Integrated cabin door rotating mechanism and cabin body of reusable spacecraft

Abstract

The utility model discloses an integrated cabin door rotating mechanism and a cabin body of a reusable spacecraft. The integrated cabin door rotating mechanism comprises a hinge structure located in the cabin body of the spacecraft and at least two sets of actuating structures arranged at intervals. Wherein the hinge structure is composed of a hinge support and a hinge body, one end of the hinge support is fixedly connected with the inner wall of the spacecraft cabin door, the other end of the hinge support is connected with one end of the hinge body through a first rotating shaft, the hinge body is rotatably arranged along the first rotating shaft, and the other end of the hinge body is fixedly connected with the inner surface of the spacecraft cabin door. The two groups of actuating structures are connected through a transmission rod, one end of each group of actuating structure is fixedly connected with the inner wall of the spacecraft cabin body, and the other end of each group of actuating structure is connected with the hinge main body so as to drive the hinge main body to rotate relative to the first rotating shaft, so that the spacecraft cabin door is opened or closed. The mechanism can solve the problem of thermal protection difficulty of the spacecraft cabin door hinge, can reduce the weight of the cabin door rotating mechanism, and improves the carrying capacity of a spacecraft.

Description

Technical Field

[0001] The utility model relates to the field of spacecraft, in particular to an integrated cabin door rotating mechanism and a cabin body of a reusable spacecraft. Background Art

[0002] The emergence of spacecraft has expanded the scope of human activities from the Earth's atmosphere to the vast universe, causing a leap in mankind's ability to understand and transform nature, and has also had a significant impact on social economy and social life.

[0003] As an important way of reusable spacecraft to travel between the earth and the sky for space missions, reusable spacecraft can help humans explore, develop and utilize space more conveniently, greatly expanding the depth and breadth of human development of outer space.

[0004] The hatch of a spacecraft is a key component that protects the payload inside the cabin, bears part of the structural load, performs thermal protection and thermal sealing functions, and is opened and closed multiple times. It is an indispensable part of a reusable spacecraft. Among them, the hatch mechanism is a key component for opening and closing the hatch, and it must adapt to the complex load conditions and diverse functional requirements of the spacecraft's full mission cycle.

[0005] Therefore, there is an urgent need to design a door rotation mechanism, which can solve the thermal protection difficulties of the spacecraft door hinges while reducing the weight of the door rotation mechanism and improving the carrying capacity of the spacecraft. Summary of the invention

[0006] The purpose of the utility model is to overcome the deficiencies of the prior art and provide an integrated door rotation mechanism for a reusable spacecraft, which can solve the difficulty of thermal protection of the spacecraft door hinges while reducing the weight of the door rotation mechanism and improving the carrying capacity of the spacecraft.

[0007] To achieve the above-mentioned purpose, the utility model provides the following technical solution: an integrated door rotation mechanism of a reusable spacecraft, comprising a hinge structure located inside the spacecraft cabin and at least two sets of actuating structures arranged at intervals, wherein:

[0008] The hinge structure comprises a hinge support and a hinge body, one end of the hinge support is fixedly connected to the inner wall of the spacecraft cabin, the other end is connected to one end of the hinge body through a first rotating shaft, and the hinge body is rotatably arranged relative to the first rotating shaft, and the other end of the hinge body is fixedly connected to the inner surface of the spacecraft cabin door;

[0009] The two groups of actuating structures are connected by a transmission rod. One end of each group of actuating structures is fixedly connected to the inner wall of the spacecraft cabin, and the other end is connected to the hinge body to drive the hinge body to rotate relative to the first rotating shaft to complete the opening or closing of the spacecraft cabin door.

[0010] Furthermore, the hinge support includes a first base plate and a first protruding column, wherein one side of the first base plate is tightly attached to and fixedly connected to the inner wall surface of the spacecraft cabin, and the other side is fixedly connected to the first protruding column, and the first protruding column is provided with a first recess on the side away from the first base plate, and the first recess is recessed toward the side of the first base plate, and the first recess is also provided with a first through hole matching the first rotating shaft.

[0011] Furthermore, the hinge body includes a second base plate and a U-shaped structure with different lengths at both ends, wherein one side of the second base plate is tightly attached to and fixedly connected to the inner surface of the spacecraft hatch, and the other side is connected to the long end of the U-shaped structure, and the short end of the U-shaped structure is connected to the first protruding column via the first connecting axis.

[0012] Furthermore, along the length direction of the short end of the U-shaped structure, a second through hole and a third through hole are provided at intervals on the short end of the U-shaped structure.

[0013] Furthermore, the actuating structure comprises an actuating support, a driver, a first driving rod, a second driving rod and the transmission rod, wherein:

[0014] One end of the actuating support is fixedly connected to the inner wall of the spacecraft cabin, and the other end is connected to one end of the first driving rod through the transmission rod, the other end of the first driving rod is connected to one end of the second driving rod through a second connecting shaft, and the second driving rod is rotatably arranged along the second connecting shaft, and the other end of the second driving rod is connected to one end of the hinge body close to the hinge support and located at the middle position of the hinge body through a third connecting shaft;

[0015] The driver is connected to the first driving rod through the transmission rod; the driver is used to drive the transmission rod to rotate, so as to further drive the first driving rod and the second driving rod to rotate, thereby driving the hinge body to open or close the spacecraft door by rotation.

[0016] Further, the actuating support comprises a third bottom plate and a second protruding column, one side of the third bottom plate is closely attached to and fixedly connected to the inner wall surface of the spacecraft cabin, and the other side is fixedly connected to the second protruding column, a second recess is provided on a side of the second protruding column away from the third bottom plate, and the second recess is recessed toward one side of the third bottom plate, and a fourth through hole is provided on the second recess;

[0017] The transmission rod is connected to the driver after passing through the fourth through hole on one side, the portion of the first driving rod located in the second recess, and the fourth through hole on the other side in sequence.

[0018] Furthermore, the first driving rod has a rectangular shape, and in the length direction of the rectangular body, both ends of the rectangular body are semi-circular arc structures, and the semi-circular arc structures at both ends of the first driving rod are respectively provided with a fifth through hole and a sixth through hole matching the transmission rod and the second connecting shaft.

[0019] Furthermore, the two ends of the second driving rod are respectively provided with a third recess, the third recesses at both ends are both recessed toward the center of the second driving rod, and the third recesses are provided with a seventh through hole, wherein:

[0020] One end of the first driving rod is embedded in the second recess and then passes through the fourth through hole, the fifth through hole on one side, and the fourth through hole on the other side in sequence through the transmission rod, and then is fixed by the first locking pin;

[0021] The other end of the first driving rod is inserted into the third recessed portion of one end of the second driving rod, and then passes through the seventh through hole, the sixth through hole, and the seventh through hole on one side in sequence through the second connecting shaft, and then is fixed by the second locking pin;

[0022] The third recess at the other end of the second driving rod is passed through the seventh through hole on one side, the third through hole located in the middle of the hinge body and the seventh through hole on the other side in sequence through the third connecting shaft, and then locked by the third locking pin.

[0023] Furthermore, the driver is a motor, the output shaft of the motor is fixedly connected to the transmission rod, and the forward and reverse movements of the output shaft of the motor are controlled by a programmable controller.

[0024] The utility model provides a cabin body, comprising the integrated cabin door rotating mechanism of any one of the above-mentioned reusable spacecrafts.

[0025] Compared with the prior art, the utility model has at least one of the following beneficial effects:

[0026] The integrated door rotation mechanism of a reusable spacecraft of the present application arranges the hinge structure and the actuating structure inside the spacecraft cabin, so that the heat sealing between the door and the cabin is easier to achieve and the sealing effect is better, thereby ensuring that the hinge structure and the actuating structure work in a normal temperature environment, avoiding direct contact between the hinge structure and the external thermal environment of the spacecraft cabin, effectively providing thermal protection for the hinge structure, thereby avoiding deformation of the hinge structure due to heat, and ensuring the stability of the hinge structure.

[0027] In addition, the two groups of actuating structures are connected by a transmission rod, so that the two groups of actuating structures can use one set of driving mechanisms to drive the other set of actuating structures to move through the transmission rod, and drive the hinge body to rotate relative to the first rotating shaft to complete the opening or closing of the spacecraft door. The setting of the transmission rod can reduce the number of driving mechanisms, thereby reducing the weight of the entire structure.

[0028] The hatch door rotation mechanism of the present application can effectively provide thermal protection for the hinge structure while ensuring a rigorous thermal seal between the hatch door and the cabin body. It can also reduce the weight of the hatch door rotation mechanism and improve the carrying capacity of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is the overall assembly diagram of the integrated door rotating mechanism of the utility model in the closed state;

[0030] Figure 2 This is the overall assembly diagram of the integrated door rotating mechanism of the utility model in the open state;

[0031] Figure 3 It is a partial assembly diagram of the closed state of the integrated door rotating mechanism of the utility model;

[0032] Figure 4 It is a partial assembly diagram of the integrated door rotating mechanism of the utility model in the open state;

[0033] Figure 5 It is a connection diagram of the hinge points of each connecting rod of the integrated cabin door rotation mechanism of the utility model;

[0034] Figure 6 It is a structural diagram of the U-shaped structure of the integrated cabin door rotating mechanism of the utility model.

[0035] Description of reference numerals:

[0036] 1 Hinge structure 2 Actuation structure

[0037] 3 hinge support 4 hinge body

[0038] 5 Spacecraft cabin 6 Spacecraft hatch

[0039] 7 first rotating shaft 8 transmission rod

[0040] 9 first bottom plate 10 first raised column

[0041] 11 Second bottom plate 12 U-shaped structure

[0042] 13 Actuating support 14 Driver

[0043] 15 first driving rod 16 second driving rod

[0044] 17 second connecting shaft 18 third bottom plate

[0045] 19 second raised column 20 third connecting shaft

[0046] 21 second through hole 22 third through hole DETAILED DESCRIPTION

[0047] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clearly understood, the spirit of the contents disclosed in the present invention will be clearly explained with the accompanying drawings and detailed descriptions below. After understanding the embodiments of the contents of the present invention, any technician in the relevant technical field can change and modify the contents of the present invention according to the techniques taught by the contents of the present invention without departing from the spirit and scope of the contents of the present invention.

[0048] The exemplary embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention. In addition, the same or similar reference numerals used in the drawings and embodiments are used to represent the same or similar parts.

[0049] The terms “first”, “second”, etc. used in this document do not particularly refer to an order or sequence, nor are they used to limit the present invention. They are only used to distinguish elements or operations described with the same technical terms.

[0050] The directional terms used in this document, such as up, down, left, right, front or back, etc., are only used to refer to the directions of the drawings. Therefore, the directional terms used are used to illustrate and not to limit the present invention.

[0051] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0052] As used herein, "and / or" includes any or all combinations of the items described.

[0053] The terms "substantially" and "approximately" used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors do not change their essence. Generally speaking, the range of slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. Those skilled in the art should understand that the aforementioned values ​​can be adjusted according to actual needs and are not limited thereto.

[0054] Certain terms used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art regarding the description of the present application.

[0055] For example, if the hatch hinges used in a spacecraft are placed outside the hatch and no thermal protection is used, the hinges need to be resistant to high temperatures, which means that the material requirements are relatively high, and thermal protection near the hinges is difficult to implement. For example, the drive mechanism can be placed inside the hatch using a four-bar linkage, but the multiple sets of parallel four-bar linkages used in the drive mechanism will increase the total weight of the spacecraft and affect the carrying capacity of the spacecraft.

[0056] See also Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, an embodiment of the utility model provides an integrated door rotation mechanism of a reusable spacecraft, comprising a hinge structure 1 located inside the spacecraft cabin and at least two sets of actuating structures 2 arranged at intervals. The hinge structure 1 is composed of a hinge support 3 and a hinge body 4. One end of the hinge support 3 is fixedly connected to the inner wall of the spacecraft cabin 5, and the other end is connected to one end of the hinge body 4 through a first rotating shaft 7. The hinge body 4 is rotatably arranged along the first rotating shaft 7, and the other end of the hinge body 4 is fixedly connected to the inner surface of the spacecraft cabin door 6.

[0057] The two groups of actuating structures 2 are connected by a transmission rod 8. One end of each group of actuating structures 2 is fixedly connected to the inner wall of the spacecraft cabin 5, and the other end is connected to the hinge body 4 to drive the hinge body 4 to rotate relative to the first rotating shaft 7 to complete the opening or closing of the spacecraft cabin door 6.

[0058] Specifically, the integrated door rotation mechanism of a reusable spacecraft of the present application is arranged inside the spacecraft cabin 5 by placing the hinge structure 1 and the actuating structure 2, so that the thermal seal between the door and the cabin is easier to achieve and the sealing effect is better, and the hinge structure 1 and the actuating structure 2 are ensured to work in a normal temperature environment, and the hinge structure 1 can be prevented from directly contacting the external thermal environment of the spacecraft cabin 5, and the hinge structure 1 can be effectively thermally protected, thereby preventing the hinge structure 1 from deforming due to heat, and ensuring the stability of the hinge 1 structure. In addition, the two groups of actuating structures 2 are connected by a transmission rod 8, so that the two groups of actuating structures 2 can use a set of driving mechanisms to drive the other group of actuating structures to move through the transmission rod 8, and by driving the hinge body 4 to rotate relative to the first rotating shaft 7, the spacecraft door 6 is opened or closed. The arrangement of the transmission rod 8 can reduce the number of driving mechanisms, thereby reducing the weight of the entire structure.

[0059] The hatch door rotation mechanism of the present application can effectively provide thermal protection for the hinge structure while ensuring a rigorous thermal seal between the hatch door and the cabin body. It can also reduce the weight of the hatch door rotation mechanism and improve the carrying capacity of the spacecraft.

[0060] like Figure 1, Figure 3 and Figure 5 As shown, in order to ensure that the hinge support 3 is firmly fixed, for example, the hinge support 3 includes a first base plate 9 and a first protruding column 10. Among them, one side of the first base plate 9 is tightly attached to and fixedly connected to the inner wall surface of the spacecraft cabin 5, and the other side is fixedly connected to the first protruding column 10. The first base plate (for example, the cross-sectional area of ​​the first base plate 9 cut along the radial direction of the first protruding column is larger than the cross-sectional area of ​​the first protruding column 10) increases the contact area with the inner wall of the spacecraft cabin, which facilitates the welding of the two and makes the two more firmly fixed. In order to facilitate the installation of the first protruding column 10 and the first rotating shaft 7, for example, the first protruding column 10 is provided with a first recessed portion on the side away from the first base plate 9, and the first recessed portion is recessed toward the side of the first base plate 9. The first recessed portion is also provided with a first through hole matching the first rotating shaft 7.

[0061] In the same embodiment, in order to facilitate the rotation of the hinge body 4, for example, the hinge body 4 includes a second bottom plate 11 and a U-shaped structure 12 with different lengths at both ends. In order to make the second bottom plate 11 tightly connected and firmly fixed to the spacecraft door 6, for example, one side of the second bottom plate 11 is closely attached to and fixedly (for example, welded) connected to the inner surface of the spacecraft door 6, and the other side is connected to the long end of the U-shaped structure 12. The short end of the U-shaped structure 12 is connected to the first protruding column 10 through the first connecting shaft 7.

[0062] like Figure 1 , Figure 3 and Figure 6 As shown, in order to facilitate the connection between the hinge body 4 and the hinge support 3 and the actuating structure 2, for example, a second through hole 21 and a third through hole 22 are arranged at intervals on the short end of the U-shaped structure 12 along the length direction of the short end of the U-shaped structure 12.

[0063] like Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, in order to facilitate the rotation of the actuating structure 2 , for example, the actuating structure 2 includes an actuating support 13 , a driver 14 , a first driving rod 15 , a second driving rod 16 and a transmission rod 8 .

[0064] Among them, one end of the actuating support 13 is fixedly connected to the inner wall of the spacecraft cabin 5, and the other end is connected to one end of the first driving rod 15 through the transmission rod 8. The other end of the first driving rod 15 is connected to one end of the second driving rod 16 through the second connecting shaft 17, and the second driving rod 16 is rotatably arranged along the second connecting shaft 17. The other end of the second driving rod 16 is connected to the hinge body 4 through the third connecting shaft 20, which is approximately the middle position of one end of the hinge support 3 (that is, the position of the short end of the U-shaped structure between the bottom of the U and the end of the short end).

[0065] The driver 14 is disposed at one end of the transmission rod 8, and is used to drive the transmission rod 8 to rotate, so as to further drive the first driving rod 15 and the second driving rod 16 to rotate, thereby driving the hinge body 4 to open or close the spacecraft door 6 by rotating. Figure 3 As shown, since the transmission rod 8 passes through the recessed through hole of the actuating support (the transmission rod 8 rotates relative to this through hole) and the through hole of the first driving rod 15 arranged in the middle, the first driving rod 15 can rotate with the transmission rod 8 when the driver is driven by the transmission rod 8. It should be pointed out that the actuating support 13 includes a third bottom plate 18 and a second protruding column 19. One side of the third bottom plate 18 is tightly attached to and fixedly connected to the inner wall surface of the spacecraft cabin 5, and the other side is fixedly connected to the second protruding column 19. The second protruding column 19 is provided with a second recessed portion on the side away from the third bottom plate 18, and the second recessed portion is recessed toward the side of the third bottom plate 18. In order to facilitate the installation with the transmission rod 8, for example, a fourth through hole is provided on the second recessed portion.

[0066] During installation, the transmission rod 8 sequentially passes through the fourth through hole on one side, the portion of the first driving rod 15 located in the second recess (the fifth through hole), and the fourth through hole on the other side to be connected to the driver 14 .

[0067] In the same embodiment, in order to ensure the stability of the structure of the first driving rod 15, for example, the first driving rod 15 has a rectangular shape. Along the length direction of the rectangular parallelepiped, both ends of the rectangular parallelepiped are semicircular arc structures, and the first driving rod 15 is provided with a fifth through hole and a sixth through hole matching the transmission rod 8 and the second connecting shaft 17 at both ends.

[0068] Specifically, the second driving rod 16 is provided with a third recess at both ends, and the third recesses at both ends are recessed toward the center of the second driving rod 16, and the third recesses are provided with a seventh through hole. One end of the first driving rod 15 is inserted into the second recess, and then passes through the fourth through hole, the fifth through hole on one side, and the fourth through hole on the other side in sequence through the transmission rod 8, and is then fixed by the first locking pin. The first locking pin can prevent the transmission rod 8 from detaching from the first driving rod 15, ensuring that the transmission rod 8 works stably.

[0069] The other end of the first driving rod 15 is inserted into the third recess at one end of the second driving rod 16, and then passes through the seventh through hole, the sixth through hole on one side, and the seventh through hole on the other side in sequence through the second connecting shaft 17, and then is fixed by the second locking pin. The second locking pin can prevent the second connecting shaft 17 from being separated from the first driving rod 15 and the second driving rod 16, thereby ensuring that the first driving rod 15 and the second driving rod 16 are stably connected.

[0070] The third recess at the other end of the second driving rod 16 passes through the seventh through hole on one side, the third through hole in the middle of the hinge body 4, and the seventh through hole on the other side in sequence through the second connecting shaft 17, and is then locked by the third locking pin. The third locking pin prevents the third connecting shaft 20 from being separated from the second driving rod 16, which is conducive to the second driving rod 16 driving the hinge body 4 to rotate.

[0071] In addition, the first bottom plate 9 , the second bottom plate 11 and the third bottom plate 18 are arranged circumferentially along the inner wall of the spacecraft cabin, and the first bottom plate 9 is located between the second bottom plate 11 and the third bottom plate 18 in the circumferential direction of the cabin.

[0072] In addition, the driver 14 is a motor, and the output shaft of the motor is fixedly connected to the transmission rod 8. In order to facilitate the control of the motor, for example, the motor can control the forward and reverse movement of its output shaft through a programmable controller. In order to make the hatch door open more smoothly and reliably, for example, a motor is provided at each end of the transmission rod 8, so that the two motors drive the hatch door to open or close at the same time.

[0073] The utility model provides a cabin body, comprising the integrated cabin door rotating mechanism of any one of the above-mentioned reusable spacecrafts.

[0074] The above embodiments can be combined with each other and have corresponding technical effects.

[0075] The above description is only an illustrative specific implementation of the present invention. Without departing from the concept and principle of the present invention, any equivalent changes and modifications made by those skilled in the art should fall within the scope of protection of the present invention.

Claims

1. An integrated door rotation mechanism for a reusable spacecraft, characterized in that: It comprises a hinge structure located inside a spacecraft cabin and at least two sets of actuating structures arranged at intervals, wherein: The hinge structure comprises a hinge support and a hinge body, one end of the hinge support is fixedly connected to the inner wall of the spacecraft cabin, and the other end is connected to one end of the hinge body through a first rotating shaft, and the hinge body is rotatably arranged relative to the first rotating shaft, and the other end of the hinge body is fixedly connected to the inner surface of the spacecraft cabin door; The two groups of actuating structures are connected by a transmission rod. One end of each group of actuating structures is fixedly connected to the inner wall of the spacecraft cabin, and the other end is connected to the hinge body to drive the hinge body to rotate relative to the first rotating shaft to complete the opening or closing of the spacecraft cabin door.

2. The integrated door rotation mechanism of a reusable spacecraft according to claim 1, characterized in that: The hinge support includes a first base plate and a first protruding column, wherein one side of the first base plate is tightly attached to and fixedly connected to the inner wall surface of the spacecraft cabin, and the other side is fixedly connected to the first protruding column; the first protruding column is provided with a first recess on the side away from the first base plate, and the first recess is recessed toward the side of the first base plate, and the first recess is also provided with a first through hole matching the first rotating shaft.

3. The integrated door rotation mechanism of a reusable spacecraft according to claim 2, characterized in that: The hinge body includes a second base plate and a U-shaped structure with different lengths at both ends, wherein one side of the second base plate is tightly attached to and fixedly connected to the inner surface of the spacecraft hatch, and the other side is connected to the long end of the U-shaped structure, and the short end of the U-shaped structure is connected to the first protruding column through the first rotating shaft.

4. The integrated door rotation mechanism of a reusable spacecraft according to claim 3, characterized in that: Along the length direction of the short end of the U-shaped structure, a second through hole and a third through hole are arranged at intervals on the short end of the U-shaped structure.

5. The integrated door rotation mechanism of a reusable spacecraft according to claim 1, characterized in that: The actuating structure comprises an actuating support, a driver, a first driving rod, a second driving rod and the transmission rod, wherein: One end of the actuating support is fixedly connected to the inner wall of the spacecraft cabin, and the other end is connected to one end of the first driving rod through the transmission rod, the other end of the first driving rod is connected to one end of the second driving rod through a second connecting shaft, and the second driving rod is rotatably arranged relative to the second connecting shaft, and the other end of the second driving rod is connected to the hinge body near the hinge support end through a third connecting shaft; The driver is connected to the first driving rod through the transmission rod; the driver is used to drive the transmission rod to rotate, so as to further drive the first driving rod and the second driving rod to rotate, thereby driving the hinge body to open or close the spacecraft door by rotation.

6. The integrated door rotation mechanism of a reusable spacecraft according to claim 5, characterized in that: The actuating support comprises a third bottom plate and a second protruding column, one side of the third bottom plate is closely attached to and fixedly connected to the inner wall surface of the spacecraft cabin, and the other side is fixedly connected to the second protruding column, a second recess is provided on the side of the second protruding column away from the third bottom plate, and the second recess is recessed toward one side of the third bottom plate, and a fourth through hole is provided on the second recess; The transmission rod is connected to the driver after passing through the fourth through hole on one side, the portion of the first driving rod located in the second recess, and the fourth through hole on the other side in sequence.

7. The integrated door rotation mechanism of a reusable spacecraft according to claim 6, characterized in that: The first driving rod has a rectangular shape, and in the length direction of the rectangular parallelepiped, both ends of the rectangular parallelepiped are semi-circular arc structures; the semi-circular arc structures at both ends of the first driving rod are respectively provided with a fifth through hole and a sixth through hole matching the transmission rod and the second connecting shaft.

8. The integrated door rotation mechanism of a reusable spacecraft according to claim 7, characterized in that: The two ends of the second driving rod are respectively provided with a third recessed portion, the third recessed portions at both ends are both recessed toward the center of the second driving rod, and the third recessed portions are provided with a seventh through hole, wherein: One end of the first driving rod is embedded in the second recess and then passes through the fourth through hole, the fifth through hole on one side, and the fourth through hole on the other side in sequence through the transmission rod, and then is fixed by the first locking pin; The other end of the first driving rod is inserted into the third recessed portion of one end of the second driving rod, and then passes through the seventh through hole, the sixth through hole, and the seventh through hole on one side in sequence through the second connecting shaft, and then is fixed by the second locking pin; The third recess at the other end of the second driving rod is passed through the seventh through hole on one side, the third through hole located in the middle of the hinge body and the seventh through hole on the other side in sequence through the third connecting shaft, and then locked by the third locking pin.

9. The integrated door rotation mechanism of a reusable spacecraft according to claim 5, characterized in that: The driver is a motor, the output shaft of the motor is fixedly connected to the transmission rod, and the forward and reverse movements of the output shaft of the motor are controlled by a programmable controller.

10. A cabin, characterized in that: An integrated door rotation mechanism for a reusable spacecraft comprising any one of claims 1-9.

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