A Locking Mechanism for CubeSat Separation and Evacuation

A technology of locking mechanism and separating mechanism, which is applied in the field of satellite launch, can solve the problems of infinite position, complex limit mechanism, low redundancy, etc., and achieve the effect of high limit reliability, convenient limit angle and convenient adjustment

Active Publication Date: 2021-04-30
BEIJING UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

With the increasing demand for CubeSat launches, various CubeSat separation mechanisms are emerging, but there are generally problems such as unlimited positions after opening the hatch, complex limit mechanisms, low redundancy, or limit deviations that affect the opening of the hatch.

Method used

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  • A Locking Mechanism for CubeSat Separation and Evacuation
  • A Locking Mechanism for CubeSat Separation and Evacuation
  • A Locking Mechanism for CubeSat Separation and Evacuation

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] Embodiment 1, the locking mechanism for the separation of the CubeSat is in the launching stage.

[0039] Such as figure 2 , is a schematic diagram of the launch stage, the cube star is locked inside the separation mechanism, and the flip-limiting long plate (2) is in a static state under the joint action of the semicircular locking block (1), the tension spring (8) and the long plate shaft (6) .

Embodiment 2

[0040] Embodiment 2, the locking process of the cubic star separation and departure locking mechanism.

[0041] Such as Figure 3-5 , when the separation mechanism receives the separation signal, the flip cover (4) opens, and when the set angle is reached, the extension spring (8) shrinks, driving the flip limit long plate (2) to rotate around the long plate shaft (6), thereby moving along the Slide down the vertical inner surface of the semicircle locking block (1) to realize clamping of the semicircle locking block (1).

[0042] Such as image 3 As mentioned above, when the flip cover does not reach the maximum limit angle, the flip limit long plate (2) enters the redundant area in advance, so that the flip cover rotating plate moves downward to realize the limit, and the design of the redundant area reduces the required processing precision.

[0043] Such as Figure 4 As mentioned above, the tension spring (8) pulls the flip limit long plate (2) into the limit locking a...

Embodiment 3

[0051] Embodiment 3, the recovering stage of the locking mechanism for separation and departure of the cubesat after the ground test.

[0052] After the ground operator completes the test of opening the hatch, lift the flip limit long plates (2) on both sides of the separation mechanism with the middle fingers of both hands, and then press the hatch (4) together with the index fingers of both hands to complete the closing action.

[0053] Further, after the flip limit long plate (2) is lifted, it will be in contact with the limit stopper (3) such as Figure 7 Contact with the surface (3-2) in the center, thereby limiting its excessive displacement, protecting the extension spring (8) from being damaged by misoperation.

[0054] Further, as Figure 8 , the limit stopper (3) is positioned by the two through holes of (3-1) with screws and the separation mechanism top frame (5).

[0055] The working principle of the present invention is:

[0056] The semicircular locking block ...

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Abstract

The invention discloses a locking mechanism for cubic star separation and departure, which includes a semicircular locking block, a flip-cover limit long plate, a limit block, a flip cover, a top frame of the separation mechanism, a long plate rotating shaft, a limit spring pad, Extension springs and other fastening accessories. When the cubesat is loaded into the separation mechanism and docked with the launch vehicle and is in the launching stage, the flip-limiting long plate is in a static state under the action of the semicircular locking block, the long plate rotating shaft and the tension spring. When the rocket enters the predetermined orbit, the cubesat separation mechanism will After receiving the rocket separation signal, the hatch cover of the separation mechanism will open, and the semicircular locking block will move together with the hatch cover. When the maximum limit position is reached, the flip limit long plate will rotate around the long plate rotation axis under the action of the tension spring and enter to the locked position, so as to realize the limited locking of the semicircular locking block, and prevent the rebound of the cover from affecting the normal orbital entry of the cubesat ejected from the separation mechanism.

Description

technical field [0001] The invention belongs to the technical field of satellite launching, in particular to a locking mechanism for separating and leaving a cabin of a cubesat. Background technique [0002] In recent years, due to my country's open policy for private aerospace, more and more private capital other than universities have gradually entered the aerospace field, especially in the research and development of CubeSat, which has advantages such as development cycle and low manufacturing cost. Star's research and development capabilities are constantly improving. With the increasing demand for CubeSat launches, various CubeSat separation mechanisms are emerging, but there are generally problems such as unlimited positions after opening the hatch, complex limit mechanisms, low redundancy, or limit deviations that affect the opening of the hatch. Contents of the invention [0003] In view of the above problems, the purpose of the present invention is to provide a lo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 陈东菊李万岭王超范京华
Owner BEIJING UNIV OF TECH
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