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Space cam-spiral combined repeated folding and unlocking mechanism

A space cam and combined technology, applied in the direction of projectiles, offensive equipment, weapon types, etc., to achieve the effect of reliable unlocking, wide application range, and precise positioning

Inactive Publication Date: 2011-12-14
ZHEJIANG SCI-TECH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is mainly to solve the problem of automatic folding of the missile wings after the cancellation of the mission of the missile folding wing launch stage (the missile leaves the launch tube), and at the same time facilitate the maintenance of the folding wings during the storage period and prolong the service life of the missile

Method used

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  • Space cam-spiral combined repeated folding and unlocking mechanism
  • Space cam-spiral combined repeated folding and unlocking mechanism

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Embodiment Construction

[0016] The present invention will be further described below in conjunction with accompanying drawing.

[0017] Such as figure 1 As shown, the space cam-spiral combined repeated folding and unlocking mechanism includes a linkage wheel 1 (providing a power source); a rotating screw 2; centripetal thrust bearings 3, 21, 22, 36; wing pin holes 4, 11, 12 , 20, 23, 29, 30, 35 (cooperate with the lock release pin for positioning and locking in the folded and unfolded position); positioning and locking); the first cylindrical cam 6 (left-handed), the second cylindrical cam 18 (right-handed); cam grooves 7, 17, 25, 33; wing follower pins 8, 15, 27, 32 (along Cam channel movement); first guide rail 10, second guide rail 13; left folding wing 16, right folding wing 26, etc. It is characterized in that the rotating screw 2 has left-handed threads and right-handed threads respectively from the center to both ends, and the first cylindrical cam 6 has threads matching the left-handed thre...

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Abstract

The invention relates to a space cam-screw combined type repeatedly folding-unfolding unlocking mechanism. An existing folding wing only has a one-off unfolding locking function so as to not repeatedly fold and unfold. According to the space cam-screw combined type repeatedly folding-unfolding unlocking mechanism disclosed by the invention, a design idea in combination with a space cam mechanism and a screw mechanism is adopted so that the rotation of a motor is converted into a linear motion of a cylindrical cam along a guide rail through a screw pair; furthermore, a driven pin is driven by the cylindrical cam to move along a cam channel so that the folding wing is repeatedly folded and unfolded; and moreover, an unlocking pin on the cam and a pin hole of the folding wing are used for entering and separating to unlock and lock the folding wing. The driven pin on the folding wing ensures that the redundancy in finally folding and unfolding positions is reliably positioned. According to the space cam-screw combined type repeatedly folding-unfolding unlocking mechanism disclosed by the invention, an enveloping space of the folding wing is minimized, the structure is compact, and thefolding wing is easy to fold, unfold, unlock and lock with high precision and high reliability.

Description

technical field [0001] The invention relates to a repeated folding and locking mechanism in an aerospace space, which is used for the movable connection of joints of space mechanisms such as missile folding wings and solar wing base plates. Background technique [0002] The repeated folding and unlocking mechanism is an important part of the space folding mechanism. At present, the vast majority of solar wings for spacecraft and folding wings for missiles in China only have a one-time unfolding and locking function, and cannot be folded and unfolded repeatedly, that is, they are folded and folded during the normal launch phase. It locks after unfolding to working state. However, the storage reliability of the equipment using a one-time deployment mechanism cannot be tested, and it cannot meet the requirements of canceling the launch mission. Contents of the invention [0003] The purpose of the present invention is mainly to solve the problem of automatic folding of the ...

Claims

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Application Information

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IPC IPC(8): F42B10/02
Inventor 胡明张苗苗金永平陈文华钱萍徐国民周健张尧潘骏刘东旭
Owner ZHEJIANG SCI-TECH UNIV
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