit height is, the larger the atmospheric resistance is in flight, the orbit reduction speed is obviously faster than that of the high orbit satellite, the more and more various spacecrafts in the ② orbit range are, the risk of collision is obviously improved, and a more reliable and rapid maneuvering obstacle avoidance means needs to be provided. Thus, low orbit satellite operation requires a chemical thruster to provide it with a high thrust rapidly to ensure that the satellite can achieve rapid orbit transfer in a shorter time. The miniature double-component chemical thruster has the advantages of simple structure, quick start, large thrust and the like, can provide reliable impulse for track lifting, can form a combined propulsion mode with cold air propulsion, electric propulsion and the like through reasonable collocation of propellant components, and provides more flexible track holding and lifting power for low-orbit satellites. In the related art, because the microminiature bi-component chemical thruster has small structural size (the diameter of a combustion chamber is in the order of tens of millimeters), complicated mixing, ignition, heat transfer, combustion and other processes are involved in the microminiature bi-component chemical thruster, the mixing and flame stabilization are difficult, tempering problems are easy to cause, and the design and development difficulties are high. Disclosure of Invention The present application aims to solve at least one of the technical problems existing in the prior art. Therefore, an object of the present application is to provide a chemical thruster, which aims to solve the problems of difficult mixing of two components of the chemical thruster, flame stabilization and easy backfire. The application provides a microminiature double-component part premixing chemical thruster, which comprises an injector and a combustion chamber, wherein the injector is provided with a first component conveying channel, a second component conveying channel and a plurality of injection holes, the injection holes are arranged at intervals along the circumferential direction and are communicated with the second component conveying channel, a combustion chamber is formed in the combustion chamber, a buffer chamber and a plurality of premixing channels are formed between the combustion chamber and the injector, the buffer chamber is communicated with the first component conveying channel, the premixing channels are arranged at intervals along the circumferential direction and are communicated with the injection holes in a one-to-one correspondence manner, each premixing channel comprises an inlet section and an outlet section, the inlet section is directly communicated with the buffer chamber, the outlet section is communicated with the combustion chamber, and the sectional area of the inlet section is smaller than that of the outlet section. According to the microminiature bi-component part premixing chemical thruster, the first component and the second component are primarily mixed in the premixing channel and conveyed into the combustion chamber for combustion, so that effective mixing and combustion of the two components can be realized, the sectional area of the inlet section of the premixing channel is smaller than that of the outlet section, the pressure difference at two sides of the premixing channel is increased, the flow velocity of the inlet section of the premixing channel is improved, tempering can be effectively prevented, the combustion stability is improved, and stable driving force can be provided for satellite orbit lifting or attitude adjustment and the like. According to some embodiments of the application, a portion of the injector or combustion chamber radially opposite the inlet section is formed with a restriction. According to some embodiments of the application, the injector is formed with a buffer portion and a premix portion, the buffer portion is axially connected with the premix portion, the housing of the combustion chamber is formed with a first connection portion and a second connection portion, the buffer portion is radially opposite to the first connection portion, a buffer cavity is formed between the buffer portion and the first connection portion, the premix portion is radially opposite to the second connection portion, and a plurality of premix channels are formed between the premix portion and the second connection portion. According to some embodiments of the application, the premix is formed with a plurality of circumferentially spaced apart projections, with a premi