Quick switching mechanism of manned spaceflight seat support rod and manned spaceflight seat

Abstract

The application discloses a quick switching mechanism of a manned space flight seat support rod and the manned space flight seat and belongs to the technical field of aerospace. The quick switching mechanism comprises a locking clamp seat, an inclined support clamping block, a torsion pin shaft and a shear-resistant pin, the inclined support clamping block is provided with a rod groove, the shear-resistant pin is connected with one end of the torsion pin shaft, the other end of the torsion pin shaft extends out of the locking clamp seat to form a shaft operating end, the torsion pin shaft comprises a rotating shaft body, a locking structure and an unlocking structure, the locking clamp part and the locking structure are matched with the shear-resistant pin, the shear-resistant pin can pass through a rod hole of the support rod to lock the support rod, the unlocking structure can be turned to the clamping position of the locking clamp part, the torsion pin shaft is in the unlocking position, and the torsion pin shaft and the shear-resistant pin can be axially moved to release the support rod. The seat posture switching operation is simple, only needs one twist, two pulls and three kicks to complete the posture switching action, special tools are not needed for the operation, the structure is small and light, mechanical structure is adopted, and the stability is high.

Description

Technical Field

[0001] This invention relates to a quick-switching mechanism for a manned spacecraft seat strut and a manned spacecraft seat, belonging to the field of aerospace technology. Background Technology

[0002] As a vital bridge for humankind's exploration of the universe, spaceflight not only showcases a nation's comprehensive strength but also serves as a frontier for technological innovation. With the rapid advancement of science and technology and the vigorous development of society, the space sector is gradually shifting towards commercialization. This commercialization will involve more private enterprises, bringing funding, technology, and talent to the space industry. It will also spur diverse demands, services, and innovations, enabling space exploration to transcend the limited scope of low Earth orbit and venture into the far reaches of the universe.

[0003] When a commercial crewed spacecraft launches, astronauts need to maintain a "sit-up, knee-down" posture in their space seats to protect their bodies. In low Earth orbit, crewed spaceflight is shorter, and space seats typically do not have attitude-switching devices; astronauts can maintain this posture until they reach their destination.

[0004] The spacecraft seat includes a seat, backrest, legs, and footrest. The seat and backrest are foldable, as are the legs and seat. Specifically, one end of the seat is rotatably connected to the backrest via a rotating joint, allowing the seat to fold and unfold. The other end of the seat is also rotatably connected to the legs via a rotating joint, allowing the legs to fold and unfold. A support strut connects the seat and legs, secured by multiple non-detachable fasteners. This strut configuration allows the astronaut to maintain a "reclining, knees bent" posture during spacecraft flight. Upon arrival at the destination, the astronaut can exit the spacecraft seat and disassemble the non-detachable fasteners using tools. The seat can fold towards the backrest, and the legs can fold towards the seat; folding the spacecraft seat does not impede the astronaut's movement.

[0005] While short-duration spaceflights generally don't require adjustments to the spacecraft seat's attitude, future manned missions exploring other planets will involve longer flights. Maintaining a "reclining, knee-bent" posture for extended periods can lead to astronaut fatigue. Therefore, once the spacecraft is stable in orbit, the spacecraft seat's attitude needs to be adjusted from a "reclining, knee-bent" to a "lying" position to reduce fatigue during prolonged flights. While struts assembled with multiple non-detachable fasteners can meet the requirement of maintaining a "reclining, knee-bent" posture, switching them from locked to unlocked is difficult, requiring the astronaut to stand up and operate. This disassembly is labor-intensive, time-consuming, and requires tools, increasing the risk of debris and making it unsuitable for operation during flight. Therefore, a rapid-switching mechanism for manned spacecraft seat struts is needed, allowing astronauts to easily adjust the spacecraft seat's attitude during flight by manipulating the struts. Summary of the Invention

[0006] This invention addresses the shortcomings of existing technologies by providing a quick-switching mechanism for manned spacecraft seat struts and a manned spacecraft seat.

[0007] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: A quick switching mechanism for a manned spacecraft seat support rod includes an anti-loosening caliper seat, a diagonal brace block, a torsion pin, and an anti-shear pin. The anti-loosening caliper seat is provided with a caliper part for clamping the torsion pin. The diagonal brace block is provided with a rod groove for positioning the support rod. The support rod is provided with a rod hole for the anti-shear pin to pass through. The two groove walls of the rod groove are respectively provided with pin holes for the pin rod of the anti-shear pin to pass through. The anti-shear pin is connected to one end of the torsion pin, and the other end of the torsion pin extends out of the anti-loosening caliper seat to form a shaft operating end.

[0008] The torsion pin includes a shaft body, a locking structure and an unlocking structure disposed on the shaft body. The caliper part cooperates with the locking structure, and the torsion pin is positioned in the locked position. The anti-shear pin passes through the rod hole of the support rod to lock the support rod. When the torsion pin is rotated, the unlocking structure rotates to the engaged position of the caliper part, unlocking the torsion pin so that it is in the unlocked position. The torsion pin and the anti-shear pin can move axially to release the support rod.

[0009] The beneficial effects of this invention are as follows: When the manned spacecraft ignites and lifts off, the astronaut maintains a "reclining with knees bent" posture in the seat to protect their body. After the spacecraft stabilizes in orbit, the seat support rods need to be removed. The astronaut can rotate the shaft operating end to turn the torsion pin to the unlocked position, and then pull the torsion pin axially. The torsion pin and the anti-shear pin move axially, and the anti-shear pin is pulled out from the rod hole of the support rod. The seat support rod is now disassembled. Without the support rod restraining the legs and seat, the astronaut can switch the seat posture by pushing forward with their feet. The seat can switch to a "flat" posture, which reduces physical fatigue caused by long-term flight. After the astronaut reaches the destination and completes the scientific mission, they only need to reassemble the seat support rods, insert the anti-shear pin into the rod hole and pin hole, and maintain the "reclining with knees bent" posture again for the return flight. The spacecraft seat can make full use of the rapid switching mechanism of the manned spacecraft seat support rods according to the length of the spacecraft flight.

[0010] Based on the above technical solution, the present invention can be further improved as follows.

[0011] Furthermore, the locking structure includes a pair of anti-loosening clamping surfaces and a locking limiting protrusion provided on the anti-loosening clamping surfaces. The pair of anti-loosening clamping surfaces are symmetrically arranged on the left and right side surfaces of the rotating shaft body. When locked, the caliper part can clamp the anti-loosening clamping surfaces. The unlocking structure includes a pair of sliding surfaces and an unlocking limiting protrusion provided on the sliding surfaces. The pair of sliding surfaces are symmetrically arranged on the upper and lower side surfaces of the rotating shaft body. The locking limiting protrusion is located between the unlocking limiting protrusion and the anti-loosening caliper seat. When unlocked, the caliper part and the sliding surface are in clearance fit.

[0012] The beneficial effects of adopting the above-mentioned further solution are that, when locked, the caliper can clamp the anti-loosening clamping surface, restricting the degree of freedom of rotation of the torsion pin around the axial center line. The free end of the caliper acts on the locking limit protrusion, which can restrict the axial displacement of the torsion pin. Rotating the torsion pin overcomes the elastic resistance of the caliper, causing the torsion pin to rotate 90 degrees, and the sliding surface rotates to the clamping position of the caliper. The clearance fit between the caliper and the sliding surface ensures the smooth sliding of the torsion pin. When the torsion pin is pulled axially, the axial displacement of the torsion pin is restricted by the unlocking limit protrusion, and the axial movement of the torsion pin will not be excessive. The anti-shear pin can be pulled out from the rod hole and pin hole of the seat support rod, and the seat support rod is disassembled. The astronaut can switch the seat from the "recumbent knee bent" to the "reclining" position by exerting force forward with his feet. The astronaut's action to switch the seat position is "twist", "pull", and "push", which can be completed within 2 seconds.

[0013] Furthermore, the thickness between a pair of sliding surfaces is less than the thickness of a pair of anti-loosening clamping surfaces.

[0014] The beneficial effect of adopting the above-mentioned further solution is that, in the locked position, the caliper can clamp the anti-loosening clamping surface and the caliper can be in a closed state. When the torsion pin is turned to the unlocked position, the thickness between the sliding surfaces is small, the caliper will not clamp the sliding surface, and the caliper can be in an open state. The axial pulling or pushing operation of the torsion pin is more convenient and faster.

[0015] Furthermore, there are two locking limit protrusions, which are respectively disposed on a pair of anti-loosening clamping surfaces.

[0016] The beneficial effect of adopting the above-mentioned further solution is that each anti-loosening clamping surface corresponds to a locking limit protrusion. When the torsion pin is in the locked position, the locking limit protrusion can limit the free end of the caliper and limit the axial displacement of the torsion pin, thus ensuring the accuracy of the locking position of the torsion pin.

[0017] Furthermore, there are two unlocking limit protrusions, which are respectively disposed on a pair of sliding surfaces.

[0018] The beneficial effect of adopting the above-mentioned further solution is that each sliding surface corresponds to an unlocking limit protrusion. When the torsion pin is in the unlocked position, the unlocking limit protrusion can limit the free end of the caliper and limit the axial displacement of the torsion pin, thus ensuring the accuracy of the unlocking position of the torsion pin.

[0019] Furthermore, the caliper includes a pair of jaws, and the clamping end of the jaws is provided with a clamping planar structure that is adapted to the anti-loosening clamping surface.

[0020] The beneficial effect of adopting the above-mentioned further solution is that the clamping plane structure can fit tightly with the anti-loosening clamping surface to prevent the torsion pin from rotating, ensuring the anti-loosening stability when the torsion pin is locked, and the anti-loosening and anti-vibration effect of the clamping surface of the caliper and the torsion pin is better.

[0021] Furthermore, the inner wall of the pliers is provided with one or more force control groove structures, which are disposed between the clamping plane structure and the anti-loosening pliers seat.

[0022] The beneficial effect of adopting the above-mentioned further solution is that different force-controlling groove structures correspond to different torsional torques during unlocking / locking. According to ergonomic requirements, the torsional torque is controlled within a reasonable range through the force-controlling groove structure.

[0023] Furthermore, the shear pin is connected to the torsion pin via a connecting rod.

[0024] The advantage of adopting the above-mentioned further solution is that the connecting rod can realize the connection between the shear pin and the torsion pin.

[0025] Furthermore, it also includes an opening and closing handwheel, which is connected to the operating end of the shaft.

[0026] The beneficial effect of adopting the above-mentioned further solution is that by setting an opening and closing handwheel at the shaft operating end, the rotation of the torsion pin shaft can be controlled by rotating the opening and closing handwheel, making it more convenient and faster to rotate and more comfortable to operate.

[0027] Furthermore, the anti-loosening caliper seat is provided with an unlocking limit post for limiting the opening and closing handwheel when it is rotated to the unlock position.

[0028] The beneficial effect of adopting the above-mentioned further solution is that when the opening and closing handwheel is rotated, the unlocking limit post can limit the unlocking position of the opening and closing handwheel to ensure that the torsion pin can be accurately rotated to the unlocking position. The unlocking limit post restricts the rotation of the opening and closing handwheel within a certain range to avoid excessive rotation.

[0029] Furthermore, the anti-loosening caliper seat is provided with a locking limit post for limiting the opening and closing handwheel to the locked position.

[0030] The beneficial effect of adopting the above-mentioned further solution is that when the opening and closing handwheel is rotated, the locking limit post can limit the locking position of the opening and closing handwheel to ensure that the torsion pin can be accurately rotated to the locking position. The locking limit post restricts the rotation of the opening and closing handwheel within a certain range and avoids excessive rotation.

[0031] The present invention also relates to a manned spacecraft seat, including a seat, a backrest, legs, and feet. The seat and the backrest are foldably connected, and the legs and the seat are foldably connected. A support rod is provided between the legs and the seat. The invention also includes a quick-switching mechanism for the manned spacecraft seat support rod as described above. The upper end of the support rod is connected to the seat through the anti-loosening caliper seat and the diagonal brace block, and / or the lower end of the support rod is connected to the legs through the anti-loosening caliper seat and the diagonal brace block.

[0032] The beneficial effects of this invention are: the quick-switching mechanism of the support rod can be located between the support rod and the seat, facilitating attitude switching operations for astronauts; it can also be located between the support rod and the leg joint, still meeting attitude switching requirements; alternatively, quick-switching mechanisms can be installed at both ends of the support rod for double safety and reliability, with attitude switching operable from both the upper and lower ends. The attitude switching operation of this manned spacecraft seat is simple, requiring only a twist, a pull, and a push to complete the transition from a "reclining with knees bent" to a "lying flat" position. No specific tools are required, the structure is compact and lightweight, and the mechanical structure ensures high stability, saving unnecessary energy consumption and space within the manned spacecraft cabin. During liftoff, the astronaut maintains a "reclining with knees bent" posture in the seat to protect their body. Once the spacecraft has stabilized in orbit, the astronauts can remove the seat support poles and switch to a "lie-down" posture. After reaching their destination and completing their scientific mission, the astronauts only need to reassemble the seat support poles and return to a "sit-up, knee-down" posture for their return journey. This manned spacecraft seat enables rapid switching between sitting and lying postures during long-distance, long-duration manned space missions exploring other planets, and has advantages such as speed, stability, reusability, and the elimination of unnecessary components. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the rapid switching mechanism of the present invention;

[0034] Figure 2 This is a structural schematic diagram of the locked strut state according to Embodiment 1 of the present invention;

[0035] Figure 3 This is a schematic diagram of the anti-loosening caliper holder of the present invention;

[0036] Figure 4 This is a schematic diagram of the torsion pin structure of the present invention;

[0037] Figure 5 This is a schematic diagram of the unlocked state structure of Embodiment 1 of the rapid switching mechanism of the present invention;

[0038] Figure 6 This is a schematic diagram of the structure of Embodiment 2 of the rapid switching mechanism of the present invention;

[0039] Figure 7 This is a schematic diagram of the unlocked state structure of Embodiment 2 of the rapid switching mechanism of the present invention;

[0040] Figure 8 This is a structural schematic diagram of the spacecraft seat of the present invention in a supine, knee-flexed position;

[0041] Figure 9 This is a schematic diagram of the axial cross-sectional structure of the strut with a quick switching mechanism at both ends of the present invention.

[0042] Figure 10 This is a structural schematic diagram of the spacecraft seat of the present invention in its reclining state;

[0043] In the diagram, 1 is the opening / closing handwheel; 101 is the handwheel protrusion; 2 is the anti-loosening caliper seat; 201 is the caliper part; 2011 is the clamping plane structure; 2012 is the force control groove structure; 202 is the unlocking limit post; 203 is the locking limit post; 3 is the torsion pin; 301 is the anti-loosening clamping surface; 302 is the locking limit protrusion; 303 is the sliding surface; 304 is the unlocking limit protrusion; 4 is the anti-shear pin; 5 is the connecting rod; 6 is the diagonal brace block; 601 is the rod groove; 602 is the pin hole; 7 is the support rod; 8 is the seat; 9 is the backrest; 10 is the leg; and 11 is the foot. Detailed Implementation

[0044] The principles and features of the present invention are described below with reference to examples. The examples are only used to explain the present invention and are not intended to limit the scope of the present invention.

[0045] Example 1, such as Figures 1-5 As shown, a quick-switching mechanism for a manned spacecraft seat support rod includes an anti-loosening caliper seat 2, a diagonal brace block 6, a torsion pin 3, and an anti-shear pin 4. The anti-loosening caliper seat 2 is provided with a caliper part 201 for clamping the torsion pin 3. The diagonal brace block 6 is provided with a rod groove 601 for positioning the support rod 7. The support rod 7 is provided with a rod hole for the anti-shear pin 4 to pass through. The two groove walls of the rod groove 601 are respectively provided with pin holes 602 for the pin of the anti-shear pin 4 to pass through. The anti-shear pin 4 is connected to one end of the torsion pin 3, and the other end of the torsion pin 3 extends out of the anti-loosening caliper seat 2 to form a shaft operating end. The anti-loosening caliper seat 2 is provided with a through hole for the torsion pin 3 to pass through.

[0046] The torsion pin 3 includes a shaft body, a locking structure and an unlocking structure disposed on the shaft body. The caliper part 201 cooperates with the locking structure, and the torsion pin 3 is positioned in the locked position. The anti-shear pin 4 passes through the rod hole of the support rod 7 to lock the support rod 7. When the torsion pin 3 is rotated, the unlocking structure rotates to the engaged position of the caliper part 201, unlocking the torsion pin 3 so that it is in the unlocked position. The torsion pin 3 and the anti-shear pin 4 can move axially to release the support rod 7.

[0047] The shape of the rod groove 601 is adapted to the end profile of the support rod 7. Under normal pressure conditions, the seat support rod 7 is in contact with the inclined brace block 6 and is subjected to force. The shear pin 4 is in clearance with the inclined brace block 6 and is not subjected to shear force. Only under the vibration conditions of manned spacecraft ignition and launch, the shear pin 4 is subjected to shear force. This can minimize the possibility of deformation of the seat support rod 7.

[0048] The locking structure includes a pair of anti-loosening clamping surfaces 301 and a locking limiting protrusion 302 provided on the anti-loosening clamping surfaces 301. The pair of anti-loosening clamping surfaces 301 are symmetrically arranged on the left and right sides of the rotating shaft body. When locked, the caliper part 201 can clamp the anti-loosening clamping surfaces 301. The unlocking structure includes a pair of sliding surfaces 303 and an unlocking limiting protrusion 304 provided on the sliding surfaces 303. The pair of sliding surfaces 303 are symmetrically arranged on the upper and lower sides of the rotating shaft body. The locking limiting protrusion 302 is located between the unlocking limiting protrusion 304 and the anti-loosening caliper seat 2. When unlocked, the caliper part 201 and the sliding surface 303 are in clearance fit. When locked, the caliper 201 clamps the anti-loosening clamping surface 301, restricting the rotational freedom of the torsion pin 3 around its axial centerline. The free end of the caliper 201 acts on the locking limit protrusion 302, restricting the axial displacement of the torsion pin 3. Rotating the torsion pin 3 overcomes the elastic resistance of the caliper 201, causing the torsion pin 3 to rotate 90 degrees. The sliding surface 303 rotates to the clamping position of the caliper 201. The caliper 201 and the sliding surface 303 are in clearance fit to ensure the smooth sliding of the torsion pin 3. A axial pull... When the torsion pin 3 is pulled, the axial displacement of the torsion pin 3 will be limited by the unlocking limit protrusion 304, and the axial movement of the torsion pin 3 will not be excessive. The anti-shear pin 4 can be pulled out from the rod hole and pin hole 602 of the seat support rod 7, and the seat support rod 7 is disassembled. The astronaut can switch the seat from the "reclining with knees bent" to the "lying back" position by exerting force forward with his feet 11. The astronaut's action to switch the seat position is "twist", "pull", and "push", and the seat position can be switched within 2 seconds.

[0049] The thickness between the pair of sliding surfaces 303 is less than the thickness between the pair of anti-loosening clamping surfaces 301. When the torsion pin 3 is turned to the unlocked position, the thickness between the sliding surfaces 303 is small, and the caliper part 201 will not clamp the sliding surfaces 303, making it more convenient and faster to pull or push the torsion pin 3 axially.

[0050] Two locking limit protrusions 302 are provided, respectively corresponding to a pair of anti-loosening clamping surfaces 301. Each anti-loosening clamping surface 301 corresponds to a locking limit protrusion 302. When the torsion pin 3 is in the locked position, the locking limit protrusion 302 can limit the free end of the caliper part 201 and limit the axial displacement of the torsion pin 3, ensuring the accuracy of the locking position of the torsion pin 3.

[0051] Two unlocking limiting protrusions 304 are provided, respectively corresponding to a pair of sliding surfaces 303. Each sliding surface 303 has a corresponding unlocking limiting protrusion 304. When the torsion pin 3 is in the unlocked position, the unlocking limiting protrusion 304 can limit the free end of the caliper 201 and limit the axial displacement of the torsion pin 3, ensuring the accuracy of the unlocking position of the torsion pin 3.

[0052] The caliper part 201 includes a pair of jaws, and the clamping end of the jaws is provided with a clamping plane structure 2011 adapted to the anti-loosening clamping surface 301. The clamping plane structure 2011 can fit tightly against the anti-loosening clamping surface 301 to prevent the torsion pin 3 from rotating, ensuring the anti-loosening stability of the torsion pin 3 when locked. The anti-loosening and anti-vibration effect of the caliper part 201 and the anti-loosening clamping surface 301 of the torsion pin 3 is better.

[0053] The inner wall of the pliers is also provided with one or more force control groove structures 2012, which are disposed between the clamping plane structure 2011 and the anti-loosening pliers seat 2.

[0054] The shear pin 4 is connected to the torsion pin 3 via a connecting rod 5. The connecting rod 5 enables the connection between the shear pin 4 and the torsion pin 3, and the requirements for the locking and unlocking positions of the shear pin 4 can be met by selecting a suitable length of connecting rod 5.

[0055] It also includes an opening / closing handwheel 1, which is connected to the operating end of the shaft. The opening / closing handwheel 1, located at the operating end of the shaft, allows for rotational control of the torsion pin 3, making rotation more convenient, faster, and more comfortable. The opening / closing handwheel 1 is provided with a handwheel protrusion 101.

[0056] The anti-loosening caliper seat 2 is provided with an unlocking limit post 202 for limiting the opening and closing handwheel 1 when rotated to the unlock position. When the opening and closing handwheel 1 is rotated, the unlocking limit post 202 can act on the handwheel protrusion 101 to limit the unlocking position of the opening and closing handwheel 1, so as to ensure that the torsion pin 3 can be accurately rotated to the unlock position. The unlocking limit post 202 restricts the rotation of the opening and closing handwheel 1 within a certain range to avoid excessive rotation.

[0057] The anti-loosening caliper seat 2 is provided with a locking limit post 203 for limiting the opening and closing handwheel 1 when it is rotated to the locked position. When the opening and closing handwheel 1 is rotated, the locking limit post 203 can act on the handwheel protrusion 101 to limit the locking position of the opening and closing handwheel 1, so as to ensure that the torsion pin 3 can be accurately rotated to the locked position. The locking limit post 203 restricts the rotation of the opening and closing handwheel 1 within a certain range to avoid excessive rotation.

[0058] Both the anti-loosening caliper seat 2 and the diagonal brace block 6 are provided with U-shaped slots that are adapted to the crossbeam on the seat. After the U-shaped slots are engaged with the crossbeam, they are then fixed by fasteners to achieve the installation and positioning of the quick switching mechanism on the seat.

[0059] Example 2, as Figure 6 and Figure 7 As shown, the connection surface of the seat 8 or leg 10 on the spacecraft seat is a planar structure. The anti-loosening caliper seat 2 and the diagonal brace block 6 are both provided with plate-like structures for connecting with the spacecraft seat. The quick-switching mechanism can be installed on the spacecraft seat by fasteners to realize the locking and unlocking action of the spacecraft seat support rod 7. The rest of the structure is the same as in Embodiment 1, so it will not be described in detail here.

[0060] like Figures 8-10 As shown, the present invention also relates to a manned spacecraft seat, including a seat 8, a backrest 9, a leg 10, and a foot 11. The seat 8 and the backrest 9 are foldably connected, and the leg 10 and the seat 8 are foldably connected. A support rod 7 is provided between the leg 10 and the seat 8. The invention also includes a quick-switching mechanism for the manned spacecraft seat support rod 7 as described above. The upper end of the support rod 7 is connected to the seat 8 through the anti-loosening caliper seat 2 and the diagonal brace block 6, and / or the lower end of the support rod 7 is connected to the leg 10 through the anti-loosening caliper seat 2 and the diagonal brace block 6.

[0061] The quick-switching mechanism of the support rod 7 can be located between the support rod 7 and the seat 8. The anti-loosening caliper seat 2 and the diagonal brace block 6 of the quick-switching mechanism are respectively connected to the seat 8, facilitating attitude switching operations for astronauts. In specific connection, it can be assembled according to the bottom structure of the seat 8. For example, if there is a crossbeam at the bottom of the seat 8, the anti-loosening caliper seat 2 and the diagonal brace block 6 can be provided with U-shaped slots that fit the crossbeam. After engaging with the crossbeam, they can be fixed with fasteners. Alternatively, it can be located between the support rod 7 and the leg 10. The anti-loosening caliper seat 2 and the diagonal brace block of the quick-switching mechanism are respectively connected to the leg 10, which can also meet the attitude switching operation requirements. If the connection surface of the leg 10 is a planar structure, the anti-loosening caliper seat 2 and the diagonal brace block 6 both have plate-like structures for connection. The plate-like structures can be installed on the leg 10 with fasteners. Alternatively, the quick-switching mechanism of the support rod 7 can be set at both ends of the support rod 7 for double insurance and greater safety and reliability. Attitude switching can be performed at both the upper and lower ends of the support rod 7.

[0062] When the manned spacecraft ignites and lifts off, the anti-loosening clamping surface 301 restricts the rotational freedom of the torsion pin 3 around its axial centerline by the clamping part 201, the locking limit protrusion 302 restricts the axial displacement of the torsion pin 3, and the anti-shear pin 4 is inserted into the rod hole and pin hole 602 to lock the support rod 7. Astronauts can maintain a "reclining and knee-bent" posture in the seat to protect their bodies. After the spacecraft stabilizes in orbit, the seat support rod 7 needs to be removed. Astronauts can turn the opening and closing handwheel 1 to overcome the elastic resistance of the clamping part 201, with a torsional torque of less than 0. A 0.7 N·m motor rotates the torsion pin 3 90 degrees. The sliding surface 303 of the torsion pin 3 and the caliper part 201 are fitted with a clearance to ensure smooth sliding of the torsion pin 3. Pulling the opening / closing handwheel 1 axially moves the torsion pin 3 axially, causing the anti-shear pin 4 to be pulled out of the rod hole of the support rod 7. The support rod 7 is then disassembled. The astronaut can switch the seat posture by pushing forward with their feet 11. The seat can switch to a "flat" posture, which reduces physical fatigue caused by long-duration flights. After reaching the destination and completing the scientific mission, the astronaut only needs to reassemble the seat support rod 7, insert the anti-shear pin 4 into the rod hole and pin hole 602, and maintain the "reclining and knee-bent" posture for the return flight. This manned spacecraft seat enables rapid switching between sitting and reclining postures during long-distance, long-duration manned space missions exploring other planets. It has advantages such as speed, stability, reusability, and no need for extra equipment.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A quick-switching mechanism for a manned spacecraft seat support rod, characterized in that, The device includes an anti-loosening caliper seat (2), a diagonal brace block (6), a torsion pin (3), and an anti-shear pin (4). The anti-loosening caliper seat (2) is provided with a caliper part (201) for clamping the torsion pin (3). The diagonal brace block (6) is provided with a rod groove (601) for positioning the support rod (7). The support rod (7) is provided with a rod hole for the anti-shear pin (4) to pass through. The two groove walls of the rod groove (601) are respectively provided with pin holes (602) for the pin rod of the anti-shear pin (4) to pass through. The anti-shear pin (4) is connected to one end of the torsion pin (3), and the other end of the torsion pin (3) extends out of the anti-loosening caliper seat (2) to form a shaft operating end. The torsion pin (3) includes a shaft body, a locking structure and an unlocking structure disposed on the shaft body. The caliper part (201) cooperates with the locking structure. The torsion pin (3) is positioned in the locked position. The anti-shear pin (4) passes through the rod hole of the support rod (7) to lock the support rod (7). When the torsion pin (3) is rotated, the unlocking structure rotates to the engaging position of the caliper part (201) to unlock the torsion pin (3) so that it is in the unlocked position. The torsion pin (3) and the anti-shear pin (4) can move axially to release the support rod (7).

2. The rapid switching mechanism for the manned spacecraft seat support rod according to claim 1, characterized in that, The locking structure includes a pair of anti-loosening clamping surfaces (301) and a locking limiting protrusion (302) provided on the anti-loosening clamping surfaces (301). The pair of anti-loosening clamping surfaces (301) are symmetrically arranged on the left and right sides of the rotating shaft body. When locked, the caliper part (201) can clamp the anti-loosening clamping surfaces (301). The unlocking structure includes a pair of sliding surfaces (303) and an unlocking limiting protrusion (304) provided on the sliding surfaces (303). The pair of sliding surfaces (303) are symmetrically arranged on the upper and lower sides of the rotating shaft body. The locking limiting protrusion (302) is located between the unlocking limiting protrusion (304) and the anti-loosening caliper seat (2). When unlocked, the caliper part (201) and the sliding surface (303) are in clearance fit.

3. The rapid switching mechanism for the manned spacecraft seat support rod according to claim 2, characterized in that, The thickness between the pair of sliding surfaces (303) is less than the thickness between the pair of anti-loosening clamping surfaces (301).

4. The quick-switching mechanism for the manned spacecraft seat support rod according to claim 2, characterized in that, Two locking limit protrusions (302) are provided, respectively disposed on a pair of anti-loosening clamping surfaces (301); and / or two unlocking limit protrusions (304) are provided, respectively disposed on a pair of sliding surfaces (303).

5. The quick-switching mechanism for the manned spacecraft seat support rod according to claim 2, characterized in that, The caliper (201) includes a pair of jaws, and the clamping end of the jaws is provided with a clamping plane structure (2011) that is adapted to the anti-loosening clamping surface (301).

6. The quick-switching mechanism for the manned spacecraft seat support rod according to claim 5, characterized in that, The inner wall of the pliers is also provided with one or more force control groove structures (2012), which are disposed between the clamping plane structure (2011) and the anti-loosening pliers seat (2).

7. The quick-switching mechanism for the manned spacecraft seat support rod according to any one of claims 1-6, characterized in that, The shear pin (4) is connected to the torsion pin (3) via a connecting rod (5).

8. The quick-switching mechanism for the manned spacecraft seat support rod according to any one of claims 1-6, characterized in that, It also includes an opening and closing handwheel (1), which is connected to the shaft operating end.

9. The quick-switching mechanism for the manned spacecraft seat support rod according to claim 8, characterized in that, The anti-loosening caliper seat (2) is provided with an unlocking limit post (202) for limiting the opening and closing handwheel (1) when it is rotated to the unlock position; and / or the anti-loosening caliper seat (2) is provided with a locking limit post (203) for limiting the opening and closing handwheel (1) when it is rotated to the locked position.

10. A manned spacecraft seat, comprising a seat (8), a backrest (9), a leg section (10), and a foot section (11), wherein the seat (8) and the backrest (9) are foldably connected, the leg section (10) and the seat (8) are foldably connected, and a support rod (7) is provided between the leg section (10) and the seat (8), characterized in that, It also includes a quick-switching mechanism for the manned spacecraft seat strut as described in any one of claims 1-9; the upper end of the strut (7) is connected to the seat (8) through the anti-loosening caliper seat (2) and the diagonal brace block (6), and / or the lower end of the strut (7) is connected to the leg (10) through the anti-loosening caliper seat (2) and the diagonal brace block (6).

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