Self-throwing-separating cowling and rocket

A fairing and self-throwing technology, which is applied to space navigation equipment, space navigation vehicles, space navigation equipment, etc., to achieve the effects of overcoming resistance and high temperature environment, fast separation speed, and stable and reliable output performance

Active Publication Date: 2019-04-16
湖北航天飞行器研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Because the rocket is flying at high speed in the atmosphere, the separation environment is very harsh. The traditional method of throwing the fairing away after the rocket breaks out of the atmosphere to release its internal spacecraft and the corresponding structure, because of

Method used

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  • Self-throwing-separating cowling and rocket
  • Self-throwing-separating cowling and rocket
  • Self-throwing-separating cowling and rocket

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] Such as figure 1 As shown, the self-throwing fairing 100 is connected with the head of the rocket body through the docking bracket 5, including:

[0051] The fairing casing includes at least two fairing pieces, and the fairing pieces are at least spliced ​​and connected by a radial connection mechanism.

[0052] The shroud separation system receives the control command of the rocket body and operates, including a separation output mechanism and an axial connection mechanism arranged in the fairing casing. The axial connection mechanism is used to connect the docking bracket 5 and the fairing casing.

[0053] Wherein, the separation output mechanism is used to push the spinner shell to separate according to a predetermined separation speed and attitude after the connection between the radial connection mechanism and the axial connection mechanism is released.

Embodiment 2

[0055] On the basis of Embodiment 1, as a specific preference, the radial connection mechanism is a radial connection separation bolt 4, which is arranged in the middle of the fairing sheet body, and is used to connect at least two split fairing sheet bodies, When the breakaway bolt receives the breakaway signal, it acts to release or weaken the connection; and / or

[0056] The axial connection mechanism is an axial connection separation bolt 7, which is arranged at the tail of the fairing sheet body, and is used to axially connect and fix the fairing shell and the docking bracket, such as image 3 , 5 As shown in , 7, the axial connection separation bolt 7 is used to connect the docking bracket and the control cabin, and at the same time as Figure 5 As shown, it can be seen that the docking bracket and the control cabin are auxiliary connected by the stud bolt S. When the separation bolt receives the separation signal from the control cabin, it will be activated by the deton...

Embodiment 3

[0060] On the basis of Embodiment 1-2, as a specific preference, the separation output mechanism includes a front end separation output actuator 3 arranged at the inner head of the fairing shell, and the two ends of the front end separation output actuator are respectively connected to the corresponding The corresponding interface connection set on the adjacent fairing body, such as figure 2 , 3 As shown, when the front-end separation output actuator receives the separation signal, it will act to open the corresponding fairing sheet for separation; and / or

[0061] The separation output mechanism includes the rear end separation output actuator 6 arranged at the rear part of the fairing shell, and the rear end separation output actuator has a body 61 and a push rod 62, such as Image 6 , 9 , 10, 11, and 12, the body is an airtight cavity, and the inside is equipped with prefabricated powder blocks and detonators (current detonators, such as electric detonators). Gas, expans...

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PUM

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Abstract

The invention discloses a self-throwing-separating cowling. The self-throwing-separating cowling is connected with the head of a rocket body through a butt-joint support, and comprises a cowling shelland a cowling throwing separating system, wherein the cowling shell comprises at least two cowling sheets, and the cowling sheets are spliced and connected at least through a radial-direction connecting mechanism; the cowling throwing separating system receives a control instruction of the rocket body for movement, and comprises a separating output mechanism and an axial-direction connecting mechanism which are arranged in the cowling shell, the axial-direction connecting mechanism is used for being connected with the butt-joint support and the cowling shell, and the separating output mechanism is used for pushing the cowling shell to be separated according to the preset separation velocity and posture after connection between the radial-direction connecting mechanism and the axial-direction connecting mechanism is relieved. As the cowling throwing separating system is arranged in the cowling shell, active movement of the separating output mechanism of the cowling throwing separatingsystem is used for acting, the resistance in the hypersonic speed state and the high-temperature-environment influence are overcome, the separating speed is high, the output performance is stable andreliable, and the self-throwing-separating cowling can be used for cowling separation under the harsh environmental condition.

Description

technical field [0001] The invention relates to a fairing and a rocket, in particular to a self-throwing fairing and a rocket, and belongs to the field of rocket structures. Background technique [0002] The fairing of the rocket plays the role of reducing the air resistance of the rocket and protecting its internal spacecraft. With the development of science and technology and the increasing research on basic scientific issues of hypersonic aerodynamic characteristics in China, new requirements are also put forward for the launch vehicle. The rocket throws off the fairing at hypersonic speeds without flying out of the atmosphere, releasing its internal spacecraft. [0003] Because the rocket is flying at high speed in the atmosphere, the separation environment is very harsh. The traditional method of throwing the fairing away after the rocket breaks out of the atmosphere to release its internal spacecraft and the corresponding structure, because of this design The object o...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 薛士明索桂兰李盛徐禄高海军巩立先
Owner 湖北航天飞行器研究所
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