Rocket-carrying telescope-feed boom deployment mechanism

A deployment mechanism and sleeve-type technology, applied in the direction of instruments, projectiles, self-propelled bombs, etc., to achieve the effects of easy assembly and disassembly, limited power saving, and simple and compact structure

Inactive Publication Date: 2010-07-28
NAT SPACE SCI CENT CAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Foreign countries such as the United States, Russia, Sweden and other countries have successfully used extension rods to detect

Method used

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  • Rocket-carrying telescope-feed boom deployment mechanism
  • Rocket-carrying telescope-feed boom deployment mechanism
  • Rocket-carrying telescope-feed boom deployment mechanism

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0046] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0047] The extension mechanism of the extension rod is mainly composed of the lower base of the extension rod 12, the upper base of the extension rod 9, the base rotating shaft 11, the base spring locking mechanism 10, the rod-shaped cylinder 21-28, the nesting pipe collar 2-8, and the thrust locking mechanism 13 ~19, connecting ring 1, locking pressing piece 20 etc. are formed, and thrust locking mechanism is made up of spring 30, locking pin 29 and fastening screw 31 again. Except base rotating shaft 11, spring 30, screw, locking pin 29 and fastening screw 31, all the other parts all adopt aerospace light alloy material to make.

[0048] figure 1 Indicates the structural configuration of the single extension rod expansion mechanism in the folded state. From bottom to top in the figure, it is: a base, the first rod-shaped cylinder 28, 7 nested tube shafts 2-8, and ...

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PUM

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Abstract

The invention discloses a rocket-carrying telescope-feed boom deployment mechanism. The rocket-carrying telescope-feed boom deployment mechanism is characterized by comprising a base and a plurality of nested extension units, wherein the base comprises a lower base, an upper base, a rotating shaft and a locking mechanism; the lower base and the upper base can rotate the boom deployment mechanism by 90 degrees and automatically fix the boom deployment mechanism through the rotating shaft and the locking mechanism; each extension unit comprises a rod-shaped cylinder, a nested pipe clamp fixed at one end of the rod-shaped cylinder, and a stop locking mechanism arranged on the nested pipe clamp; the other end of the nested pipe clamp is nested into the rod-shaped cylinder of the next extension unit so as to limit the movement of the rod-shaped cylinder of the next extension unit; the base is connected with the rod-shaped cylinder at the bottommost end of the extension units through the upper base, and the diameters of the rod-shaped cylinders gradually decrease according to the design sizes and assembly space; and the boom deployment mechanism also comprises a connecting ring.

Description

technical field [0001] The invention relates to a sleeve-type extension rod deployment mechanism for sounding rocket space science detection, in particular to an arrow-mounted sleeve-type extension rod deployment mechanism. Background technique [0002] Sounding rockets mainly use the detection equipment carried on the rocket to detect parameters such as atmospheric trace components, space electric field, ionospheric electrons, ion density, and electron temperature. Among them, the detection equipment for electrons, ions, and electric fields requires its probes to extend The aerodynamic outer surface of the rocket has a certain distance to avoid the influence of the residual magnetism of the rocket body and the surface layer of the airflow, so it is required to extend these probes with an extension rod expansion mechanism. These extension rod parts are often installed in the rocket fairing or on the joint surface where the rocket body and the engine are separated. Because th...

Claims

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Application Information

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IPC IPC(8): F42B15/08G01W1/08
Inventor 杨萱姜秀杰刘波孟新郑建华孙健刘元
Owner NAT SPACE SCI CENT CAS
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