Satellite deorbit device

Abstract

The present application relates to the field of satellite mechanisms, and in particular to a satellite deorbit device; the satellite deorbit device comprises a base plate, side covers, a power source assembly, a driven assembly, a sail boom mechanism and a locking mechanism, the surrounding areas of the base plate are rotatably connected to a plurality of side covers, wherein a power source assembly and a driven assembly connected thereto for transmission are provided in a central area, the driven assembly is slidably connected to one end of the locking mechanism, and the other end is clamped to the side cover; the base plate and the plurality of side covers constitute an accommodating space, the accommodating space is provided with an expandable sail film, the corners of the sail film are fixedly connected to the protruding end of the sail boom mechanism, the sail boom mechanism is connected to the driven assembly and is driven to extend therefrom; the satellite deorbit device of the present application can control the power source assembly through a control signal, and control the sail deployment process of the satellite deorbit device; improve the success rate of deploying the deorbit sail, and reduce the satellite's hovering time.

Description

Technical Field

[0001] The present application relates to the field of satellite mechanisms, and in particular to a satellite deorbiting device. Background Art

[0002] At the end of a satellite's lifespan, it's often necessary to actively deorbit it to prevent it from remaining in orbit for an extended period and impacting other satellites. Currently used active deorbiting technologies involve either carrying sufficient fuel to control the satellite's orbit at the end of its lifespan, or deploying a deorbiting sail to increase the satellite's windward surface, accelerating its deorbiting.

[0003] Deorbiting sails are commonly used to deorbit microsatellites to reduce their weight. Typically, upon receiving ground commands, these devices release the sails using stored elastic potential energy. However, due to the multiple elastic potential energy storage mechanisms involved in deploying, the sail membrane can become entangled with other mechanisms, causing the sail to become uncontrollable. Furthermore, since the elastic potential energy storage mechanisms are housed within the deorbiting device, they are susceptible to creep deformation over extended periods in space, affecting their deployed shape. This can lead to incomplete deployment of the sails, causing them to fail and ultimately increasing the satellite's time in space. Therefore, there is a need for an improved satellite deorbiting device to address these issues. Summary of the Invention

[0004] In response to the above-mentioned problems of the prior art, the purpose of the present application is to provide a satellite deorbit device, in which the power source component can actively control the sail deployment process of the satellite deorbit device, and then can control the power source component through a control signal to control the sail deployment process of the satellite deorbit device; through active control, the extension speed of the boom mechanism can be controlled, and the deployment time of the deorbit sail can be accurately regulated, which can improve the deployment success rate of the deorbit sail and reduce the satellite's hovering time.

[0005] In order to solve the above problems, the present application provides a satellite deorbit device, including a base plate, a side cover plate, a power source assembly, a driven assembly, a sail boom mechanism and a locking mechanism, wherein the surrounding areas of the base plate are rotatably connected to the multiple side cover plates, wherein the central area is provided with the power source assembly and the driven assembly transmission-connected thereto, the driven assembly is slidingly connected to one end of the locking mechanism, and the other end of the locking mechanism is clamped with the side cover plate; the base plate and the multiple side cover plates can form an accommodating space, and the accommodating space is provided with an expandable sail film, the corners of the sail film are fixedly connected to the protruding end of the sail boom mechanism, and the sail boom mechanism is connected to the driven assembly and driven to extend thereby.

[0006] In one embodiment, the power source assembly includes a driving mechanism and an active mechanism, the driving mechanism is fixedly connected to the base plate, the driving mechanism is drivingly connected to the active mechanism, and the active mechanism is transmission-connected to the driven assembly.

[0007] In one embodiment, the satellite deorbit device further includes a boom mechanism limiting portion, the boom mechanism is inserted into the boom mechanism limiting portion, and the boom mechanism limiting portion is fixedly connected to the bottom plate.

[0008] In one embodiment, the satellite deorbit device further comprises a sandwich plate, wherein the sandwich plate is fixedly connected to the base plate;

[0009] The locking mechanism includes a locking rod and a rotating shaft, one end of the rotating shaft is rotatably connected to the locking rod, and the other end of the rotating shaft is fixedly connected to the plywood layer; one end of the locking rod is slidably connected to the driven assembly, and the other end of the locking rod is clamped with the side cover plate.

[0010] In one embodiment, the driven assembly includes a rotating member and a guide member, the rotating member is transmission-connected to the active mechanism, and one end of the guide member is fixedly connected to the rotating member; a sliding groove is provided on the locking rod, and the other end of the guide member is slidingly connected to the sliding groove.

[0011] In one embodiment, the locking rod is further provided with a guide member sliding outlet, and the guide member sliding outlet is arranged on the side wall of the sliding groove close to one end of the rotating shaft.

[0012] In one embodiment, the locking rod is further provided with a clamping hook, and the side cover is provided with a clamping portion matching the clamping hook; the locking rod is clamped to the side cover through the cooperation between the clamping hook and the clamping portion.

[0013] In one embodiment, the satellite deorbit device further comprises a clamping and adjusting assembly, wherein the clamping and adjusting assembly is fixedly connected to the base plate, and the clamping and adjusting assembly is disposed adjacent to the driven assembly;

[0014] One end of the sail boom mechanism passes through the gap between the pressing and adjusting component and the driven component, and is then inserted into the limiting portion of the sail boom mechanism, and the pressing and adjusting component is pressed against the sail boom mechanism.

[0015] In one embodiment, the driven assembly includes a driven roller, and the driven roller is transmission-connected to the active mechanism.

[0016] In one embodiment, the clamping and adjusting assembly includes a clamping wheel, the driven roller is arranged adjacent to the clamping wheel, and the driven roller and the clamping wheel are respectively in contact with the boom mechanism.

[0017] In one embodiment, the compression adjustment assembly further includes an elastic member, the compression wheel is connected to one end of the elastic member, and the compression wheel can move along the elastic direction of the elastic member under the action of an external force to compress the elastic member.

[0018] Due to the above technical solution, the satellite deorbit device described in this application has the following beneficial effects:

[0019] 1. The satellite deorbit device of the present application has a power source component that can actively control the sail deployment process of the satellite deorbit device, and then can control the power source component through a control signal to control the sail deployment process of the satellite deorbit device; through active control, the extension speed of the boom mechanism can be controlled, and the deployment time of the deorbit sail can be accurately regulated, thereby effectively improving the deployment success rate of the deorbit sail and reducing the satellite's hovering time.

[0020] 2. The satellite deorbit device of the present application guides the movement of the sail boom mechanism through the limiting part of the sail boom mechanism, thereby avoiding hooking between the unfolded sail films and improving the reliability and adaptability of the satellite deorbit device.

[0021] 3. The satellite deorbit device of the present application forms a crank slider four-bar mechanism by slidingly connecting the locking rod and the rotating part to reduce the torque requirement when the locking rod and the rotating part are disconnected; at the same time, the other end of the locking rod is clamped with the side cover plate, and the two ends of the locking rod are fixed at the same time to achieve the limitation of the side cover plate, thereby improving the locking reliability of the satellite deorbit device.

[0022] 4. The satellite deorbit device of the present application realizes the limitation of the side cover plate with a simple mechanical structure by clamping the locking rod with the side cover plate, thereby reducing the limitation requirements for the side cover plate, simplifying the design of the connection relationship between the side cover plate and the bottom plate, simplifying the structure of the satellite deorbit device, and reducing the complexity of the system.

[0023] 5. The satellite deorbit device of the present application adjusts the pressure applied to the boom mechanism by adjusting the compression amount of the elastic member, thereby adjusting the active friction force when the boom mechanism is extended, thereby enhancing the adaptability of the satellite deorbit device to boom mechanisms of different forms or different friction coefficients and achieving structural decoupling. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] To more clearly illustrate the technical solution of this application, the following briefly introduces the drawings required for use in the embodiments or descriptions of the prior art. Obviously, the drawings described below are merely some embodiments of this application, and those skilled in the art can derive other drawings based on these drawings without inventive effort.

[0025] Figure 11 is a schematic diagram of the external structure of a satellite deorbit device provided in an embodiment of the present application in an unfolded state;

[0026] Figure 2 This is a schematic diagram of the internal structure of a satellite deorbit device in an unfolded state provided in an embodiment of the present application. Figure 1 ;

[0027] Figure 3 This is a schematic diagram of the internal structure of a satellite deorbit device in an unfolded state provided in an embodiment of the present application. Figure 2 ;

[0028] Figure 4 This is a schematic structural diagram of a power source component of a satellite deorbit device provided in an embodiment of the present application;

[0029] Figure 5 This is a schematic structural diagram of a driven component of a satellite deorbit device provided in an embodiment of the present application;

[0030] Figure 6 This is a schematic diagram of the structure of a boom mechanism storage assembly of a satellite deorbit device provided in an embodiment of the present application;

[0031] Figure 7 This is a schematic structural diagram of a compression adjustment component of a satellite deorbit device provided in an embodiment of the present application;

[0032] Figure 8 This is a schematic structural diagram of a locking mechanism of a satellite deorbit device provided in an embodiment of the present application;

[0033] Figure 9 This is a schematic diagram of the internal structure of a satellite deorbit device in an unfolded state provided in an embodiment of the present application. Figure 3 ;

[0034] Figure 10 This is a schematic diagram of the sail-spreading effect of a satellite deorbit device provided in an embodiment of the present application.

[0035] Among them, 1-bottom plate, 2-side cover plate, 21-clamping part, 3-power source assembly, 31-driving mechanism, 32-active mechanism, 33-driving mechanism fixing seat, 34-driving mechanism lubricating bushing, 35-active mechanism fixing part, 4-driven assembly, 41-rotating part, 42-guide part, 43-driven roller, 44-driven assembly mounting seat, 45-roller upper lubricating bushing, 46-roller lower lubricating bushing, 5-sail boom mechanism, 6-locking mechanism, 61-locking rod, 611-sliding groove, 612-guide member sliding outlet, 613-clamping hook, 62-rotating shaft, 63- Locking and lubricating bushing, 64-first locking mechanism, 65-second locking mechanism, 7-sail boom mechanism limiting part, 8-sandwich plate, 9-tensioning adjustment assembly, 91-tensioning wheel, 92-elastic member, 93-tensioning wheel base, 94-tensioning wheel cover, 95-elastic member lubricating ring, 96-tensioning adjustment nut, 97-tensioning device mounting seat, 98-tensioning adjustment rod, 10-upper cover, 11-unfolding hinge, 12-sail boom mechanism storage assembly, 121-rotating shaft upper cover, 122-rotating shaft, 123-storage assembly lubricating bushing, 124-sail boom mechanism storage box, 13-sail spreading film. DETAILED DESCRIPTION

[0036] The following will be combined with the accompanying drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0037] References to "one embodiment" or "embodiment" herein refer to specific features, structures, or characteristics that may be included in at least one implementation of the present application. Throughout the description of this application, it should be understood that the terms "upper," "lower," "left," "right," "top," and "bottom," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely for ease of description and simplification. They do not indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and are therefore not to be construed as limiting the present application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly specifying the number of the technical features referred to. Thus, a feature designated "first" or "second" may explicitly or implicitly include one or more of the features. Furthermore, the terms "first," "second," etc., are used to distinguish similar objects and are not necessarily used to describe a specific order or sequential sequence. It should be understood that such terms are interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described herein.

[0038] Combine Figure 1-10 , introduces a satellite deorbit device provided by an embodiment of the present application, including a base plate 1, a side cover plate 2, a power source component 3, a driven component 4, a sail boom mechanism 5 and a locking mechanism 6. The surrounding areas of the base plate 1 are rotatably connected to multiple side cover plates 2, wherein the central area is provided with a power source component 3 and a driven component 4 connected thereto for transmission, the driven component 4 is slidably connected to one end of the locking mechanism 6, and the other end of the locking mechanism 6 is clamped with the side cover plate 2; the base plate 1 and multiple side cover plates 2 can form an accommodating space, and an expandable sail film 13 is provided in the accommodating space, and the corners of the sail film 13 are fixedly connected to the protruding end of the sail boom mechanism 5, and the sail boom mechanism 5 is connected to the driven component 4 and driven to extend thereby; the power source Component 3 can actively control the sail deployment process of the satellite deorbit device, and then can control the power source component 3 through a control signal to control the sail deployment process of the satellite deorbit device; through active control, the extension speed of the boom mechanism 5 can be controlled, and the deployment time of the deorbit sail can be accurately regulated, which can improve the deployment success rate of the deorbit sail and reduce the satellite's hovering time; specifically, a control instruction can be issued through the ground control center to control the operating speed of the power source component 3 to control the extension speed of the boom mechanism 5; during the movement of the driven component 4, the locking mechanism 6 can be disconnected from the driven component 4, releasing the limit of the locking mechanism 6 on the driven component 4, and ensuring that the satellite deorbit device can be unlocked normally.

[0039] Specifically, the power source assembly 3, the driven assembly 4, the boom mechanism 5 and the locking mechanism 6 are arranged in the accommodating space; when the locking mechanism 6 is disengaged from the side cover plate 2, the side cover plate 2 rotates relative to the base plate 1 in a direction away from the power source assembly 3 until a preset angle is formed with the base plate 1; the power source assembly 3 is transmission-connected with the driven assembly 4, and the boom mechanism 5 is transmission-connected with the driven assembly 4; when the power source assembly 3 is running, the driven assembly 4 moves under the driving action of the power source assembly 3, thereby respectively driving the locking mechanism 6 and the boom mechanism 5 to move, so that the locking mechanism 6 is respectively disengaged from the connection between the driven assembly 4 and the side cover plate 2, so that the side cover plate 2 can rotate relative to the base plate 1 in a direction away from the power source assembly 3, and the boom mechanism 5 can be extended in a direction away from the power source assembly 3.

[0040] In an embodiment of the present application, the satellite deorbit device may include multiple boom mechanisms 5 and multiple driven components 4, the power source component 3 may be arranged in the middle of the accommodating space, and multiple driven components 4 may be arranged around the power source component 3, the power source component 3 and the driven component 4 are connected in transmission, the boom mechanisms 5 and the driven components 4 are arranged in a one-to-one correspondence, a single driven component 4 can drive a single boom mechanism 5 to move, and realize the independent control of the boom mechanism 5 by the driven component 4; since during the operation of the satellite, the internal mechanism of the satellite may be damaged due to certain factors, resulting in a certain boom mechanism 5 being unable to be deployed or insufficiently deployed; the boom mechanism 5 is independently driven and controlled by the driven component 4, and in the event that a certain boom mechanism 5 fails to deploy, the remaining boom mechanisms 5 can be normally extended in the direction away from the power source component 3, thereby improving the fault tolerance of the satellite deorbit device during the sail deployment process.

[0041] In some embodiments, please refer to Figure 2-3 The satellite deorbit device may include four boom mechanisms 5 and four driven assemblies 4.

[0042] In an embodiment of the present application, the locking mechanism 6 may include a first locking mechanism 64 and a second locking mechanism 65, and the lengths of the first locking mechanism 64 and the second locking mechanism 65 are inconsistent. Specifically, the length of the first locking mechanism 64 is greater than the length of the second locking mechanism 65; one end of the first locking mechanism 64 and the second locking mechanism 65 can be respectively slidably connected to the same driven component 4, and the first locking mechanism 64 and the second locking mechanism 65 are staggered with each other, and the other ends of the first locking mechanism 64 and the second locking mechanism 65 are clamped with different side cover plates 2; when the power source component 3 is not in operation, by respectively connecting the staggered first locking mechanisms 64 and the second locking mechanisms 65 to the same driven component 4 in a transmission manner, the clamping limit between multiple side cover plates 2 and the base plate 1 can be achieved, thereby improving the reliability of the satellite deorbit device and reducing the design cost of the satellite deorbit device.

[0043] In the examples of this application, please refer to Figure 2 One end of the first locking mechanism 64 and the second locking mechanism 65 can be slidably connected to different driven components respectively, and the first locking mechanism 64 and the second locking mechanism are arranged at intervals. The other ends of the first locking mechanism 64 and the second locking mechanism 65 are clamped with the same side cover plate 2; when the power source component 3 is not running, the same side cover plate 2 is clamped by the first locking mechanism 64 and the second locking mechanism 65 arranged at intervals, which can improve the stability of the clamping limit between the side cover plate 2 and the base plate 1, thereby improving the reliability of the satellite deorbit device.

[0044] In the embodiment of the present application, the sail-spreading film 13 can be a single-layer compressed film. The edges and corners of the sail-spreading film 13 are fixedly connected to the protruding ends of the sail boom mechanism 5, and the rest of the film is retracted in the accommodating space. When the power source assembly 3 is in operation, the locking mechanism 6 is disconnected from the side cover plate 2, so that the side cover plate 2 rotates relative to the bottom plate 1 in a direction away from the power source assembly 3. The sail boom mechanism 5 drives the sail-spreading film 13 to extend in a direction away from the power source assembly 3 and expands the compressed sail-spreading film 13. The sail boom mechanism 5 can support the gradually expanded sail-spreading film 13, forming a Figure 10 Satellite deorbiting sail shown.

[0045] In the examples of this application, please refer to Figure 1 , multiple side cover plates 2 and the bottom plate 1 can be hinged. Specifically, multiple side cover plates 2 and the bottom plate 1 are connected by multiple expansion hinges 11. The expansion hinge 11 includes a first hinge plate, a second hinge plate, a central shaft and an expansion spring. The central shaft and the expansion spring are plated with a molybdenum disulfide film to prevent vacuum cold welding. It should be noted that vacuum cold welding refers to the phenomenon that the contact surfaces between solids and solids are welded together due to ultra-low temperature in a vacuum; the first hinge plate is fixedly connected to the bottom plate 1, the second hinge plate is fixedly connected to the side cover plate 2, and the first hinge plate and the second hinge plate are respectively rotatably connected to the central shaft; the second hinge plate The hinge plate can rotate around the central axis and then rotate relative to the first hinge plate; the expansion spring is arranged in the accommodating space, and the two ends of the expansion spring are fixedly connected to the first hinge plate and the second hinge plate respectively. When the locking mechanism 6 is engaged with the side cover plate 2, the expansion spring is in a pre-tightened state. When the locking mechanism 6 is disengaged from the side cover plate 2, the second hinge plate can be rotated relative to the first hinge plate in a direction away from the power source assembly 3 under the action of the elastic force of the expansion spring, thereby making the side cover plate 2 and the bottom plate 1 rotate to the same plane; by setting the expansion hinge 11, the structural complexity of the satellite deorbit device can be reduced, thereby saving costs.

[0046] In an embodiment of the present application, the power source component 3 may include a driving mechanism 31 and an active mechanism 32. The driving mechanism 31 is fixedly connected to the base plate 1. The driving mechanism 31 is drivenly connected to the active mechanism 32. The active mechanism 32 is transmission-connected to the driven component 4. The driving mechanism 31 can drive the active mechanism 32 to rotate, thereby driving the driven component 4 to rotate.

[0047] In the examples of this application, please refer to Figure 4The power source assembly 3 may further include a drive mechanism fixing seat 33, a drive mechanism lubricating bushing 34 and an active mechanism fixing piece 35. The drive mechanism fixing seat 33 is fixedly connected to the base plate 1, the drive mechanism 31 is fixedly connected to the drive mechanism fixing seat 33, the drive mechanism 31 and the active mechanism 32 are fixedly connected via the active mechanism fixing piece 35, and the drive mechanism lubricating bushing 34 is arranged between the drive mechanism 31 and the active mechanism 32 to reduce the transmission friction between the drive mechanism 31 and the active mechanism 32.

[0048] In an embodiment of the present application, the driving mechanism 31 can be a driving motor, such as a rotating motor, the active mechanism 32 can be a gear structure, such as a driving gear, the active mechanism fixing part 35 can be a fastener, such as a pin, the driving gear is sleeved on one end of the rotating motor, the driving gear and the rotating motor are coaxially connected by a pin, and the other end of the rotating motor is fixedly connected to the base plate; the driving mechanism lubricating bushing 34 is coated with a molybdenum disulfide film to prevent vacuum cold welding between the rotating motor and the driving gear and the driving mechanism lubricating bushing 34 respectively, thereby improving the reliability of the satellite deorbit device.

[0049] In an embodiment of the present application, the satellite deorbit device may further include a mast mechanism limiting portion 7, the mast mechanism 5 is inserted into the mast mechanism limiting portion 7, and the mast mechanism limiting portion 7 is fixedly connected to the base plate 1; specifically, when the driving mechanism 31 is running, the mast mechanism 5 is driven by the driven component 4 and extends axially along the mast mechanism limiting portion 7; the movement of the mast mechanism 5 is guided by the mast mechanism limiting portion 7, thereby avoiding hooking between the unfolded sail films 13, thereby improving the reliability and adaptability of the satellite deorbit device.

[0050] In an embodiment of the present application, the satellite deorbit device may further include a sandwich plate 8, which is fixedly connected to the base plate 1; the locking mechanism 6 may include a locking rod 61 and a rotating shaft 62, one end of the rotating shaft 62 is rotatably connected to the locking rod 61, and the other end of the rotating shaft 62 is fixedly connected to the sandwich layer; one end of the locking rod 61 is slidably connected to the driven component, and the other end of the locking rod is clamped to the side cover plate; specifically, the driven component 4 can drive the locking rod 61 to rotate relative to the rotating shaft 62.

[0051] In an embodiment of the present application, the sandwich plate 8 can be suspended above the driven component 4 to reduce the length of the rotating shaft 62, thereby reducing the manufacturing cost of the satellite deorbit device; the plate surface of the sandwich plate 8 is arranged parallel to the plate surface of the base plate 1 to improve the stability of the satellite deorbit device.

[0052] In an embodiment of the present application, the satellite deorbit device may further include an upper cover plate 10, which is fixedly connected to the interlayer plate 8 suspended above the driven component 4, and can form an enclosed accommodation space with the side cover plate 2 and the bottom plate 1 to protect the structure inside the satellite deorbit device.

[0053] In an embodiment of the present application, the locking mechanism 6 may further include a locking lubricating bushing 63, which is sleeved on the rotating shaft 62 to reduce the friction between the locking mechanism 6 and the sandwich plate 8; the locking lubricating bushing 63 is coated with a molybdenum disulfide film to prevent vacuum cold welding.

[0054] In an embodiment of the present application, the driven component 4 may include a rotating member 41 and a guide member 42, the rotating member 41 is transmission-connected to the active mechanism 32, and one end of the guide member 42 is fixedly connected to the rotating member 41; a sliding groove 611 is provided on the locking rod 61, and the other end of the guide member 42 is slidingly connected to the sliding groove 611.

[0055] Specifically, the active mechanism 32 can drive the rotating member 41 to rotate, thereby driving the guide member 42 to slide in the sliding groove 611 , thereby driving the locking rod 61 to rotate and disengage from the side cover plate 2 .

[0056] In some embodiments, the locking mechanism 6 includes a first locking mechanism 64 and a second locking mechanism 65, and the first locking mechanism 64 and the second locking mechanism 65 are coated with a molybdenum disulfide film; the driven component 4 includes a first guide member that cooperates with the first locking mechanism 64, and a second guide member that cooperates with the second locking mechanism 65, the length of the first guide member 42 is greater than the length of the second guide member 43, the first guide member and the second guide member are fixedly connected to the rotating member 41, the first locking mechanism 64 includes a first locking rod, and the second locking mechanism 65 includes a second locking rod, and the first locking rod can be vertically staggered with the second locking rod.

[0057] When the active mechanism 32 drives the rotating member 41 to rotate, the first guide member and the second guide member slide in the corresponding sliding groove 611 without contacting each other until the locking rod 61 is separated from the side cover 2, thereby ensuring the success rate of the operation of the satellite deorbit device and improving the reliability of the satellite deorbit device.

[0058] In the embodiment of the present application, the rotating member 41 can be a driven gear, which is connected to the driving gear in a transmission manner. The tooth surface of the driving gear is coated with a molybdenum dioxide film to prevent vacuum cold welding of the contact surfaces of the driving gear and the driven gear under vacuum conditions; the guide member 42 can be a locking hook, and the sliding groove 611 is sleeved on the locking hook.

[0059] In the embodiment of the present application, the driven component 4 may further include a driven component mounting seat 44 , and the driven component mounting seat 44 is fixedly connected to the base plate 1 .

[0060] In an embodiment of the present application, a guide member sliding outlet 612 is provided on the locking rod 61, and the guide member sliding outlet 612 is arranged on the side wall of the sliding groove 611 close to one end of the rotating shaft 62. The guide member 42 can slide out from the guide member sliding outlet 42 to disengage the locking rod 61 from the connection with the rotating member 41.

[0061] In the embodiment of the present application, a snap-fit ​​hook 613 is further provided on the locking rod 61, and a snap-fit ​​portion 21 matching the snap-fit ​​hook 613 is provided on the side cover plate 2; the locking rod 61 is snap-fitted to the side cover plate 2 through the cooperation between the snap-fit ​​hook 613 and the snap-fit ​​portion 21; by snapping the locking rod 61 to the side cover plate 2, the side cover plate 2 is limited by a simple mechanical structure, which reduces the requirement for limiting the side cover plate 2, simplifies the design of the connection relationship between the side cover plate 2 and the base plate 1, simplifies the structure of the satellite deorbit device, and reduces the complexity of the system.

[0062] In an embodiment of the present application, the clamping portion 21 can be a lug lap plate, and the clamping surface of the clamping hook 613 and the lug lap plate is plated with a molybdenum disulfide film to prevent vacuum cold welding; the locking rod 61 and the driven gear form a crank slider mechanism, specifically, the driven gear, the locking hook and the sliding groove 611 form a crank slider mechanism, the driven gear serves as the active rod in the crank slider mechanism, the locking hook and the sliding groove 611 serve as the slider mechanism, and the clamping hook 613 serves as the driven rod; by forming a crank slider mechanism, the torque requirement when the locking rod 61 is disconnected from the rotating part 41 can be reduced; at the same time, the other end of the locking rod 61 is clamped with the side cover plate 2, and the two ends of the locking rod 61 are fixed at the same time to achieve the limitation of the side cover plate, thereby improving the reliability of the satellite deorbit device locking and reducing the cost of the satellite deorbit device.

[0063] In an embodiment of the present application, the satellite deorbit device may further include a clamping adjustment component 9, which is fixedly connected to the base plate 1, and the clamping adjustment component 9 is arranged adjacent to the driven component 4; one end of the boom mechanism 5 passes through the gap between the clamping adjustment component 9 and the driven component 4, and is passed through the boom mechanism limiting portion 7, and the clamping adjustment component 9 is pressed against the boom mechanism 5.

[0064] In the embodiment of the present application, the driven component 4 includes a driven roller 43 , which is in transmission connection with the active mechanism 32 ; specifically, the active mechanism 32 can drive the driven roller 43 to rotate.

[0065] In the embodiment of the present application, the clamping adjustment assembly 9 includes a clamping wheel 91 , and the driven roller 43 is disposed adjacent to the clamping wheel 91 . The driven roller 43 and the clamping wheel 91 are respectively in contact with the boom mechanism 5 .

[0066] In the embodiment of the present application, the driven roller 43 and the rotating member 41 are coaxially connected, and the driven roller 43 and the rotating member 41 rotate synchronously. The driven roller 43 is coated with a tungsten carbide film to increase the friction between the driven roller 43 and the boom mechanism 5, so that the driven roller 43 can drive the boom mechanism 5 to move.

[0067] In the examples of this application, please refer to Figure 5 The driven component 4 may further include an upper roller lubricating bushing 45 and a lower roller lubricating bushing 46. The upper roller lubricating bushing 45 and the lower roller lubricating bushing 46 are respectively fixedly connected to both sides of the driven roller 43. The upper roller lubricating bushing 45 and the lower roller lubricating bushing 46 are respectively plated with molybdenum disulfide films to prevent vacuum cold welding.

[0068] In an embodiment of the present application, the clamping adjustment assembly 9 also includes an elastic member 92 , and the clamping wheel 91 is connected to one end of the elastic member 92 . Under the action of external force, the clamping wheel 91 can move along the elastic direction of the elastic member 92 to compress the elastic member 92 .

[0069] In the embodiment of the present application, when the active mechanism 32 drives the driven roller 43 to rotate, the driven roller 43 can drive the boom mechanism 5 to move axially along the boom mechanism limiting portion 7, and then the boom mechanism 5 can drive the clamping wheel 91 to rotate to compress the elastic member 92, so that the boom mechanism 5 can be extended in the direction away from the power source assembly 3; by adjusting the compression amount of the elastic member 92, the pressure applied to the boom mechanism 5 is adjusted, and then the active friction force of the boom mechanism 5 when extending is adjusted, thereby enhancing the adaptability of the satellite deorbit device to boom mechanisms 5 of different forms or different friction coefficients, and realizing structural coupling.

[0070] In the examples of this application, please refer to Figure 7The clamping adjustment assembly 9 can also include a clamping wheel base 93, a clamping wheel cover 94, an elastic member lubricating ring 95, a clamping adjustment nut 96, a clamping device mounting seat 97 and a clamping adjustment rod 98. The clamping wheel base 93 and the clamping wheel cover 94 are respectively fixedly connected to the clamping wheel 91, and the clamping wheel base 93 and the clamping wheel cover 94 are fixedly connected to form an accommodating space for accommodating the clamping wheel 91. The elastic member lubricating ring 95 is arranged between the clamping wheel base 93 and the elastic member 92. The clamping adjustment rod 98 is fixed to the base plate 1 through the clamping device mounting seat 97. One end of the elastic member 92 is fixedly connected to the clamping wheel base 93 through the elastic member lubricating ring 95, and the other end of the elastic member 92 is fixedly connected to the clamping adjustment nut 96; the clamping wheel base 93 can move relative to the base plate 1 under the rotation of the clamping wheel 91 to compress The elastic member 92 is compressed; the contact surfaces of the pressure wheel base 93 and the pressure wheel cover 94 are plated with molybdenum disulfide to prevent vacuum cold welding; the elastic member lubricating ring 95 is provided with molybdenum disulfide to prevent vacuum cold welding; the pressure wheel 91 is plated with tungsten carbide to increase the friction between the pressure wheel and the boom mechanism; by adjusting the position of the tightening adjustment nut 96 on the tightening adjustment rod 98, the initial elastic potential energy of the elastic member 92 is adjusted so that the driven roller 43 and the pressure wheel 91 are respectively in contact with the boom mechanism 5; by adjusting the compression amount of the elastic member 92 by the tightening adjustment nut 96, the pressure applied to the boom mechanism 5 is adjusted, and then the active friction force of the boom mechanism 5 when it is extended is adjusted, thereby enhancing the adaptability of the satellite deorbit device to boom mechanisms 5 of different forms or different friction coefficients, and realizing structural coupling.

[0071] In the examples of this application, see Figure 6 The satellite deorbit device also includes a sail boom mechanism storage assembly 12, which includes a shaft upper cover plate 121, a shaft 122, a storage assembly lubricating bushing 123 and a sail boom mechanism storage box 124. One end of the shaft 122 is rotatably connected to the shaft upper cover plate 121, and the shaft 122 is rotatably connected to the sail boom mechanism storage box 124 through the storage assembly lubricating bushing 123. The sail boom mechanism storage box 124 is fixedly connected to the base plate 1; the contact surface between the storage assembly lubricating bushing 123 and the shaft upper cover plate 121 is coated with a molybdenum disulfide film to prevent vacuum cold welding; the material of the sail boom mechanism 5 can be carbon fiber material, and the sail boom mechanism 5 is wound around the shaft 122 and then stored in the sail boom mechanism storage box 124.

[0072] The satellite deorbit device provided in the embodiments of the present application has the following beneficial effects:

[0073] 1. The satellite deorbit device of the present application has a power source component that can actively control the sail deployment process of the satellite deorbit device, and then can control the power source component through a control signal to control the sail deployment process of the satellite deorbit device; by controlling the operating speed of the power source component, the extension speed of the boom mechanism is controlled, and the deployment time of the deorbit sail is precisely regulated, thereby improving the deployment success rate of the deorbit sail and reducing the satellite's hovering time.

[0074] 2. The satellite deorbit device of the present application guides the movement of the sail boom mechanism through the limiting part of the sail boom mechanism, thereby avoiding hooking between the unfolded sail films and improving the reliability and adaptability of the satellite deorbit device.

[0075] 3. The satellite deorbit device of the present application forms a crank slider four-bar mechanism by slidingly connecting the locking rod and the rotating part to reduce the torque requirement when the locking rod and the rotating part are disconnected; at the same time, the other end of the locking rod is clamped with the side cover plate, and the two ends of the locking rod are fixed at the same time to achieve the limitation of the side cover plate, thereby improving the locking reliability of the satellite deorbit device.

[0076] 4. The satellite deorbit device of the present application realizes the limitation of the side cover plate with a simple mechanical structure by clamping the locking rod with the side cover plate, thereby reducing the limitation requirements for the side cover plate, simplifying the design of the connection relationship between the side cover plate and the bottom plate, simplifying the structure of the satellite deorbit device, and reducing the complexity of the system.

[0077] 5. The satellite deorbit device of the present application adjusts the pressure applied to the boom mechanism by adjusting the compression amount of the elastic member, thereby adjusting the active friction force when the boom mechanism is extended, thereby enhancing the adaptability of the satellite deorbit device to boom mechanisms of different forms or different friction coefficients and achieving structural decoupling.

[0078] The working principle of the satellite deorbit device provided in the embodiment of the present application is as follows:

[0079] During the satellite launch and normal operation stage, the side cover 2 is fixedly connected to the base plate 1 by the unfolding hinge 11 and the locking mechanism 6 to ensure that the satellite deorbit device will not be locked due to misunderstanding, thereby preventing the satellite deorbit device from being deployed prematurely; at the end of the satellite's life, the driving mechanism 31 receives an operating instruction to operate, and the operating instruction can be a control instruction issued by the ground control center, or a control instruction issued by the satellite's own control center under set conditions; the driving mechanism 31 drives the active mechanism 32 to rotate, and then drives the driven component 4 to rotate. Specifically, the rotation of the driven component 4 is divided into the rotation of the rotating member 41 and the rotation of the driven roller 43. The rotating member 41 and the driven roller 43 can be synchronously rotated; the rotating member 41 drives the guide member 42 to slide in the sliding groove 611, and then drives the rotating rod relative to The rotating shaft 62 rotates, and the contact area of ​​the clamping hook 613 relative to the clamping portion 21 gradually decreases; then, the guide member 42 is disconnected from the locking rod 61, the locking rod 61 is released from the limit of the rotating member 41, and the contact area of ​​the clamping hook 613 and the clamping portion 21 is zero, and the locking rod 61 is disconnected from the side cover 2; the side cover 2 can be rotated relative to the bottom plate 1 under the elastic force of the unfolding hinge, so that the sail-spreading film 13 in the satellite deorbit device can be extended out of the device along with the boom mechanism 5; the rotation of the driven roller 43 can drive the boom mechanism 5 to extend axially along the boom mechanism limiting portion 7, and the boom mechanism 5 drives the rotation of the pressure wheel 91 to compress the elastic member 92, thereby reducing the pressing force applied to the boom mechanism 5, so that the boom mechanism 5 can successfully extend from the storage assembly, forming a Figure 10 The satellite is shown in the state of extended and retracted sails.

[0080] The above description has fully disclosed the specific embodiments of this application. It should be noted that any changes made by those skilled in the art to the specific embodiments of this application do not depart from the scope of the claims of this application. Accordingly, the scope of the claims of this application is not limited to the above specific embodiments.

Claims

1. A satellite deorbiting device, characterized in that: It comprises a bottom plate (1), a side cover plate (2), a power source assembly (3), a driven assembly (4), a sail boom mechanism (5) and a locking mechanism (6). The surrounding areas of the bottom plate (1) are rotatably connected to the plurality of side cover plates (2), wherein the central area is provided with the power source assembly (3) and the driven assembly (4) connected thereto in a transmission manner, the driven assembly (4) being slidably connected to one end of the locking mechanism (6), and the other end of the locking mechanism (6) being engaged with the side cover plate (2); The bottom plate (1) and the plurality of side cover plates (2) form an accommodating space, wherein an expandable sail film (13) is provided in the accommodating space, and the corners of the sail film (13) are fixedly connected to the protruding end of the sail boom mechanism (5), and the sail boom mechanism (5) is connected to the driven component (4) and is driven to extend therefrom; The power source assembly (3) is controlled by a control signal to control the sail deployment process of the satellite deorbit device; the power source assembly (3) includes a driving mechanism (31) and an active mechanism (32), and the driving mechanism (31) is drivingly connected to the active mechanism (32); The locking mechanism (6) includes a locking rod (61), the driven assembly (4) includes a rotating member (41) and a guide member (42), and the rotating member (41) is transmission-connected to the active mechanism (32); One end of the locking rod (61) is slidably connected to the rotating member (41); the other end of the locking rod (61) is clamped to the side cover plate (2); One end of the guide member (42) is fixedly connected to the rotating member (41); a sliding groove (611) is provided on the locking rod (61), and the other end of the guide member (42) is slidably connected to the sliding groove (611); The locking rod (61) is further provided with a guide member sliding outlet (612), which is arranged on the side wall of the sliding groove (611) close to one end of the rotating shaft (62); the guide member (42) can slide out of the guide member sliding outlet (612) to disengage the locking rod (61) from the connection with the rotating member (41); The rotating member (41), the guide member (42) and the locking rod (61) form a crank slider mechanism.

2. A satellite deorbiting device according to claim 1, characterized in that: The driving mechanism (31) is fixedly connected to the base plate (1), and the active mechanism (32) is transmission-connected to the driven component (4).

3. A satellite deorbiting device according to claim 1, characterized in that: It also includes a sail gantry mechanism limiting portion (7), the sail gantry mechanism (5) is arranged in the sail gantry mechanism limiting portion (7), and the sail gantry mechanism limiting portion (7) is fixedly connected to the bottom plate (1).

4. A satellite deorbiting device according to claim 1, characterized in that: It also includes a sandwich plate (8), wherein the sandwich plate (8) is fixedly connected to the bottom plate (1); The locking mechanism (6) further comprises a rotating shaft (62), one end of which is rotationally connected to the locking rod (61), and the other end of which is fixedly connected to the sandwich plate (8).

5. The satellite deorbiting device according to claim 1, wherein: The locking rod (61) is further provided with a clamping hook (613), and the side cover (2) is provided with a clamping portion (21) matching the clamping hook (613); the locking rod (61) is clamped to the side cover (2) by the clamping hook (613) cooperating with the clamping portion (21).

6. A satellite deorbiting device according to claim 3, characterized in that: The invention also includes a pressing adjustment component (9), which is fixedly connected to the base plate (1) and is arranged adjacent to the driven component (4); one end of the sail girders (5) passes through the gap between the pressing adjustment component (9) and the driven component (4) and is then passed through the limiting portion (7) of the sail girders, and the pressing adjustment component (9) is pressed against the sail girders (5).

7. A satellite deorbiting device according to claim 6, characterized in that: The driven assembly (4) comprises a driven roller (43), and the driven roller (43) is in transmission connection with the active mechanism (32).

8. A satellite deorbiting device according to claim 7, characterized in that: The clamping adjustment assembly (9) includes a clamping wheel (91), the driven roller (43) is arranged adjacent to the clamping wheel (91), and the driven roller (43) and the clamping wheel (91) are respectively in contact with the sail boom mechanism (5).

9. A satellite deorbiting device according to claim 8, characterized in that: The compression adjustment assembly (9) further includes an elastic member (92), the compression wheel (91) being connected to one end of the elastic member (92), and the compression wheel (91) being able to move along the elastic direction of the elastic member (92) under the action of an external force to compress the elastic member (92).

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