Rope anti-hooking device and spacecraft unfolding mechanism

Abstract

The utility model provides a rope hooking prevention device and a spacecraft unfolding mechanism. The rope hooking prevention device at least comprises a fixed support, a movable support and a central support. The bottom of the fixed support is installed on a fixed plate of a spacecraft through a shape memory alloy gasket, the bottom of the movable support is installed on an unfolding plate of the spacecraft through a shape memory alloy gasket, and the central support is arranged between the fixed support and the movable support. A rope winding drum is arranged at the top of the central support, and a channel allowing a rope to be wound and released is formed in the rope winding drum; the first end of the rope is connected with the top of the fixed support, the second end of the rope is connected with the top of the movable support, and the part, between the two ends, of the rope is collected in the rope collecting barrel. When the unfolding mechanism is unfolded, the movable support moves in the unfolding direction, and the folded rope is dragged to be released in order. In the releasing process, the rope is always approximately tensioned and does not float at will.

Description

TECHNICAL FIELD

[0001] The utility model relates to space vehicle technical field especially relates to a rope anti-hooking device and space vehicle deployment mechanism. BACKGROUND

[0002] At present in the field of space vehicles, large deployable mechanisms are urgently needed to provide larger area battery arrays and larger antenna sizes to meet the higher functional and performance index requirements of space vehicles. Tensioned ropes play an important role in controlling the deployment speed of large deployment mechanisms, enhancing the rigidity of deployment mechanisms, and adjusting the geometric accuracy of the deployment array. Because the ropes are easily hooked by the protruding parts of the space vehicle during the control of the deployment process of the deployment mechanism, the normal release of the ropes is affected.

[0003] Therefore, there is an urgent need to provide a rope anti-hooking device for a space vehicle deployment mechanism. SUMMARY

[0004] To solve the above technical problems, the utility model provides a rope anti-hooking device and a space vehicle deployment mechanism. The utility model aims to overcome the shortcomings of the prior art and provide a rope anti-hooking device for a deployment mechanism. In the folded state of the deployment mechanism, the ropes are folded according to a certain method (such as a running knot). When the mechanism is deployed, the folded ropes are released in order, eliminating the risk of hooking of the ropes and ensuring that the large deployment mechanism can be smoothly deployed.

[0005] Because the space vehicle faces a low-temperature environment after reaching space, the rope anti-hooking device of the present application needs to consider the influence of temperature changes on its stability.

[0006] The utility model provides a rope anti-hooking device on one aspect, be applied to space vehicle deployment mechanism, at least include: fixed support, mobile support and central support, the fixed support bottom is installed to the fixed plate of space vehicle through shape memory alloy gasket, the mobile support bottom is installed to the deployment plate of space vehicle through shape memory alloy gasket, the central support is set up between the fixed support and the mobile support, the central support top is equipped with the rope winding drum, the rope winding drum inside is equipped with the groove for the rope winding and release, the first end of the rope is connected with the fixed support top, the second end is connected with the mobile support top, and the rope between both ends is wound in the rope winding drum.

[0007] In one embodiment, the fixed support, the central support and the mobile support are hollow structures.

[0008] In one embodiment, the central support is installed to the fixed plate through a shape memory alloy gasket.

[0009] In one embodiment, the fixed support, the central support and the mobile support are coaxially and collinearly arranged.

[0010] In one embodiment, a plurality of the central supports are arranged between the fixed support and the mobile support, and each of the central supports is provided with the rope winding drum on the top thereof, and the part of the rope between the two ends is wound in the rope winding drum.

[0011] In any one of the above embodiments, the fixed support is provided with a first mounting hole for the rope to pass through on the top thereof, and the first end of the rope is connected to the fixed support by a clamp after passing through the first mounting hole.

[0012] In one embodiment, the mobile support is provided with a second mounting hole for the rope to pass through on the top thereof, and the second end of the rope is connected to the mobile support by a clamp after passing through the second mounting hole.

[0013] In one embodiment, the first mounting hole and the second mounting hole are coaxially and collinearly arranged.

[0014] In one embodiment, the inner surface of the channel of the rope winding drum is covered with a low-friction coefficient material.

[0015] The utility model also provides a spacecraft deployment mechanism comprising the rope anti-hooking device of any one of the above embodiments.

[0016] The rope anti-hooking device and the spacecraft deployment mechanism solve the problem of storage and arrangement of the tensioning rope during winding, and also realize the orderly release of the rope in a nearly tensioned state, effectively avoid the hooking and winding of the rope with the spacecraft body or external structure during deployment, improve the deployment reliability, and completely avoid the risk of rope hooking. At the same time, the rope anti-hooking device is provided with a shape memory alloy gasket at the connection with the spacecraft deployment mechanism, which automatically compensates for the installation gap when the temperature changes in space.

[0017] After reading the detailed description and viewing the drawings, those skilled in the art will recognize additional features and advantages. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the utility model or the prior art, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the utility model, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0019] Figure 1It is the overall structure schematic diagram of the rope anti-hooking device of the embodiment of the utility model.

[0020] Figure 2 It is the cross section schematic diagram of the first shape memory alloy gasket of the embodiment of the utility model.

[0021] Figure 3 It is the cross section schematic diagram of the second shape memory alloy gasket of the embodiment of the utility model. DETAILED DESCRIPTION

[0022] The features and exemplary embodiments of each aspect of the utility model will be described in detail below, in order to make the purpose, technical scheme and advantages of the utility model more clear and apparent, the utility model will be described in further detail below in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the utility model, for example, the principle of the utility model, and are not configured to limit the utility model. In addition, the components in the drawings are not necessarily drawn to scale. For example, the size of some components in the drawings can be enlarged for other components or areas to help understand the embodiments of the utility model.

[0023] The orientation words appearing in the following description are the directions shown in the drawings, and are not limited to the specific structure of the embodiments of the utility model. In the description of the utility model, it should be pointed out that, unless otherwise specified, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0024] In addition, the terms "including", "containing", "having" or any other variant thereof are intended to cover non-exclusive inclusion, so that the inclusion of a series of element structures or components not only includes those elements, but also includes other components not explicitly listed or inherent in the structure, component. Without more limitation, the elements defined by the sentence "including" do not exclude the presence of other same elements in the article or device including the elements.

[0025] Spatially relative terms such as "beneath", "below", "lower", "under", "above", "upper", "over", and "on" are used for ease of description to explain the positioning of one element relative to a second element. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in addition to the orientation depicted in the figures. For example, if a device described is turned over, elements described as "below" or "beneath" other elements would then be oriented "above" the other elements - the same applies to the adjectives "above" and "below". For another example, if a device is turned over and a first element is described as "on" a second element, it will be understood that, upon turning the device over and looking at the device from the first orientation, the first element is now oriented "below" the second element. Similarly, the term "element" is used to describe any element, region, part, section, etc. and is not intended to be limited to a single element unless specifically designated as such. Like terms are used to describe like elements throughout the description.

[0026] The present application can be implemented without some of these specific details, which are known to those skilled in the art. The following description of the embodiments is merely provided to provide a better understanding of the present application by showing examples of the present application.

[0027] The present application provides a rope anti-hooking device applicable to a large deployable mechanism. The rope anti-hooking device can be used to fold the rope in the folded state of the deployable mechanism. The folded rope can be released in order when the deployable mechanism is unfolded, and the rope is tensioned after the deployable mechanism is unfolded to the position. Since the rope anti-hooking device is applied to a spacecraft, it will face a low-temperature environment in space. In order to increase stability and prevent a gap from being formed after the connection part is cold contracted, the rope anti-hooking device of the present application is provided with a shape memory alloy at the connection part.

[0028] Referring to Figure 1 and Figure 2In particular, the rope anti-hooking device comprises at least a fixed support 1, a movable support 2, a central support 3 and a rope winding drum 4. The fixed support 1 is installed on the fixed plate of the spacecraft through the first shape memory alloy gasket 8 at the bottom, and the movable support 2 is installed on the unfolding plate of the spacecraft through the first shape memory alloy gasket 8 at the bottom. The central support 3 is arranged between the fixed support 1 and the movable support 2, and the top of the central support 3 is provided with the rope winding drum 4, and the rope winding drum 4 is internally provided with a channel for winding and releasing the rope 5. The first end of the rope 5 is connected with the fixed support 1, the second end is connected with the movable support 2, and the rope between the two ends is wound in the rope winding drum 4. During the process that the unfolding mechanism of the spacecraft changes from the winding state to the unfolding state, the movable support 2 moves along the unfolding direction (the direction away from the fixed support 1) with the moving plate, and drags the rope 5 to be orderly pulled out from the rope winding drum 4. During the unfolding and releasing process, the rope 5 is always approximately tensioned and will not be randomly fluttered, and after the unfolding mechanism is unfolded to the position, the movable support at the far end stops moving, and the rope 5 reaches the tensioned state. The rope winding drum 4 of the embodiment not only has the function of accommodating, but also has the function of tensioning the rope. With the rope being pulled out, the rope winding drum 4 can keep the rope in the tensioned state at any time, so as to effectively avoid that the rope is hooked by the edges and corners of the spacecraft unfolding plate.

[0029] The rope winding drum 4 has two outlets, the first outlet is arranged towards the fixed support 1, and the second outlet is arranged towards the movable support 2. The rope 5 can be wound out along the first outlet or the second outlet alone, or can be wound out along the first outlet and the second outlet simultaneously.

[0030] The rope anti-hooking device of the embodiment of the utility model adopts the shape memory alloy gasket at the connecting positions of the fixed support and the spacecraft body and the connecting positions of the movable support and the spacecraft body, so that the installation gap is automatically compensated when the temperature changes, and the stability and reliability of the rope anti-hooking device of the embodiment are increased. Under the temperature change or mechanical stress, the shape memory alloy gasket can actively adjust the deformation, restore the preset shape and continuously provide the compression force at the installation position.

[0031] Further, since the rope anti-hooking device of the utility model is applied to the spacecraft, in order to avoid increasing the load of the spacecraft, the fixed support 1, the central support 3 and the movable support 2 can be designed as the hollow structure without affecting the structural stability. Further, the shape memory alloy can be designed as the hollow structure, so that the weight of the rope anti-hooking device of the utility model is greatly reduced.

[0032] The rope anti-hooking device is applied to the unfolding mechanism of a spacecraft, wherein the fixed support is fixedly arranged on the non-unfolding part (fixed plate) of the unfolding mechanism, and the position of the fixed support is unchanged in the unfolding process of the unfolding mechanism. The movable support is fixedly arranged on the unfolding part (movable plate) of the unfolding mechanism, and the movable support moves with the unfolding part in the unfolding process of the unfolding mechanism. The central support can be arranged on the non-unfolding part (fixed plate) of the unfolding mechanism or on the unfolding part (movable plate).

[0033] For example, the central support 3 is arranged on the fixed plate close to the fixed support 1. In this embodiment, the positions of the central support 3 and the fixed support 1 are unchanged, and the distance between the central support 3 and the fixed support 1 is unchanged in the unfolding and releasing process of the spacecraft unfolding mechanism. At this time, the rope is orderly released along the winding drum 4 to the opening (second outlet) on the side of the movable support 2, until the unfolding mechanism is unfolded to the position and is tensioned.

[0034] Alternatively, in one embodiment, the central support is arranged on the movable plate close to the movable support. With the unfolding and releasing of the unfolding mechanism, the central support 3 moves with the movable plate correspondingly, and the distance between the movable support 2 and the central support 3 can be unchanged or changed in this process. Specifically, the movable plate can be divided into different unfolding plates, and the unfolding degrees of the unfolding plates are not completely same. If the movable support 2 and the central support 3 are arranged on different unfolding plates, the distance between the movable support 2 and the central support 3 is changed in the unfolding process of the unfolding mechanism. If the movable support 2 and the central support 3 are arranged on the same unfolding plate, the distance between the movable support 2 and the central support 3 is unchanged in the unfolding process of the unfolding mechanism.

[0035] Therefore, after the winding drum 4 winds the middle part of the rope 5, the winding drum 4 is arranged to be capable of winding the rope out of the first outlet and the second outlet.

[0036] Meanwhile, referring to Figure 1 and Figure 3 In one embodiment, the central support 3 is installed on the fixed plate through a second shape memory alloy gasket 9. In order to reduce the weight, the second shape memory alloy gasket 9 is designed as a rectangular ring structure, and the four corners of the periphery are provided with mounting holes for matching the central support.

[0037] In the above embodiment, in order to further avoid the hooking risk of the rope, the fixed support 1, the central support 3 and the movable support 2 can be coaxially and collinearly arranged. Such arrangement can also realize the control of the unfolding stiffness and array accuracy of the mechanism, and improve the unfolding reliability.

[0038] Further, if the size of the unfolding mechanism after unfolding is large, resulting in a long length of the required rope, and it is difficult to fully wind the long rope in one winding drum, a method of winding the rope in the winding drums in sequence after connecting the winding drums in series can be used. Specifically, a plurality of central supports can be arranged between the fixed support and the moving support, and a winding drum is arranged on the top of each central support and the bottom of each central support is connected to the spacecraft through the second shape memory alloy. In this way, the part of the rope between the two ends can be wound in the winding drums in sequence, and the problem of storage and arrangement of the rope when the large unfolding mechanism is tensioned is solved.

[0039] Referring to Figure 1 In any of the above embodiments, the connection mode of the rope and the fixed support and the connection mode of the rope and the moving support can be freely selected, and the connection is stable and reliable. For example, the bottom of the fixed support 1 is arranged on the fixed plate of the spacecraft unfolding mechanism, the top of the fixed support 1 is provided with a first mounting hole through which the rope 5 passes, and the first end of the rope 5 is connected to the fixed support 1 through the clamp 6 after passing through the first mounting hole. The bottom of the moving support 2 is arranged on the moving plate of the spacecraft unfolding mechanism, the top of the moving support 2 is provided with a second mounting hole through which the rope 5 passes, and the second end of the rope 5 is connected to the moving support 2 through the clamp 7 after passing through the second mounting hole.

[0040] Specifically, the fixed support, the central support and the moving support can be installed on the spacecraft through bolts, and a corresponding shape memory alloy gasket is arranged at the installation position. Then, the length of the required rope is determined according to the size of the spacecraft unfolding mechanism, the two ends of the rope are fixed to the fixed support and the moving support through the clamp, the middle part of the rope is wound in the winding drum of the central support, and the axial position of the rope in the tensioned state is limited through the clamp.

[0041] In the above embodiment, the first mounting hole and the second mounting hole are coaxially and collinearly arranged.

[0042] The rope anti-hooking device can be arranged in the winding drum, and the rope is wound in the grooves in the form of a running knot. In this way, the rope can be restrained by the running knot at all times before the unfolding mechanism is unfolded, and after the unfolding mechanism starts to unfold, the running knot of the rope is opened in an orderly manner, so that the rope is released in an orderly manner under a certain tension, thereby avoiding the randomness and uncertainty of the position of the rope and eliminating the risk of mutual hooking.

[0043] In order to avoid the friction of the rope with the inner wall of the groove of the winding drum from hindering the unwinding of the rope, a low-friction coefficient material can be covered on the inner surface of the groove of the winding drum, thereby obviously reducing the failure rate of the unwinding of the rope.

[0044] The above embodiments can be combined with each other, and have corresponding technical effects.

[0045] The utility model provides a spacecraft unfolding mechanism, and the spacecraft unfolding mechanism at least includes the rope anti-hooking device in any one of the above embodiment.

[0046] The above merely describes the preferred embodiments of the utility model and is not intended to limit the utility model. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. A rope anti-hooking device applied to a spacecraft deployment mechanism, characterized in that, At least comprising: a fixed support, a moving support and a central support; the fixed support is installed on the fixed plate of the spacecraft through a shape memory alloy pad, the moving support is installed on the unfolding plate of the spacecraft through a shape memory alloy pad, the central support is arranged between the fixed support and the moving support; the top of the central support is provided with a rope winding drum, the inside of the rope winding drum is provided with a channel for winding and releasing the rope; The first end of the rope is connected with the top of the fixed support, the second end of the rope is connected with the top of the moving support, and the rope between the two ends is wound in the rope winding drum.

2. The rope anti-entanglement device of claim 1, wherein, The fixed support, the central support and the moving support are hollow structures.

3. The rope anti-entanglement device of claim 2, wherein, The central support is installed on the fixed plate through a shape memory alloy pad.

4. The rope anti-entanglement device of claim 3, wherein, The fixed support, the central support and the moving support are coaxial and collinear.

5. The rope anti-entanglement device of claim 1, wherein, A plurality of central supports are arranged between the fixed support and the moving support, the top of each central support is provided with a rope winding drum, and the part of the rope between the two ends is wound in each rope winding drum.

6. Rope anti-entanglement device according to any one of claims 1 to 5, characterized in that The top of the fixed support is provided with a first mounting hole through which the rope passes; the first end of the rope is connected with the fixed support through a clamp after passing through the first mounting hole.

7. The rope anti-entanglement device of claim 6, wherein, The top of the moving support is provided with a second mounting hole through which the rope passes; the second end of the rope is connected with the moving support through a clamp after passing through the second mounting hole.

8. The rope anti-entanglement device of claim 7, wherein, The first mounting hole and the second mounting hole are coaxial and collinear.

9. The rope anti-entanglement device of claim 1, wherein, The inner surface of the channel of the rope winding drum is covered with a low-friction coefficient material.

10. A spacecraft deployment mechanism, characterized by, At least comprising the rope anti-hooking device according to any one of claims 1 to 9.

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