A launch locking mechanism

Abstract

The present invention provides a launch locking mechanism for locking the primary mirror of a space telescope, comprising a separation part and a fixing part; the separation part comprises a servo motor interface, a base, and a locking screw, wherein the servo motor interface is fixedly connected above the base, and the locking screw is fixedly connected below the base; the fixing part comprises a housing, a first limiter with a through hole, a nut sleeve, a split nut, a separation top plate, a first elastic body, a second elastic body, an alloy wire fixing part, an SMA alloy wire, a pulley, a pulley shaft, a pulley limiter sleeve, and an alloy wire mounting seat; the locking screw of the separation part is threadedly connected to the split nut through the through hole of the first limiter of the fixing part. The launch locking mechanism provided by the present invention deforms the SMA alloy by changing its temperature, and cooperates with the restoring force of the elastic body to realize the deployment and recovery of the primary mirror of the space telescope, and the control mode is simple and the reliability is high.

Description

Technical Field

[0001] The invention relates to a locking mechanism, in particular to a launch locking mechanism used for locking a primary mirror of a space telescope. Background Art

[0002] The working environment in space is relatively complex, there is a possibility of electromagnetic signal interference, and it is difficult to repair the equipment. This puts higher requirements on the control accuracy and reliability of the equipment. The existing launch locking mechanism often uses signal control, and there are many drive mechanisms and the structure is relatively complex. Therefore, the launch locking device using traditional control methods has the problems of poor control stability and insufficient reliability.

[0003] Therefore, technicians in this field are committed to developing a high-reliability, simple-structured launch locking mechanism that relies on temperature to control the deformation of SMA alloy, thereby controlling the deployment and retraction of the primary mirror of a space telescope. Summary of the invention

[0004] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present invention is the low reliability problem of the original multi-driving mechanism and multi-signal control, and the launch locking action is achieved by controlling the deformation of the SMA alloy through temperature changes.

[0005] To achieve the above-mentioned object, the present invention provides a launch locking mechanism for locking a primary mirror of a space telescope, comprising a separation portion and a fixing portion;

[0006] The separation part includes a servo motor interface, a base, and a locking screw, wherein the servo motor interface is fixedly connected above the base, and the locking screw is fixedly connected below the base;

[0007] The fixing part includes an outer shell, a first limiting member with a through hole, a nut sleeve, a split nut, a separation top plate, a first elastic body, a second elastic body, an alloy wire fixing member, an SMA alloy wire, a pulley, a pulley shaft, a pulley limiting sleeve, and an alloy wire mounting seat; a platform with a through hole is provided inside the outer shell, the second elastic body is placed on the platform, the nut sleeve is placed on the second elastic body, and the inside of the nut sleeve is respectively provided with an alloy wire fixing member, a first elastic body, a split top plate, and a split nut from bottom to top, and the first limiting member is placed on the top of the outer shell; the pulley shaft is provided below the platform, the pulley passes through the pulley shaft, and the pulley limiting sleeve is placed at both ends of the pulley; the alloy wire mounting seat is provided on the outer shell, and the SMA alloy wire passes through the alloy wire mounting seat, the pulley, and the through hole of the platform and is fixed to the alloy wire fixing member;

[0008] The locking screw of the separation part is threadedly connected to the split nut through the through hole of the first limiting member of the fixing part.

[0009] Furthermore, the split nut has no less than 2 petals.

[0010] Furthermore, the SMA alloy wire is a temperature memory alloy.

[0011] Furthermore, the SMA alloy wire is selected from at least one of titanium-nickel-copper alloy, titanium-nickel-iron alloy, titanium-nickel-chromium alloy, copper-nickel alloy, copper-aluminum alloy, copper-zinc alloy and iron alloy.

[0012] Furthermore, the SMA alloy wire is connected to a temperature control device.

[0013] Furthermore, the base is provided with mounting holes around it for connection with the main mirror; and the servo motor interface is connected with the servo motor via a key.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] The launch locking mechanism provided by the present invention realizes the deployment and locking action of the primary mirror of the space telescope by changing the temperature of the SMA alloy to cause it to deform and cooperate with the restoring force of the elastic body. It can complete multiple launch locking actions, has high reliability, simple structure and low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a stereoscopic diagram of the launch locking mechanism of the present invention;

[0017] Figure 2 yes Figure 1 Section view along line AA;

[0018] Figure 3 yes Figure 1 Section view along line BB. DETAILED DESCRIPTION

[0019] The present invention is described below with reference to the accompanying drawings to make its technical content clearer and easier to understand.

[0020] In the drawings, components with the same structure are indicated by the same numerical reference numerals, and components with similar structures or functions are indicated by similar numerical reference numerals. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thickness of the components is appropriately exaggerated in some places in the drawings.

[0021] like Figure 1 , Figure 2 , Figure 3As shown, the launch locking mechanism includes a separation part and a fixing part; the separation part includes a servo motor interface 14, a base 15, and a locking screw 16, the servo motor interface 14 and the locking screw 16 are respectively fixed on the upper and lower sides of the base 15, wherein the servo motor interface 14 is provided with a keyway, and can be connected to the servo motor through a key; the base 15 is provided with mounting holes 17 around it for connecting with the primary mirror;

[0022] The fixing part includes an outer shell 1, a first limiting member 2 with a through hole, a nut sleeve 3, a split nut 4, a separation top plate 5, a first elastic body 6, a second elastic body 7, an alloy wire fixing member 8, an SMA alloy wire 12, a pulley 10, a pulley shaft 9, a pulley limiting sleeve 11, and an alloy wire mounting seat 13; a platform with a through hole is provided inside the outer shell 1, the second elastic body 7 is placed on the platform, the nut sleeve 3 is placed on the second elastic body 7, and the nut sleeve 3 can move up and down with the contraction of the second elastic body 7; the inside of the nut sleeve 3 is respectively provided with an alloy wire fixing member 8, a first elastic body 6, a separation top plate 5, and a split nut 4 from bottom to top; the first limiting member 2 is placed on the top of the outer shell 1 and is connected by overfitting for use The fixed part plays a limiting role when in contact with the separating part; the pulley shaft 9 is arranged under the platform, the pulley 10 passes through the pulley shaft 9, the pulley limiting sleeve is placed on one side of the pulley 10, and the pulley shaft on the other side has a limiting step; the alloy wire mounting seat 13 is arranged on the outer shell 1, and one end of the SMA alloy wire 12 passes through the alloy wire mounting seat 13, passes through the pulley 10, passes through the through hole of the platform and is fixed on the alloy wire fixing part 8, and the other end of the SMA alloy wire 12 is connected to the temperature control device; there is a limiting knot at one end of the SMA alloy wire 12, and when the SMA alloy wire contracts, the limiting knot contacts the alloy wire mounting seat 13 for limiting; the locking screw 16 of the separating part is threadedly connected to the split nut 4 through the through hole of the first limiting part 2 of the fixing part. The SMA alloy wire 13 is connected to an external temperature control device. When the temperature is controlled to cause the SMA alloy wire 13 to shrink and deform, the SMA alloy wire 13 pulls the nut sleeve 3 downward, the second elastomer 7 is compressed, and the first elastomer 6 pushes out the separation top plate 5. At this time, the petals of the split nut 4 are separated to make the locking screw 16 disengage from the split nut 4, completing the launching action of the separation part; when the temperature is controlled to cause the SMA alloy wire 13 to stretch and restore its original length, the second elastomer 7 is reset, the nut sleeve 3 moves up, the split nut 4 is closed, and is received in the nut sleeve. The separation end is connected to a servo motor to drive the separation end to rotate, and is screwed together with the split nut through a thread to complete the locking action.

[0023] In some preferred embodiments, the split nut 4 has no less than 2 petals.

[0024] In some preferred embodiments, the SMA alloy wire 12 is a temperature memory alloy, including but not limited to titanium-nickel-copper alloy, titanium-nickel-iron alloy, titanium-nickel-chromium alloy, copper-nickel alloy, copper-aluminum alloy, copper-zinc alloy, and iron alloy.

Claims

1. A launch locking mechanism for locking the primary mirror of a space telescope, characterized in that: comprising a separation portion and a fixing portion; The separation part includes a servo motor interface, a base, and a locking screw, wherein the servo motor interface is fixedly connected above the base, and the locking screw is fixedly connected below the base; The fixing part includes an outer shell, a first limiting member with a through hole, a nut sleeve, a split nut, a separation top plate, a first elastic body, a second elastic body, an alloy wire fixing member, an SMA alloy wire, a pulley, a pulley shaft, a pulley limiting sleeve, and an alloy wire mounting seat; a platform with a through hole is provided inside the outer shell, the second elastic body is placed on the platform, the nut sleeve is placed on the second elastic body, and the inside of the nut sleeve is respectively provided with an alloy wire fixing member, a first elastic body, a split top plate, and a split nut from bottom to top, and the first limiting member is placed on the top of the outer shell; the pulley shaft is provided below the platform, the pulley passes through the pulley shaft, and the pulley limiting sleeve is placed at both ends of the pulley; the alloy wire mounting seat is provided on the outer shell, the SMA alloy wire passes through the alloy wire mounting seat, the pulley, and the through hole of the platform and is fixed to the alloy wire fixing member, and the SMA alloy wire is connected to a temperature control device; The locking screw of the separation part is threadedly connected with the petal nut through the through hole of the first limiting member of the fixing part; The base is provided with mounting holes around it for connecting with the main mirror; the servo motor interface is connected with the servo motor through a key; Wherein, the split nut has no less than 2 petals, and the SMA alloy wire is a temperature memory alloy.

2. The launch locking mechanism according to claim 1, characterized in that: The SMA alloy wire is selected from at least one of titanium-nickel-copper alloy, titanium-nickel-iron alloy, titanium-nickel-chromium alloy, copper-nickel alloy, copper-aluminum alloy, copper-zinc alloy and iron alloy.

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