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Aerospace sequential deployment mechanism

A technology for deploying mechanisms and aerospace space, applied in space navigation equipment, space navigation equipment, space navigation vehicles, etc., can solve the problems of uncontrollable deployment sequence, deployment speed, large impact force and vibration, etc., and achieve simplified power source , small shock and vibration, energy-saving effect

Active Publication Date: 2009-12-16
湖南哈工机器人研究院有限公司
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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 to provide an aerospace space sequential deployment mechanism to solve the problems that the deployment sequence is uncontrollable and the deployment speed, impact force and vibration are relatively large when the aerospace space mechanism is deployed.

Method used

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Experimental program
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specific Embodiment approach 1

[0007] Specific implementation mode one: combine figure 1 , Figure 2-a~Figure 2-d Describe this embodiment, the aerospace space sequence deployment mechanism of this embodiment is comprised of spring damper 1, space mechanism frame 2, first member 3, bent shape connecting rod 4, first driving part 5, first connecting rod 6, The second component 7, the second driving part 8, the third component 9, the arc pull rod 10, the roller 11, the thruster 12, and the pyrotechnic cutting device 13 are composed; One end is connected, and the other end of pyrotechnic cutting device 13 is connected with space mechanism frame 2 by thruster 12, and at this moment, aerospace space sequential deployment mechanism is in locked state, and the other end of third component 9 and one end of second component 7 Hinged at the first hinge point A, the second driving part 8 is arranged at the first hinge point A of the third member 9 and the second member 7, and provides a driving torque for the expansi...

specific Embodiment approach 2

[0008] Specific implementation mode two: combination figure 1 , Figure 4 To illustrate this embodiment, the first driving part 5 of this embodiment is composed of a first elastic driving part 5-1 and a first harmonic reducer; the first harmonic reducer is composed of a first harmonic reducer wave generator 5-2. The first harmonic reducer short-cup flexible wheel 5-3, the first harmonic reducer rigid wheel 5-4; the first elastic driving part 5-1 and the first harmonic reducer wave generator The device 5-2 is coaxial, one end of the first elastic driving part 5-1 is fixedly connected to the first member 3, and the other end of the first elastic driving part 5-1 is connected to the first harmonic reducer wave generator 5-2 The first harmonic reducer wave generator 5-2 is driven to rotate around its own axis by using the energy stored in the first elastic drive part 5-1, and the rigid wheel 5-4 of the first harmonic reducer is fixed to the first member 3 Then, the first harmoni...

specific Embodiment approach 3

[0009] Specific implementation mode three: combination figure 1 , image 3 To illustrate this embodiment, the second driving part 8 of this embodiment is composed of a second elastic driving part 8-1 and a second harmonic reducer; the second harmonic reducer is composed of a second harmonic reducer wave generator 8-2. The second harmonic reducer short-cup flexible wheel 8-3, the second harmonic reducer rigid wheel 8-4; the second elastic driving part 8-1 and the second harmonic reducer wave generator The device 8-2 is coaxial, one end of the second elastic driving part 8-1 is fixedly connected to the second member 7, and the other end of the second elastic driving part 8-1 is connected to the wave generator 8-2 of the second harmonic reducer The second harmonic reducer wave generator 8-2 rotates around its own axis by using the energy stored in the second elastic drive part 8-1, and the second harmonic reducer rigid wheel 8-4 is fixed to the second member 7 Then, the second ...

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Abstract

An aerospace space order deployment mechanism relates to an aerospace space deployment mechanism. Aiming at solving the problems of the uncontrollable deployment sequence, comparatively high deployment speed, comparatively strong shock and vibration of the aerospace mechanism, one end of a third component (9) is connected with the frame (2) of the aerospace mechanism by a flame cutting device (13) and a thruster (12); both ends of a second component (7) are articulated with the third component and a first component; a second drive component and a first drive component are respectively arranged at two articulated points; a spring damper (1) is articulated with the first component (3) and the frame (2) of the aerospace mechanism respectively; a curved link rod (4) is articulated with the first component (3) and a first link rod (6) respectively and is fixedly connected with an arc tie rod (10); a roller wheel (11) is arranged on the arc guide groove of the arc tie rod (10) and the first link rod (6) is articulated with the second component (7); the frame (2) of the aerospace mechanism is articulated with the first component (3). By adopting the deployment mechanism of the invention, the order deployment of the aerospace, low deployment speed, small shock and vibration can be realized.

Description

technical field [0001] The invention relates to an aerospace deployment mechanism. Background technique [0002] Some aerospace mechanisms are in a folded state when launching, and after reaching the predetermined space position, the lock is released, and the aerospace mechanism is unfolded. Since the unfolding sequence is uncontrollable, the unfolding speed, impact force and vibration are also relatively large, causing the entire spaceflight to collapse. The deployment mechanism produces vibrations that affect its performance, see the paper "Dynamic Analysis of the Deployment of Flexible Attachments of Large and Complex Spacecrafts" in the fourth issue of "China Space Science and Technology" in 2000. Contents of the invention [0003] The object of the present invention is to provide a sequential deployment mechanism for aerospace space to solve the problems that the deployment sequence is uncontrollable and the deployment speed, impact force and vibration are relatively ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22
Inventor 高海波邓宗全陶建国刘荣强胡明
Owner 湖南哈工机器人研究院有限公司
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