A wedge-type hinge deployment mechanism

Abstract

The present invention provides a wedge-type hinge deployment mechanism, which relates to the field of aerospace technology and includes a wedge-type hinge. The wedge-type hinge specifically includes: a hook hinge assembly, whose circumferential surface includes an interconnected circular arc surface and a limiting surface, and the limiting surface is located inside the circle where the circular arc surface is located; a locking hinge assembly, including an interconnected locking hinge body and a limiting wedge, and the locking hinge assembly is rotationally connected to the hook hinge assembly; when the locking hinge assembly rotates relative to the hook hinge assembly, the limiting wedge moves along the circular arc surface until it abuts the limiting surface. The present invention uses a wedge-type hinge to rotationally connect the components of aerospace vehicles such as solar wings and sun visors, thereby realizing folding and unfolding functions; the limiting wedge moves along the circular arc surface to realize unfolding between the components; when the locking hinge body rotates to a certain angle, the limiting wedge abuts against the limiting surface to limit rotation, thereby realizing a locking function, avoiding shaking between the components, increasing the locking stiffness, improving the locking effect, and ensuring the stable operation of the aerospace vehicle.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a wedge-type hinge deployment mechanism. Background Art

[0002] The solar panels, sun visors and other components of a spacecraft usually need to be folded in advance for launch, and then unfolded and locked through a hinged unfolding mechanism to achieve functions such as the solar panels unfolding to provide energy for the satellite.

[0003] However, existing hinge deployment mechanisms usually use a locking hook embedded in a slide to achieve deployment locking. There is an inevitable gap between the locked locking hook and the slide, which may cause shaking between the components of the deployed spacecraft, resulting in poor locking stiffness and heavy weight. Summary of the Invention

[0004] The problem solved by the present invention is how to improve the locking effect of the hinge deployment mechanism.

[0005] In order to solve the above problems, the present invention provides a wedge hinge deployment mechanism, including a wedge hinge, wherein the wedge hinge specifically includes:

[0006] A hook hinge assembly, wherein the circumferential surface of the hook hinge assembly includes an arc surface and a limiting surface connected to each other, and the limiting surface is located inside the circle where the arc surface is located;

[0007] A locking hinge assembly, the locking hinge assembly comprising a locking hinge body and a limiting wedge that are connected to each other, the locking hinge assembly being rotatably connected to the hook hinge assembly;

[0008] When the locking hinge assembly rotates relative to the hook hinge assembly, the limiting wedge is adapted to move along the arc surface until it abuts against the limiting surface.

[0009] Optionally, the wedge hinge further comprises a first torsional elastic member, one end of the first torsional elastic member is connected to the hook hinge assembly, and the other end is connected to the locking hinge body.

[0010] Optionally, the locking hinge assembly also includes a second torsional elastic member, one end of the second torsional elastic member is connected to the limiting wedge block, and the other end is connected to the locking hinge body, and one end of the limiting wedge block is rotatably connected to the locking hinge body, and the second torsional elastic member is suitable for driving the other end of the limiting wedge block to abut against the circumferential surface of the hook hinge assembly.

[0011] Optionally, the wedge-type hinge expansion mechanism includes at least two wedge-type hinges, and the wedge-type hinge also includes a linkage wheel and a linkage rope, the linkage wheel is installed on the locking hinge body or the hook hinge assembly, and the two ends of the linkage rope are respectively installed on the linkage wheels of two of the wedge-type hinges.

[0012] Optionally, the linkage rope includes a fixed end, a first adjusting member and a linkage rope body, the fixed end is sleeved on both ends of the linkage rope body, the first adjusting member is used to adjust the tension of the linkage rope body, and the first adjusting member is located at one end of the linkage rope body.

[0013] Optionally, the linkage rope body is a Kevlar rope.

[0014] Optionally, the linkage wheel includes a linkage wheel body and a rope end fixing portion, the rope end fixing portion is arranged on the outer side wall of the linkage wheel body, and the central axis of the rope end fixing portion is tangent to the linkage wheel body.

[0015] Optionally, the wedge hinge further includes a rope passing rack, which is used to support the linkage rope body and is installed on the hook hinge assembly or the lock hinge body.

[0016] Optionally, the wedge-type hinge further includes a second adjusting member, which is disposed on the hook hinge assembly or the lock hinge body, and is used to adjust the unfolding angle between the hook hinge assembly and the lock hinge body.

[0017] Optionally, the limiting surface is a planar structure, the circumferential surface of the limiting wedge block includes an involute curved surface, and the limiting wedge block is suitable for abutting against the limiting surface through the involute curved surface.

[0018] Compared with the prior art, the wedge-type hinge deployment mechanism described in the present invention uses a wedge-type hinge to rotationally connect the components of aerospace vehicles such as solar wings and sun visors, thereby realizing the folding and unfolding functions between the components of the aerospace vehicle; when it is necessary to unfold, for example, the solar wing, the limiting wedge can move along the arc surface to facilitate the rotation of the locking hinge body relative to the hook hinge assembly, thereby realizing the unfolding between the components of the aerospace vehicle; when the locking hinge body is rotated to a certain angle relative to the hook hinge assembly, since the limiting wedge is no longer limited by the arc surface, the limiting wedge can abut against the limiting surface inside the circle where the arc surface is located, thereby limiting the rotation of the locking hinge body relative to the hook hinge assembly in at least one direction (for example, limiting the rotation of the locking hinge body relative to the hook hinge assembly in the counterclockwise direction around the Y-axis in the figure or the figure), realizing the locking function of the hook hinge assembly and the locking hinge body after deployment, avoiding the shaking between the components such as the solar wing to a certain extent, and compared with the hinge deployment mechanism in the form of a lock hook embedded in a slide, the locking stiffness is improved, the locking effect is improved, and the stable operation of the aerospace vehicle is ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic cross-sectional view of a wedge-type hinge deployment mechanism provided by an embodiment of the present invention when folded;

[0020] Figure 2 A schematic cross-sectional view of a wedge-type hinge deployment mechanism according to an embodiment of the present invention when deployed;

[0021] Figure 3 A schematic diagram of the partial structure of a wedge-type hinge provided in an embodiment of the present invention after being applied to a solar wing;

[0022] Figure 4 The embodiment of the present invention provides Figure 3 The enlarged schematic diagram of point Ⅰ in the middle;

[0023] Figure 5 The embodiment of the present invention provides Figure 3 The enlarged schematic diagram of the middle part Ⅱ;

[0024] Figure 6 A schematic cross-sectional view of the fixed end and the first adjusting member provided in an embodiment of the present invention.

[0025] Description of reference numerals:

[0026] 1. Hook hinge assembly; 11. Arc surface; 12. Limiting surface; 13. Hook hinge connection; 2. Lock hinge assembly; 21. Lock hinge body; 22. Limiting wedge; 221. Involute surface; 23. Second torsional elastic member; 24. Lock hinge connection; 3. First torsional elastic member; 4. Linkage wheel; 41. Linkage wheel body; 42. Rope end fixing part; 5. Linkage rope; 51. Linkage rope body; 52. Fixed end; 521. Adjusting cap; 522. Core shaft; 523. Rope loop; 53. First adjusting member; 531. First adjusting nut; 532. First adjusting screw; 6. Rope passing frame; 7. Second adjusting member; 71. Second adjusting nut; 72. Second adjusting screw; 800. Solar wing; 900. Solar wing connection frame. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0028] It should be noted that in the coordinate system XYZ provided herein, the positive direction of the X axis represents the right, the negative direction of the X axis represents the left, the positive direction of the Y axis represents the back, the negative direction of the Y axis represents the front, the positive direction of the Z axis represents the top, and the negative direction of the Z axis represents the bottom. At the same time, it should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein.

[0029] An embodiment of the present invention provides a wedge-type hinge deployment mechanism, including a wedge-type hinge, and the wedge-type hinge specifically includes: a hook hinge assembly 1, the circumferential surface of the hook hinge assembly 1 includes an arc surface 11 and a limiting surface 12 connected to each other, and the limiting surface 12 is located inside the circle where the arc surface 11 is located; a locking hinge assembly 2, the locking hinge assembly 2 includes a locking hinge body 21 and a limiting wedge 22 connected to each other, and the locking hinge assembly 2 is rotatably connected to the hook hinge assembly 1; when the locking hinge assembly 2 rotates relative to the hook hinge assembly 1, the limiting wedge 22 is suitable for moving along the arc surface 11 until it abuts against the limiting surface 12.

[0030] Specifically, combined Figures 1 to 3As shown, the following describes an embodiment of the present invention by taking the solar wing 800 as an example, the hook hinge assembly 1 also includes a hook hinge connection part 13 integrally connected thereto, the hook hinge connection part 13 is relatively fixedly connected to the solar wing 800 by a bolt fastener, the locking hinge assembly 2 also includes a locking hinge connection part 24 integrally connected to the locking hinge body 21, the locking hinge connection part 24 is relatively fixedly connected to another solar wing 800 by a bolt fastener, the hook hinge assembly 1 is hinged to the locking hinge body 21 so that the locking hinge body 21 is relatively fixed relative to the hook hinge assembly 1. Figure 1 or Figure 2 The locking hinge body 21 is rotated clockwise until the limiting wedge 22 abuts against the limiting surface 12 to limit the locking hinge body 21 relative to the hook hinge assembly 1. Figure 1 or Figure 2 Rotate counterclockwise.

[0031] Exemplarily, the limiting wedge 22 is a latch or a structure similar to a latch, which can be extended and retracted toward the hinge center between the hook hinge assembly 1 and the lock hinge body 21. When the two solar wings 800 are folded, the angle between the two solar wings 800 is 0°. Due to the limitation of the arc surface 11, the limiting wedge 22 retracts to a certain extent in the direction away from the hinge center; when the two solar wings 800 are unfolded, the two solar wings 800 rotate relative to the hook hinge assembly 1 and the lock hinge body 21 until the angle between them is 180°. After the latch slides to the position of the limiting surface 12 relative to the arc surface 11, since the limiting surface 12 is located inside the circle where the arc surface 11 is located (that is, on the side of the curved contour line where the arc surface 11 is located close to the center of curvature), the latch can be extended toward the hinge center and then abut against the limiting surface 12, so as to limit the rotation of the hook hinge assembly 1 relative to the lock hinge assembly 2 to a certain extent (not shown in the diagram of this solution).

[0032] It should be noted that the arc surface 11 can include an arc surface 11 formed by a partial curve of a perfect circle, or an arc surface 11 formed by a partial curve of an ellipse. There is no specific restriction on its shape, as long as it can not interfere with the movement of the limiting wedge 22 along the arc surface 11 as the locking hinge body 21 rotates; in addition, the angle through which the corresponding locking hinge body 21 rotates when the parts of the aerospace vehicle are unfolded and folded (i.e., the unfolding angle) can be specifically designed according to actual needs. For example, in order to avoid interference with other parts, the angle between the parts when folding is set to an angle greater than 0°. Under such a design, the unfolding angle can be less than 180°.

[0033] Compared with the prior art, the wedge-type hinge deployment mechanism described in the embodiment of the present invention uses a wedge-type hinge to rotatably connect the components of aerospace vehicles such as solar wings 800 and sun visors, thereby realizing the folding and unfolding functions between the components of the aerospace vehicle; when it is necessary to unfold, for example, the solar wing 800, the limiting wedge 22 can move along the arc surface 11 to facilitate the rotation of the locking hinge body 21 relative to the hook hinge assembly 1, thereby realizing the deployment between the components of the aerospace vehicle; when the locking hinge body 21 is rotated to a certain angle relative to the hook hinge assembly 1, since the limiting wedge 22 is no longer limited by the arc surface 11, the limiting wedge 22 can abut against the limiting surface 12 inside the circle where the arc surface 11 is located, thereby limiting the rotation of the locking hinge body 21 relative to the hook hinge assembly 1 in at least one direction (for example, limiting the rotation of the locking hinge body 21 relative to the hook hinge assembly 1 in at least one direction). Figure 1 or Figure 2 The locking function of the hook hinge assembly 1 and the locking hinge body 21 after deployment is realized, which to a certain extent avoids the shaking between the components such as the solar wing 800, increases the locking stiffness, improves the locking effect, and ensures the stable operation of the spacecraft.

[0034] Optionally, the wedge hinge further includes a first torsional elastic member 3 , one end of which is connected to the hook hinge assembly 1 , and the other end of which is connected to the locking hinge body 21 .

[0035] Specifically, combined Figure 1 and Figure 2 As shown, the first torsional elastic member 3 is a scroll spring. When the solar wing 800 is folded, the deployment angle between the hook hinge assembly 1 and the locking hinge body 21 is 0°. At this point, the scroll spring has a certain amount of elastic potential energy. When the solar wing 800 is deployed, the elastic potential energy of the scroll spring is gradually converted into kinetic energy, causing the locking hinge body 21 to rotate clockwise about the Y-axis in the figure relative to the hook hinge assembly 1. As the locking hinge body 21 rotates, the limiting wedge 22 moves along the arc surface 11 to the position of the limiting surface 12. The limiting wedge 22 then abuts the limiting surface 12, locking the solar wing 800 after deployment.

[0036] In this way, the elastic potential energy is stored by the first torsional elastic member 3 and converted into kinetic energy to drive the locking hinge body 21 to rotate relative to the hook hinge assembly 1, thereby realizing the automatic deployment of the components of the aerospace vehicle. Moreover, since the first torsional elastic member 3 is elastic, it can be reused many times, so that, for example, the components of the solar wing 800 can be folded again after deployment.

[0037] Optionally, the locking hinge assembly 2 also includes a second torsional elastic member 23, one end of the second torsional elastic member 23 is connected to the limiting wedge block 22, and the other end is connected to the locking hinge body 21, and one end of the limiting wedge block 22 is rotatably connected to the locking hinge body 21, and the second torsional elastic member 23 is suitable for driving the other end of the limiting wedge block 22 to abut against the circumferential surface of the hook hinge assembly 1.

[0038] Specifically, combined Figure 1 and Figure 2 As shown, the second torsional elastic member 23 is a torsion spring. During assembly, the wedge-type hinge deployment mechanism typically requires pre-compression of the torsion spring before it is mounted on the rotating shaft of the locking hinge body 21. The limiting wedge 22 is rotatably mounted on the rotating shaft about the Y-axis in the figure. When the solar wing 800 is not deployed, one end of the torsion spring abuts the limiting wedge 22, causing the limiting wedge 22 to abut against the arc surface 11, while the other end abuts against the locking hinge body 21. After the solar wing 800 is deployed, the locking hinge body 21 rotates relative to the hook hinge assembly 1 until the limiting wedge 22 moves to the position of the limiting surface 12. The elastic potential energy of the torsion spring is converted into kinetic energy to drive the limiting wedge 22 to rotate until the surface of the limiting wedge 22 abuts against the limiting surface 12.

[0039] In this way, the elastic potential energy is stored by the second torsional elastic member 23 and converted into kinetic energy to drive the limiting wedge block 22 to move relative to the locking hinge body 21 to abut against the circumferential surface of the hook hinge assembly 1. When the locking hinge body 21 rotates relative to the hook hinge assembly 1, the limiting wedge block 22 moves along the arc surface 11 until it reaches the position of the limiting surface 12. The second torsional elastic member 23 drives the limiting wedge block 22 to abut against the limiting surface 12, so as to realize the locking function of the hook hinge assembly 1 and the locking hinge body 21 after unfolding. Moreover, since the second torsional elastic member 23 is elastic, it can be reused many times, so that, for example, the components of the solar wing 800 can be folded again after unfolding.

[0040] Optionally, the limiting surface 12 is a planar structure, the circumferential surface of the limiting wedge block 22 includes an involute curved surface 221 , and the limiting wedge block 22 is suitable for abutting against the limiting surface 12 through the involute curved surface 221 .

[0041] Specifically, combined Figure 1 and Figure 2 As shown, the projection of the involute surface 221 on the ZX plane in the figure is an involute arc, and the projection of the limiting surface 12 on the ZX plane in the figure is a straight line. When the locking hinge body 21 rotates clockwise relative to the hook hinge assembly 1 in the figure to an extended angle of 180°, the limiting wedge 22 moves to the position of the limiting surface 12, and the involute surface 221 abuts the limiting surface 12 of the planar structure.

[0042] In this way, the pressure angle at the abutment position between the involute surface 221 and the limiting surface 12 is smaller than the friction angle, thereby realizing mechanical self-locking of the hook hinge assembly 1 and the locking hinge body 21 after deployment; and when the deployment angle has a smaller range of deviation, the limiting wedge block 22 can adaptively move relative to the locking hinge body 21 (for example, the limiting wedge block 22 rotates around the Y-axis in the figure) to maintain the abutment between the involute surface 221 and the limiting surface 12, thereby improving the adaptability of the wedge-type hinge deployment mechanism when the deployment angle of, for example, the solar wing 800 has a certain deviation.

[0043] Optionally, the wedge-type hinge expansion mechanism includes at least two wedge-type hinges, and the wedge-type hinge also includes a linkage wheel 4 and a linkage rope 5, the linkage wheel 4 is installed on the locking hinge body 21 or the hook hinge assembly 1, and the two ends of the linkage rope 5 are respectively installed on the linkage wheels 4 of two of the wedge-type hinges.

[0044] For example, in combination Figures 1 to 5 As shown, two solar wings 800 are rotatably connected to each other through a wedge-type hinge, one of the solar wings 800 is rotatably connected to the solar wing connecting frame 900 through another wedge-type hinge, and the solar wing 800 is connected to the main body of the spacecraft through the solar wing connecting frame 900. The linkage wheel 4 is relatively fixedly mounted on the locking hinge body 21, and one end of the linkage rope 5 is mounted on Figure 4 (i.e. the enlarged view of position Ⅰ in FIG3 ) is shown on the lock hinge body 21, and the other end is mounted on Figure 5 (Right now Figure 3 The locking hinge body 21 shown in the enlarged view at position II in the middle is engaged to enable the linkage wheels 4 of the two wedge hinges to rotate synchronously (i.e., to be linked). Similarly, when the wedge hinge deployment mechanism includes more than two wedge hinges, a similar solution can also be used to achieve linkage of multiple wedge hinges.

[0045] In this way, by respectively installing the two ends of the linkage rope 5 on the linkage wheels 4 of two of the multiple wedge-type hinges, the linkage of the wedge-type hinges is achieved, thereby realizing the function of synchronous folding and synchronous unfolding between multiple components such as the solar wing 800.

[0046] Optionally, combined Figure 3 and Figure 4 As shown, the linkage rope 5 includes a fixed end 52, a first adjusting member 53 and a linkage rope body 51. The fixed end 52 is sleeved on both ends of the linkage rope body 51. The first adjusting member 53 is used to adjust the tension of the linkage rope body 51, and the first adjusting member 53 is located at one end of the linkage rope body 51.

[0047] Specifically, combined Figure 6As shown, the fixed end 52 includes an adjusting cap 521, a core shaft 522 and a rope loop 523. One end of the linkage rope body 51 is loosened and passed through the inside of the rope loop 523. The core shaft 522 is inserted into the loosened part of the linkage rope body 51, and then the adjusting cap 521 is used to abut against the core shaft 522 in the positive direction of the Z axis in the figure to tighten the loosened part of the linkage rope body 51 between the core shaft 522 and the rope loop 523. The first adjusting member 53 includes a first adjusting nut 531 and a first adjusting screw 532 which are threadedly connected to each other. The first adjusting nut 531 is installed on the linkage wheel 4, the first adjusting screw 532 is installed on the rope loop 523, and the linkage rope body 51 is passed through a through hole opened on the first adjusting screw 532. When the first adjusting nut 531 rotates relative to the first adjusting screw 532, the first adjusting screw 532 is screwed in or out of the first adjusting nut 531 along the Z-axis in the figure to adjust the distance between the fixed end 52 and the linkage wheel 4, thereby adjusting the tension of the linkage rope body 51.

[0048] In this way, the tension of the linkage rope body 51 is adjusted by the first adjusting member 53 so as to achieve better transmission effects of the linkage wheels 4 of different wedge-type hinges, and further to achieve higher synchronization when the wedge-type hinges are unfolded.

[0049] Optionally, the linkage wheel 4 includes a linkage wheel body 41 and a rope end fixing portion 42 , wherein the rope end fixing portion 42 is provided on an outer side wall of the linkage wheel body 41 , and a central axis of the rope end fixing portion 42 is tangent to the linkage wheel body 41 .

[0050] Specifically, combined Figure 4 As shown, the rope end fixing part 42 is integrally connected to the linkage wheel body 41. The rope end fixing part 42 is provided with a central through hole to relatively fixedly connect the linkage rope body 51. The central axis of the central through hole (i.e. the central axis of the rope end fixing part 42) is tangent to the circle where the linkage wheel body 41 is located.

[0051] In this way, compared with setting the rope end fixing part 42 on the side of the linkage wheel body 41 (that is, the surface located at the circle where the linkage wheel body 41 is located), this embodiment reduces the bending of the linkage rope body 51 by setting the central axis of the rope end fixing part 42 to be tangent to the circle where the linkage wheel body 41 is located, so that the linkage rope body 51 is consistent with the transmission direction, reduces friction resistance, and further improves the synchronization of transmission between different wedge-type hinges through the linkage wheel 4 and the linkage rope 5.

[0052] Optionally, the linkage rope body 51 is a Kevlar rope.

[0053] In this way, compared with using a steel wire rope with poor flexibility as the linkage rope body 51, the Kevlar rope used in this embodiment is more flexible and can achieve a smaller turning radius. Therefore, the size parameters of the linkage wheel 4 can be reduced accordingly, so that the overall weight of the wedge-type hinge deployment structure is reduced, thereby reducing the weight of the spacecraft.

[0054] Optionally, the wedge hinge further includes a rope passing rack 6 , which is used to support the linkage rope body 51 and is mounted on the hook hinge assembly 1 or the lock hinge body 21 .

[0055] Specifically, combined Figure 5 As shown, the rope frame 6 is installed on the hook hinge assembly 1, and the roller on the rope frame 6 supports the linkage rope body 51 so that there is a certain distance between the linkage rope body 51 and the solar wing 800.

[0056] In this way, by setting up a rope frame 6 to support the linkage rope body 51, the linkage rope body 51 will not interfere with the components of the solar wing 800, for example, during the transmission process, thereby avoiding damage to the components of the spacecraft; and the supporting force of the rope frame 6 facilitates increasing the tension of the linkage rope body 51, thereby improving the synchronization of transmission between different wedge-type hinges through the linkage wheel 4 and the linkage rope 5.

[0057] Optionally, the wedge-type hinge further includes a second adjusting member 7 , which is disposed on the hook hinge assembly 1 or the locking hinge body 21 , and is used to adjust the unfolding angle between the hook hinge assembly 1 and the locking hinge body 21 .

[0058] Specifically, combined Figure 1 and Figure 2 As shown, the second adjusting member 7 includes a second adjusting nut 71 and a second adjusting screw 72 that are threadedly connected to each other. One end of the second adjusting screw 72 is threadedly connected to the hook hinge assembly 1. When the solar wing 800 is unfolded, the other end of the second adjusting screw 72 faces the locking hinge body 21, and the locking hinge body 21 rotates relative to the hook hinge assembly 1 to the position of the second adjusting screw 72 and abuts against it.

[0059] Due to structural changes in the solar wing 800 and other factors, the spacecraft's flatness requirements for the solar wing 800 may change. The second adjusting screw 72 can be screwed into or out of the hook hinge assembly 1, and then the second adjusting nut 71 is tightened to fix the position of the second adjusting screw 72 relative to the hook hinge assembly 1. This allows the locking hinge body 21 to rotate relative to the hook hinge assembly 1 to the position of the second adjusting screw 72 and abut against it, thereby increasing or decreasing the deployment angle of the wedge hinge accordingly.

[0060] In this way, the unfolding angle of the hook hinge assembly 1 and the lock hinge body 21 is adjusted by the second adjusting member 7, so that the solar wing 800 connected to the wedge-type hinge can adjust the unfolding angle to adapt to working conditions with inconsistent flatness requirements for the solar wing 800.

[0061] Although the present disclosure is disclosed as above, the protection scope of the present disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A wedge-type hinge deployment mechanism, characterized in that: A wedge-type hinge is provided, wherein the wedge-type hinge specifically comprises: A hook hinge assembly (1), wherein the circumferential surface of the hook hinge assembly (1) comprises an arc surface (11) and a limiting surface (12) connected to each other, and the limiting surface (12) is located inside the circle where the arc surface (11) is located; A locking hinge assembly (2), the locking hinge assembly (2) comprising a locking hinge body (21) and a limiting wedge (22) connected to each other, the locking hinge assembly (2) being rotationally connected to the hook hinge assembly (1); When the locking hinge assembly (2) rotates relative to the hook hinge assembly (1), the limiting wedge (22) is adapted to move along the arc surface (11) until it abuts against the limiting surface (12); The wedge-type hinge further comprises a first torsional elastic member (3), one end of the first torsional elastic member (3) being connected to the hook hinge assembly (1), and the other end being connected to the locking hinge body (21); The locking hinge assembly (2) further includes a second torsional elastic member (23), one end of the second torsional elastic member (23) is connected to the limiting wedge block (22), and the other end is connected to the locking hinge body (21), and one end of the limiting wedge block (22) is rotatably connected to the locking hinge body (21), and the second torsional elastic member (23) is suitable for driving the other end of the limiting wedge block (22) to abut against the peripheral surface of the hook hinge assembly (1); The wedge-type hinge deployment mechanism includes at least two wedge-type hinges, and the wedge-type hinges further include a linkage wheel (4) and a linkage rope (5), wherein the linkage wheel (4) is mounted on the locking hinge body (21) or the hook hinge assembly (1), and the two ends of the linkage rope (5) are respectively mounted on the linkage wheels (4) of two of the wedge-type hinges; The limiting surface (12) is a planar structure, the circumferential surface of the limiting wedge (22) includes an involute curved surface (221), and the limiting wedge (22) is suitable for abutting against the limiting surface (12) via the involute curved surface (221); The fixed end (52) includes an adjusting cap (521), a core shaft (522) and a rope loop (523); The first adjusting member (53) comprises a first adjusting nut (531) and a first adjusting screw (532) that are threadedly connected to each other. The first adjusting nut (531) is mounted on the linkage wheel (4), the first adjusting screw (532) is mounted on the rope sleeve (523), and the linkage rope body (51) is passed through a through hole opened on the first adjusting screw (532).

2. The wedge-type hinge deployment mechanism according to claim 1, characterized in that: The linkage rope (5) comprises a fixed end (52), a first adjusting member (53) and a linkage rope body (51), wherein the fixed end (52) is sleeved on both ends of the linkage rope body (51), and the first adjusting member (53) is used to adjust the tension of the linkage rope body (51), and the first adjusting member (53) is located at one end of the linkage rope body (51).

3. The wedge hinge deployment mechanism according to claim 2, characterized in that: The linkage rope body (51) is a Kevlar rope.

4. The wedge-type hinge deployment mechanism according to claim 2, characterized in that: The linkage wheel (4) comprises a linkage wheel body (41) and a rope end fixing portion (42), wherein the rope end fixing portion (42) is arranged on an outer side wall of the linkage wheel body (41), and a central axis of the rope end fixing portion (42) is tangent to the linkage wheel body (41).

5. The wedge-type hinge deployment mechanism according to claim 2, characterized in that: The wedge-type hinge further comprises a rope rack (6), the rope rack (6) being used to support the linkage rope body (51), and the rope rack (6) being mounted on the hook hinge assembly (1) or the lock hinge body (21).

6. The wedge hinge deployment mechanism according to claim 1, characterized in that: The wedge hinge further comprises a second adjusting member (7), the second adjusting member (7) being arranged on the hook hinge assembly (1) or the locking hinge body (21), and the second adjusting member (7) being used to adjust the unfolding angle between the hook hinge assembly (1) and the locking hinge body (21).

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