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Attitude control system and small rocket launcher

A technology for a rocket and a decompression device, applied in the field of rockets, can solve the problems of high cost and low carrying capacity of small launch vehicles, and achieve the effects of reduced quality, low preparation cost and test cost, and reduced structural mass and volume.

Inactive Publication Date: 2018-11-23
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide an attitude control system to solve the technical problems of low carrying capacity and high cost of small launch vehicles existing in the prior art

Method used

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  • Attitude control system and small rocket launcher
  • Attitude control system and small rocket launcher
  • Attitude control system and small rocket launcher

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Effect test

Embodiment 1

[0042] figure 1 Schematic diagram of the structure of the attitude control system provided by the embodiment of the present invention; figure 2Schematic diagram of the structure of the cold air thruster provided by the embodiment of the present invention; image 3 Structural schematic diagram of the self-locking valve provided for the embodiment of the present invention; Figure 4 Schematic diagram of the structure of the valve core provided by the embodiment of the present invention; Figure 5 The distribution diagram of the cold air thrusters provided by the embodiment of the present invention.

[0043] Such as Figure 1-Figure 5 As shown, the attitude control system provided by the embodiment of the present invention includes: a high-pressure nitrogen cylinder 1, a first pressure sensor 2, a second pressure sensor 7, an electric explosion valve 4, a decompression device, a safety valve 8 and a cold air thruster 9; Wherein, the first pressure sensor 2 is arranged betwee...

Embodiment 2

[0065] Embodiment 2 of the present invention provides a small launch vehicle, which includes a rocket body in which a main engine and the attitude control system provided in Embodiment 1 above are installed.

[0066] In this embodiment, since the small launch vehicle includes the attitude control system provided in the first embodiment above, it has all the beneficial effects of the attitude control system, which will not be repeated here.

[0067] Further, as Figure 5 As shown, in a preferred implementation of this embodiment, the attitude control system includes four cold air thrusters 9, and the four cold air thrusters 9 are all located at the bottom of the rocket body and distributed on both sides of the rocket body. 9 and the vertical axis of the rocket body are at an angle of 45°.

[0068] Specifically, the attitude control system adopts the layout of four air-conditioning thrusters 9, such as Figure 5 , four cold air thrusters 9 are distributed on both sides of the ...

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Abstract

The invention provides an attitude control system and a small rocket launcher, and relates to the technical field of rockets. The technical problems of low carrying capacity and high cost of an existing small rocket launcher are solved. The attitude control system comprises a high-pressure nitrogen bottle, a first pressure sensor, a second pressure sensor, an electric explosion valve, a pressure reduction device, a safety valve and a cold air thruster, wherein the first pressure sensor is arranged between the high-pressure nitrogen bottle and the electric explosion valve and is used for detecting pressure of the nitrogen which flows out of the high-pressure nitrogen bottle; the pressure reduction device is connected with the electric explosion valve; the second pressure sensor is arrangedbetween the pressure reduction device and the safety valve and is used for detecting the pressure of the nitrogen which flows out of the pressure reduction device; and the safety valve is connected with the cold air thruster. The device has the advantages of simple structure and low cost, and the provided thrust force just meets a control requirement of the small rocket launcher, and therefore, waste is avoided.

Description

technical field [0001] The invention relates to the technical field of rockets, in particular to an attitude control system and a small launch vehicle. Background technique [0002] During the flight of the spacecraft, the attitude control must be carried out through the attitude control system at every moment. The attitude control includes the three-axis control of the spacecraft's pitch, yaw, and roll. [0003] The attitude control systems of existing large-scale launch vehicles mostly use dual-component propulsion systems and single-component propulsion systems with reactions. The dual-component propulsion system requires a separate propellant supply system, and, in the working process, the two components contact and react to generate high-temperature working fluid, and corresponding propellant injection atomization devices and thermal protection devices are required. Therefore, the structure of the bicomponent propulsion system is very complicated, and the invalid load...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/56F02K9/58
CPCF02K9/56F02K9/566F02K9/58
Inventor 袁军娅韩志龙王鹏程朱浩
Owner BEIHANG UNIV
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