Sealing cabin door device of freight spaceship

Abstract

A freight spaceship sealing cabin door device comprises a cabin door body, a cabin door frame, a door body lateral sliding guide mechanism, a control mechanism and a cabin door porthole. A lateral sliding opening mode is innovatively adopted for the cabin door body, the cabin door body and the cabin door frame in the opening state can be kept in a relatively parallel state, occupation of the cabin door body on the space in a freight spaceship cabin is greatly reduced, interference of the cabin door body on normal operation of astronauts in the freight spaceship cabin is reduced, and the safety of the freight spaceship cabin is improved. The probability that astronauts and cargoes collide with the cabin door body is reduced, and the safety of on-orbit operation is improved. The cabin door porthole is arranged in the center of the cabin door body, the newly-designed control mechanism is arranged in the circumferential direction of the cabin door porthole, reliable opening and closing of the cabin door can be met through the newly-designed control mechanism, and astronauts can be helped to observe, study and judge the conditions in the freight spaceship cabin in advance through the cabin door porthole before the cabin door is opened. And the functionality of the sealed cabin door device of the freight spaceship is effectively expanded.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft technology, and in particular relates to a sealed hatch device for a cargo spacecraft. Background Technology

[0002] Cargo spacecraft are the core spacecraft for carrying out space cargo missions. They are used not only to provide large-scale cargo resupply to the space station, but also need to operate in orbit for extended periods. Therefore, the cargo spacecraft's sealed hatch system is one of the key mechanisms to ensure that the cargo spacecraft can adapt to the vacuum and sealed environment. It needs to ensure the cargo spacecraft's airtightness during its independent flight phase, as well as its normal opening after docking with the space station to facilitate astronauts' entry into the cargo spacecraft for cargo handling and organization. It also needs to ensure the cargo spacecraft can be reliably closed before separating from the space station.

[0003] Currently, traditional cargo spacecraft sealed hatch devices generally adopt a hinge-based flip-opening method. The control handle is located in the center of the hatch. By rotating the control handle, the multi-point mechanical locks are released. After the pressure difference on both sides of the hatch is balanced, the hatch can be pushed to flip open around its connecting hinge.

[0004] However, with traditional sealed cargo spacecraft hatches, the hatch body and frame typically form an angle of approximately 90 degrees when opened. This not only occupies significant space within the cargo spacecraft but also interferes with astronauts' work. Astronauts are prone to bumping into the open hatch, and cargo handling and organization can also cause collisions, creating safety hazards for on-orbit operations. Furthermore, the central placement of the control handle restricts the possibility of installing a porthole. This prevents astronauts from directly observing the cargo spacecraft's interior through the porthole after docking and before the hatch opens. Therefore, pre-emptive observation and assessment of the cargo spacecraft's interior before hatch opening is clearly impossible with traditional sealed cargo spacecraft hatch systems. Summary of the Invention

[0005] To address the problems of existing technologies, this invention provides a cargo spacecraft sealed hatch device. The hatch body innovatively adopts a lateral sliding opening method, allowing the hatch body and frame to remain relatively parallel when open. This significantly reduces the hatch body's footprint within the cargo spacecraft cabin, minimizes interference with astronauts' normal operations, reduces the probability of collisions between astronauts / cargo and the hatch body, and improves the safety of on-orbit operations. A hatch porthole is located in the center of the hatch body, and a newly designed control mechanism is positioned along the circumference of the porthole. This newly designed control mechanism ensures reliable opening and closing of the hatch. The porthole allows astronauts to observe and assess the situation inside the cargo spacecraft before the hatch is opened, effectively expanding the functionality of the cargo spacecraft sealed hatch device.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a cargo spacecraft sealed hatch device, comprising a hatch body, a hatch frame, a lateral sliding guide mechanism, a control mechanism, and a hatch porthole; the hatch frame adopts a circular structure and is fixedly mounted on the cargo spacecraft cabin; the lateral sliding guide mechanism is disposed between the hatch frame and the cargo spacecraft cabin; the hatch body adopts a disc-shaped structure and is mounted on the lateral sliding guide mechanism; the hatch porthole adopts a circular structure and is fixedly mounted in the center of the hatch body; the control mechanism is disposed on the hatch body outside the circumference of the hatch porthole.

[0007] A first guide support roller and a second guide support roller are arranged side by side at the top of the hatch body, and a third guide support roller and a fourth guide support roller are arranged side by side at the bottom of the hatch body. A door body centering and alignment limiter and a door handle are fixedly installed on the front circumferential side of the hatch body. A pressure balance hole is opened on the hatch body, and a pressure balance valve is installed in the pressure balance hole. The number of door body centering and alignment limiters is at least three, and the multiple door body centering and alignment limiters are evenly distributed along the circumferential direction of the hatch body. All door body centering and alignment limiters are in abutting contact with the inner surface of the center hole of the hatch frame. The number of door handles is at least one, and when there are multiple door handles, the multiple door handles are evenly distributed along the circumferential direction.

[0008] A hatch sealing groove is provided on the back of the hatch frame. There are at least two hatch sealing grooves. All hatch sealing grooves are concentrically distributed with the hatch frame, and a hatch sealing ring is installed in each hatch sealing groove. A pressing groove is provided on the front of the hatch frame. There are several pressing grooves, which are evenly distributed along the circumference of the hatch frame. A pressure point switch is provided in each pressing groove.

[0009] The lateral sliding guide mechanism for the door includes a first L-shaped guide support rail, a second L-shaped guide support rail, a third L-shaped guide support rail, a fourth L-shaped guide support rail, and a rail adapter bracket; the rail adapter bracket is fixedly installed on the cargo spacecraft cabin; the long support arm sections of the first and second L-shaped guide support rails are fixedly abutted together side by side, and the short support arm sections of the first and second L-shaped guide support rails are distributed parallel and spaced apart; the ends of the long support arm sections of the first and second L-shaped guide support rails are fixedly connected to the rail adapter bracket, and the front ends of the short support arm sections of the first and second L-shaped guide support rails are fixedly connected to the door frame; the first The guide support roller is located inside the first L-shaped guide support slide rail, and the second guide support roller is located inside the second L-shaped guide support slide rail; the long support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly attached to each other side by side, and the short support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are distributed in parallel at intervals; the ends of the long support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly connected to the slide rail adapter bracket, and the front ends of the short support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly connected to the hatch frame; the third guide support roller is located inside the third L-shaped guide support slide rail, and the fourth guide support roller is located inside the fourth L-shaped guide support slide rail.

[0010] The control mechanism includes a force-applying component, a circumferential transmission component, a radial transmission component, and a pressure roller. The force-applying component, circumferential transmission component, and radial transmission component are all mounted on the hatch body. The force-applying component is connected to the circumferential transmission component, and the circumferential transmission component is connected to the radial transmission component. The pressure roller is mounted on the radial transmission component. There is one set of each force-applying component and circumferential transmission component. Several sets of radial transmission components are evenly distributed along the circumference of the hatch body, and each set of radial transmission components is equipped with a pressure roller.

[0011] The force-applying assembly includes a force-applying handle, a force-applying shaft, and a force-applying gear. A force-applying shaft mounting hole is provided on the hatch body, and the force-applying shaft is coaxially inserted into the mounting hole. Friction-reducing bearings are installed at both ends of the mounting hole. A force-applying shaft hole sealing groove is provided on the surface of the force-applying shaft. There are at least two force-applying shaft hole sealing grooves. When there are multiple grooves, all grooves are concentrically distributed with the force-applying shaft, and a sealing ring is installed in each groove. One end of the force-applying shaft extends to the outside of the front of the hatch body, and the force-applying handle is fixedly installed at the end of the extended section of the force-applying shaft. The force-applying gear is coaxially fixedly fitted into the middle of the extended section of the force-applying shaft, and a protective cover is provided on the outside of the gear, which is fixedly connected to the hatch body.

[0012] A force-applying shaft locking device is provided between the force-applying gear and the hatch body; the force-applying shaft locking device includes a locking handle, a locking threaded rod, and a clamping arm type locking block; the root of the clamping arm type locking block is fixedly connected to the hatch body; one end of the locking threaded rod is threaded to the clamping arm portion of the clamping arm type locking block, and the locking handle is fixedly connected to the other end of the locking threaded rod; the force-applying shaft is located between the two clamping arms of the clamping arm type locking block.

[0013] The circumferential transmission assembly includes a transmission disc, an arc-shaped rack, and cam slots. The transmission disc has a circular structure and is located directly in front of the hatch body. The transmission disc and the hatch body are coaxially distributed, and the inner diameter of the central hole of the transmission disc is not less than the outer diameter of the hatch window. The transmission disc is rotatably connected to the hatch body through a turntable bearing. The arc-shaped rack is set on the outer circumferential edge of the transmission disc and is concentrically distributed with the transmission disc. The arc-shaped rack and the transmission disc have an integral structure, and the arc-shaped rack meshes with the force-applying gear. The cam slots are set on the disc body of the transmission disc. The number of cam slots is equal to the number of radial transmission assemblies, and several cam slots are evenly distributed along the circumference of the transmission disc.

[0014] The cam slot is divided into a door locking and holding arc section, a door locking and unlocking transition section, and a door unlocking and holding arc section. The door locking and holding arc section is adjacent to the outer peripheral edge of the transmission disk and is concentrically distributed with the transmission disk. The door unlocking and holding arc section is adjacent to the center hole of the transmission disk and is concentrically distributed with the transmission disk. The door locking and unlocking transition section is located between the door locking and holding arc section and the door unlocking and holding arc section, and the connection between the door locking and unlocking transition section and the door locking and holding arc section and the door unlocking and holding arc section is a smooth transition.

[0015] The radial transmission assembly includes a guide rail slide seat, a U-shaped transition slider, a transmission pin, a first force transmission block, a force transmission threaded rod, a second force transmission block, a triangular force transmission link, a linear force transmission link, an L-shaped force transmission link, and a transition base. The guide rail slide seat is fixedly installed on the hatch body and adjacent to the hatch porthole. The U-shaped transition slider is slidably connected to the guide rail slide seat and has a sliding degree of freedom along the radial direction of the hatch body. The transmission pin is installed at the open end of the U-shaped transition slider, and the transmission pin is perpendicular to the transmission disc and located in the cam hole groove. The first force transmission block is hinged to the closed end of the U-shaped transition slider through a first shaft pin. One end of the force transmission threaded rod is screwed and fixed to the first force transmission block. The second force transmission block is threaded to the other end of the force transmission threaded rod, and the force transmission threaded rod is perpendicular to both the first shaft pin and the transmission pin. The first corner point of the triangular force transmission link passes through the first... The second pin is hinged to the second force transmission block. The second corner point of the triangular force transmission link is hinged to the adapter base via the third pin. The adapter base is fixedly installed on the hatch body and adjacent to the hatch frame. The third triangular point of the triangular force transmission link is hinged to one end of the linear force transmission link via the fourth pin. The other end of the linear force transmission link is hinged to the inflection point of the L-shaped force transmission link via the fifth pin. One end of the L-shaped force transmission link is hinged to the adapter base via the sixth pin. A seventh pin is installed at the other end of the L-shaped force transmission link. The clamping wheel is rotatably mounted on the seventh pin. The first, second, third, fourth, fifth, sixth, and seventh pins are distributed in parallel. A trigger rod is fixedly installed at the shaft end of the seventh pin. The trigger rod works in conjunction with the pressure point switch in the clamping groove. The number of clamping grooves is equal to the number of circumferential transmission components. The clamping grooves work in conjunction with the clamping wheel.

[0016] The beneficial effects of this invention are: The cargo spacecraft sealed hatch device of this invention innovatively adopts a lateral sliding opening method for the hatch body. In the open state, the hatch body and the hatch frame remain relatively parallel, significantly reducing the hatch body's footprint on the cargo spacecraft's interior space, minimizing interference with astronauts' normal operations inside the cargo spacecraft, reducing the probability of collisions between astronauts / cargo and the hatch body, and improving the safety of on-orbit operations. A hatch porthole is located in the center of the hatch body, and a newly designed control mechanism is arranged along the circumference of the porthole. This newly designed control mechanism ensures reliable opening and closing of the hatch. The porthole allows astronauts to observe and assess the situation inside the cargo spacecraft before the hatch is opened, effectively expanding the functionality of the cargo spacecraft sealed hatch device. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of a cargo spacecraft sealing hatch device when the hatch is closed, according to the present invention. Figure 2 This is a schematic diagram of the structure of a cargo spacecraft sealing hatch device when the hatch is opened, according to the present invention. Figure 3 This is a schematic diagram of the structure of a cargo spacecraft sealing hatch device when the hatch is closed (the lateral sliding guide mechanism of the hatch body is not shown). Figure 4 This is a schematic diagram of the assembly structure of the hatch frame, the door body centering limiter, the guide support roller, the hatch handle, and the hatch window of the present invention. Figure 5 This is a front view of the hatch frame of the present invention; Figure 6 This is a schematic diagram of the rear side of the hatch frame of the present invention; Figure 7 This is a schematic diagram of the lateral sliding guide mechanism for the door body according to the present invention; Figure 8 This is a schematic diagram of the assembly structure of the hatch frame, force application component and circumferential transmission component of the present invention; Figure 9 for Figure 8 Sectional view of AA; Figure 10 This is a schematic diagram of the force-applying shaft locking device of the present invention; Figure 11 This is a schematic diagram of the transmission disc of the present invention; Figure 12 This is a partial schematic diagram of the transmission disc of the present invention. Figure 13 This is a schematic diagram of the assembly structure of the radial transmission component and the pressure wheel of the present invention; In the diagram, 1—hatch door body, 2—hatch door frame, 3—door body lateral sliding guide mechanism, 4—control mechanism, 5—hatch door porthole, 6—first guide support roller, 7—second guide support roller, 8—third guide support roller, 9—fourth guide support roller, 10—door body centering limiter, 11—pressure balance hole, 12—pressure balance valve, 13—first L-shaped guide support slide rail, 14—second L-shaped guide support slide rail, 15—third L-shaped guide support slide rail, 16—fourth L-shaped guide support slide rail, 17—slide rail adapter bracket, 18—hatch door sealing ring, 19—pressure roller, 20—hatch door handle, 21—force application handle, 22—force application shaft, 23—force application gear, 24—force application shaft mounting hole, 25—force application shaft anti-friction bearing, 26—force application shaft hole sealing ring, 27—protective cover 28—Force-applying shaft locking device; 29—Locking handle; 30—Locking threaded rod; 31—Clamping arm type locking block; 32—Transmission disc; 33—Arc-shaped rack; 34—Cam hole groove; 35—Door locking and holding arc section; 36—Door locking and unlocking transition section; 37—Door unlocking and holding arc section; 38—Guide rail slide seat; 39—U-shaped adapter slider; 40—Transmission roller pin; 41—First force transmission. 42—Force transmission threaded rod, 43—Second force transmission block, 44—Triangular force transmission link, 45—Linear force transmission link, 46—L-shaped force transmission link, 47—Adapter base, 48—First shaft pin, 49—Second shaft pin, 50—Third shaft pin, 51—Fourth shaft pin, 52—Fifth shaft pin, 53—Sixth shaft pin, 54—Seventh shaft pin, 55—Trigger rod, 56—Pressure groove, 57—Pressure point switch. Detailed Implementation

[0018] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0019] like Figures 1-13 As shown, a cargo spacecraft sealed hatch device includes a hatch body 1, a hatch frame 2, a lateral sliding guide mechanism 3, a control mechanism 4, and a hatch porthole 5. The hatch frame 2 has a circular structure and is fixedly mounted on the cargo spacecraft cabin. The lateral sliding guide mechanism 3 is located between the hatch frame 2 and the cargo spacecraft cabin. The hatch body 1 has a disc-shaped structure and is mounted on the lateral sliding guide mechanism 3. The hatch porthole 5 has a circular structure and is fixedly mounted in the center of the hatch body 1. The control mechanism 4 is located on the hatch body 1 on the outer side of the circumference of the hatch porthole 5.

[0020] A first guide support roller 6 and a second guide support roller 7 are arranged side by side at the top of the hatch body 1, and a third guide support roller 8 and a fourth guide support roller 9 are arranged side by side at the bottom of the hatch body 1. A door centering limiter 10 and a door handle 20 are fixedly installed on the front circumferential side of the hatch body 1, respectively. A pressure balance hole 11 is opened on the hatch body 1, and a pressure balance valve 12 is installed in the pressure balance hole 11. The number of door centering limiters 10 is at least three, and the multiple door centering limiters 10 are evenly distributed along the circumferential direction of the hatch body 1. All door centering limiters 10 are in abutting contact with the inner surface of the center hole of the hatch frame 2. The number of door handles 20 is at least one, and when the number of door handles 20 is multiple, the multiple door handles 20 are evenly distributed along the circumferential direction.

[0021] In this embodiment, there are four door centering and alignment limiters 10, with one door centering and alignment limiter 10 arranged every 90°; there are two hatch handles 20, with the two hatch handles 20 distributed at a 180° phase angle.

[0022] A hatch sealing groove is provided on the back of the hatch frame 2. There are at least two hatch sealing grooves. All hatch sealing grooves are concentrically distributed with the hatch frame 2. A hatch sealing ring 18 is installed in each hatch sealing groove. A pressing groove 56 is provided on the front of the hatch frame 2. There are several pressing grooves 56. The pressing grooves 56 are evenly distributed along the circumference of the hatch frame 2. A pressure point switch 57 is provided in each pressing groove 56.

[0023] In this embodiment, there are two door sealing grooves, two door sealing rings 18, eight pressing grooves 56, and eight pressure point switches 57.

[0024] The lateral sliding guide mechanism 3 of the door body includes a first L-shaped guide support slide rail 13, a second L-shaped guide support slide rail 14, a third L-shaped guide support slide rail 15, a fourth L-shaped guide support slide rail 16, and a slide rail adapter bracket 17; the slide rail adapter bracket 17 is fixedly installed on the cargo spacecraft cabin; the long support arm sections of the first L-shaped guide support slide rail 13 and the second L-shaped guide support slide rail 14 are fixedly attached together side by side, and the short support arm sections of the first L-shaped guide support slide rail 13 and the second L-shaped guide support slide rail 14 are distributed parallel and spaced apart; the ends of the long support arm sections of the first L-shaped guide support slide rail 13 and the second L-shaped guide support slide rail 14 are fixedly connected to the slide rail adapter bracket 17, and the front ends of the short support arm sections of the first L-shaped guide support slide rail 13 and the second L-shaped guide support slide rail 14 are fixedly connected to the cabin door frame 2; the first The guide support roller 6 is located inside the first L-shaped guide support slide rail 13, and the second guide support roller 7 is located inside the second L-shaped guide support slide rail 14; the long support arm sections of the third L-shaped guide support slide rail 15 and the fourth L-shaped guide support slide rail 16 are fixedly attached to each other side by side, and the short support arm sections of the third L-shaped guide support slide rail 15 and the fourth L-shaped guide support slide rail 16 are distributed parallel and spaced apart; the ends of the long support arm sections of the third L-shaped guide support slide rail 15 and the fourth L-shaped guide support slide rail 16 are fixedly connected to the slide rail adapter bracket 17, and the front ends of the short support arm sections of the third L-shaped guide support slide rail 15 and the fourth L-shaped guide support slide rail 16 are fixedly connected to the door frame 2; the third guide support roller 8 is located inside the third L-shaped guide support slide rail 15, and the fourth guide support roller 9 is located inside the fourth L-shaped guide support slide rail 16.

[0025] The control mechanism 4 includes a force-applying component, a circumferential transmission component, a radial transmission component, and a pressure wheel 19. The force-applying component, the circumferential transmission component, and the radial transmission component are all mounted on the hatch body 1. The force-applying component is connected to the circumferential transmission component, and the circumferential transmission component is connected to the radial transmission component. The pressure wheel 19 is mounted on the radial transmission component. The force-applying component and the circumferential transmission component are each a set. The radial transmission component is a plurality of sets, which are evenly distributed along the circumference of the hatch body 1. Each set of radial transmission components is equipped with a pressure wheel 19.

[0026] In this embodiment, the number of radial transmission components is eight sets.

[0027] The force-applying assembly includes a force-applying handle 21, a force-applying shaft 22, and a force-applying gear 23. A force-applying shaft mounting hole 24 is provided on the hatch body 1, and the force-applying shaft 22 is coaxially inserted into the force-applying shaft mounting hole 24. Force-applying shaft anti-friction bearings 25 are installed at both ends of the force-applying shaft mounting hole 24. A force-applying shaft hole sealing groove is provided on the surface of the force-applying shaft 22, with at least two grooves. When there are multiple sealing grooves, all... The sealing grooves of the force-applying shaft holes are all concentrically distributed with the force-applying shaft 22, and a force-applying shaft hole sealing ring 26 is installed in each force-applying shaft hole sealing groove; one end of the force-applying shaft 22 extends to the outside of the front of the hatch body 1, and the force-applying handle 21 is fixedly installed at the end of the extension section of the force-applying shaft 22; the force-applying gear 23 is coaxially fixedly fitted in the middle of the extension section of the force-applying shaft 22, and a protective cover 27 is provided on the outside of the force-applying gear 23, and the protective cover 27 is fixedly connected to the hatch body 1.

[0028] In this embodiment, there are two sealing grooves for the force-applying shaft hole and two sealing rings 26 for the force-applying shaft hole.

[0029] A force-applying shaft locking device 28 is provided between the force-applying gear 23 and the hatch body 1; the force-applying shaft locking device 28 includes a locking handle 29, a locking threaded rod 30, and a clamping arm type locking block 31; the root of the clamping arm type locking block 31 is fixedly connected to the hatch body 1; one end of the locking threaded rod 30 is threaded to the clamping arm portion of the clamping arm type locking block 31, and the locking handle 29 is fixedly connected to the other end of the locking threaded rod 30; the force-applying shaft 22 is located between the two clamping arms of the clamping arm type locking block 31.

[0030] The circumferential transmission assembly includes a transmission disk 32, an arc-shaped rack 33, and a cam slot 34. The transmission disk 32 adopts a circular structure and is located directly in front of the hatch body 1. The transmission disk 32 is coaxially distributed with the hatch body 1, and the inner diameter of the central hole of the transmission disk 32 is not less than the outer diameter of the hatch window 5. The transmission disk 32 is rotatably connected to the hatch body 1 through a turntable bearing. The arc-shaped rack 33 is set on the outer peripheral edge of the transmission disk 32. The arc-shaped rack 33 is concentrically distributed with the transmission disk 32 and adopts an integral structure with the transmission disk 32. The arc-shaped rack 33 meshes with the force-applying gear 23. The cam slot 34 is set on the disk body of the transmission disk 32. The number of cam slots 34 is equal to the number of radial transmission assemblies, and the cam slots 34 are evenly distributed along the circumference of the transmission disk 32.

[0031] The cam slot 34 is divided into a door locking and holding arc section 35, a door locking and unlocking transition section 36, and a door unlocking and holding arc section 37. The door locking and holding arc section 35 is adjacent to the outer peripheral edge of the transmission disk 32, and the door locking and holding arc section 35 and the transmission disk 32 are concentrically distributed. The door unlocking and holding arc section 37 is adjacent to the center hole of the transmission disk 32, and the door unlocking and holding arc section 37 and the transmission disk 32 are concentrically distributed. The door locking and unlocking transition section 36 is located between the door locking and holding arc section 35 and the door unlocking and holding arc section 37, and the connection between the door locking and unlocking transition section 36 and the door locking and holding arc section 35 and the door unlocking and holding arc section 37 is a smooth transition.

[0032] The radial transmission assembly includes a guide rail slide seat 38, a U-shaped transition slider 39, a transmission roller pin 40, a first force transmission block 41, a force transmission threaded rod 42, a second force transmission block 43, a triangular force transmission connecting rod 44, a linear force transmission connecting rod 45, an L-shaped force transmission connecting rod 46, and a transition base 47. The guide rail slide seat 38 is fixedly installed on the hatch door body 1 and adjacent to the hatch door window 5. The U-shaped transition slider 39 is slidably connected to the guide rail slide seat 38 and has a sliding degree of freedom along the radial direction of the hatch door body 1. The transmission roller pin 40 is... The transmission pin 40 is mounted on the open end of the U-shaped transition slider 39 and is perpendicularly distributed to the transmission disc 32, with the transmission pin 40 located within the cam slot 34. The first force transmission block 41 is hinged to the closed end of the U-shaped transition slider 39 via the first shaft pin 48. One end of the force transmission threaded rod 42 is screwed and fixed to the first force transmission block 41. The second force transmission block 43 is threaded to the other end of the force transmission threaded rod 42, with the force transmission threaded rod 42 perpendicularly distributed to both the first shaft pin 48 and the transmission pin 40. The first corner of the triangular force transmission connecting rod 44 is connected to the second shaft pin. 49 is hinged to the second force transmission block 43, and the second corner point of the triangular force transmission link 44 is hinged to the transition base 47 through the third shaft pin 50. The transition base 47 is fixedly installed on the hatch door body 1 and adjacent to the hatch door frame 2; the first triangular point of the triangular force transmission link 44 is hinged to one end of the linear force transmission link 45 through the fourth shaft pin 51, and the other end of the linear force transmission link 45 is hinged to the inflection point of the L-shaped force transmission link 46 through the fifth shaft pin 52; one end of the L-shaped force transmission link 46 is hinged to the transition base 47 through the sixth shaft pin 53. The other end of the L-shaped force transmission link 46 is equipped with a seventh shaft pin 54, and the clamping wheel 19 is rotatably mounted on the seventh shaft pin 53; the first shaft pin 48, the second shaft pin 49, the third shaft pin 50, the fourth shaft pin 51, the fifth shaft pin 52, the sixth shaft pin 53 and the seventh shaft pin 54 are distributed in parallel; a trigger rod 55 is fixedly installed at the shaft end of the seventh shaft pin 54, and the trigger rod 55 is used in conjunction with the pressure point switch 57 in the clamping groove 56. The number of clamping grooves 56 is equal to the number of circumferential transmission components, and the clamping grooves 56 are used in conjunction with the clamping wheel 19.

[0033] The following describes a single use of the present invention with reference to the accompanying drawings: During the independent flight phase of the cargo spacecraft, the hatch is closed. The sealing between the hatch body 1 and the hatch frame 2 is ensured by multiple hatch sealing rings 18, and the compression between the hatch body 1 and the hatch frame 2 is ensured by the locking of the control mechanism 4.

[0034] After the cargo spacecraft docks with the space station, and before the hatch is opened, the astronauts can use the hatch window 5 to observe and assess the situation inside the cargo spacecraft. Only after confirming that there are no abnormalities inside the cargo spacecraft can the hatch opening procedure be carried out.

[0035] Before opening the hatch, first open the pressure balance valve 12 until the pressure difference on both sides of the hatch body 1 is completely eliminated. Then, hold the locking handle 29 of the force-applying shaft lock 28 and turn the locking handle 29 in the unlocking direction. This will cause the locking threaded rod 30 to rotate in the unlocking direction, so that the two clamping arms of the clamping arm type locking block 31 gradually move away from each other. This will release the clamping and fixing of the two clamping arms of the clamping arm type locking block 31 on the force-applying shaft 22, allowing the force-applying shaft 22 to regain its rotational freedom.

[0036] After the force-applying shaft locking device 28 completes the unlocking operation, hold the force-applying handle 21 and turn the force-applying handle 21 in the unlocking direction. The force-applying shaft 22 drives the force-applying gear 23 to rotate. Under the meshing transmission action of the force-applying gear 23 and the arc-shaped rack 33, the transmission disc 32 is further driven to rotate. As the transmission disc 32 rotates, the transmission roller pin 40 moves from the hatch locking retaining arc section 35 of the cam hole groove 34 to the hatch unlocking retaining arc section 37.

[0037] As the transmission roller pin 40 moves along the locking and unlocking transition section 36 of the hatch, it generates a radial thrust, which drives the U-shaped transition slider 39 to slide along the guide rail groove seat 38. This radial thrust is then transmitted to the triangular transmission rod 44 via the first force transmission block 41, the force transmission threaded rod 42, and the second force transmission block 43. This causes the triangular transmission rod 44 to deflect around the third shaft pin 50. Consequently, the triangular transmission rod 44 and the linear transmission rod 45 pass the dead point position, and the linear transmission rod 45 further drives the L-shaped transmission rod 46 to deflect around the sixth shaft pin 53. Finally, this causes the clamping wheel 19 to flip and lift off the clamping groove 56, while the trigger rod 55 disengages from the pressure point switch 57 in the clamping groove 56. The unlocking process ends when the transmission roller pin 40 moves to the end of the hatch unlocking holding arc section 37.

[0038] After the hatch unlocking operation is completed, the astronaut first grasps the hatch handle 20 and then pushes the hatch body 1. Since the pressure difference on both sides of the hatch body 1 has been eliminated by the opened pressure balance valve 12, the hatch body 1 can be pushed relatively smoothly as long as the thrust is applied normally during the opening process. Then, through the lateral sliding guide mechanism 3, the hatch body 1 moves longitudinally a small distance along the short support arm section of the four L-shaped guide support slide rails by four sets of guide support rollers, then enters the long support arm section of the four L-shaped guide support slide rails, and then moves laterally a large distance along the long support arm section of the four L-shaped guide support slide rails until the hatch body 1 is completely removed from the hatch frame 2, and the hatch opening is completed.

[0039] Once the hatch is opened, astronauts can enter the cargo spacecraft and begin cargo handling and organization. Because hatch 1 innovatively employs a lateral sliding opening mechanism, it remains relatively parallel to the hatch frame 2 when open. This significantly reduces the space occupied by hatch 1 within the cargo spacecraft, minimizes interference with astronauts' normal operations, and lowers the probability of collisions between astronauts / cargo and hatch 1, thus improving the safety of on-orbit operations.

[0040] When the cargo spacecraft completes all its on-orbit missions and needs to evacuate the space station, the astronauts will manually close the hatch. First, they will grasp the hatch body 1 and apply a lateral pulling force, causing the hatch body 1 to move a large distance laterally along the long support arm section of the four L-shaped guide support slide rails via four sets of guide support rollers. When the hatch body 1 moves in front of the hatch frame 2, they will then grasp the hatch handle 20 and pull the hatch body 1 longitudinally, causing the hatch body 1 to move a small distance longitudinally along the short support arm section of the four L-shaped guide support slide rails via four sets of guide support rollers, until the hatch body 1 is close to the hatch frame 2. At the same time, the hatch body 1 will automatically center and align itself through multiple door centering and alignment limiters 10 evenly distributed along the circumference.

[0041] After the hatch body 1 and the hatch frame 2 have completed the abutment operation, hold the force application handle 21 and turn the force application handle 21 in the locking direction. The force application shaft 22 drives the force application gear 23 to rotate. Under the meshing transmission action of the force application gear 23 and the arc rack 33, the transmission disk 32 is further driven to rotate. As the transmission disk 32 rotates, the transmission roller pin 40 moves from the hatch unlocking retaining arc section 37 of the cam hole groove 34 to the hatch locking retaining arc section 35.

[0042] During the movement of the transmission roller pin 40 along the door locking and unlocking transition section 36, a radial pulling force is generated on the transmission roller pin 40, which drives the U-shaped transition slider 39 to slide along the guide rail slide seat 38. This causes the radial thrust to be transmitted to the triangular transmission rod 44 via the first force transmission block 41, the force transmission threaded rod 42, and the second force transmission block 43. This causes the triangular transmission rod 44 to deflect around the third shaft pin 50 until the triangular transmission rod 44 and the linear transmission rod 45 reach their dead points. During the deflection of the triangular transmission rod 44, the linear transmission rod 45 drives the L-shaped transmission rod 46 to deflect around the sixth shaft pin 53, ultimately causing the pressure wheel 19 to flip and enter the pressure groove 56. Simultaneously, the trigger rod 55 and the pressure point switch 57 in the pressure groove 56 are triggered. When the transmission roller pin 40 moves to the end of the door locking and holding arc section 35, the locking process ends.

[0043] At the end of the locking operation, the feedback signal from the pressure point switch 57 can be used to determine whether the pressure wheel 19 is properly tightened. If the feedback signal from the pressure point switch 57 is normal, it means that the pressure wheel 19 is properly tightened. If the feedback signal from the pressure point switch 57 does not meet the set requirements, the position of the second force transmission block 43 can be adjusted by turning the force transmission threaded rod 42, thereby adjusting the deflection angle of the triangular force transmission link 44 around the third shaft pin 50, thus achieving precise fine-tuning of the deflection positions of the linear force transmission link 45 and the L-shaped force transmission link 46, and finally achieving precise fine-tuning of the clamping position of the pressure wheel 19.

[0044] After the clamping wheel 19 is clamped in place, first close the pressure balance valve 12, then hold the locking handle 29 of the force-applying shaft locker 28, and then turn the locking handle 29 in the locking direction to drive the locking threaded rod 30 to rotate in the locking direction, so that the two clamping arms of the clamping arm type locking block 31 gradually approach each other until the two clamping arms of the clamping arm type locking block 31 clamp and fix the force-applying shaft 22, so that the rotational freedom of the force-applying shaft 22 is locked, and the hatch closing is completed.

[0045] The solutions in the embodiments are not intended to limit the scope of protection of the present invention. All equivalent implementations or modifications that do not depart from the present invention are included in the scope of protection of the present invention.

Claims

1. A sealed hatch device for a cargo spacecraft, characterized in that: The system includes a hatch body, a hatch frame, a lateral sliding guide mechanism, a control mechanism, and a hatch porthole. The hatch frame has a circular structure and is fixedly mounted on the cargo spacecraft's cabin. The lateral sliding guide mechanism is located between the hatch frame and the cargo spacecraft's cabin. The hatch body has a disc-shaped structure and is mounted on the lateral sliding guide mechanism. The hatch porthole has a circular structure and is fixedly mounted in the center of the hatch body. The control mechanism is located on the hatch body outside the circumference of the hatch porthole.

2. The cargo spacecraft sealed hatch device according to claim 1, characterized in that: A first guide support roller and a second guide support roller are arranged side by side at the top of the hatch body, and a third guide support roller and a fourth guide support roller are arranged side by side at the bottom of the hatch body. A door body centering and alignment limiter and a door handle are fixedly installed on the front circumferential side of the hatch body. A pressure balance hole is opened on the hatch body, and a pressure balance valve is installed in the pressure balance hole. The number of door body centering and alignment limiters is at least three, and the multiple door body centering and alignment limiters are evenly distributed along the circumferential direction of the hatch body. All door body centering and alignment limiters are in abutting contact with the inner surface of the center hole of the hatch frame. The number of door handles is at least one, and when there are multiple door handles, the multiple door handles are evenly distributed along the circumferential direction.

3. The cargo spacecraft sealed hatch device according to claim 1, characterized in that: A hatch sealing groove is provided on the back of the hatch frame. There are at least two hatch sealing grooves. All hatch sealing grooves are concentrically distributed with the hatch frame, and a hatch sealing ring is installed in each hatch sealing groove. A pressing groove is provided on the front of the hatch frame. There are several pressing grooves, which are evenly distributed along the circumference of the hatch frame. A pressure point switch is provided in each pressing groove.

4. A cargo spacecraft sealed hatch device according to claim 2, characterized in that: The lateral sliding guide mechanism for the door includes a first L-shaped guide support rail, a second L-shaped guide support rail, a third L-shaped guide support rail, a fourth L-shaped guide support rail, and a rail adapter bracket; the rail adapter bracket is fixedly installed on the cargo spacecraft cabin; the long support arm sections of the first and second L-shaped guide support rails are fixedly abutted together side by side, and the short support arm sections of the first and second L-shaped guide support rails are distributed parallel and spaced apart; the ends of the long support arm sections of the first and second L-shaped guide support rails are fixedly connected to the rail adapter bracket, and the front ends of the short support arm sections of the first and second L-shaped guide support rails are fixedly connected to the door frame; the first The guide support roller is located inside the first L-shaped guide support slide rail, and the second guide support roller is located inside the second L-shaped guide support slide rail; the long support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly attached to each other side by side, and the short support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are distributed in parallel at intervals; the ends of the long support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly connected to the slide rail adapter bracket, and the front ends of the short support arm sections of the third L-shaped guide support slide rail and the fourth L-shaped guide support slide rail are fixedly connected to the hatch frame; the third guide support roller is located inside the third L-shaped guide support slide rail, and the fourth guide support roller is located inside the fourth L-shaped guide support slide rail.

5. A cargo spacecraft sealed hatch device according to claim 3, characterized in that: The control mechanism includes a force-applying component, a circumferential transmission component, a radial transmission component, and a pressure roller. The force-applying component, circumferential transmission component, and radial transmission component are all mounted on the hatch body. The force-applying component is connected to the circumferential transmission component, and the circumferential transmission component is connected to the radial transmission component. The pressure roller is mounted on the radial transmission component. There is one set of each force-applying component and circumferential transmission component. Several sets of radial transmission components are evenly distributed along the circumference of the hatch body, and each set of radial transmission components is equipped with a pressure roller.

6. A cargo spacecraft sealed hatch device according to claim 5, characterized in that: The force-applying assembly includes a force-applying handle, a force-applying shaft, and a force-applying gear. A force-applying shaft mounting hole is provided on the hatch body, and the force-applying shaft is coaxially inserted into the mounting hole. Friction-reducing bearings are installed at both ends of the mounting hole. A force-applying shaft hole sealing groove is provided on the surface of the force-applying shaft. There are at least two force-applying shaft hole sealing grooves. When there are multiple grooves, all grooves are concentrically distributed with the force-applying shaft, and a sealing ring is installed in each groove. One end of the force-applying shaft extends to the outside of the front of the hatch body, and the force-applying handle is fixedly installed at the end of the extended section of the force-applying shaft. The force-applying gear is coaxially fixedly fitted into the middle of the extended section of the force-applying shaft, and a protective cover is provided on the outside of the gear, which is fixedly connected to the hatch body.

7. A cargo spacecraft sealed hatch device according to claim 6, characterized in that: A force-applying shaft locking device is provided between the force-applying gear and the hatch body; the force-applying shaft locking device includes a locking handle, a locking threaded rod, and a clamping arm type locking block; the root of the clamping arm type locking block is fixedly connected to the hatch body; one end of the locking threaded rod is threaded to the clamping arm portion of the clamping arm type locking block, and the locking handle is fixedly connected to the other end of the locking threaded rod; the force-applying shaft is located between the two clamping arms of the clamping arm type locking block.

8. A cargo spacecraft sealed hatch device according to claim 6, characterized in that: The circumferential transmission assembly includes a transmission disc, an arc-shaped rack, and cam slots. The transmission disc has a circular structure and is located directly in front of the hatch body. The transmission disc and the hatch body are coaxially distributed, and the inner diameter of the central hole of the transmission disc is not less than the outer diameter of the hatch window. The transmission disc is rotatably connected to the hatch body through a turntable bearing. The arc-shaped rack is set on the outer circumferential edge of the transmission disc and is concentrically distributed with the transmission disc. The arc-shaped rack and the transmission disc have an integral structure, and the arc-shaped rack meshes with the force-applying gear. The cam slots are set on the disc body of the transmission disc. The number of cam slots is equal to the number of radial transmission assemblies, and several cam slots are evenly distributed along the circumference of the transmission disc.

9. A cargo spacecraft sealed hatch device according to claim 8, characterized in that: The cam slot is divided into a door locking and holding arc section, a door locking and unlocking transition section, and a door unlocking and holding arc section. The door locking and holding arc section is adjacent to the outer peripheral edge of the transmission disk and is concentrically distributed with the transmission disk. The door unlocking and holding arc section is adjacent to the center hole of the transmission disk and is concentrically distributed with the transmission disk. The door locking and unlocking transition section is located between the door locking and holding arc section and the door unlocking and holding arc section, and the connection between the door locking and unlocking transition section and the door locking and holding arc section and the door unlocking and holding arc section is a smooth transition.

10. A cargo spacecraft sealed hatch device according to claim 8, characterized in that: The radial transmission assembly includes a guide rail slide seat, a U-shaped transition slider, a transmission pin, a first force transmission block, a force transmission threaded rod, a second force transmission block, a triangular force transmission link, a linear force transmission link, an L-shaped force transmission link, and a transition base. The guide rail slide seat is fixedly installed on the hatch body and adjacent to the hatch porthole. The U-shaped transition slider is slidably connected to the guide rail slide seat and has a sliding degree of freedom along the radial direction of the hatch body. The transmission pin is installed at the open end of the U-shaped transition slider, and the transmission pin is perpendicular to the transmission disc and located in the cam hole groove. The first force transmission block is hinged to the closed end of the U-shaped transition slider through a first shaft pin. One end of the force transmission threaded rod is screwed and fixed to the first force transmission block. The second force transmission block is threaded to the other end of the force transmission threaded rod, and the force transmission threaded rod is perpendicular to both the first shaft pin and the transmission pin. The first corner point of the triangular force transmission link passes through the first... The second pin is hinged to the second force transmission block. The second corner point of the triangular force transmission link is hinged to the adapter base via the third pin. The adapter base is fixedly installed on the hatch body and adjacent to the hatch frame. The third triangular point of the triangular force transmission link is hinged to one end of the linear force transmission link via the fourth pin. The other end of the linear force transmission link is hinged to the inflection point of the L-shaped force transmission link via the fifth pin. One end of the L-shaped force transmission link is hinged to the adapter base via the sixth pin. A seventh pin is installed at the other end of the L-shaped force transmission link. The clamping wheel is rotatably mounted on the seventh pin. The first, second, third, fourth, fifth, sixth, and seventh pins are distributed in parallel. A trigger rod is fixedly installed at the shaft end of the seventh pin. The trigger rod works in conjunction with the pressure point switch in the clamping groove. The number of clamping grooves is equal to the number of circumferential transmission components. The clamping grooves work in conjunction with the clamping wheel.

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