A lifting mechanism for use outside a spacecraft cabin

Abstract

This invention discloses a lifting mechanism for use outside a spacecraft cabin, comprising a mounting base for fixing to the cabin body, a load top plate for fixing the payload, and a telescopic cylinder connecting the mounting base and the load top plate. The telescopic cylinder includes several nested sleeves, with adjacent sleeves slidably connected by a sliding structure. A locking structure is provided between adjacent sleeves to automatically lock their relative positions when the adjacent sleeves are slidably extended into their final positions. A lock-free screw assembly is provided between the load top plate and the mounting base to lock the relative positions between the load top plate and the mounting base when the telescopic cylinder is in a fully retracted state. The lock-free screw assembly can be released by external force. This invention allows the payload equipment to reach the required working position simply by unlocking the lock-free screw assembly and manually lifting it, greatly reducing the complexity of on-orbit operations for astronauts and avoiding the inconvenience caused by replacing mounting brackets in orbit.

Description

Technical Field

[0001] This invention relates to the field of spacecraft external payload installation technology, specifically a lifting mechanism for spacecraft external payloads. Background Technology

[0002] With the continuous development of manned spaceflight, due to the limitations of the launch envelope, payloads such as panoramic cameras and antennas installed outside the spacecraft cannot be installed in positions that meet the working potential field requirements during the launch phase. After the spacecraft enters orbit, it needs to be lifted in orbit. This operation is generally completed by astronauts exiting the spacecraft to replace the mounting brackets at different heights. That is, the original launch brackets are first disassembled and then new brackets are installed, which increases the complexity of the astronauts' in-orbit operations and the length of the extravehicular activity, thus increasing the difficulty and safety risks of the mission. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a lifting mechanism that can be manually lifted to bring the load equipment to the working position and can be used for various load equipment that need to be lifted in orbit.

[0004] To achieve the above objectives, the present invention designs a lifting mechanism for the outside of a spacecraft cabin, including a mounting base for fixing to the cabin body, a load top plate for fixing the load, and a telescopic cylinder connecting the mounting base and the load top plate.

[0005] The telescopic cylinder includes several nested sleeves, and adjacent sleeves are slidably connected by a sliding structure. A locking structure is provided between adjacent sleeves, which is used to automatically lock the relative position of the two when adjacent sleeves are slidably stretched into place.

[0006] A non-detachable screw assembly is provided between the load top plate and the mounting base for locking the relative position between the load top plate and the mounting base when the telescopic cylinder is in the fully retracted state.

[0007] Preferably, the sleeve located on the inner side of the adjacent sleeves is the inner sleeve, and the sleeve located on the outer side is the outer sleeve.

[0008] The sliding structure includes a slide bar and a slide groove. The slide bar is located on the outer wall of the inner sleeve along the telescopic direction of the telescopic cylinder, and the slide groove is located on the inner wall of the outer sleeve along the telescopic direction of the telescopic cylinder. The slide bar is slidably connected to the slide groove.

[0009] Preferably, the locking structure includes a stretching limiting component and a retraction limiting component. The stretching limiting component restricts the stretching movement of adjacent sleeves when they are stretched to their full positions, and the retraction limiting component restricts the retraction movement of adjacent sleeves when they are stretched to their full positions. The retraction limiting component includes:

[0010] Mounting base, connected to the outer wall of the outer sleeve;

[0011] A locking pin is slidably connected to the mounting base along the radial direction of the telescopic cylinder, and one end of the locking pin facing the radial inner side of the telescopic cylinder passes through the side wall of the outer sleeve and extends into the slide groove from the bottom surface of the slide groove.

[0012] An elastic element is disposed between the mounting base and the locking pin, for driving the locking pin to abut against the slide bar in the slide groove;

[0013] A locking hole is provided in the slide bar. When the adjacent sleeve is stretched into place, the locking pin is engaged in the locking hole under the elastic force of the elastic element. The locking pin abuts against the inner wall of the locking hole on the side of the load top plate to restrict the retraction movement of the adjacent sleeve.

[0014] Preferably, the stretching limiting assembly includes a first limiting member on the outer wall of the inner sleeve and a second limiting member on the inner wall of the outer sleeve. The first limiting member and the second limiting member abut against each other when the telescopic cylinder is stretched into place to limit the stretching movement of adjacent sleeves.

[0015] Preferably, the locking hole has a conical surface on the side near the load top plate, and the locking pin has a conical head at the end facing the radial inner side of the telescopic cylinder. The surface of the conical head that abuts against the conical surface when the telescopic cylinder is stretched into place has a self-locking angle design between it and the conical surface.

[0016] Preferably, the slide bar is provided with a slide track arranged along the telescopic direction of the telescopic cylinder, and one end of the locking pin facing the radial inner side of the telescopic cylinder is slidably connected to the slide track; one end of the slide track is connected to the locking hole.

[0017] Preferably, in the telescopic cylinder, except for the innermost adjacent sleeve, the axial length of the outer sleeve of the other adjacent sleeves is less than the axial length of the inner sleeve.

[0018] Preferably, except for the innermost and outermost sleeves, the outer side walls of the other sleeves in the telescopic cylinder are provided with clamping blocks, and the end face of the clamping block facing the load top plate is flush with the end face of the sleeve connected to the clamping block facing the load top plate.

[0019] Except for the innermost adjacent sleeve, the sum of the length of the outer sleeve and the length of the clamping block connected to the inner sleeve in the other adjacent sleeves along the axial length of the telescopic cylinder is equal to the length of the inner sleeve.

[0020] Preferably, the load top plate is provided with heat dissipation flaps;

[0021] And / or, the mounting base is provided with weight-reducing grooves and / or reinforcing ribs.

[0022] Preferably, the non-detachable screw assembly includes a non-detachable screw and locking holes respectively provided on the load top plate and the mounting base, wherein the non-detachable screw is threadedly connected to the locking holes on the load top plate and the mounting base respectively when the telescopic cylinder is fully retracted.

[0023] Preferably, the non-detachable screw assembly includes a non-detachable screw and locking holes respectively provided on the load top plate and the mounting base, wherein the non-detachable screw is threadedly connected to the locking holes on the load top plate and the mounting base respectively when the telescopic cylinder is fully retracted.

[0024] Compared with existing technologies, this invention eliminates the need for astronauts to disassemble and install the support. By simply releasing the locking of the non-detachable screw assembly and then manually lifting or stretching the telescopic cylinder, the payload equipment installed on the payload top plate can reach the required working position, greatly reducing the complexity of on-orbit operations for astronauts. This mechanism features strong load-bearing capacity, reliable and secure clamping, low deployment resistance, reliable locking in place, and good rigidity in the deployed state. It can be used as a mounting bracket for various payloads such as panoramic cameras and antennas that require manual lifting by astronauts outside the spacecraft, avoiding the operational inconvenience caused by astronauts replacing mounting brackets in orbit. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of a lifting mechanism for use outside a spacecraft cabin according to the present invention;

[0026] Figure 2 This is a schematic diagram of a lifting mechanism for the exterior of a spacecraft cabin when fully retracted, according to the present invention.

[0027] Figure 3 This is a schematic diagram of a lifting mechanism for the exterior of a spacecraft cabin in its fully deployed state, according to the present invention.

[0028] Figure 4 This is a cross-sectional schematic diagram of a lifting mechanism for the exterior of a spacecraft cabin according to the present invention when fully deployed.

[0029] Figure 5 This is a schematic diagram of the structure of a second-stage sleeve according to the present invention;

[0030] Figure 6 This is a top view schematic diagram of a second-stage sleeve according to the present invention;

[0031] Figure 7 A schematic diagram of the structure of a retractable limiting component (excluding locking holes) according to the present invention;

[0032] Figure 8 This is a schematic diagram of the structure of a load-bearing top plate according to the present invention;

[0033] Figure 9 This is a top view schematic diagram of a load-bearing top plate according to the present invention;

[0034] Figure 10 This is a schematic diagram of the structure of a mounting base according to the present invention;

[0035] Figure 11 This is a top view of a mounting base according to the present invention.

[0036] Explanation of reference numerals in the attached figures:

[0037] 1: Mounting base; 2: Load-bearing top plate; 3: Telescopic cylinder; 3-1: First-stage sleeve; 3-2: Second-stage sleeve; 3-3: Third-stage sleeve; 3-4: Fourth-stage sleeve; 3-5: Fifth-stage sleeve; 4: Retraction limiting assembly; 4-1: Mounting seat; 4-1a: Actuating port; 4-2: Locking pin; 4-2a: Stop block; 4-3: Spring; 5: Heat dissipation folding lug; 6: Non-removable screw; 7: Clamping block;

[0038] 1a: Reinforcing rib; 1b: Weight reduction groove; 2a: Mounting foot; 2b: Load mounting area; 3a: Sliding bar; 3b: Sliding groove; 3c: Sliding track; 3d: Locking hole; 3e: Through hole; 3f: First limiting member; 3g: Second limiting member. Detailed Implementation

[0039] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0040] See Figures 1 to 11 A lifting mechanism for use outside a spacecraft cabin is disclosed, which can be used for the installation of payloads such as panoramic cameras outside the spacecraft cabin. The lifting mechanism includes a mounting base 1 for fixing to the cabin body, a load top plate 2 for fixing the payload, and a telescopic cylinder 3 connecting the mounting base 1 and the load top plate 2. The telescopic cylinder 3 includes several nested sleeves, with adjacent sleeves slidably connected by a sliding structure. A locking structure is provided between adjacent sleeves to automatically lock their relative positions when adjacent sleeves are slidably extended into their final positions. A non-detachable screw assembly is provided between the load top plate 2 and the mounting base 1 to lock the relative positions between the load top plate 2 and the mounting base 1 when the telescopic cylinder 3 is in the fully retracted state, and the non-detachable screw assembly can be released by external force.

[0041] The telescopic cylinder 3 is the main load-bearing component of the lifting mechanism used outside the spacecraft cabin. Specifically, in this embodiment, the telescopic cylinder 3 adopts a five-stage sleeve, which consists of a first-stage sleeve 3-1, a second-stage sleeve 3-2, a third-stage sleeve 3-3, a fourth-stage sleeve 3-4, and a fifth-stage sleeve 3-5, arranged sequentially from the load top plate 2 to the mounting base 1. In other embodiments, the number of stages of the telescopic cylinder 3 can be designed according to actual needs, and there is no limitation here.

[0042] For ease of explanation, the sleeve located on the inside of an adjacent sleeve is called the inner sleeve, and the sleeve located on the outside is called the outer sleeve.

[0043] The sliding structure includes a slider 3a and a groove 3b. The slider 3a is located on the outer wall of the inner sleeve along the telescopic direction of the telescopic cylinder 3, and the groove 3b is located on the inner wall of the outer sleeve along the telescopic direction of the telescopic cylinder 3. The slider 3a is slidably connected within the groove 3b. When multiple sets of sliding structures are provided between adjacent sleeves, it is preferable that the multiple sets of sliding structures are evenly distributed circumferentially and that the grooves 3b and sliders 3a on the same sleeve are staggered. In this embodiment, three sets of sliding structures are provided between adjacent sleeves, and the three sets of sliding structures are evenly distributed circumferentially around the telescopic cylinder 3, i.e., spaced 120 degrees apart. The sliders 3a and grooves 3b on the same sleeve are staggered by 60 degrees. Of course, in other embodiments, the number and arrangement of sliding structures can be set according to actual conditions, and no restrictions are imposed here.

[0044] The locking structure includes a stretching limiting component and a retraction limiting component 4. The stretching limiting component is used to restrict the stretching movement of adjacent sleeves when they are stretched to the correct position, and the retraction limiting component 4 is used to restrict the retraction movement of adjacent sleeves when they are stretched to the correct position.

[0045] The retraction limiting assembly 4 includes a mounting base 4-1, a locking pin 4-2, an elastic element, and a locking hole 3d. The mounting base 4-1 is connected to the outer wall of the outer sleeve. The locking pin 4-2 is slidably connected to the mounting base 4-1 along the radial direction of the telescopic cylinder 3, and one end of the locking pin 4-2 facing the radially inner side of the telescopic cylinder 3 passes through the side wall of the outer sleeve and extends into the slide groove 3b from the bottom surface of the groove 3b. The elastic element is located between the mounting base 4-1 and the locking pin 4-2, and is used to drive the locking pin 4-2 to abut against the slide bar 3a in the slide groove 3b. The locking hole 3d is located in the slide bar 3a. When the adjacent sleeve is stretched into place, the locking pin 4-2 is engaged in the locking hole 3d under the elastic force of the elastic element. The locking pin 4-2 abuts against the inner side wall of the locking hole 3d near the load top plate 2, thereby restricting the retraction movement of the adjacent sleeve.

[0046] Specifically, in this embodiment, a mounting boss is provided on the corresponding outer wall of the groove 3b of the outer sleeve, and a through hole 3e is provided on the mounting boss for the locking pin 4-2 to pass through. The mounting base 4-1 is provided with a cavity with openings at both ends along the sliding direction of the locking pin 4-2. The opening at one end along the radial inner side of the telescopic cylinder 3 is called the first opening, and the other is called the second opening. The end face of the first opening of the mounting base 4-1 can be fixed to the mounting boss by fasteners or the like, and the first opening covers the through hole 3e, so that the locking pin 4-2 can extend into the through hole 3e through the first opening. More specifically, the mounting base 4-1 and the through hole 3e can be arranged on the outer sleeve close to the load top plate 2. The end of the locking pin 4-2 facing the radial outer side of the telescopic cylinder 3 extends out of the cavity from the second opening.

[0047] A stop 4-2a is provided on the locking pin 4-2. The elastic element can be a spring 4-3, which is sleeved on the locking pin 4-2. The two ends of the spring 4-3 abut against one end face of the stop 4-2a and the inner wall of the inner cavity of the mounting base 4-1. The purpose of the stop 4-2a is to provide a force-applying surface for the spring 4-3, and the locking pin 4-2 can slide linearly in the mounting base 4-1 through the cooperation between the stop 4-2a and the inner wall of the upper cavity of the mounting base 4-1 (that is, the locking pin 4-2 has only one degree of freedom to slide in the radial direction of the telescopic cylinder 3 relative to the mounting base 4-1). An actuation port 4-1a is provided on the side of the mounting base 4-1 (that is, the circumferential direction of the locking pin 4-2). The two ends of the actuation port 4-1a in the length direction are distributed to correspond to the start and stop positions of the stroke of the locking pin 4-2.

[0048] A slide rail 3c is provided on the slide bar 3a, which is arranged along the telescopic direction of the telescopic cylinder 3. Specifically, the slide rail 3c can be set on the center line of the slide bar 3a. The end of the locking pin 4-2 facing the radially inner side of the telescopic cylinder 3 is slidably connected in the slide rail 3c. One end of the slide rail 3c is connected to the locking hole 3d. When the corresponding adjacent sleeve is stretched, the slide bar 3a slides in the slide groove 3b, and the end of the locking pin 4-2 facing the radially inner side of the telescopic cylinder 3 slides in the slide rail 3c on the slide bar 3a until the locking pin 4-2 reaches the position of the locking hole 3d, and is locked into the locking hole 3d under the action of the spring 4-3. The setting of the slide rail 3c can make the sliding trajectory of the locking pin 4-2 on the slide bar 3a more stable.

[0049] The locking hole 3d is tapered on the side near the load top plate 2, and the locking pin 4-2 is set as a conical head on the radially inner side facing the telescopic cylinder 3. When the adjacent sleeves are stretched into place, the inclined sidewall of the conical head near the load top plate 2 abuts against the tapered surface. At this time, if the locking pin 4-2 is to continue sliding radially inward towards the telescopic cylinder 3, the outer sleeve needs to move relative to the inner sleeve towards the mounting base 1. However, the stretching limit assembly restricts the stretching movement of the two adjacent sleeves. Therefore, the locking pin 4-2 cannot continue to slide radially inward towards the telescopic cylinder 3.

[0050] To prevent the conical head of the locking pin 4-2 from sliding out of the locking hole 3d along the conical surface towards the load-bearing top plate 2 when the lifting mechanism is in operation (i.e., when the telescopic cylinder 3 is fully extended), a self-locking angle design is provided between the surface of the conical head that abuts against the conical surface and the conical surface when the telescopic cylinder 3 is stretched into place. The angle of the self-locking angle design depends on the coefficient of friction of the two materials used to make the conical surface and the conical head, and can be designed according to actual conditions. Furthermore, the locking hole 3d is opened up to the axial end face of the sleeve facing the mounting base 1 on the side close to the mounting base 1. The purpose of opening it up is to avoid over-constraint with the tension limiting component.

[0051] The tension limiting assembly includes a first limiting member 3f disposed on the outer wall of the inner sleeve and a second limiting member 3g disposed on the inner wall of the outer sleeve. The first limiting member 3f and the second limiting member 3g abut against each other when the telescopic cylinder 3 is stretched into place to limit the adjacent sleeve from continuing to slide.

[0052] Specifically, in this embodiment, the first limiting member 3f is positioned close to the mounting base 1, and the second limiting member 3g is positioned close to the load top plate 2. When two adjacent sleeves are stretched into place, the surface of the first limiting member 3f facing the load top plate 2 abuts against the surface of the second limiting member 3g facing the mounting base 1, thereby restricting the two adjacent sleeves from continuing to slide. Preferably, the two abutting surfaces are both located in a plane perpendicular to the axial direction of the telescopic cylinder 3. Three sets of limiting components are evenly distributed around the circumference of the telescopic cylinder 3 between adjacent sleeves. The first limiting member 3f and the second limiting member 3g on the same sleeve are offset by 60 degrees, and the first limiting member 3f / second limiting member 3g and the adjacent sliding strip 3a / sliding groove 3b are offset by 30 degrees. Of course, in other embodiments, the number and arrangement of the limiting components can be adjusted according to actual conditions, and no restrictions are imposed here.

[0053] In the telescopic sleeve 3, except for the innermost adjacent sleeve, the axial length of the outer sleeve is less than that of the inner sleeve in all other adjacent sleeves. The difference in axial length is mainly to avoid the retraction limiting component 4. Since the retraction limiting component 4 is the same between each adjacent sleeve, the difference in axial length between each level of sleeve can be the same. Among them, the axial lengths of the first-level sleeve 3-1 and the second-level sleeve 3-2 are equal.

[0054] In the telescopic cylinder 3, except for the innermost and outermost sleeves, the outer walls of the remaining sleeves are provided with clamping blocks 7; specifically, in this embodiment, clamping blocks 7 are provided on the second-stage sleeve 3-2, the third-stage sleeve 3-3, and the fourth-stage sleeve 3-4. The end face of the clamping block 7 facing the load top plate 2 is flush with the end face of the sleeve connected to the clamping block 7 facing the load top plate 2. In the telescopic cylinder 3, except for the innermost adjacent sleeve, along the axial length of the telescopic cylinder 3, the sum of the length of the outer sleeve and the length of the clamping block 7 connected to the inner sleeve is equal to the length of the inner sleeve. The clamping blocks 7 are provided to ensure that the telescopic cylinder 3 presses each stage of the sleeves tightly onto the mounting base 1 when it is fully retracted. The clamping blocks 7 can be connected to the corresponding sleeves by fasteners such as bolts; multiple clamping blocks 7 can be evenly distributed around the circumference of the telescopic cylinder 3 on the same sleeve.

[0055] Mounting base 1 is designed to conform to the curved surface of the cabin. Mounting base 1 is connected to the cabin using screws and rivets, and thermal insulation pads are used between mounting base 1 and the cabin for heat insulation installation. In addition, mounting base 1 has weight-reducing grooves 1b and reinforcing ribs 1a, and all edges are rounded to meet ergonomic and safety design requirements.

[0056] The sleeve closest to the mounting base 1 in the telescopic cylinder 3, which is the fifth-stage sleeve 3-5 in this embodiment, is screwed to the mounting base 1. The sleeve closest to the load top plate 2 in the telescopic cylinder 3, which is the first stage, can be installed on the load top plate 2 by countersunk screws.

[0057] The captive screw assembly includes a captive screw 6 and locking holes respectively located on the load top plate 2 and the mounting base 1. When the telescopic cylinder 3 is fully retracted, the captive screw 6 is threadedly connected to the locking holes on both the load top plate 2 and the mounting base 1, thereby achieving a fixed connection between the load top plate 2 and the mounting base 1. Specifically, a mounting foot 2a integrally formed with the load top plate 2 can be provided, and the locking hole is provided on the mounting foot 2a. The captive screw 6 passes through the locking hole on the mounting foot 2a and then enters the locking hole on the mounting base 1. To make the fixation of the load top plate 2 and the mounting base 1 more stable, multiple sets of captive screw assemblies can be provided.

[0058] like Figure 9 As shown, in this embodiment, the load top plate 2 is rectangular in shape, and mounting feet 2a are provided at the four corners of the rectangular load top plate 2. Diagonal ribs are provided on the mounting feet 2a to enhance the structural rigidity. The load top plate 2 has heat dissipation flaps 5 provided downward between two adjacent mounting feet 2a to increase the heat dissipation area.

[0059] The surfaces of the sliding bar 3a, sliding track 3c, first limiting member 3f, and second limiting member 3g that abut against each other can all undergo hard anodizing treatment to increase their wear resistance. The remaining areas of the sleeve, except for the hard anodized areas, undergo bright anodizing treatment to ensure the absorption rate. The load top plate 2, except for the load mounting area 2b, also undergoes bright anodizing treatment to ensure the absorption rate; simultaneously, it is sprayed with spacecraft thermal control white paint to further ensure the absorption rate; all edges of the load top plate 2 are rounded to meet ergonomic safety design requirements. Spacecraft thermal control white paint is sprayed on the heat dissipation lug 5 to ensure the absorption rate. A TAN film can be plated on the conical head of the locking pin 4-2 to increase the coefficient of friction.

[0060] The lifting mechanism for spacecraft cabins provided in this embodiment is mounted on the spacecraft cabin via a mounting base 1. The fifth-stage sleeve 3-5 of the telescopic cylinder 3 is fixed to the mounting base 1 with screws. The fourth-stage sleeve 3-4 to the first-stage sleeve are nested sequentially. The load top plate 2 is mounted on the first-stage sleeve 3-1. When the lifting mechanism is retracted, the first-stage sleeve 3-1 and the second-stage sleeve 3-2 are at the same height, and both are pressed against the mounting base 1 by the load top plate 2. The clamping blocks 7 installed on the second-stage sleeve 3-2 to the fourth-stage sleeve 3-4 can transmit clamping force, thereby pressing the third-stage sleeve 3-3 and the fourth-stage sleeve 3-4 together. Four M5 captive screws 6 installed on the load top plate 2 are tightened onto the mounting base 1 to achieve the clamping of the entire lifting mechanism.

[0061] After the spacecraft enters orbit, the astronauts exit the capsule and use an M5 power tool to unlock the four M5 captive screws 6. The spacecraft is then lifted via a handrail on the payload. During lifting, the various sleeves extend. Under the action of spring 4-3, locking pin 4-2 abuts against the slide rail 3c of the inner sleeve's slide bar 3a. As the sleeves extend and slide, when locking pin 4-2 reaches the locking hole 3d, it inserts into the locking hole 3d under the action of spring 4-3, engaging with the conical surface on the locking hole 3d to restrict the retraction movement of adjacent sleeves. At this time, the first limiting member 3f and the second limiting member 3g of the two adjacent sleeves abut against each other, restricting the extension and retraction movement between the adjacent sleeves. In the deployed state, the thermal control design on the lifting mechanism effectively dissipates heat during payload equipment operation.

[0062] The lifting mechanism for spacecraft exterior provided in this embodiment fully considers the mechanical environment during spacecraft launch, the alternating temperature environment in orbit, and the inconvenience of on-orbit operation for astronauts in terms of structural design, operational clearance design, and thermal design.

[0063] In existing designs, astronauts need to replace payload supports after extravehicular activity (EVA), involving disassembly and installation. This process is complex and inconvenient for astronauts wearing spacesuits, typically taking tens of minutes. However, with the extravehicular lifting mechanism provided in this embodiment, astronauts only need to loosen the retaining screw 6 after EVA to achieve lifting, making the operation simple and convenient, taking only a few minutes.

[0064] Although the preferred embodiments of the present invention have been disclosed above, they are not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any brief modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A lifting mechanism for use outside a spacecraft cabin, characterized in that, Includes a mounting base for fixing to the cabin, a load top plate for fixing the load, and a telescopic cylinder connecting the mounting base and the load top plate; The telescopic cylinder includes several nested sleeves, and adjacent sleeves are slidably connected by a sliding structure. A locking structure is provided between adjacent sleeves, which is used to automatically lock the relative position of the two when adjacent sleeves are slidably stretched into place. A non-removable screw assembly is provided between the load top plate and the mounting base for locking the relative position between the load top plate and the mounting base when the telescopic cylinder is in the fully retracted state; Among the adjacent sleeves, the sleeve located on the inner side is the inner sleeve, and the sleeve located on the outer side is the outer sleeve. The sliding structure includes a slide bar and a slide groove. The slide bar is disposed on the outer wall of the inner sleeve along the telescopic direction of the telescopic cylinder, and the slide groove is disposed on the inner wall of the outer sleeve along the telescopic direction of the telescopic cylinder. The slide bar is slidably connected to the slide groove. The locking structure includes a stretching limiting component and a retraction limiting component. The stretching limiting component is used to restrict the stretching movement of the adjacent sleeves when they are stretched to their full positions. The retraction limiting component is used to restrict the retraction movement of the adjacent sleeves when they are stretched to their full positions. The retractable limiting component includes: Mounting base, connected to the outer wall of the outer sleeve; A locking pin is slidably connected to the mounting base along the radial direction of the telescopic cylinder, and one end of the locking pin facing the radial inner side of the telescopic cylinder passes through the side wall of the outer sleeve and extends into the slide groove from the bottom surface of the slide groove. An elastic element is disposed between the mounting base and the locking pin, for driving the locking pin to abut against the slide bar in the slide groove; A locking hole is provided in the slide bar. When the adjacent sleeve is stretched into place, the locking pin is engaged in the locking hole under the elastic force of the elastic element. The locking pin abuts against the inner wall of the locking hole on the side of the load top plate to restrict the retraction movement of the adjacent sleeve.

2. The lifting mechanism for spacecraft exterior as described in claim 1, characterized in that, The stretching limiting assembly includes a first limiting member on the outer wall of the inner sleeve and a second limiting member on the inner wall of the outer sleeve. The first limiting member and the second limiting member abut against each other when the telescopic cylinder is stretched into place to limit the stretching movement of adjacent sleeves.

3. The lifting mechanism for spacecraft exterior as described in claim 1, characterized in that, The locking hole has a conical surface on the side near the load top plate, and the locking pin has a conical head at the end facing the radial inner side of the telescopic cylinder. The surface of the conical head that abuts against the conical surface when the telescopic cylinder is stretched into place has a self-locking angle design between it and the conical surface.

4. The lifting mechanism for spacecraft exterior as described in claim 1, characterized in that, The slide bar is provided with a slide track arranged along the telescopic direction of the telescopic cylinder, and the end of the locking pin facing the radial inner side of the telescopic cylinder is slidably connected to the slide track; one end of the slide track is connected to the locking hole.

5. The lifting mechanism for the exterior of a spacecraft cabin as described in claim 1, characterized in that, Except for the innermost adjacent sleeve, the axial length of the outer sleeve in the telescopic cylinder is smaller than the axial length of the inner sleeve.

6. The lifting mechanism for spacecraft exterior as described in claim 5, characterized in that, Except for the innermost and outermost sleeves, all other sleeves in the telescopic cylinder are provided with clamping blocks on their outer side walls. The end face of the clamping block facing the load top plate is flush with the end face of the sleeve connected to the clamping block facing the load top plate. Except for the innermost adjacent sleeve, the sum of the length of the outer sleeve and the length of the clamping block connected to the inner sleeve in the other adjacent sleeves along the axial length of the telescopic cylinder is equal to the length of the inner sleeve.

7. The lifting mechanism for spacecraft exterior as described in claim 1, characterized in that, The load top plate is provided with heat dissipation flaps; And / or, the mounting base is provided with weight-reducing grooves and / or reinforcing ribs.

8. The lifting mechanism for spacecraft exterior as described in claim 1, characterized in that, The non-detachable screw assembly includes a non-detachable screw and locking holes respectively provided on the load top plate and the mounting base. The non-detachable screw is threadedly connected to the locking holes on the load top plate and the mounting base respectively when the telescopic cylinder is fully retracted.

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