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Fairing inclined pushing axial separation device

A technology of axial separation and fairing, which is applied in the docking device of aerospace vehicles, transportation and packaging, space navigation equipment, etc., can solve the problems of insufficient vertical installation of the separation mechanism and occupation of the envelope space of the fairing, and achieve the goal of packaging The effect of small network space

Pending Publication Date: 2021-02-12
航天科工火箭技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When the axial distance of the column section is relatively small, the column section is not enough to install the separation mechanism vertically. If the separation mechanism is moved radially inward and installed vertically, the separation mechanism will occupy a large envelope space of the fairing

Method used

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  • Fairing inclined pushing axial separation device
  • Fairing inclined pushing axial separation device
  • Fairing inclined pushing axial separation device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Such as Figure 1-Figure 5 As shown, a fairing obliquely pushes the axial separation device, including a spring separation mechanism, a flat ball socket base, and a hinge base;

[0034] The spring separation mechanism includes a sleeve, a separation spring and a spring push rod. The sleeve is a straight cylinder. In this embodiment, the sleeve is a straight cylinder, and one end thereof is set as a closed end. There is a first ear, the other end is open, the length of the separation spring is less than the length of the sleeve, the separation spring is arranged in the sleeve, and one end of it is embedded in the inner end surface of the closed end of the sleeve, so The spring push rod is a straight rod set in the sleeve, one end of which is provided with a flat ball head and the open end facing the sleeve is located outside the sleeve, and the other end is close to the other end of the separation spring, The separation spring pushes the spring push rod to provide thrus...

Embodiment 2

[0044] like Figure 1-Figure 6 As shown, a fairing obliquely pushes the axial separation device, including a spring separation mechanism, a flat ball socket base, and a hinge base;

[0045] The spring separation mechanism includes a sleeve, a separation spring and a spring push rod. The sleeve is a straight cylinder. In this embodiment, the sleeve is a straight cylinder, and one end thereof is set as a closed end. There is a first ear, the other end is open, the length of the separation spring is less than the length of the sleeve, the separation spring is arranged in the sleeve, and one end of it is embedded in the inner end surface of the closed end of the sleeve, so The spring push rod is a straight rod set in the sleeve, one end of which is provided with a flat ball head and the open end facing the sleeve is located outside the sleeve, and the other end is close to the other end of the separation spring, The separation spring pushes the spring push rod to provide thrust f...

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Abstract

The invention discloses a fairing inclined pushing axial separation device which comprises a spring separation mechanism, a flat ball socket base and a hinge base. The separation spring is in a compressed state, and an included angle exists between the spring separation mechanism and the axis of the fairing. According to the fairing separating device, enough enveloping space can be provided for effective loads, the safety distance between the fairing and the effective loads in the separating process is guaranteed, and the problems that the internal space of the fairing is limited, and a springseparating mechanism cannot be installed sufficiently are solved; in the fairing separation process, the flat ball head rotates in the direction away from the effective load in the middle plane of the flat ball socket, and the sleeve rotates around the hinge base in the direction close to the effective load. The hinge seat, the flat ball head and the flat ball socket are matched to work, so thatthe problem of clamping stagnation in the separation process due to an included angle between the spring separation mechanism and the axis of the fairing is solved, and the device is reliable in work.

Description

technical field [0001] The invention relates to the technical field of aircraft shroud separation, in particular to an oblique thrust axial separation device for fairings. Background technique [0002] The separate launch problem is a major class of problems to be solved in systems in the fields of aeronautics, spaceflight and weapons. When the carrier flies at a relatively thin altitude in the atmosphere, the effect of atmospheric resistance is already very small, and the payload no longer needs the protection of the fairing. In order to save fuel, improve the mass characteristics of the aircraft, and improve flight performance, it is necessary to The hood is thrown away to reduce the structural weight. [0003] The fairing axial separation method is a common separation method of the rocket fairing, and there is a long overlapping distance between the fairing and the final stage. During the separation process of the fairing, the mass, the moment of inertia of the center o...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 周思博翟海涛代志刚胡吉军刘家欣李义飞
Owner 航天科工火箭技术有限公司
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