An intake valve assembly for an aircraft auxiliary power system

Abstract

The present invention relates to the technical field of air intake valves, and in particular to an air intake valve assembly for an aircraft auxiliary power system. The present invention comprises a mounting shell, the mounting shell is provided with a through hole, the mounting shell is fixedly connected with a symmetrically distributed first hinge seat, the symmetrically distributed first hinge seats are rotatably connected with a rotating shaft, the rotating shaft is fixedly connected with a symmetrically distributed second hinge seat, the symmetrically distributed second hinge seat is commonly fixedly connected with a rotating plate, the mounting shell is fixedly connected with a motor through a mounting frame, the mounting shell is rotatably connected with a rotating shell fixed with the output shaft of the motor through the mounting frame, the outer side of the rotating shell is rotatably connected with a rotating ring, the rotating shell is provided with a circumferentially uniformly distributed first slide groove, and a first limiting column is slidably connected in the first slide groove. The present invention allows the connection between the rotating shell and the rotating ring to be disconnected, thereby avoiding overheating damage caused by the inability to rotate the output shaft of the motor when the rotating plate cannot be opened, and at the same time avoiding damage to the output shaft or the rotating shaft of the rotating plate.

Description

Technical Field

[0001] The invention relates to the technical field of air intake valves, and in particular to an air intake valve assembly for an aircraft auxiliary power system. Background Art

[0002] The aircraft auxiliary power system is mainly used to start the main engine and supply air to the cabin, and provide auxiliary power for various onboard equipment. Usually when the main engine is not working when the aircraft is on the ground, the main air and power sources come from the aircraft auxiliary power system.

[0003] The aircraft's auxiliary power system needs to inhale air from outside the fuselage through the air inlets on the fuselage. Part of the airflow is used to provide oxygen for combustion of the engine in the auxiliary power system, and another part of the airflow is used to cool the engine in the auxiliary power system. The air inlets of the auxiliary power system are closed when not in use to prevent debris from entering, and are opened during operation to allow gas to enter. However, in cold and humid weather, the gate of the air inlet will be frozen and unable to be opened. Forcing it open will damage components such as the motor, affecting the normal operation of the aircraft. Summary of the invention

[0004] In order to overcome the shortcomings mentioned in the above background technology, the present invention provides an intake valve assembly for an aircraft auxiliary power system.

[0005] The technical solution of the present invention is: an intake valve assembly for an aircraft auxiliary power system, comprising a mounting shell, the mounting shell is provided with a through hole, the mounting shell is fixed with a symmetrically distributed first hinge seat, the symmetrically distributed first hinge seats are jointly rotatably connected with a rotating shaft, the rotating shaft is fixed with a symmetrically distributed second hinge seat, the symmetrically distributed second hinge seat is jointly fixed with a rotating plate, the rotating plate blocks the through hole of the mounting shell, the mounting shell is fixed with a motor on one side close to the first hinge seat through a mounting frame, the mounting shell is rotatably connected with a rotating shell fixed with the output shaft of the motor through the mounting frame, the outer side of the rotating shell is rotatably connected with a rotating ring, the rotating shell is provided with a circumferentially uniformly distributed first slide groove, a first limiting column is slidably connected in the first slide groove, a spring is provided between the first limiting column and the rotating shell, the rotating ring is provided with a circumferentially uniformly distributed limiting groove, the first limiting column is limitedly matched with the adjacent limiting groove on the rotating ring, and the rotating ring and the rotating shaft are matched through a gear ring gear.

[0006] As a preferred technical solution of the present invention, the area of ​​the rotating plate is larger than the cross-sectional area of ​​the air intake pipe of the auxiliary power system, and a sealing gasket is provided between the two.

[0007] As a preferred technical solution of the present invention, the auxiliary power system intake pipe is slidably connected with a sliding ring, a circumferentially evenly distributed spring is arranged between the sliding ring and the auxiliary power system intake pipe, and a circumferentially evenly distributed impact column is fixedly connected to the side of the sliding ring close to the rotating plate, and the impact column is in contact with the rotating plate.

[0008] As a preferred technical solution of the present invention, the side of the mounting shell close to the sliding ring is rotatably connected to the first friction wheel through a mounting frame, the side of the first friction wheel close to the sliding ring is fixedly connected to a rotating disk, the side of the rotating disk close to the sliding ring is slidably connected to a sliding column, the sliding column is extrusion-fitted with the sliding ring, and the rotating disk is provided with symmetrical and evenly distributed elastic protrusions, which are extrusion-limited with the sliding column.

[0009] As a preferred technical solution of the present invention, the rotating shell is provided with a second slide groove, the first slide grooves evenly distributed circumferentially are connected to the second slide grooves, the second slide grooves are spline-connected with the second friction wheel, the first slide groove and the second slide groove are both filled with liquid, and the second friction wheel is frictionally matched with the first friction wheel.

[0010] As a preferred technical solution of the present invention, the facing sides of the second friction wheel and the first friction wheel are both made of elastic friction material, so as to make the second friction wheel fit tightly with the first friction wheel.

[0011] As a preferred technical solution of the present invention, the opposite sides of the symmetrically distributed first hinged seats are slidably connected with second limit columns, a spring is arranged between the second limit column and the adjacent first hinged seat, and the second hinged seat is provided with a limit groove which cooperates with the adjacent second limit column.

[0012] As a preferred technical solution of the present invention, it also includes a torsion plate, the rotating plate is provided with a through hole, the torsion plate is rotatably connected to the through hole of the rotating plate, symmetrically distributed torsion springs are provided between the torsion plate and the rotating plate, the torsion plate is slidably connected with symmetrically distributed wedge-shaped buckles, the rotating plate is provided with symmetrically distributed limiting grooves, and the wedge-shaped buckles are limitedly matched with adjacent limiting grooves on the rotating plate.

[0013] As a preferred technical solution of the present invention, a slope is provided on one side of the wedge-shaped buckle close to the adjacent second hinged seat, and the slope is pressed and matched with the rotating plate.

[0014] As a preferred technical solution of the present invention, the torsion plate is slidably connected with a symmetrically distributed transmission rod, the transmission rod is fixedly connected to the adjacent wedge-shaped buckle, the torsion plate is provided with a symmetrically distributed third slide groove, a sliding plate is slidably connected in the third slide groove, the sliding plate is fixedly connected to the adjacent transmission rod, the torsion plate is provided with a fixed plate, a cavity is formed between the fixed plate and the torsion plate and is filled with liquid, the torsion plate is provided with symmetrically distributed connecting holes, the connecting holes connect the adjacent third slide groove with the cavity between the fixed plate and the torsion plate, the connecting position of the connecting hole and the adjacent third slide groove is located on the side of the adjacent sliding plate close to the adjacent transmission rod, the fixed plate is elastic, and the fixed plate cooperates with the auxiliary power system intake pipe sealing.

[0015] The beneficial effect is that the present invention allows the rotating shell and the rotating ring to be disconnected, thereby preventing the motor output shaft from being unable to rotate and causing overheating damage when the rotating plate cannot be opened, and at the same time preventing the output shaft or the rotating shaft of the rotating plate from being damaged.

[0016] The impact column is made to impact the rotating plate quickly, thereby breaking the frozen ice between the rotating plate and the mounting shell, so that the rotating plate can be opened normally.

[0017] When the transmission between the rotating shell and the rotating ring is lost, the transmission is made between the rotating shell and the first friction wheel, so that the impact column is actuated when the rotating plate cannot be opened, and the impact column is not actuated when the rotating plate is opened normally.

[0018] When the fixed plate is hit, the torsion plate is rotated so that the impact object passes through the through hole of the rotating plate, thereby preventing the impact object from entering the auxiliary power system intake pipe, thereby protecting the auxiliary power system and reducing the risk of damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0020] Figure 2 It is a schematic diagram of the three-dimensional structure of the first hinge seat, the rotating shaft and the second hinge seat of the present invention;

[0021] Figure 3 It is a schematic diagram of the three-dimensional structure of the rotating shell and the rotating ring of the present invention;

[0022] Figure 4 It is a three-dimensional structural cross-sectional view of the first hinge seat and the second hinge seat of the present invention;

[0023] Figure 5 It is a three-dimensional structural cross-sectional view of the rotating shell of the present invention;

[0024] Figure 6It is a three-dimensional structural cross-sectional view of the rotating plate and the torsion plate of the present invention;

[0025] Figure 7 It is an exploded view of the rotating plate, the torsion plate and the fixed plate of the present invention;

[0026] Figure 8 A three-dimensional structural cross-sectional view of the installation housing and the rotating plate of the present invention;

[0027] Fig. 9 for Figure 8 Enlarged view of point A in the middle.

[0028] Parts names and serial numbers in the figure: 1-installation shell, 101-auxiliary power system intake pipe, 2-first hinge seat, 3-rotation shaft, 4-second hinge seat, 5-rotation plate, 6-motor, 7-rotation shell, 701-first slide groove, 702-second slide groove, 8-rotation ring, 9-first limit column, 10-sliding ring, 11-impact column, 12-first friction wheel, 13-rotation disk, 14-sliding column, 15-second friction wheel, 16-second limit column, 17-torsion plate, 1701-third slide groove, 1702-connecting hole, 18-wedge buckle, 19-transmission rod, 20-sliding plate, 21-fixed plate. DETAILED DESCRIPTION

[0029] The following is a detailed description of an intake valve assembly for an aircraft auxiliary power system provided by the present invention in conjunction with the accompanying drawings and specific embodiments. At the same time, it is explained here that in order to make the embodiments more detailed, the following embodiments are the best and preferred embodiments, and those skilled in the art may also adopt other alternatives to implement some known technologies; and the accompanying drawings are only for a more specific description of the embodiments, and are not intended to specifically limit the present invention.

[0030] In cold and humid weather, the gate of the aircraft's auxiliary power system air inlet will be frozen, making it impossible to open. Forcing it open will damage the motor and other components, affecting the normal operation of the aircraft.

[0031] Embodiment 1: An intake valve assembly for an aircraft auxiliary power system, such as Figure 1-Figure 5As shown, it includes a mounting shell 1, which is provided with a rectangular through hole for air flow to pass through, and the lower side of the mounting shell 1 is fixedly connected with two first hinge seats 2 which are symmetrically distributed front and back, and the two first hinge seats 2 are rotatably connected with a rotating shaft 3, and the rotating shaft 3 is fixedly connected with two second hinge seats 4 which are symmetrically distributed front and back, and the upper sides of the two second hinge seats 4 are commonly fixed with a rotating plate 5, and the rotating plate 5 blocks the through hole of the mounting shell 1, thereby preventing debris from entering the auxiliary power system intake pipe 101, and when the auxiliary power system is started, the rotating plate 5 releases the blockage of the through hole of the mounting shell 1, and the area of ​​the rotating plate 5 is larger than the cross-sectional area of ​​the auxiliary power system intake pipe 101, and a sealing gasket is arranged between the two, thereby ensuring the sealing between the rotating plate 5 and the auxiliary power system intake pipe 101, and preventing water and other debris from entering, and the front part of the lower side of the mounting shell 1 is installed through The mounting frame is fixed with the motor 6, and the mounting shell 1 is rotatably connected with the rotating shell 7 fixed with the output shaft of the motor 6 through the mounting frame, and the outer side of the rotating shell 7 is rotatably connected with the rotating ring 8, and the rotating shell 7 is provided with three first sliding grooves 701 evenly distributed in the circumference, and the first limiting column 9 is slidably connected in the first sliding groove 701, and a spring is arranged between the first limiting column 9 and the rotating shell 7, and the spring is initially in a compressed state, and is used to provide the first limiting column 9 with a force to connect the rotating shell 7 and the rotating ring 8, and the rotating ring 8 is provided with three limiting grooves evenly distributed in the circumference, and the first limiting column 9 is limitedly matched with the adjacent limiting grooves on the rotating ring 8, and when the first limiting column 9 is inserted into the adjacent limiting grooves on the rotating ring 8, the relative rotation between the rotating shell 7 and the rotating ring 8 needs to overcome the resistance provided by the springs adjacent to the three first limiting columns 9, and the rotating ring 8 is matched with the rotating shaft 3 through the ring gear.

[0032] like Figure 1-Figure 3 As shown, a rectangular sliding ring 10 is slidably connected to the outer side of the auxiliary power system intake pipe 101, and four mounting seats evenly distributed in the circumferential direction are arranged on the outer side of the auxiliary power system intake pipe 101. A spring is arranged between the four mounting seats and the sliding ring 10, and the spring is used to reset the sliding ring 10. Four circumferentially evenly distributed impact columns 11 are fixedly connected to the upper side of the sliding ring 10, and the impact columns 11 are in contact with the rotating plate 5. When the sliding ring 10 is reset, the impact columns 11 move with it and impact the rotating plate 5, thereby causing the rotating plate 5 to vibrate, and then the frozen ice covering the rotating plate 5 is shattered.

[0033] like Figure 3-Figure 5As shown, the lower side of the mounting shell 1 is rotatably connected to the first friction wheel 12 through the mounting frame, and the rear side of the first friction wheel 12 is fixedly connected to a rotating disk 13, and a vertical sliding groove is arranged on the rear side of the rotating disk 13, in which a sliding column 14 is slidably connected, and the sliding column 14 is squeezed and matched with the sliding ring 10. When the sliding column 14 rotates with the rotating disk 13, the sliding column 14 presses the sliding ring 10 down, and the sliding column 14 is reset as the sliding ring 10 is reset, and four triangular elastic protrusions which are symmetrical up and down and evenly distributed left and right are arranged on the inner side of the sliding groove of the rotating disk 13, and the protrusions are squeezed and limited with the sliding column 14, and when the sliding column 14 contacts with two adjacent elastic protrusions, when the sliding column 14 is subjected to a certain pressure, the two adjacent elastic protrusions are squeezed, thereby releasing the limitation of the two adjacent protrusions on the sliding column 14.

[0034] like Figure 5 As shown, the rotating shell 7 is provided with a second slide groove 702, the three first slide grooves 701 are all connected to the second slide groove 702, the second slide groove 702 is spline-connected with the second friction wheel 15, the first slide groove 701 and the second slide groove 702 are filled with liquid, the liquid mentioned here and below is hydraulic oil for transmission, the second friction wheel 15 and the first friction wheel 12 are friction-matched, when the second friction wheel 15 contacts the first friction wheel 12, the second friction wheel 15 drives the first friction wheel 12 to rotate, the second friction wheel 15 and the first friction wheel 12 facing sides are elastic friction materials, which are used to make the second friction wheel 15 fit closely with the first friction wheel 12 to avoid the second friction wheel 15 from contacting the first friction wheel 12 too early or too late when the first limiting column 9 moves, when the three first limiting columns 9 are completely separated from the adjacent limiting grooves on the rotating ring 8, the second friction wheel 15 contacts the first friction wheel 12 and generates a certain pressure to deform.

[0035] like Figure 4 As shown, the opposite sides of the two first hinge seats 2 are slidably connected with second limit columns 16, and a spring is arranged between the second limit columns 16 and the adjacent first hinge seats 2. The spring is used to insert the adjacent second limit columns 16 into the limit grooves of the adjacent second hinge seats 4, thereby assisting in fixing the rotating plate 5 in the open state. The second hinge seat 4 is provided with a limit groove that cooperates with the adjacent second limit columns 16.

[0036] When using the device, first install the device on the aircraft, connect the mounting shell 1 to the aircraft fuselage shell, connect the auxiliary power system air intake pipe 101 to the auxiliary power system air intake port, and when starting the auxiliary power system, the motor 6 drives the rotating shell 7 to rotate, and the rotating shell 7 drives the rotating ring 8 to rotate through the three first limit columns 9, and the rotating ring 8 drives the rotating shaft 3 to rotate through the ring gear, and the rotating shaft 3 drives the rotating plate 5 to rotate through the two second hinge seats 4, so that the auxiliary power system air intake pipe 101 is connected to the outside.

[0037] When the rotating plate 5 and the mounting shell 1 are stuck due to freezing or other reasons, the rotating ring 8 cannot drive the rotating plate 5 to open. At this time, the rotating shell 7 drives the first limiting column 9 to rotate, and the first limiting column 9 is squeezed by the rotating ring 8 to move toward the direction close to the axis of the rotating shell 7 and compress the adjacent spring. At the same time, the liquid pressure in the second slide groove 702 increases, pushing the second friction wheel 15 to move backward and contact the first friction wheel 12. At this time, the rotating shell 7 drives the first friction wheel 12 to rotate through the second friction wheel 15, and the first friction wheel 12 drives the rotating disk 13 to rotate, and the rotating disk 13 drives the sliding column 14 to rotate. When the sliding column 14 rotates, it squeezes the sliding ring 10 to move downward, and when the sliding ring 10 moves downward, it compresses the four adjacent springs.

[0038] When the sliding column 14 rotates to the point where the elastic force of the four springs adjacent to the sliding ring 10 is greater than the resistance provided by the two elastic protrusions adjacent to the sliding column 14, the sliding ring 10 moves upward under the action of the adjacent springs and pushes the sliding column 14 to move. The sliding column 14 squeezes the adjacent elastic protrusions. When the sliding column 14 passes over the adjacent protrusions, the sliding column 14 and the sliding ring 10 move upward rapidly. The sliding ring 10 drives the impact column 11 to move upward rapidly and hit the rotating plate 5, causing the rotating plate 5 to vibrate, thereby shattering the frozen ice between the rotating plate 5 and the mounting shell 1, so that the rotating plate 5 can be opened. At this time, the sliding column 14 moves to the upper side with the sliding ring 10, and squeezes the other two elastic protrusions again, so that the sliding column 14 is stuck again. Then the sliding column 14 continues to rotate to squeeze the sliding ring 10 downward, and the above actions are repeated until the rotating plate 5 can be opened.

[0039] When the ice between the rotating plate 5 and the mounting shell 1 is broken, the rotating shell 7 drives the first limiting column 9 to rotate until it is aligned with the adjacent limiting groove on the rotating ring 8. The first limiting column 9 is reset under the action of the adjacent spring, so that the rotating shell 7 drives the rotating ring 8 to rotate through the first limiting column 9. The rotating ring 8 drives the rotating plate 5 to open. When the first limiting column 9 is reset, the second friction wheel 15 is reset synchronously. When the rotating plate 5 is opened, it drives the two second hinge seats 4 to rotate. When the limiting groove of the second hinge seat 4 is aligned with the adjacent second limiting column 16, the second limiting column 16 is inserted into the limiting groove of the adjacent second hinge seat 4 under the action of the adjacent spring, thereby assisting the fixing of the rotating plate 5. At the same time, the motor 6 is turned off. When the auxiliary power system is turned off, the starting motor 6 is reversed and drives the rotating plate 5 to close. When the rotating plate 5 is closed, it drives the two second hinge seats 4 to rotate. The second hinge seat 4 presses the adjacent second limiting column 16 back into the adjacent first hinge seat 2, and the second limiting column 16 compresses the adjacent spring.

[0040] Embodiment 2: Based on embodiment 1, Figure 1 and Figure 6-Figure 9As shown, a torsion plate 17 is also included. The rotating plate 5 is provided with a through hole, which is used to allow the impactor to pass through. The torsion plate 17 is rotatably connected to the through hole of the rotating plate 5. Two groups of symmetrically distributed torsion springs are provided between the torsion plate 17 and the rotating plate 5. Each group of torsion springs includes two symmetrically distributed torsion springs. The torsion springs are used to reset the torsion plate 17. The torsion plate 17 is slidably connected with two wedge-shaped buckles 18 symmetrically distributed front and back. The wedge-shaped buckles 18 are provided with downward inclined surfaces, which are pressed and matched with the rotating plate 5. When the rotating plate 5 presses the inclined surfaces on the wedge-shaped buckles 18, the wedge-shaped buckles 18 move to the left. The rotating plate 5 is provided with limiting grooves symmetrically distributed front and back. The wedge-shaped buckles 18 are limitedly matched with adjacent limiting grooves on the rotating plate 5. When the wedge-shaped buckles 18 are inserted into the adjacent limiting grooves on the rotating plate 5, the torsion plate 17 blocks the through hole of the rotating plate 5.

[0041] like Figure 7 and Fig. 9 As shown, the torsion plate 17 is slidably connected to two transmission rods 19 symmetrically distributed front and back, and the transmission rod 19 is fixedly connected to the left side of the adjacent wedge-shaped buckle 18. The torsion plate 17 is provided with two third sliding grooves 1701 symmetrically distributed front and back, and a sliding plate 20 is slidably connected in the third sliding groove 1701, and the sliding plate 20 is fixedly connected to the adjacent transmission rod 19. A fixed plate 21 is provided on the lower side of the torsion plate 17, and a cavity is formed between the fixed plate 21 and the torsion plate 17 and is filled with liquid. The liquid is used to transmit between the fixed plate 21 and the two wedge-shaped buckles 18. The torsion plate 17 is provided with two L-shaped connecting holes 1702 symmetrically distributed front and back. The connecting hole 1702 connects the adjacent third slide groove 1701 with the cavity between the fixed plate 21 and the torsion plate 17. The connecting position between the connecting hole 1702 and the adjacent third slide groove 1701 is located on the right side of the adjacent sliding plate 20, so that when the liquid enters the third slide groove 1701, it squeezes the adjacent sliding plate 20 to move to the left. The fixed plate 21 is elastic. When the fixed plate 21 is impacted, it deforms, thereby squeezing the liquid between it and the torsion plate 17. The fixed plate 21 is sealed with the auxiliary power system intake pipe 101. When the rotating plate 5 is closed, the fixed plate 21 contacts the auxiliary power system intake pipe 101 to form a seal.

[0042] When the auxiliary power system is started during aircraft flight, the gate of the auxiliary power system air inlet is in an open state. At this time, if an oncoming bird hits the gate, it may cause damage to the gate or even cause the bird to fall into the auxiliary power system air inlet, affecting the normal operation of the auxiliary power system.

[0043] When the rotating plate 5 is in the open state and is hit by a flying bird or the like (the device moves from right to left, and the flying bird moves from left to right), the flying bird hits the fixed plate 21, and the fixed plate 21 is deformed, squeezing the liquid between the fixed plate 21 and the torsion plate 17, and the liquid between the two is pressed into the third slide groove 1701, so that the sliding plate 20 moves, and the sliding plate 20 drives the adjacent transmission rod 19 to move, and the transmission rod 19 drives the adjacent wedge buckle 18 to move, and the wedge buckle 18 is separated from the limiting groove on the rotating plate 5. At this time, the torsion plate 17 is opened under the action of the flying bird's impact and the adjacent torsion spring is charged, so that the flying bird passes through the opened part of the torsion plate 17 and the rotating plate 5, preventing the flying bird from entering. The auxiliary power system intake pipe 101 causes damage to the auxiliary power system. When the bird passes through, the torsion plate 17 is reset under the action of the adjacent torsion spring, the fixed plate 21 returns to its original state and drives the wedge buckle 18 to reset. The torsion plate 17 drives the two wedge buckles 18 to rotate. The inclined surface of the wedge buckle 18 is squeezed by the rotating plate 5, and the wedge buckle 18 moves toward the direction close to the sliding plate 20. When the wedge buckle 18 moves, the sliding plate 20 draws the liquid between the torsion plate 17 and the fixed plate 21 into the adjacent third slide groove 1701, and the fixed plate 21 is deformed. When the torsion plate 17 is reset, the fixed plate 21 returns to its original state and drives the wedge buckle 18 to insert into the adjacent limit groove on the rotating plate 5.

[0044] The above is a detailed introduction to the present application. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. At the same time, for general technical personnel in this field, according to the idea of ​​the present application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. An intake valve assembly for an aircraft auxiliary power system, comprising a mounting shell (1), the mounting shell (1) being provided with a through hole, the mounting shell (1) being fixedly connected to symmetrically distributed first hinge seats (2), the symmetrically distributed first hinge seats (2) being rotatably connected together with a rotating shaft (3), the rotating shaft (3) being fixedly connected to symmetrically distributed second hinge seats (4), the symmetrically distributed second hinge seats (4) being fixedly connected together with a rotating plate (5), the rotating plate (5) blocking the through hole of the mounting shell (1), a motor (6) being fixedly connected to a side of the mounting shell (1) close to the first hinge seat (2) via a mounting frame, characterized in that: The invention also comprises a rotating shell (7) fixedly connected to the output shaft of the motor (6), the rotating shell (7) being rotatably connected to the mounting housing (1) via a mounting frame, a rotating ring (8) being rotatably connected to the outer side of the rotating shell (7), the rotating shell (7) being provided with a first sliding groove (701) evenly distributed in the circumferential direction, a first limiting column (9) being slidably connected in the first sliding groove (701), a spring being provided between the first limiting column (9) and the rotating shell (7), the rotating ring (8) being provided with a limiting groove evenly distributed in the circumferential direction, the first limiting column (9) being limitedly matched with the adjacent limiting groove on the rotating ring (8), and the rotating ring (8) being matched with the rotating shaft (3) via a gear ring gear.

2. The air intake valve assembly for an aircraft auxiliary power system according to claim 1, characterized in that: The area of ​​the rotating plate (5) is larger than the cross-sectional area of ​​the auxiliary power system air intake pipe (101), and a sealing gasket is provided between the two.

3. The air intake valve assembly for an aircraft auxiliary power system according to claim 1, characterized in that: The auxiliary power system air intake pipe (101) is slidably connected to a sliding ring (10), a circumferentially uniformly distributed spring is arranged between the sliding ring (10) and the auxiliary power system air intake pipe (101), a circumferentially uniformly distributed impact column (11) is fixedly connected to a side of the sliding ring (10) close to the rotating plate (5), and the impact column (11) is in contact with the rotating plate (5).

4. The air intake valve assembly for an aircraft auxiliary power system according to claim 3, characterized in that: A first friction wheel (12) is rotatably connected to a side of the mounting shell (1) close to the sliding ring (10) via a mounting frame; a rotating disk (13) is fixedly connected to a side of the first friction wheel (12) close to the sliding ring (10); a sliding column (14) is slidably connected to a side of the rotating disk (13) close to the sliding ring (10); the sliding column (14) is extrusion-fitted with the sliding ring (10); and the rotating disk (13) is provided with symmetrical and evenly distributed elastic protrusions, which are extrusion-limitedly fitted with the sliding column (14).

5. The air intake valve assembly for an aircraft auxiliary power system according to claim 4, characterized in that: The rotating shell (7) is provided with a second slide groove (702), the first slide grooves (701) uniformly distributed in the circumferential direction are all connected to the second slide groove (702), the second slide groove (702) is spline-connected with a second friction wheel (15), the first slide groove (701) and the second slide groove (702) are both filled with liquid, and the second friction wheel (15) is frictionally matched with the first friction wheel (12).

6. The air intake valve assembly for an aircraft auxiliary power system according to claim 5, characterized in that: The facing sides of the second friction wheel (15) and the first friction wheel (12) are both made of elastic friction material, so as to enable the second friction wheel (15) to fit tightly with the first friction wheel (12).

7. The air intake valve assembly for an aircraft auxiliary power system according to claim 1, characterized in that: The opposite sides of the symmetrically distributed first hinge seats (2) are slidably connected with second limiting columns (16), a spring is provided between the second limiting columns (16) and the adjacent first hinge seats (2), and the second hinge seat (4) is provided with a limiting groove that cooperates with the adjacent second limiting columns (16).

8. The air intake valve assembly for an aircraft auxiliary power system according to claim 3, characterized in that: The invention also comprises a torsion plate (17), the rotating plate (5) being provided with a through hole, the torsion plate (17) being rotatably connected to the through hole of the rotating plate (5), symmetrically distributed torsion springs being provided between the torsion plate (17) and the rotating plate (5), the torsion plate (17) being slidably connected to symmetrically distributed wedge-shaped buckles (18), the rotating plate (5) being provided with symmetrically distributed limiting grooves, the wedge-shaped buckles (18) being limitedly matched with adjacent limiting grooves on the rotating plate (5).

9. The air intake valve assembly for an aircraft auxiliary power system according to claim 8, characterized in that: A sloped surface is provided on one side of the wedge-shaped buckle (18) adjacent to the second hinged seat (4), and the sloped surface is pressed and matched with the rotating plate (5).

10. The air intake valve assembly for an aircraft auxiliary power system according to claim 8, characterized in that: The torsion plate (17) is slidably connected to symmetrically distributed transmission rods (19), the transmission rods (19) are fixedly connected to the adjacent wedge-shaped buckles (18), the torsion plate (17) is provided with symmetrically distributed third slide grooves (1701), a sliding plate (20) is slidably connected in the third slide grooves (1701), the sliding plate (20) is fixedly connected to the adjacent transmission rods (19), the torsion plate (17) is provided with a fixing plate (21), a cavity is formed between the fixing plate (21) and the torsion plate (17) and is filled with liquid, The torsion plate (17) is provided with symmetrically distributed connecting holes (1702), the connecting holes (1702) connecting the adjacent third slide groove (1701) with the cavity between the fixed plate (21) and the torsion plate (17), the connecting position of the connecting hole (1702) and the adjacent third slide groove (1701) is located on a side of the adjacent sliding plate (20) close to the adjacent transmission rod (19), the fixed plate (21) is elastic, and the fixed plate (21) is in sealing cooperation with the auxiliary power system intake pipe (101).

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