Aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin and deformation method

Abstract

An aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin and deformation method, which relates to the technical field of deformation of a type of aircraft cabin. The present invention solves the problem that the existing aircraft cabin cannot meet the requirements of realizing its shape change during flight, resulting in the inability of the aircraft to adapt to a wider range of flight conditions and flight states, and also resulting in the inability of the aircraft to achieve high maneuverability. The present invention completes the cabin deformation function by combining a skin and a deformation mechanism. The servo electric cylinder in the deformation mechanism pushes the annular moving platform, and the mechanism connecting rod on the annular moving platform moves accordingly. A fixed hinge is designed on the cabin skin to be connected to the mechanism connecting rod, so that when the servo electric cylinder moves, the skin is driven to move to realize cabin deformation. The present invention is used to meet the needs of aircraft cross-domain flight for aerodynamic shape changes, and to realize the ability of future aircraft cabins to adaptively deform.

Description

Technical Field

[0001] The present invention relates to the technical field of deformation of a type of aircraft cabin, and in particular to an aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin and a deformation method. Background Art

[0002] The aircraft of this type involved in the present invention, as a comprehensive product of aviation and aerospace, has very obvious advantages, and has the characteristics of good aerodynamic characteristics, long flight distance, and high flight speed. In addition to accommodating various components, the cabin of this type of aircraft is used to provide the aircraft with a good aerodynamic shape. Since this type of aircraft often has to experience complex environments such as flying in the atmosphere and space and re-entering the atmosphere, the requirements for its cabin shape are quite different in each flight phase. However, this type of aircraft only designs the cabin into a corresponding fixed shape based on fixed flight conditions and flight states. Once the design point is exceeded, the flight performance drops sharply, and there may even be a risk of the aircraft losing control. In addition, the cabin with a fixed shape cannot meet the high maneuverability requirements of this type of aircraft. Therefore, the aircraft cabin must have the function of realizing shape changes during flight.

[0003] In summary, the existing aircraft cabin cannot meet the requirements of realizing its shape change during flight, resulting in the aircraft being unable to adapt to a wider range of flight conditions and flight states, and also resulting in the aircraft being unable to achieve high maneuverability. Summary of the Invention

[0004] The purpose of the present invention is to solve the problem that the existing aircraft cabin cannot meet the requirements of realizing its appearance change during flight, resulting in the aircraft being unable to adapt to a wider range of flight conditions and flight states, and also resulting in the aircraft being unable to achieve high maneuverability, and further to provide an aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin and deformation method.

[0005] The technical solution of the present invention is:

[0006] A multi-dimensional deformable cabin of an aircraft combined skin-deformation mechanism, comprising a cabin front cone 1, a deformation mechanism 4, a rear fairing ring 5, a cabin support frame 6, a plurality of cabin front skins 2 and a plurality of cabin rear skins 3. The cabin front cone 1 and the cabin support frame 6 are coaxially arranged from front to back. A plurality of cabin front skins 2 are evenly arranged along the circumference of the front section of the cabin support frame 6. A plurality of cabin rear skins 3 corresponding to the plurality of cabin front skins 2 are evenly arranged along the circumference of the middle section of the cabin support frame 6. The rear side of each cabin front skin 2 is connected by a composite hinge. The chain is hinged to the front side of the corresponding cabin rear end skin 3, and the rear section of the cabin support frame 6 is provided with a rear fairing ring 5. A deformation mechanism 4 is provided between the cabin support frame 6 and the cabin front end skin 2 and the cabin rear end skin 3. The deformation mechanism 4 includes an annular moving platform 11, six moving platform driving mechanisms, multiple skin driving mechanisms, multiple skeleton hinges 8 and multiple first guide rail slider mechanisms. The annular moving platform 11 is sleeved on the cabin support frame 6. Six moving platform driving mechanisms are provided circumferentially between the annular moving platform 11 and the rear end plate. The front and rear ends of the moving platform driving mechanisms are respectively connected to the annular moving platform 11 and the rear end plate. The annular dynamic platform 11 is hinged to the rear end plate; a plurality of skin drive mechanisms are provided circumferentially between the annular dynamic platform 11 and the front end plate 32 of the cabin support frame 6, and the plurality of skin drive mechanisms correspond one to one with the plurality of cabin front end skins 2 and / or the plurality of cabin rear end skins 3, respectively. The rear side of each cabin rear end skin 3 is hinged to the middle frame ring plate 33 of the cabin support frame 6 through a frame hinge 8, and the front side of each cabin front end skin 2 is hinged to the first guide rail slider mechanism through a fixed hinge, and the first guide rail slider mechanism is installed on the cabin support frame 6; each skin driving mechanism includes a second guide rail slider mechanism, a ball joint rod 12 and a mechanism connecting rod 14, the rear side of the second guide rail slider mechanism is hinged to the front side of the annular dynamic platform 11 through the ball joint rod 12, the front side of the second guide rail slider mechanism is hinged to the rear end of the corresponding mechanism connecting rod 14 through a fixed hinge, the front end of the mechanism connecting rod 14 is connected to the corresponding composite hinge for connecting the rear side of the cabin front end skin 2 and the front side of the cabin rear end skin 3, and the relative movement of the cabin rear end skin 3 and the cabin front end skin 2 is completed by the deformation mechanism 4, thereby realizing the deformation of the aircraft cabin.

[0007] Furthermore, the number of the front end skin 2 of the cabin, the rear end skin 3 of the cabin, the skin drive mechanism, the skeleton hinge 8, the first guide rail slider mechanism, the skeleton hinge 8, the first guide rail slider mechanism, the second guide rail slider mechanism, the ball joint rod 12 and the mechanism connecting rod 14 are all twelve.

[0008] Furthermore, each moving platform driving mechanism includes a vertical Hooke's joint 7, a servo electric cylinder 9 and a ball joint 10. The rear end of the servo electric cylinder 9 is hinged to the front side of the rear end plate through the vertical Hooke's joint 7, and the front end of the servo electric cylinder 9 is hinged to the rear side of the annular moving platform 11 through the ball joint 10.

[0009] Furthermore, the first guide rail slider mechanism includes a follower slider 16 and two short slide rails 17. Two first slide rail holes are processed on the follower slider 16. The two short slide rails 17 pass through the two first slide rail holes respectively. The front and rear ends of the two short slide rails 17 are respectively fixed to the front short slide rail connecting ring plate 36 and the rear short slide rail connecting ring plate 37 of the cabin support frame 6. The outer side of the follower slider 16 is hinged to the front side of the cabin front end skin 2 through a fixed hinge.

[0010] Furthermore, the second guide rail slider mechanism includes a driving slider 13 and two long slide rails 15. Two second slide rail holes are processed on the driving slider 13. The two long slide rails 15 pass through the two second slide rail holes respectively. The front and rear ends of the two long slide rails 15 are respectively fixed to the front long slide rail connecting ring plate 34 and the rear long slide rail connecting ring plate 35 of the cabin support frame 6. The rear side of the driving slider 13 is hinged to the front side of the annular dynamic platform 11 through the ball joint rod 12, and the front side of the driving slider 13 is hinged to the rear end of the corresponding mechanism connecting rod 14 through a fixed hinge.

[0011] Furthermore, the driving slider 13, the mechanism connecting rod 14, the cabin front end skin 2, and the cabin rear end skin 3 form a crank double slider mechanism.

[0012] Furthermore, the six servo electric cylinders 9 can drive the annular moving platform 11 to realize axial telescopic movement or swing through different extension amounts. The annular moving platform 11 drives multiple driving sliders 13 to move along multiple long slide rails 15 respectively. The multiple driving sliders 13 respectively drive multiple mechanism connecting rods 14 to move. The multiple mechanism connecting rods 14 respectively drive multiple cabin rear end skins 3 to rotate around multiple skeleton hinges 8. At the same time, the multiple cabin front end skins 2 are also driven by the mechanism connecting rods 14 to make multiple follow-up sliders 16 move along multiple short slide rails 17, thereby realizing the movement of the cabin front end skin 2 and the cabin rear end skin 3, and then realizing the change in the appearance of the aircraft cabin.

[0013] Furthermore, the first slide rail hole of each follower slider 16 is equipped with a linear bearing 18, and each linear bearing 18 has two annular grooves on the outer surface thereof, which respectively cooperate with two retaining springs 19, thereby fixing the follower slider 16 and the linear bearing 18 together, and the inner side of each linear bearing 18 cooperates with the short slide rail 17, thereby realizing the sliding of the follower slider 16 on the short slide rail 17, and each short slide rail 17 is fixed to the cabin support frame 6 by its corresponding connecting nut 23, and a gasket 20 is provided between the connecting nut 23 and the supporting surface of the cabin support frame 6. At the same time, the hinge head on the outer side of each follower slider 16 cooperates with the hinge mouth on the front side of a cabin front end skin 2, and is connected with a bolt 21, two first shaft sleeves 22 and a connecting nut 23, thereby realizing the rotational movement of the cabin front end skin 2 around the follower slider 16, and then transmitting the movement to the linear bearing 18, so that it slides along the short slide rail 17, realizing the follow-up of the cabin front end skin support.

[0014] Furthermore, the upper end of the Hooke hinge bottom shaft 27 of each vertical Hooke hinge 7 cooperates with the hinge mouth at the bottom of a servo electric cylinder 9, and is connected using an end cover 26, a pin shaft 28 and two second shaft sleeves 29, thereby realizing the rotational movement of the servo electric cylinder around the hinge point of the vertical Hooke hinge 7. At the same time, the lower end of the Hooke hinge bottom shaft 27 cooperates with two deep groove ball bearings 30, and a Hooke hinge bottom cover 25 and a locking nut 31 are used to fix the two deep groove ball bearings 30 on the Hooke hinge bottom shaft 27. The outer side of the deep groove ball bearing 30 cooperates with the inner side of the Hooke hinge base 24, thereby realizing the rotational movement of the Hooke hinge bottom shaft 27 around the vertical axis of the vertical Hooke hinge 7. The fixed connection between the vertical Hooke hinge 7 and the cabin support frame 6 is achieved by connecting the outer edge of the Hooke hinge base 24 to the cabin support frame 6 with bolts.

[0015] A method for deforming an aircraft combined skin-deformation mechanism multi-dimensional deformable cabin based on any one of the embodiments 6 to 9 is implemented by the following steps:

[0016] Step 1: Complete the cabin's movement from symmetrical retracted deformation to symmetrical intermediate deformation and then to symmetrical extended deformation:

[0017] Initially, all six servo cylinders 9 retract to their origin positions, and the mechanism connecting rod 14 pulls the front and rear skins 2 and 3 of the cabin body back into the cabin body. At this time, the cabin body shape is in its initial state, that is, a symmetrical retracted deformation state. From the cabin body cross-section, the angle between the front and rear skins 2 and 3 of the cabin body is less than 180°.

[0018] The servo electric cylinder 9 provides the power for the deformation of the cabin. The six servo electric cylinders 9 extend to the same length to make the front skin 2 of the cabin and the rear skin 3 of the cabin horizontal, pushing the annular moving platform 11 to move forward along the cabin axis. The annular moving platform 11 pushes each driving slider 13 to move forward along the long slide rail 15 along the cabin axis. The power is transmitted to each mechanism link 14. The mechanism link 14 rotates backward relative to the hinge point on the driving slider 13. Since the front end of the mechanism link 14 is connected to the front skin 2 of the cabin and the rear skin 3 of the cabin through a composite hinge, the mechanism link 14 While rotating relatively backward, the composite hinge point is pushed outward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin around the hinge point, the follower slider 16 moves forward along the short slide rail 17 along the axis of the cabin, and the power transmission process ends. At this time, the cabin shape is deformed into a symmetrical intermediate deformation state. From the cross section of the cabin, the angle between the front end skin 2 of the cabin and the rear end skin 3 of the cabin is 180°.

[0019] The servo electric cylinder 9 provides the power for the cabin deformation again, and the six servo electric cylinders 9 continue to extend the same length to the position where the front end skin 2 of the cabin and the rear end skin 3 of the cabin are convex, pushing the annular moving platform 11 to continue to move forward along the cabin axis. The annular moving platform 11 pushes each driving slider 13 to continue to move forward along the long slide rail 15 along the cabin axis. The power is transmitted to each mechanism link 14, and the mechanism link 14 continues to rotate backward relative to the hinge point on it and the driving slider 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin and the rear end skin 3 of the cabin through a composite hinge, the mechanism link 1 4 rotates relatively backward while continuing to push the composite hinge point outward, and the rear end skin 3 of the cabin body continues to rotate toward the outside of the cabin body around the hinge point of the skeleton hinge 8 between its rear end and the cabin body support skeleton 6. At the same time, the front end skin 2 of the cabin body continues to rotate toward the outside of the cabin body around the hinge point of its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin body around the hinge point, the follower slider 16 continues to move forward along the short slide rail 17 along the cabin body axis. The power transmission process ends. At this time, the cabin body shape is deformed into a symmetrical extended deformation state. From the perspective of the cabin body cross section, the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body is greater than 180°.

[0020] Step 2: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower concave deformation state:

[0021] Initially, all six servo cylinders 9 are retracted to their shortest positions, and the mechanism connecting rod 14 pulls the skin back into the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross-section, the angle between the cabin front skin 2 and the cabin rear skin 3 is less than 180°.

[0022] Six servo electric cylinders 9 provide the power for the deformation of the cabin, among which the two servo electric cylinders 9 on the top provide more extension than the other four servo electric cylinders 9. At this time, the two servo electric cylinders 9 on the top extend to the same length to make the front end skin 2 of the cabin and the rear end skin 3 of the cabin horizontal, pushing the upper side of the annular moving platform 11 to move forward along the cabin axis, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the lower side, and the annular moving platform 11 pushes the upper side driving sliders 13 to move forward along the long slide rails 15 along the cabin axis, and the power is transmitted to the upper side mechanism connecting rods 14, and the mechanism connecting rod 14 rotates backward relative to the hinge point on the driving slider 13. Since the front end of the mechanism connecting rod 14 and the front end skin 2 and the rear end skin 3 of the cabin are connected by a composite The hinge is connected, so the mechanism link 14 rotates relatively backward while pushing the composite hinge point outward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin around the hinge point, the upper follower sliders 16 move forward along the short slide rails 17 along the cabin axis, and the power transmission process ends. At this time, the cabin shape is deformed into a flat upper and concave lower deformation state. From the cross section of the cabin, the angle between the front end skin 2 of the cabin on the upper side and the rear end skin 3 of the cabin is 180 degrees, and the angle between the front end skin 2 of the cabin on the lower side and the rear end rigid skin support is less than 180 degrees.

[0023] Step 3: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower convex deformation state:

[0024] Initially, all six servo cylinders 9 are retracted to their shortest positions, and the mechanism connecting rod 14 pulls the skin back into the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross-section, the angle between the cabin front skin 2 and the cabin rear skin 3 is less than 180°.

[0025] Six servo cylinders 9 provide the power for cabin deformation, among which the two lower servo cylinders 9 provide more extension than the other four servo cylinders 9, and the four upper servo cylinders 9 extend the same length to a position where the front end skin 2 of the cabin and the rear end skin 3 of the cabin are horizontal, pushing the upper side of the annular moving platform 11 to move forward along the cabin axis, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the lower side, and the annular moving platform 11 pushes the upper drive sliders 13 to move forward along the long slide rails 15 along the cabin axis, and the power is transmitted to the upper mechanism connecting rods 14, and the mechanism connecting rods 14 rotate backward relative to each other around the hinge points on the drive sliders 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin and the rear end skin 3 of the cabin through a composite hinge, the mechanism link 14 pushes the composite hinge point outward while rotating relatively backward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end rigid skin support around the hinge point, the upper follower sliders 16 move forward along the short slide rail 17 along the axis of the cabin; next, the two servo electric cylinders 9 below the cabin provide power for cabin deformation, and the two servo electric cylinders 9 below extend. The same length is to the position where the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body are in a convex state, pushing the lower side of the annular moving platform 11 to move forward along the axis of the cabin body, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the upper side, and the annular moving platform 11 pushes the lower side driving sliders 13 to move forward along the long slide rails 15 along the axis of the cabin body, and the power is transmitted to the lower side mechanism links 14, and the mechanism links 14 rotate backward relative to each other around the hinge points on the driving sliders 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body through a composite hinge, the mechanism link 14 pushes the composite hinge outward while rotating relatively backward. At this point, the rear end skin 3 of the cabin body rotates toward the outside of the cabin body around the hinge point of the skeleton hinge 8 between its rear end and the cabin body support skeleton 6, and at the same time, the front end skin 2 of the cabin body rotates toward the outside of the cabin body around the hinge point of the follower slider 16 between its front end. During the rotation of the front end skin 2 of the cabin body around the hinge point, each follower slider 16 on the lower side moves forward along the short slide rail 17 along the cabin body axis, and the power transmission process ends. At this time, the cabin body shape is deformed into a flat upper and convex lower deformation state. From the cross section of the cabin body, the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body on the upper side is 180°, and the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body on the lower side is greater than 180°.

[0026] So far, the three steps of the above-mentioned aircraft cabin deformation mechanism are steps for the cabin to achieve three different deformation states.

[0027] Compared with the prior art, the present invention has the following effects:

[0028] 1. The present invention uses a servo electric cylinder 9 to input power and utilizes a combined skin-deformation mechanism to achieve deformation of different types of aircraft cabins, meeting the requirements of maintaining a good aerodynamic shape under different flight conditions and flight states, while also providing the aircraft with high maneuverability.

[0029] 2. The deformation mechanism 4 of the present invention includes six vertical Hooke's hinges 7, twelve skeleton hinges 8, six servo electric cylinders 9, six ball joints 10, an annular moving platform 11, twelve ball joint rods 12, twelve driving sliders 13, twelve mechanism connecting rods 14, twenty-four long slide rails 15, twelve follower sliders 16 and twenty-four short slide rails 17, among which the driving sliders 13, the mechanism connecting rods 14 and the front end skin 2 and the rear end skin 3 of the cabin body form a crank double slider mechanism.

[0030] 3. The present invention uses the deformation mechanism 4 to achieve the deformation function of the aircraft cabin. The deformation mechanism 4 completes the relative movement of the cabin rear end skin 3 and the cabin front end skin 2, thereby achieving the goal of aircraft cabin deformation.

[0031] 4. The deformation mechanism of the present invention not only occupies less space in the aircraft cabin, but also can realize different types of deformation. After deformation, it still has a certain load-bearing capacity, taking into account the design requirements of deformation and load-bearing. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 This is a schematic structural diagram of the aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin of the present invention;

[0033] Figure 2 This is a schematic diagram of the internal structure of the aircraft cabin of the present invention after removing the cabin front cone 1 and the rear fairing ring 5;

[0034] Figure 3 The present invention Figure 2 A partial enlarged view of point A in the middle;

[0035] Figure 4 The present invention Figure 2 Cross-sectional view of the connection position at A in the middle;

[0036] Figure 5 It is an axonometric view of the vertical Hooke's hinge of the present invention;

[0037] Figure 6 The present invention Figure 5 Cross-section in the middle BB direction;

[0038] Figure 7 is an axonometric view of the cabin support frame 6 of the present invention;

[0039] Figure 8It is an exploded view of the aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin of the present invention.

[0040] In the figure: 1-cabin front cone; 2-cabin front skin; 3-cabin rear skin; 4-deformation mechanism; 5-rear fairing ring; 6-cabin support frame; 7-vertical Hook hinge; 8-frame hinge; 9-servo electric cylinder; 10-ball joint; 11-annular dynamic platform; 12-ball joint rod; 13-driving slide; 14-mechanism connecting rod; 15-long slide rail; 16-following slide; 17-short slide rail; 18-linear bearing; 19-circlip; 20-gasket; 1-bolt; 22-first bushing; 23-connecting nut; 24-Hook's hinge base; 25-Hook's hinge bottom cover; 26-end cover; 27-Hook's hinge bottom shaft; 28-pin shaft; 29-second bushing; 30-deep groove ball bearing; 31-locking nut; 32-front end plate of the skeleton; 33-middle ring plate of the skeleton; 34-front long slide rail connecting ring plate; 35-rear long slide rail connecting ring plate; 36-front short slide rail connecting ring plate; 37-rear short slide rail connecting ring plate. DETAILED DESCRIPTION

[0041] Specific implementation method 1: Combination Figures 1 to 8The present embodiment is described. The present embodiment is a multi-dimensional deformable cabin of an aircraft combined skin-deformation mechanism type, which includes a cabin front cone 1, a deformation mechanism 4, a rear fairing ring 5, a cabin support frame 6, a plurality of cabin front end skins 2 and a plurality of cabin rear end skins 3. The cabin front cone 1 and the cabin support frame 6 are coaxially arranged from front to back. The front section of the cabin support frame 6 is evenly arranged with a plurality of cabin front end skins 2 along the circumference. The middle section of the cabin support frame 6 is evenly arranged with a plurality of cabin rear end skins 3 corresponding to the plurality of cabin front end skins 2 along the circumference. Each cabin front end skin The rear side of the hull is hinged to the front side of the corresponding cabin rear end skin 3 through a composite hinge. The rear section of the cabin support frame 6 is provided with a rear fairing ring 5. A deformation mechanism 4 is provided between the cabin support frame 6 and the cabin front end skin 2 and the cabin rear end skin 3. The deformation mechanism 4 includes an annular dynamic platform 11, six dynamic platform drive mechanisms, multiple skin drive mechanisms, multiple skeleton hinges 8 and multiple first guide rail slider mechanisms. The annular dynamic platform 11 is sleeved on the cabin support frame 6. Six dynamic platform drive mechanisms are provided along the circumferential direction between the annular dynamic platform 11 and the rear end plate. The dynamic platform drive mechanism The front and rear ends are hinged to the annular dynamic platform 11 and the rear end plate respectively; a plurality of skin driving mechanisms are arranged circumferentially between the annular dynamic platform 11 and the front end plate 32 of the cabin support frame 6, and the plurality of skin driving mechanisms correspond one to one with the plurality of cabin front end skins 2 and / or the plurality of cabin rear end skins 3 respectively, and the rear side of each cabin rear end skin 3 is hinged to the middle ring plate 33 of the cabin support frame 6 through a frame hinge 8, and the front side of each cabin front end skin 2 is hinged to the first guide rail slider mechanism through a fixed hinge, and the first guide rail slider mechanism is installed on the cabin The front side of the support skeleton 6; each skin driving mechanism includes a second guide rail slider mechanism, a ball joint rod 12 and a mechanism connecting rod 14, the rear side of the second guide rail slider mechanism is hinged to the front side of the annular dynamic platform 11 through the ball joint rod 12, the front side of the second guide rail slider mechanism is hinged to the rear end of the corresponding mechanism connecting rod 14 through a fixed hinge, the front end of the mechanism connecting rod 14 is connected to the corresponding composite hinge for connecting the rear side of the cabin front skin 2 and the front side of the cabin rear end skin 3, and the relative movement of the cabin rear end skin 3 and the cabin front end skin 2 is completed through the deformation mechanism 4, thereby realizing the deformation of the aircraft cabin.

[0042] Specific implementation method 2: Combination Figure 1 and Figure 2 To describe this embodiment, the number of the cabin front end skin 2, cabin rear end skin 3, skin drive mechanism, skeleton hinge 8, first guide rail slider mechanism, skeleton hinge 8, first guide rail slider mechanism, second guide rail slider mechanism, ball joint rod 12, and mechanism connecting rod 14 in this embodiment is twelve. The other components and connection relationships are the same as those in the first embodiment.

[0043] Specific implementation method three: Combination Figure 1 、 Figure 2、 Figure 5 and Figure 6 To explain this embodiment, each movable platform drive mechanism comprises a vertical Hooke's joint 7, a servo cylinder 9, and a ball joint 10. The rear end of the servo cylinder 9 is hinged to the front of the rear end plate via the vertical Hooke's joint 7, while the front end of the servo cylinder 9 is hinged to the rear of the annular movable platform 11 via the ball joint 10. The front end of the servo cylinder 9 is threadedly connected to a ball joint 10. This arrangement enables the movable platform drive mechanism to drive the annular movable platform 11 to achieve axial telescopic motion or oscillation. Other components and connections are identical to those in the first or second embodiments.

[0044] Specific implementation method four: Combination Figures 1 to 4 This embodiment describes the first guide rail slider mechanism, which includes a follower slider 16 and two short rails 17. The follower slider 16 is provided with two first rail holes, through which the two short rails 17 extend. The front and rear ends of the two short rails 17 are respectively fixed to the front short rail connecting ring plate 36 and the rear short rail connecting ring plate 37 of the cabin support frame 6. The outer side of the follower slider 16 is hinged to the front side of the cabin front end skin 2 via a fixed hinge. The remaining components and connections are identical to those of the first, second, or third embodiments.

[0045] In this embodiment, the aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin includes twelve follower sliders 16 and twenty-four short slide rails 17 .

[0046] Specific implementation method five: Combination Figure 1 and Figure 2 To describe this embodiment, the second guide rail slider mechanism includes a drive slider 13 and two long slide rails 15. The drive slider 13 is machined with two second slide rail holes, through which the two long slide rails 15 pass. The front and rear ends of the two long slide rails 15 are respectively fixed to the front long slide rail connecting ring plate 34 and the rear long slide rail connecting ring plate 35 of the cabin support frame 6. The rear side of the drive slider 13 is hinged to the front side of the annular dynamic platform 11 via a ball joint rod 12. The front side of the drive slider 13 is hinged to the rear end of the corresponding mechanism connecting rod 14 via a fixed hinge. Other components and connection relationships are the same as those of Specific Embodiments 1, 2, 3, or 4.

[0047] In this embodiment, the aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin includes twelve driving sliders 13 and twenty-four long slide rails 15.

[0048] Specific implementation method six: combination Figure 1 and Figure 2To describe this embodiment, the drive slider 13, the mechanism connecting rod 14, the cabin front end skin 2, and the cabin rear end skin 3 form a crank double slider mechanism. The other components and connection relationships are the same as those of the first, second, third, fourth, or fifth embodiments.

[0049] Specific implementation method seven: combination Figure 1 and Figure 2 To explain this embodiment, the six servo cylinders 9 of this embodiment can drive the annular movable platform 11 to achieve axial telescopic movement or swinging through different extension amounts. The annular movable platform 11 drives multiple drive sliders 13 to move along multiple long slide rails 15. The multiple drive sliders 13 respectively drive multiple mechanism links 14 to move. The multiple mechanism links 14 respectively drive multiple cabin rear end skins 3 to rotate about multiple skeleton hinges 8. Simultaneously, the multiple cabin front end skins 2 are also driven by the mechanism links 14 to cause multiple follower sliders 16 to follow along multiple short slide rails 17, thereby achieving movement of the cabin front end skin 2 and the cabin rear end skin 3, and thus achieving changes in the aircraft cabin's appearance. The other components and connection relationships are the same as those of the first, second, third, fourth, fifth, or sixth embodiments.

[0050] Specific implementation method eight: combination Figure 3 and Figure 4 To explain this embodiment, in this embodiment, the first slide rail hole of each follower slider 16 is equipped with a linear bearing 18, and each linear bearing 18 has two annular grooves on the outer surface thereof, which respectively cooperate with two retaining springs 19, thereby fixing the follower slider 16 and the linear bearing 18 together, and the inner side of each linear bearing 18 cooperates with the short slide rail 17, thereby realizing the sliding of the follower slider 16 on the short slide rail 17, and each short slide rail 17 is fixed to the cabin support frame 6 by its corresponding connecting nut 23, and a gasket 20 is provided between the connecting nut 23 and the supporting surface of the cabin support frame 6. At the same time, the hinge head on the outer side of each follower slider 16 cooperates with the hinge mouth on the front side of a cabin front end skin 2, and is connected with a bolt 21, two first shaft sleeves 22 and a connecting nut 23, thereby realizing the rotational movement of the cabin front end skin 2 around the follower slider 16, and then transmitting the movement to the linear bearing 18, so that it slides along the short slide rail 17, realizing the follow-up of the cabin front end skin support. Other components and connection relationships are the same as those in the first, second, third, fourth, fifth, sixth or seventh embodiment.

[0051] Specific implementation method nine: Combination Figure 5 and Figure 6To explain this embodiment, the upper end of the Hook hinge bottom shaft 27 of each vertical Hook hinge 7 in this embodiment mates with the hinge opening at the bottom of a servo electric cylinder 9 and is connected using an end cap 26, a pin 28, and two second bushings 29, thereby enabling the servo electric cylinder to rotate about the hinge point of the vertical Hook hinge 7. Simultaneously, the lower end of the Hook hinge bottom shaft 27 mates with two deep groove ball bearings 30, which are secured to the Hook hinge bottom shaft 27 using a Hook hinge bottom cap 25 and a locking nut 31. The outer sides of the deep groove ball bearings 30 mate with the inner sides of the Hook hinge base 24, thereby enabling the Hook hinge bottom shaft 27 to rotate about the vertical axis of the vertical Hook hinge 7. The fixed connection between the vertical Hook hinge 7 and the cabin support frame 6 is achieved by bolting the outer edge of the Hook hinge base 24 to the cabin support frame 6. Other components and connection relationships are the same as those of the first, second, third, fourth, fifth, sixth, seventh, or eighth embodiments.

[0052] Specific implementation method ten: Combination Figures 1 to 8 This embodiment describes a deformation method of an aircraft combined skin-deformation mechanism multi-dimensional deformation cabin based on any one of the specific embodiments from Specific Embodiments 6 to Specific Embodiments 9. The aircraft cabin deformation method is achieved by the following steps:

[0053] Step 1: Complete the cabin's movement from symmetrical retracted deformation to symmetrical intermediate deformation and then to symmetrical extended deformation:

[0054] Initially, all six servo cylinders 9 retract to their origin positions, and the mechanism connecting rod 14 pulls the front and rear skins 2 and 3 of the cabin body back into the cabin body. At this time, the cabin body shape is in its initial state, that is, a symmetrical retracted deformation state. From the cabin body cross-section, the angle between the front and rear skins 2 and 3 of the cabin body is less than 180°.

[0055] The servo electric cylinder 9 provides the power for the deformation of the cabin. The six servo electric cylinders 9 extend to the same length to make the front skin 2 of the cabin and the rear skin 3 of the cabin horizontal, pushing the annular moving platform 11 to move forward along the cabin axis. The annular moving platform 11 pushes each driving slider 13 to move forward along the long slide rail 15 along the cabin axis. The power is transmitted to each mechanism link 14. The mechanism link 14 rotates backward relative to the hinge point on the driving slider 13. Since the front end of the mechanism link 14 is connected to the front skin 2 of the cabin and the rear skin 3 of the cabin through a composite hinge, the mechanism link 14 While rotating relatively backward, the composite hinge point is pushed outward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin around the hinge point, the follower slider 16 moves forward along the short slide rail 17 along the axis of the cabin, and the power transmission process ends. At this time, the cabin shape is deformed into a symmetrical intermediate deformation state. From the cross section of the cabin, the angle between the front end skin 2 of the cabin and the rear end skin 3 of the cabin is 180°.

[0056] The servo electric cylinder 9 provides the power for the cabin deformation again, and the six servo electric cylinders 9 continue to extend the same length to the position where the front end skin 2 of the cabin and the rear end skin 3 of the cabin are convex, pushing the annular moving platform 11 to continue to move forward along the cabin axis. The annular moving platform 11 pushes each driving slider 13 to continue to move forward along the long slide rail 15 along the cabin axis. The power is transmitted to each mechanism link 14, and the mechanism link 14 continues to rotate backward relative to the hinge point on it and the driving slider 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin and the rear end skin 3 of the cabin through a composite hinge, the mechanism link 1 4 rotates relatively backward while continuing to push the composite hinge point outward, and the rear end skin 3 of the cabin body continues to rotate toward the outside of the cabin body around the hinge point of the skeleton hinge 8 between its rear end and the cabin body support skeleton 6. At the same time, the front end skin 2 of the cabin body continues to rotate toward the outside of the cabin body around the hinge point of its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin body around the hinge point, the follower slider 16 continues to move forward along the short slide rail 17 along the cabin body axis. The power transmission process ends. At this time, the cabin body shape is deformed into a symmetrical extended deformation state. From the perspective of the cabin body cross section, the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body is greater than 180°.

[0057] In step one, the deformable cabin of the aircraft can achieve a symmetrical retracted deformation state, a symmetrical intermediate deformation state and a symmetrical extended deformation state. When changing from the symmetrical retracted deformation state to the symmetrical extended deformation state, the aerodynamic heat on the outer surface of the aircraft cabin during flight can be reduced, so that the local aerodynamic heat is lower than that of the aircraft cabin with a fixed shape.

[0058] Step 2: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower concave deformation state:

[0059] Initially, all six servo cylinders 9 are retracted to their shortest positions, and the mechanism connecting rod 14 pulls the skin back into the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross-section, the angle between the cabin front skin 2 and the cabin rear skin 3 is less than 180°.

[0060] Six servo electric cylinders 9 provide the power for the deformation of the cabin, among which the two servo electric cylinders 9 on the top provide more extension than the other four servo electric cylinders 9. At this time, the two servo electric cylinders 9 on the top extend to the same length to make the front end skin 2 of the cabin and the rear end skin 3 of the cabin horizontal, pushing the upper side of the annular moving platform 11 to move forward along the cabin axis, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the lower side, and the annular moving platform 11 pushes the upper side driving sliders 13 to move forward along the long slide rails 15 along the cabin axis, and the power is transmitted to the upper side mechanism connecting rods 14, and the mechanism connecting rod 14 rotates backward relative to the hinge point on the driving slider 13. Since the front end of the mechanism connecting rod 14 and the front end skin 2 and the rear end skin 3 of the cabin are connected by a composite The hinge is connected, so the mechanism link 14 rotates relatively backward while pushing the composite hinge point outward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end skin 2 of the cabin around the hinge point, the upper follower sliders 16 move forward along the short slide rails 17 along the cabin axis, and the power transmission process ends. At this time, the cabin shape is deformed into a flat upper and concave lower deformation state. From the cross section of the cabin, the angle between the front end skin 2 of the cabin on the upper side and the rear end skin 3 of the cabin is 180 degrees, and the angle between the front end skin 2 of the cabin on the lower side and the rear end rigid skin support is less than 180 degrees.

[0061] In step 2, the aircraft can realize a deformation state from a symmetrical retracted state to a flat upper and concave lower state. This deformation form can improve the aerodynamic efficiency of the aircraft during flight, improve the aircraft's lift-to-drag ratio and increase the aircraft's range.

[0062] Step 3: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower convex deformation state:

[0063] Initially, all six servo cylinders 9 are retracted to their shortest positions, and the mechanism connecting rod 14 pulls the skin back into the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross-section, the angle between the cabin front skin 2 and the cabin rear skin 3 is less than 180°.

[0064] Six servo cylinders 9 provide the power for cabin deformation, among which the two lower servo cylinders 9 provide more extension than the other four servo cylinders 9, and the four upper servo cylinders 9 extend the same length to a position where the front end skin 2 of the cabin and the rear end skin 3 of the cabin are horizontal, pushing the upper side of the annular moving platform 11 to move forward along the cabin axis, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the lower side, and the annular moving platform 11 pushes the upper drive sliders 13 to move forward along the long slide rails 15 along the cabin axis, and the power is transmitted to the upper mechanism connecting rods 14, and the mechanism connecting rods 14 rotate backward relative to each other around the hinge points on the drive sliders 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin and the rear end skin 3 of the cabin through a composite hinge, the mechanism link 14 pushes the composite hinge point outward while rotating relatively backward, and the rear end skin 3 of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge 8 between its rear end and the cabin support skeleton 6. At the same time, the front end skin 2 of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider 16. During the rotation of the front end rigid skin support around the hinge point, the upper follower sliders 16 move forward along the short slide rail 17 along the axis of the cabin; next, the two servo electric cylinders 9 below the cabin provide power for cabin deformation, and the two servo electric cylinders 9 below extend. The same length is to the position where the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body are in a convex state, pushing the lower side of the annular moving platform 11 to move forward along the axis of the cabin body, that is, the annular moving platform 11 rotates and swings forward around the ball hinges on the upper side, and the annular moving platform 11 pushes the lower side driving sliders 13 to move forward along the long slide rails 15 along the axis of the cabin body, and the power is transmitted to the lower side mechanism links 14, and the mechanism links 14 rotate backward relative to each other around the hinge points on the driving sliders 13. Since the front end of the mechanism link 14 is connected to the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body through a composite hinge, the mechanism link 14 pushes the composite hinge outward while rotating relatively backward. At this point, the rear end skin 3 of the cabin body rotates toward the outside of the cabin body around the hinge point of the skeleton hinge 8 between its rear end and the cabin body support skeleton 6, and at the same time, the front end skin 2 of the cabin body rotates toward the outside of the cabin body around the hinge point of the follower slider 16 between its front end. During the rotation of the front end skin 2 of the cabin body around the hinge point, each follower slider 16 on the lower side moves forward along the short slide rail 17 along the cabin body axis, and the power transmission process ends. At this time, the cabin body shape is deformed into a flat upper and convex lower deformation state. From the cross section of the cabin body, the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body on the upper side is 180°, and the angle between the front end skin 2 of the cabin body and the rear end skin 3 of the cabin body on the lower side is greater than 180°.

[0065] In step three, the aircraft can achieve a symmetrical retracted deformation state to a flat upper and convex lower deformation state. This deformation form can reduce the aerodynamic heat on the lower surface of the aircraft cabin, improve the maneuverability of the aircraft, and improve the aerodynamic efficiency of the aircraft.

[0066] So far, the three steps of the above-mentioned aircraft cabin deformation mechanism are steps for the cabin to achieve three different deformation states. By controlling the extension amount of each servo electric cylinder 9, the cabin can be deformed into more forms of deformation states.

[0067] The other components and connection relationships are the same as those in the first, second, third, fourth, fifth, sixth, seventh, eighth or ninth embodiment.

[0068] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin, characterized by: It comprises a cabin front cone (1), a deformation mechanism (4), a rear fairing ring (5), a cabin support frame (6), a plurality of cabin front end skins (2) and a plurality of cabin rear end skins (3). The cabin front cone (1) and the cabin support frame (6) are coaxially arranged from front to back. A plurality of cabin front end skins (2) are evenly arranged on the front section of the cabin support frame (6) along the circumference. A plurality of cabin rear end skins (3) corresponding to the plurality of cabin front end skins (2) are evenly arranged on the middle section of the cabin support frame (6) along the circumference. The rear side of each cabin front end skin (2) is connected to the corresponding cabin rear end skin (3) through a composite hinge. The front side of the cabin support frame (6) is hinged, and the rear section of the cabin support frame (6) is provided with a rear fairing ring (5). A deformation mechanism (4) is provided between the cabin support frame (6) and the cabin front end skin (2) and the cabin rear end skin (3). The deformation mechanism (4) includes an annular moving platform (11), six moving platform driving mechanisms, multiple skin driving mechanisms, multiple skeleton hinges (8) and multiple first guide rail slider mechanisms. The annular moving platform (11) is sleeved on the cabin support frame (6). Six moving platform driving mechanisms are provided along the circumferential direction between the annular moving platform (11) and the rear end plate. The front and rear ends of the moving platform driving mechanisms are respectively connected to the annular moving platform (11). ) and the rear end plate; a plurality of skin driving mechanisms are provided along the circumferential direction between the annular dynamic platform (11) and the front end plate (32) of the cabin support frame (6), and the plurality of skin driving mechanisms correspond to the plurality of cabin front end skins (2) and / or the plurality of cabin rear end skins (3) respectively. The rear side of each cabin rear end skin (3) is hinged to the middle ring plate (33) of the cabin support frame (6) through a frame hinge (8), and the front side of each cabin front end skin (2) is hinged to the first guide rail slider mechanism through a fixed hinge. The first guide rail slider mechanism is installed on the cabin support frame (6). Front side; each skin driving mechanism includes a second guide rail slider mechanism, a ball hinge rod (12) and a mechanism connecting rod (14); the rear side of the second guide rail slider mechanism is hinged to the front side of the annular dynamic platform (11) through the ball hinge rod (12); the front side of the second guide rail slider mechanism is hinged to the rear end of the corresponding mechanism connecting rod (14) through a fixed hinge; the front end of the mechanism connecting rod (14) is connected to the corresponding composite hinge for connecting the rear side of the cabin front skin (2) and the front side of the cabin rear skin (3); the relative movement of the cabin rear skin (3) and the cabin front skin (2) is completed through the deformation mechanism (4), thereby realizing the deformation of the aircraft cabin.

2. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 1, characterized in that: The number of the cabin front end skin (2), the cabin rear end skin (3), the skin drive mechanism, the skeleton hinge (8), the first guide rail slider mechanism, the skeleton hinge (8), the first guide rail slider mechanism, the second guide rail slider mechanism, the ball hinge rod (12) and the mechanism connecting rod (14) is twelve.

3. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 2, characterized in that: Each moving platform driving mechanism includes a vertical Hooke's joint (7), a servo electric cylinder (9) and a ball joint (10). The rear end of the servo electric cylinder (9) is hinged to the front side of the rear end plate through the vertical Hooke's joint (7), and the front end of the servo electric cylinder (9) is hinged to the rear side of the annular moving platform (11) through the ball joint (10).

4. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 2 or 3, characterized in that: The first guide rail slider mechanism includes a follower slider (16) and two short slide rails (17). Two first slide rail holes are processed on the follower slider (16). The two short slide rails (17) pass through the two first slide rail holes respectively. The front and rear ends of the two short slide rails (17) are respectively fixed to the front short slide rail connecting ring plate (36) and the rear short slide rail connecting ring plate (37) of the cabin support frame (6). The outer side of the follower slider (16) is hinged to the front side of the cabin front end skin (2) through a fixed hinge.

5. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 4, characterized in that: The second guide rail slider mechanism includes a driving slider (13) and two long slide rails (15). Two second slide rail holes are processed on the driving slider (13). The two long slide rails (15) pass through the two second slide rail holes respectively. The front and rear ends of the two long slide rails (15) are respectively fixed to the front long slide rail connecting ring plate (34) and the rear long slide rail connecting ring plate (35) of the cabin support frame (6). The rear side of the driving slider (13) is hinged to the front side of the annular moving platform (11) through the ball hinge rod (12). The front side of the driving slider (13) is hinged to the rear end of the corresponding mechanism connecting rod (14) through a fixed hinge.

6. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 5, characterized in that: The driving slider (13), the mechanism connecting rod (14), the cabin front end skin (2), and the cabin rear end skin (3) form a crank double slider mechanism.

7. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 6, characterized in that: The six servo electric cylinders (9) can drive the annular movable platform (11) to realize axial telescopic movement or swing through different extension amounts. The annular movable platform (11) drives the plurality of driving sliders (13) to move along the plurality of long slide rails (15) respectively. The plurality of driving sliders (13) respectively drive the plurality of mechanism connecting rods (14) to move. The plurality of mechanism connecting rods (14) respectively drive the plurality of cabin rear end skins (3) to rotate around the plurality of skeleton hinges (8). At the same time, the plurality of cabin front end skins (2) are also driven by the mechanism connecting rods (14) to make the plurality of follow-up sliders (16) follow along the plurality of short slide rails (17), thereby realizing the movement of the cabin front end skin (2) and the cabin rear end skin (3), and further realizing the change of the appearance of the aircraft cabin.

8. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 7, characterized in that: The first slide rail hole of each follower slider (16) is equipped with a linear bearing (18). The outer surface of each linear bearing (18) has two annular grooves respectively matched with two retaining springs (19), thereby fixing the follower slider (16) and the linear bearing (18) together. The inner side of each linear bearing (18) matches with the short slide rail (17), thereby realizing the sliding of the follower slider (16) on the short slide rail (17). Each short slide rail (17) is fixed to the cabin support frame (6) by its corresponding connecting nut (23). The connecting nut (2 3) A gasket (20) is provided between the support surface of the cabin support frame (6), and the hinge head on the outside of each follower slider (16) cooperates with the hinge opening on the front side of a cabin front end skin (2), and is connected using a bolt (21), two first shaft sleeves (22) and a connecting nut (23), thereby realizing the rotational movement of the cabin front end skin (2) around the follower slider (16), and then transmitting the movement to the linear bearing (18), so that it slides along the short slide rail (17), thereby realizing the follow-up of the cabin front end skin support.

9. The aircraft combined skin-deformation mechanism type multi-dimensional deformable cabin according to claim 8, characterized in that: The upper end of the Hooke hinge bottom shaft (27) of each vertical Hooke hinge (7) cooperates with the hinge opening at the bottom of a servo electric cylinder (9) and is connected by an end cover (26), a pin shaft (28) and two second shaft sleeves (29), thereby realizing the rotational movement of the servo electric cylinder around the hinge point of the vertical Hooke hinge (7). At the same time, the lower end of the Hooke hinge bottom shaft (27) cooperates with two deep groove ball bearings (30), and a Hooke hinge bottom cover (25) and a locking nut (31) are used to fix the two deep groove ball bearings (30) on the Hooke hinge bottom shaft (27). The outer side of the deep groove ball bearing (30) cooperates with the inner side of the Hooke hinge base (24), thereby realizing the rotational movement of the Hooke hinge bottom shaft (27) around the vertical axis of the vertical Hooke hinge (7). The vertical Hooke hinge (7) is fixedly connected to the cabin support frame (6) by connecting the outer edge of the Hooke hinge base (24) to the cabin support frame (6) with bolts.

10. A method for deforming an aircraft combined skin-deformation mechanism multi-dimensional deformable cabin according to any one of claims 6 to 9, characterized in that: The aircraft cabin deformation method is achieved through the following steps: Step 1: Complete the cabin's movement from symmetrical retracted deformation to symmetrical intermediate deformation and then to symmetrical extended deformation: Initially, the six servo electric cylinders (9) are all retracted to the origin position, and the mechanism connecting rod (14) pulls the cabin front skin (2) and the cabin rear skin (3) back into the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross section, the angle between the cabin front skin (2) and the cabin rear skin (3) is less than 180°; The servo electric cylinder (9) provides the power for the deformation of the cabin. The six servo electric cylinders (9) extend to the same length to a position where the front skin (2) and the rear skin (3) of the cabin are in a horizontal state, pushing the annular moving platform (11) to move forward along the axis of the cabin. The annular moving platform (11) pushes each driving slider (13) to move forward along the long slide rail (15) along the axis of the cabin. The power is transmitted to each mechanism connecting rod (14). The mechanism connecting rod (14) rotates backward relative to the hinge point on the driving slider (13). Since the front end of the mechanism connecting rod (14) is connected to the front skin (2) and the rear skin (3) of the cabin through a composite hinge, the mechanism connecting rod The rod (14) rotates relatively backward while pushing the composite hinge point outward, and the rear end skin (3) of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge (8) between its rear end and the cabin support skeleton (6). At the same time, the front end skin (2) of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider (16). During the rotation of the front end skin (2) of the cabin around the hinge point, the follower slider (16) moves forward along the short slide rail (17) along the axis of the cabin, and the power transmission process ends. At this time, the cabin shape is deformed into a symmetrical intermediate deformation state. When viewed from the cabin cross section, the angle between the front end skin (2) of the cabin and the rear end skin (3) of the cabin is 180°. The servo electric cylinder (9) provides the power for the cabin deformation again. The six servo electric cylinders (9) continue to extend the same length to a position where the front skin (2) and the rear skin (3) of the cabin are in a convex state, pushing the annular moving platform (11) to continue to move forward along the cabin axis. The annular moving platform (11) pushes each driving slider (13) to continue to move forward along the long slide rail (15) along the cabin axis. The power is transmitted to each mechanism connecting rod (14). The mechanism connecting rod (14) continues to rotate backward relative to the hinge point on the driving slider (13). Since the front end of the mechanism connecting rod (14) is connected to the front skin (2) and the rear skin (3) of the cabin through a composite hinge, the mechanism The connecting rod (14) rotates relatively backward while continuing to push the composite hinge point outward, and the rear end skin (3) of the cabin body continues to rotate toward the outside of the cabin body around the hinge point of the skeleton hinge (8) between its rear end and the cabin body support skeleton (6). At the same time, the front end skin (2) of the cabin body continues to rotate toward the outside of the cabin body around the hinge point between its front end and the follower slider (16). During the process of the front end skin (2) of the cabin body rotating about the hinge point, the follower slider (16) continues to move forward along the short slide rail (17) along the cabin body axis. The power transmission process ends. At this time, the cabin body shape is deformed into a symmetrical stretch deformation state. When viewed from the cabin body cross section, the angle between the front end skin (2) of the cabin body and the rear end skin (3) of the cabin body is greater than 180°. Step 2: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower concave deformation state: Initially, the six servo electric cylinders (9) are all retracted to the shortest position, and the mechanism connecting rod (14) pulls the skin back to the inside of the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross section, the angle between the cabin front skin (2) and the cabin rear skin (3) is less than 180°; Six servo electric cylinders (9) provide the power for the deformation of the cabin, wherein the two servo electric cylinders (9) on the upper side provide a greater extension than the other four servo electric cylinders (9). At this time, the two servo electric cylinders (9) on the upper side extend to the same length to make the cabin front skin (2) and the cabin rear skin (3) present a horizontal state, pushing the upper side of the annular moving platform (11) to move forward along the cabin axis, that is, the annular moving platform (11) rotates and swings forward around the ball hinge points on the lower side, and the annular moving platform (11) pushes the upper side driving sliders (13) to move forward along the long slide rail (15) along the cabin axis, and the power is transmitted to the upper side mechanism connecting rods (14), and the mechanism connecting rods (14) rotate backward relative to each other around the hinge point on the driving slider (13). Due to the front end of the mechanism connecting rod (14) and the cabin front skin (2) and the cabin rear skin (3 ) are connected by a composite hinge, so the mechanism link (14) rotates relatively backward while pushing the composite hinge point outward, and the rear end skin (3) of the cabin rotates toward the outside of the cabin around the hinge point of the skeleton hinge (8) between its rear end and the cabin support skeleton (6), and at the same time, the front end skin (2) of the cabin rotates toward the outside of the cabin around the hinge point between its front end and the follower slider (16). During the rotation of the front end skin (2) of the cabin around the hinge point, the upper side follower sliders (16) move forward along the cabin axis along the short slide rail (17), and the power transmission process ends. At this time, the cabin shape is deformed into a flat upper and concave lower deformation state. From the cross section of the cabin, the angle between the cabin front end skin (2) on the upper side of the cabin and the cabin rear end skin (3) is 180°, and the angle between the cabin front end skin (2) on the lower side of the cabin and the rear end rigid skin support is less than 180°. Step 3: Complete the action of the cabin body from symmetrical retraction deformation to upper flat and lower convex deformation state: Initially, the six servo electric cylinders (9) are all retracted to the shortest position, and the mechanism connecting rod (14) pulls the skin back to the inside of the cabin. At this time, the cabin shape is in the initial state, that is, the symmetrical retracted deformation state. From the cabin cross section, the angle between the cabin front skin (2) and the cabin rear skin (3) is less than 180°; Six servo electric cylinders (9) provide power for the deformation of the cabin, wherein the two lower servo electric cylinders (9) provide a greater extension than the other four servo electric cylinders (9), and the four upper servo electric cylinders (9) extend the same length to a position where the front end skin (2) of the cabin and the rear end skin (3) of the cabin are in a horizontal state, pushing the upper side of the annular moving platform (11) to move forward along the axis of the cabin, that is, the annular moving platform (11) rotates and swings forward around the ball hinge points on the lower side, and the annular moving platform (11) pushes the upper side driving sliders (13) to move forward along the long slide rails (15) along the axis of the cabin, and the power is transmitted to the upper side mechanism connecting rods (14), and the mechanism connecting rods (14) rotate backward relative to the hinge points on the driving sliders (13). Since the front end of the mechanism connecting rod (14) is connected to the front end skin (2) of the cabin body and the rear end skin (3) of the cabin body through a composite hinge, the mechanism connecting rod (14) pushes the composite hinge point outward while rotating relatively backward, and the rear end skin (3) of the cabin body rotates toward the outside of the cabin body around the hinge point of the skeleton hinge (8) between its rear end and the cabin body support skeleton (6). At the same time, the front end skin (2) of the cabin body rotates toward the outside of the cabin body around the hinge point between its front end and the follower slider (16). During the rotation of the front end rigid skin support around the hinge point, the upper side follower sliders (16) move forward along the short slide rail (17) along the cabin body axis. Next, the two servo electric cylinders (9) below the cabin body provide the power for cabin body deformation, and the two servo electric cylinders (9) below extend The length of the same length is to the position where the front end skin (2) of the cabin body and the rear end skin (3) of the cabin body are in a convex state, and the lower side of the annular moving platform (11) is pushed to move forward along the axis of the cabin body, that is, the annular moving platform (11) rotates and swings forward around the ball hinge points on the upper side, and the annular moving platform (11) pushes the lower side driving sliders (13) to move forward along the long slide rail (15) along the axis of the cabin body, and the power is transmitted to the lower side mechanism connecting rods (14), and the mechanism connecting rods (14) rotate backward relative to each other around the hinge point on the driving slider (13). Since the front end of the mechanism connecting rod (14) is connected to the front end skin (2) of the cabin body and the rear end skin (3) of the cabin body through a composite hinge, the mechanism connecting rod (14) pushes the composite hinge points outward while rotating backward relative to each other. The rear end skin (3) of the cabin rotates outwards of the cabin around the hinge point of the skeleton hinge (8) between its rear end and the cabin support skeleton (6), and at the same time, the front end skin (2) of the cabin rotates outwards of the cabin around the hinge point of the follower slider (16) between its front end. During the rotation of the front end skin (2) of the cabin around the hinge point, the lower side follower sliders (16) move forward along the cabin axis along the short slide rail (17), and the power transmission process ends. At this time, the cabin shape is deformed into a flat upper and convex lower deformation state. From the perspective of the cabin cross section, the angle between the cabin front end skin (2) on the upper side of the cabin and the cabin rear end skin (3) is 180°, and the angle between the cabin front end skin (2) on the lower side of the cabin and the cabin rear end skin (3) is greater than 180°. So far, the three steps of the aircraft cabin deformation mechanism are the steps for the cabin to achieve three different deformation states.

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