Deployable and compacted release antenna mechanism

Abstract

The application provides a radiator mechanism capable of being repeatedly unfolded, folded, compressed and released in orbit, and is especially suitable for a space-earth shuttle. The radiator mechanism comprises a driving device, a driven hinge, a driving locking device and a radiator plate. One longitudinal side of the radiator plate is connected with a spacecraft body through the driving device and the driven hinge. The driving device is used for driving the radiator plate to be repeatedly unfolded and folded in orbit. The driving locking device comprises a locking unit arranged on the spacecraft body and a locking hook arranged on the radiator plate. The locking unit is used for locking and unlocking the locking hook, so that the radiator plate is repeatedly compressed and released.

Description

Technical Field

[0001] This invention relates to a thermal radiation mechanism, specifically a reusable and compressible thermal radiation mechanism for a spacecraft that can retract and compress, belonging to the field of spacecraft mechanism technology. Background Technology

[0002] The deployable thermal radiator installed on the spacecraft needs to be retracted and pressed against the spacecraft cabin during launch and withstand the mechanical environment test of the launch phase. After entering orbit, the pressing constraint is released and the thermal radiator is deployed to increase the heat dissipation area and improve the radiator's working efficiency. During reentry, it needs to be retracted and pressed against the spacecraft cabin again and withstand the mechanical environment of the reentry phase. According to the thermal protection requirements and aerodynamic layout of the spacecraft, the spacecraft cabin is cylindrical. In order to increase the maximum envelope of other payloads installed inside the cabin, the deployable thermal radiator should have the same curvature as the cabin, and the radiator's retracted envelope should be as small as possible. Since heat pipes need to be laid inside the deployable thermal radiator and heat dissipation efficiency needs to be considered, the radiator is relatively large, has a low fundamental frequency, and requires multiple pressing points to improve the retraction stiffness. Considering energy constraints, the energy consumption during deployment, retraction, locking, and unlocking should be minimized. Therefore, based on the structure, installation location, and working characteristics of this load, a mechanism is needed that can be repeatedly deployed and compressed in orbit, provides strong folding stiffness, adapts to the compact layout space and non-planar shape inside the spacecraft cabin, and has the smallest possible total weight.

[0003] A review of existing technologies reveals that all deployable radiators currently used on spacecraft are designed for one-time deployment and locking. A patent, exemplified by application number CN202210345458.5, discloses a deployable thermal radiator whose deployment locking mechanism and clamping release device are both designed for single-use operation, lacking the functionality for repeated deployment, retrieval, and clamping release. Therefore, it is unsuitable for the repeated deployment, retrieval, and clamping release requirements of spacecraft operating between Earth and space. Summary of the Invention

[0004] In view of this, in order to solve the problem that the deployable radiators on existing spacecraft cannot be repeatedly compressed and released and repeatedly deployed and retracted, this invention proposes an on-orbit radiator mechanism that can be repeatedly deployed and retracted and compressed and released, which is particularly suitable for spacecraft traveling between Earth and space.

[0005] An on-orbit retractable and compressible radiator mechanism includes: an active drive unit, a driven hinge, an active locking unit, and a radiator plate;

[0006] The longitudinal side of the radiating plate is connected to the aircraft body via an active drive device and a driven hinge. The active drive device is used to drive the radiating plate to repeatedly deploy and retract in orbit.

[0007] The active locking device includes a locking unit installed on the aircraft fuselage and a locking hook installed on the radiating plate. By locking and unlocking the locking hook through the locking unit, the radiating plate can be repeatedly pressed and released.

[0008] As a preferred embodiment of the present invention, it further includes an elastic support device; the elastic support device includes a plurality of metal rubber blocks disposed on the back side of the radiating plate.

[0009] In a preferred embodiment of the present invention, the active drive device includes: a support A, a rotating shaft A, a transmission assembly A, a drive motor A, and a linear reciprocating motion mechanism A;

[0010] The support A is fixedly connected to the aircraft body; the support A supports a rotating shaft A via lugs, and the axis of the rotating shaft A is parallel to the longitudinal direction of the radiating plate; the outer shell of the transmission assembly A is rotatably connected to the rotating shaft A.

[0011] The rotation output by the drive motor A is transmitted to the linear reciprocating motion mechanism A after being reversed by the transmission component A. The linear reciprocating motion mechanism A converts the rotation into linear motion, which is output by the output shaft of the linear reciprocating motion mechanism A.

[0012] The male hinge A, female hinge A, and rotating shaft C form a hinged structure; the male hinge A is fixedly connected to the radiating plate, and the female hinge A is fixed to the aircraft body; the male hinge A and female hinge A are respectively rotatably connected to the rotating shaft C, and the axis of the rotating shaft C is parallel to the longitudinal direction of the radiating plate; the output shaft of the linear reciprocating motion mechanism A drives the male hinge A to rotate around the axis of the rotating shaft C, thereby driving the radiating plate to rotate around the axis of the rotating shaft C, realizing the unfolding and retraction of the radiating plate.

[0013] In a preferred embodiment of the present invention, a trigger rod is provided on the male hinge A, and an unfolding switch that cooperates with the trigger rod is provided at a set position on the female hinge A;

[0014] When the radiating plate is unfolded to a predetermined angle position, the trigger rod triggers the unfolding position switch, and the drive motor A automatically stops.

[0015] In a preferred embodiment of the present invention, the locking unit includes: a drive motor B, a base, a transmission assembly B, a linear reciprocating motion mechanism B, a support B, and a pressing roller;

[0016] The drive motor B is supported on the aircraft body by a base. The rotation output of the drive motor B is converted into linear motion by the linear reciprocating motion mechanism B and output by the output shaft of the linear reciprocating motion mechanism B. The end of the output shaft of the linear reciprocating motion mechanism B is connected to a pressure roller through a rotating shaft C.

[0017] Once the radiant plate is retracted into place, the drive motor B drives the output shaft of the linear reciprocating motion mechanism B to extend, causing the clamping roller to press against the locking hook, thereby achieving the clamping of the radiant plate.

[0018] In a preferred embodiment of the present invention, the locking hook is L-shaped, the vertical part of the locking hook is connected to the radiating plate, and the upper end surface of the horizontal part serves as the locking surface. The locking surface includes a smoothly connected arc segment and a straight segment, wherein the arc segment is located on the outer side. The locking force applied to the radiating plate can be adjusted by adjusting the height difference between the pressing roller and the straight segment of the locking hook.

[0019] In a preferred embodiment of the present invention, the vertical part of the locking hook is connected to the radiating plate by a screw and an elongated hole along the vertical direction of the long shaft, and the position of the locking hook in the vertical direction is adjusted by the elongated hole.

[0020] In a preferred embodiment of the present invention, the active locking device is provided with a retraction-to-position trigger switch. When the radiating plate is retracted to the position, the retraction-to-position trigger switch is triggered. The active driving device stops after a delay to achieve initial pre-tightening of the elastic support device.

[0021] As a preferred embodiment of the present invention

[0022] In a preferred embodiment of the present invention, the active drive device is located at the middle position of the longitudinal side of the radiating plate, with a driven hinge on each side.

[0023] Beneficial effects:

[0024] (1) The radiator mechanism of the present invention can realize the on-orbit repeated deployment and retraction function of the radiator through the active drive device and the driven hinge, and realize the on-orbit repeated compression and release through the active locking device, so that the radiator can resist the mechanical load of the launch section and the reentry section; making it suitable for space-to-ground reciprocating spacecraft.

[0025] (2) In this invention, several metal rubber blocks are set on the back of the radiant plate as elastic support devices. By installing metal rubber blocks of different thicknesses, the metal rubber blocks are elastically deformed when locked, so that the radiant plate can adapt to the non-planar installation structure and fit tightly with it through the elastic support device, and improve the locking stiffness of the radiant plate.

[0026] (3) In this invention, the locking surface of the locking hook includes a smoothly connected arc segment and a straight segment. The arc segment can ensure that the pressing roller can climb the straight segment. The locking force applied to the radiating plate can be adjusted by adjusting the height difference between the pressing roller and the straight segment of the locking hook.

[0027] (4) In this invention, one end of the locking hook is connected to the radiation plate to be pressed by a screw and an elongated hole. The position of the locking hook in the vertical direction can be adjusted by the elongated hole.

[0028] (5) The radiator mechanism in this invention has a compact layout and a small envelope size, which effectively utilizes the entire arc-shaped envelope space and minimizes the occupation of the effective load installation space.

[0029] (6) The self-holding capability of the active drive device in this invention can realize the on-orbit attitude maintenance of the radiator.

[0030] (7) In this invention, after the trigger switch for retraction is triggered, the active drive device stops after a delay, which can achieve contact and initial pre-tightening of the elastic support device. Attached Figure Description

[0031] Figure 1 This is a schematic diagram (front view) of the thermal radiator of the present invention in its retracted state;

[0032] Figure 2 This is a schematic diagram of the retracted state of the thermal radiator of the present invention (reverse side);

[0033] Figure 3 This is a schematic diagram of the thermal radiator of the present invention in its deployed state;

[0034] Figure 4 This is a schematic diagram of an active drive device;

[0035] Figure 5 This is a schematic diagram of a driven hinge;

[0036] Figure 6 This is a schematic diagram of the locking state of the active locking device;

[0037] Figure 7 This is a schematic diagram showing the unlocked state of the active locking device.

[0038] Wherein: 1-Active drive device; 2-Driven hinge; 3-Active locking device; 4-Radiating plate; 5-Elastic support device;

[0039] 101-Support A; 102-Shaft A; 103-Transmission Component A; 104-Drive Motor A; 105-Output Shaft of Linear Reciprocating Motion Mechanism A; 106-Shaft B; 107-Male Hinge A; 108-Shaft C; 109-Female Hinge A; 110-Trigger Rod; 111-Expanded Position Switch;

[0040] 201-Female hinge B; 202-Male hinge B; 203-Shaft D;

[0041] 301-Drive motor B; 302-Base; 303-Linear reciprocating motion mechanism B; 304-Output shaft of linear reciprocating motion mechanism B; 305-Support B; 306-Pressure roller; 307-Rotating shaft C; 308-Unlocking position switch; 309-Unlocking position trigger post; 310-Locking position switch; 311-Locking position trigger post; 312-Retraction position switch. Detailed Implementation

[0042] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments.

[0043] This embodiment provides an on-orbit retractable and compressible radiator mechanism, which can achieve repeated on-orbit retraction and compressible release, and is particularly suitable for spacecraft traveling between Earth and space.

[0044] like Figure 1 and Figure 2 As shown, the thermal radiator mechanism includes: an active drive device 1, a driven hinge 2, an active locking device 3, a radiating plate 4, and an elastic support device 5. This mechanism enables the radiating plate 4 to: a) repeatedly unfold and retract in orbit via the active drive device 1 and the driven hinge 2 (unfolding refers to the radiating plate 4 unfolding upwards to a state at a set angle with the aircraft body, and retracting refers to the radiating plate 4 retracting downwards onto the surface of the aircraft body); b) repeatedly press and release in orbit via the active locking device 3 and the elastic support device 5 (pressing refers to pressing the radiating plate 4 firmly onto the surface of the aircraft body after retraction, and releasing refers to releasing the pressing).

[0045] The radiant plate 4 is arc-shaped (its concave side is the front and its convex side is the back), with a fluid circuit embedded inside and a thermal control white paint sprayed on its surface.

[0046] The active drive device 1 is used to drive the radiating plate 4 to repeatedly deploy and retract on the track, and the active drive device 1 has the function of stopping immediately when deployed and has self-holding capability. The active drive device 1 is disposed on one longitudinal side of the radiating plate 4; preferably, the active drive device 1 is disposed in the middle of the side of the radiating plate 4; for example Figure 4As shown, the active drive device 1 includes: a support A101, a rotating shaft A102, a transmission assembly A103, a drive motor A104, a linear reciprocating motion mechanism A, a rotating shaft B106, a male hinge A107, a rotating shaft C108, a female hinge A109, a trigger rod 110, and an unfolding switch 111. A rectangular notch is provided on the radiating plate 4 at the location for mounting the active drive device 1. The support A101 is fixedly connected to the aircraft body at the corresponding location. The support A101 has lugs for supporting the rotating shaft A102, and the axis of the rotating shaft A102 is parallel to the longitudinal direction of the radiating plate 4. The power output end of the drive motor A104 is connected to the linear reciprocating motion mechanism A through the transmission assembly A103. The rotation output by the drive motor A104 is reversed by the transmission assembly A103 and transmitted to the linear reciprocating motion mechanism A. The linear reciprocating motion mechanism A converts the rotation into linear motion, which is output from its linear motion output end, i.e., the output shaft 105 of the linear reciprocating motion mechanism A. As an example, transmission component A103 is a gearbox, and linear reciprocating motion mechanism A is a lead screw and nut mechanism. Compared to the drive motor A104 directly driving the linear reciprocating motion mechanism, setting transmission component A103 between the two for reversing reduces the overall length of the active drive device 1, facilitating its installation. The housing of transmission component A103 is rotatably connected to the rotating shaft A102 via lugs, allowing it to rotate around the axis of rotating shaft A102. Male hinge A107, female hinge A109, and rotating shaft C108 form a hinged structure, wherein male hinge A107 is fixedly connected to the radial plate 4 (specifically, two male hinges connected together are respectively set on both sides of the rectangular notch opening), and female hinge A109 is fixed to the aircraft fuselage; male hinge A107 and female hinge A109 are rotatably connected to rotating shaft C108, and the axis of rotating shaft C108 is parallel to the longitudinal direction of the radial plate 4. The output shaft 105 of the linear reciprocating motion mechanism A is used to drive the male hinge A107 to rotate around the axis of the rotating shaft C108, thereby driving the radiating plate 4 to rotate around the axis of the rotating shaft C108, realizing the unfolding and retraction of the radiating plate 4. Specifically, the connecting plate used to connect the two male hinges A107 is provided with a lug, and the output shaft 105 of the linear reciprocating motion mechanism A is rotatably connected to the rotating shaft B106 supported on the lug. The output shaft 105 of the linear reciprocating motion mechanism A extends and retracts the connecting plate, causing it to rotate around the axis of the rotating shaft C108.

[0047] To achieve immediate shutdown upon deployment of the radiating plate 4, a trigger rod 110 is installed on the male hinge A107 (specifically, on the connecting plate connecting the two male hinges A107), and a deployment-to-position switch 111 cooperating with the trigger rod 110 is installed on the female hinge A109. When the radiating plate 4 is deployed to a predetermined angle position, the trigger rod 110 triggers the preset deployment-to-position switch 111 to achieve immediate shutdown upon deployment (i.e., after the trigger rod 110 triggers the deployment-to-position switch 111, the drive motor A104 stops). Then, based on the self-holding capability of the active drive device 1 (the internal friction torque of the transmission component A103), the on-rail posture of the radiating plate 4 is maintained.

[0048] On the longitudinal side of the radiating plate 4, where the active drive device 1 is located, a driven hinge 2 is provided on each of the two longitudinal sides of the active drive device 1. The driven hinges 2 are used to cooperate with the active drive device 1 to realize the expansion and contraction of the radiating plate 4. Figure 5 As shown, the driven hinge 2 includes: a female hinge B201, a male hinge B202 and a rotating shaft D203. One end of the male hinge B202 is fixedly connected to the radiating plate 4, and the other end is rotatably connected to one end of the female hinge B201 through the rotating shaft D203. The other end of the female hinge B201 is fixedly connected to the aircraft body.

[0049] An active locking device 3 is disposed on another longitudinal side of the radiating plate 4, used to constrain the degree of freedom of the radiating plate 4 in the unfolding direction (i.e., to press the folded radiating plate 4 against the surface of the aircraft body via the active locking device 3) and to press the elastic support device 5. Preferably, the active locking device 3 is positioned opposite to the active drive device 1. Figure 6 , Figure 7As shown, the active locking device 3 includes a locking unit mounted on the aircraft fuselage and a locking hook 401 mounted on the radiating plate 4. The locking unit includes a drive motor B301, a base 302, a linear reciprocating motion mechanism B303, a support B305, a pressure roller 306, and a rotating shaft C307. The drive motor B301 is supported on the aircraft fuselage by the base 302, and the axis of the output shaft of the drive motor B301 is parallel to the longitudinal direction of the radiating plate 4. The rotation output of the drive motor B301 is converted into linear motion by the linear reciprocating motion mechanism B303 and output by the output shaft 304 of the linear reciprocating motion mechanism B. As an example, the linear reciprocating motion mechanism B303 is a lead screw and nut mechanism. Thus, the drive motor B301 can drive the linear motion output end of the linear reciprocating motion mechanism B, i.e., the output shaft 304 of the linear reciprocating motion mechanism B, to perform reciprocating linear motion along the longitudinal direction of the radiating plate 4. To support and guide the output shaft 304 of the linear reciprocating motion mechanism B, a support B305 is installed on the aircraft fuselage. The output shaft 304 of the linear reciprocating motion mechanism B passes through a guide cylinder installed on the support B305. After passing through the guide cylinder on the support B305, the end of the output shaft 304 of the linear reciprocating motion mechanism B is connected to a clamping roller 306 via a rotating shaft C307. A locking hook 401 is provided on the radiating plate 4 to cooperate with the clamping roller 306. When the radiating plate 4 is retracted into place, the drive motor B301 drives the output shaft 304 of the linear reciprocating motion mechanism B to extend, so that the clamping roller 306 clamps the locking hook 401, thereby achieving the clamping of the radiating plate 4.

[0050] As an example, the radiating plate 4 is provided with an L-shaped locking hook 401. The vertical part of the L-shaped locking hook 401 is connected to the radiating plate 4 by screws and an elongated hole (the long axis is along the vertical direction). The position of the locking hook 401 in the vertical direction can be adjusted through the elongated hole. The upper end face of the horizontal part of the L-shaped locking hook 401 serves as the locking surface. Its shape is a smooth connection between an arc segment and a straight segment, with the arc segment located on the outside. The arc segment ensures that the pressing roller 306 can smoothly climb up the straight segment, thereby pressing the locking hook 401. The locking force applied to the radiant plate 4 can be adjusted by adjusting the height difference between the pressing roller 306 and the straight section of the locking hook 401. This locking force is determined by calibrating the current of the drive motor B301 during the locking process to determine the driving force of the linear reciprocating motion output shaft 105. Finally, the normal force at the contact point between the pressing roller 306 and the locking hook 401 is calculated based on the static balance analysis of the linear reciprocating motion output shaft 105, the support B305 and the pressing roller 306. This is the locking force applied to the radiant plate 4 by the active locking device 3.

[0051] The elastic support device 5 includes several metal rubber blocks disposed on the back of the radiating plate 4. The positions of the metal rubber blocks are determined based on the locations of the radiating plate 4 with larger amplitudes under mechanical conditions, as determined in the design analysis. The stiffness of the metal rubber blocks can be determined based on mechanical analysis, thus allowing the stiffness of the elastic support device 5 to be adjusted according to usage requirements. During processing, the stiffness of the metal rubber blocks can be varied by adjusting its process parameters. Furthermore, by installing metal rubber blocks of different thicknesses, the metal rubber blocks will undergo elastic deformation during locking, enabling the radiating plate 4 to adapt to non-planar installation structures and fit tightly against them through the elastic support device 5, thereby improving the locking stiffness of the radiating plate 4.

[0052] A retraction-to-position switch 312 is provided on the base 302 of the active locking device 3. When the radiating plate 4 is retracted into position, the retraction-to-position switch 312 is triggered, and the drive motor A104 in the active drive device 1 stops, ceasing the retraction action. Preferably, after the retraction-to-position switch 312 is triggered, the drive motor A104 stops after a delay, achieving contact and initial pre-tightening with the elastic support device 5.

[0053] In addition, an unlocking switch 308 and a locking switch 310 are respectively provided on the housing of the linear reciprocating motion mechanism B303; wherein the locking switch 310 is located on the front side of the linear reciprocating motion mechanism B303's linear movement on the housing, and the unlocking switch 308 is located on the rear side of the linear reciprocating motion mechanism B303's linear movement on the housing; two opposite sides of the housing of the linear reciprocating motion mechanism B303 are respectively provided with strip grooves, and the unlocking trigger post 309 and the locking trigger post 311 are respectively located in the two strip grooves and connected to the linear movement part of the linear reciprocating motion mechanism B303, and can follow it to perform linear movement. Before the radiant plate 4 unfolds, the active locking device 3 is first unlocked (i.e., the pressing roller 306 disengages from the locking hook 401), releasing the constraint on the degree of freedom of the unfolding direction of the radiant plate 4, allowing the radiant plate 4 to unfold. During the unlocking process, the drive motor B301 drives the pressing roller 306 to move away from the locking hook 401. After unlocking, the unlocking trigger pin 309 triggers the unlocking switch 308 (e.g., ...). Figure 7 (As shown in the state), drive motor B301 stops. When the radiating plate 4 retracts to the predetermined position, the retraction position switch 312 is triggered, and the contact and initial pre-tightening of the elastic support device 5 are achieved through a delayed stop; drive motor B301 drives the pressing roller 306 to move toward the locking hook 401 and press it against the locking hook 401. After locking in place, the locking position trigger pin 311 triggers the locking position switch 310 (as shown in the state). Figure 6 (As shown in the state), drive motor B301 stops, and active locking device 3 achieves constraint on the degree of freedom of the unfolding direction of radiant plate 4 and final pre-tightening of elastic support device 5 through locking, thereby achieving the pressing of radiant plate.

[0054] Thus, the radiating plate 4, connected to the active drive device 1 and the driven hinge 2, achieves repeated unfolding and retraction of the radiating plate 4 through the drive of the active drive device 1 and the auxiliary support of the driven hinge 2. When the radiating plate 4 retracts to a predetermined position under the drive of the active drive device 1, it triggers the retraction position switch 312 preset on the active locking device 3, and achieves contact and initial pre-tightening of the elastic support device 5 through a delayed stop. After the radiating plate 4 is retracted, the active locking device 3 locks the radiating plate 4 to constrain the degree of freedom of the unfolding direction and to finally pre-tighten the elastic support device 5, thereby achieving the pressing of the radiating plate 4. When the radiating plate 4 is in the retracted state, the active locking device 3 unlocks, releasing the constraint on the degree of freedom of the unfolding direction of the radiating plate 4. The radiating plate 4 can unfold through the active drive device 1 and the driven hinge 2, and the immediate stop action of unfolding to the desired position is achieved by triggering the unfolding position switch 111 preset on the active drive device 1. After the radiating plate 4 is deployed, its on-orbit attitude is maintained by the self-holding capability of the active drive device 1.

[0055] This radiator mechanism is particularly suitable for thermal radiators or other similar loads on spacecraft that require repeated deployment and retraction in orbit and have high clamping stiffness requirements during launch and reentry phases. The size of the radiator plate can be designed according to actual needs, and the overall layout of the mechanism can be adjusted based on the size and mass of the radiator plate. It is suitable not only for radiators but also for other non-planar loads of different volumes and sizes that require repeated deployment and retraction, as well as repeated clamping and release in orbit, demonstrating good scalability.

[0056] Although the present invention has been described in detail above with general descriptions and specific embodiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

Claims

1. A radiator mechanism capable of repeated deployment, retraction, and compression release in orbit, characterized in that, For use in space-to-ground reciprocating aircraft, including: active drive unit, driven hinge, active locking device and radial plate; The longitudinal side of the radiating plate is connected to the aircraft body via an active drive device and a driven hinge. The active drive device is used to drive the radiating plate to repeatedly deploy and retract in orbit. The active locking device includes a locking unit installed on the aircraft fuselage and a locking hook installed on the radiating plate. By locking and unlocking the locking hook through the locking unit, the radiating plate can be repeatedly pressed and released. The active drive device includes: a support A, a rotating shaft A, a transmission assembly A, a drive motor A, and a linear reciprocating motion mechanism A; The radiating plate has a rectangular notch at the location where the active drive device is installed. The support A is fixedly connected to the aircraft body; the support A supports a rotating shaft A via lugs, and the axis of the rotating shaft A is parallel to the longitudinal direction of the radiating plate; the outer shell of the transmission assembly A is rotatably connected to the rotating shaft A. The rotation output by the drive motor A is transmitted to the linear reciprocating motion mechanism A after being reversed by the transmission component A. The linear reciprocating motion mechanism A converts the rotation into linear motion, which is output by the output shaft of the linear reciprocating motion mechanism A. The male hinge A, female hinge A, and rotating shaft C form a hinged structure; two male hinges A connected together are respectively set on both sides of the opening end of the rectangular notch, and the female hinge A is fixed to the aircraft body; the male hinge A and female hinge A are respectively rotatably connected to the rotating shaft C, and the axis of the rotating shaft C is parallel to the longitudinal direction of the radiating plate; the output shaft of the linear reciprocating motion mechanism A drives the male hinge A to rotate around the axis of the rotating shaft C, thereby driving the radiating plate to rotate around the axis of the rotating shaft C, realizing the unfolding and retraction of the radiating plate.

2. The on-orbit reusable and compressible radiator mechanism as described in claim 1, characterized in that, It also includes an elastic support device; the elastic support device includes several metal rubber blocks disposed on the back of the radiating plate.

3. The on-orbit reusable and compressible radiator mechanism as described in claim 1, characterized in that, The male hinge A is provided with a trigger rod, and the female hinge A is provided with an unfolding switch at a set position that cooperates with the trigger rod; When the radiating plate is unfolded to a predetermined angle position, the trigger rod triggers the unfolding position switch, and the drive motor A automatically stops.

4. The on-orbit reusable and compressible radiator mechanism as described in claim 1 or 2, characterized in that, The locking unit includes: a drive motor B, a base, a transmission assembly B, a linear reciprocating motion mechanism B, a support B, and a pressure roller; The drive motor B is supported on the aircraft body by a base. The rotation output of the drive motor B is converted into linear motion by the linear reciprocating motion mechanism B and output by the output shaft of the linear reciprocating motion mechanism B. The end of the output shaft of the linear reciprocating motion mechanism B is connected to a pressure roller through a rotating shaft C. Once the radiant plate is retracted into place, the drive motor B drives the output shaft of the linear reciprocating motion mechanism B to extend, causing the clamping roller to press against the locking hook, thereby achieving the clamping of the radiant plate.

5. The on-orbit reusable and compressible radiator mechanism as described in claim 4, characterized in that, The locking hook is L-shaped, with its vertical part connected to the radiating plate and its upper surface of the horizontal part serving as the locking surface. The locking surface includes a smoothly connected arc segment and a straight segment, with the arc segment located on the outer side. The locking force applied to the radiating plate can be adjusted by adjusting the height difference between the pressing roller and the straight segment of the locking hook.

6. The on-orbit reusable and compressible radiator mechanism as described in claim 5, characterized in that, The vertical part of the locking hook is connected to the radiating plate by a screw and an elongated hole along the vertical direction on a long shaft, and the position of the locking hook in the vertical direction is adjusted through the elongated hole.

7. The on-orbit reusable and compressible radiator mechanism as described in claim 2, characterized in that, The active locking device is equipped with a retraction-to-position switch. When the radiating plate is retracted to the position, the retraction-to-position switch is triggered. The active drive device stops after a delay to achieve initial pre-tightening of the elastic support device.

8. The on-orbit reusable and compressible radiator mechanism as described in claim 4, characterized in that, Also includes: Unlocked position switch, locked position switch, unlocked position trigger post, and locked position trigger post; The housing of the linear reciprocating motion mechanism B is respectively equipped with an unlocking switch and a locking switch; The unlocking trigger post and the locking trigger post are respectively connected to the linear motion part of the linear reciprocating motion mechanism B, and can follow it to perform linear motion; During the unlocking process of the locking unit, after the unlocking is completed, the unlocking completion trigger pin triggers the unlocking completion switch, and the locking unit stops. During the locking process of the locking unit, after the locking is in place, the locking position trigger pin triggers the locking position switch, and the locking unit stops.

9. The on-orbit reusable and compressible radiator mechanism as described in claim 1 or 2, characterized in that, The active drive device is located at the middle of the longitudinal side of the radiating plate, with a driven hinge on each side.

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