Auxiliary simulation device for aviation aircraft

Abstract

The invention relates to the technical field of simulation training, in particular to an auxiliary simulation device for an aviation aircraft, which comprises a linear moving assembly, an auxiliary rotating assembly, a main rotating assembly and an energy recovery assembly, and is characterized in that the linear moving assembly comprises a supporting pipe, a sleeve, a first limiting sliding block, a movable seat and a supporting frame; the two ends of the supporting pipe are installed on the ground through supporting frames correspondingly, a limiting groove is formed in the supporting pipe, the inner wall of the limiting groove is slidably connected with a first limiting sliding block, the first limiting sliding block is fixedly connected with the inner wall of a sleeve, the sleeve is slidably connected with the supporting pipe, and the outer wall of the sleeve is rotationally connected with a movable seat; the movable seat can rotate on the sleeve, so that the second rotating shaft, the rotating frame, the cabin, the first rotating shaft and the sliding block are driven to rotate with the supporting pipe as the axis, and the rotating motion of a pilot under a certain turning radius is simulated. And rotation among the movable seat, the cabin and the rotating frame does not influence one another, and direction adjustment is more flexible.

Description

Technical Field

[0001] The invention relates to the technical field of simulation training, in particular to an auxiliary simulation device for aviation aircraft. Background Art

[0002] With the rapid development of aerospace industry, the replacement of aircraft vehicles is accelerating. The auxiliary simulation device for aerospace vehicles is a typical simulation system. It is a flight motion simulation equipment based on flight kinematics. It integrates virtual reality technology, 3D real-time rendering technology, computer graphics technology, computer interface technology, multimedia and other advanced technologies.

[0003] The existing auxiliary simulation devices for aerospace vehicles have been widely used. They have the advantages of simple operation, safety and comfort, and are capable of simulating the actual flight status of aircraft on the ground. They are not restricted by any site, environment, weather, air traffic control and many other factors, making training efficient and convenient. When pilots use auxiliary simulation devices for flight training, they can repeatedly practice difficult items according to their own conditions to improve training efficiency. The use of auxiliary simulation devices can avoid safety hazards caused by pilot operational errors and ensure the safety of personnel and equipment.

[0004] At present, a Chinese invention with application number 201410814354.X discloses a flight simulation training device, including a vertically arranged main shaft and a cantilever beam arranged on the main shaft through a bearing sleeve, and a training cabin is provided at one end of the cantilever beam. Although the body posture of the pilot or astronaut can be adjusted to be consistent with the direction of the force on which they bear the overload, thereby improving the real sense of simulated flight, the direction adjustment is not flexible enough, and it is difficult to recover the energy after acceleration, the energy consumption is high, and it is not environmentally friendly. Summary of the invention

[0005] The technical problem to be solved by the present invention is that the direction adjustment of the auxiliary simulation device in the related art is not flexible enough, and it is difficult to recover the energy after acceleration, the energy consumption is high, and it is not environmentally friendly.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions: an auxiliary simulation device for an aviation aircraft, comprising a linear motion component, a secondary rotation component, a main rotation component and an energy recovery component, wherein the linear motion component comprises a support tube, a sleeve, a first limit slider, a movable seat and a support frame, wherein both ends of the support tube are respectively installed on the ground through the support frame, a limit groove is provided on the support tube, the inner wall of the limit groove is slidably connected to the first limit slider, the first limit slider is fixedly connected to the inner wall of the sleeve, the sleeve is slidably connected to the support tube, and the outer wall of the sleeve is rotatably connected to the movable seat; the secondary rotation component comprises a cabin, a first rotating shaft and a slider, and the two ends of the cabin are respectively The auxiliary rotating assembly is fixedly connected to the first rotating shaft, and the first rotating shaft is rotatably connected to the slider; the main rotating assembly includes a second rotating shaft and a rotating frame, the inner wall of the rotating frame is slidably connected to the slider, the rotating frame is fixedly connected to one end of the second rotating shaft, and the other end of the second rotating shaft is rotatably connected to the movable seat, the main rotating assembly and the auxiliary rotating assembly are respectively provided with two groups, which are respectively located on both sides of the movable seat; the energy recovery assembly includes a second cylinder, a second piston head, a second push rod and a second limiting slider, the inner wall of the second cylinder is slidably connected to the second piston head, the second piston head is fixedly connected to one end of the second push rod, the other end of the second push rod is fixedly connected to the second limiting slider, and the second limiting slider is slidably connected to the limiting groove.

[0007] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, the outer wall of the sleeve is fixedly connected to the first gear, the first gear is meshedly connected to the second gear, the second gear is fixedly connected to the first motor, and the first motor is fixedly connected to the movable seat.

[0008] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, wherein: the first rotating shaft is fixedly connected to the third gear, the third gear is meshedly connected to the fourth gear, the fourth gear is fixedly connected to the second motor, and the second motor is fixedly connected to the slider.

[0009] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, the slider is threadedly connected to a screw rod, one end of the screw rod is rotatably connected to a rotating frame, the other end of the screw rod is fixedly connected to a third motor, and the third motor is fixedly connected to the rotating frame.

[0010] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, the second rotating shaft is fixedly connected to the fifth gear, the fifth gear is meshedly connected to the sixth gear, the sixth gear is fixedly connected to the fourth motor, and the fourth motor is fixedly connected to the movable seat.

[0011] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, it also includes a driving assembly, which includes a first cylinder, a first piston head and a first push rod. The inner wall of the first cylinder is slidably connected to the first piston head, one end of the first piston head is fixedly connected to the first push rod, and the other end of the first push rod faces the support tube.

[0012] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, the energy recovery component also includes a first fixed ring, a first movable rod, a first spring, a first fixed disk, a first triangular block and an air duct, the first fixed ring is fixedly connected to the second cylinder, and the inner wall of the first fixed ring is slidably connected to the first movable rod, one end of the first movable rod is fixedly connected to the first triangular block, and the other end of the first movable rod is fixedly connected to the first fixed disk, the first movable rod is sleeved with a first spring, one end of the first spring is fixedly connected to the first fixed ring, and the other end of the first spring is fixedly connected to the first fixed disk, and the second cylinder is connected to the first cylinder through the air duct.

[0013] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, wherein: a limiting member is arranged on the first cylinder, and the limiting member includes a second fixed ring, a second movable rod, a second spring, a second fixed plate and a second triangular block, the second fixed ring is fixedly connected to the first cylinder, the inner wall of the second fixed ring is slidably connected to the second movable rod, one end of the second movable rod is fixedly connected to the second fixed plate, and the other end of the second movable rod is fixedly connected to the second triangular block, the second movable rod is sleeved with a second spring, one end of the second spring is fixedly connected to the second fixed ring, and the other end of the second spring is fixedly connected to the second fixed plate.

[0014] As a preferred solution of the auxiliary simulation device for aviation aircraft described in the present invention, wherein: the outer wall of the support tube is fixedly connected to the fixed block, the fixed block is fixedly connected to the first telescopic rod, one end of the first telescopic rod is fixedly connected to the third triangular block, the third triangular block is located above the limiting groove, the other end of the first telescopic rod is fixedly connected to the second telescopic rod through a connecting tube, the bottom end of the second telescopic rod is fixedly connected to the outer wall of the second cylinder, and the second telescopic rod is against the lower surface of the first fixed plate.

[0015] As a preferred solution of the auxiliary simulation device for aviation aircraft of the present invention, the outer wall of the first cylinder is fixedly connected to one end of the electric push rod, and the other end of the electric push rod is against the lower surface of the second fixed plate.

[0016] Beneficial effects of the present invention: The movable seat in the present invention can rotate on the sleeve, thereby driving the second rotating shaft, the rotating frame, the cockpit, the first rotating shaft and the slider to rotate with the support tube as the axis, simulating the rotation movement of the pilot at a certain turning radius. Moreover, the rotation of the movable seat, the cockpit and the rotating frame does not affect each other, and the direction adjustment is more flexible.

[0017] When the movable seat and the sleeve drive the first limit slider to hit the second limit slider, the first limit slider pushes the second limit slider to move, and the second limit slider pushes the second piston head to slide in the second cylinder through the second push rod, compressing the gas inside the second cylinder on the right side of the second piston head in the figure. Under the action of the gas, the sleeve and the movable seat are decelerated. At the same time, the gas inside the second cylinder can be compressed to store energy and recover the energy after acceleration, which is more environmentally friendly. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the embodiment of the present disclosure.

[0019] Figure 2 It is a schematic diagram of the structure of the movable seat in the embodiment of the present disclosure.

[0020] Figure 3 It is a schematic diagram of the slider structure in the embodiment of the present disclosure.

[0021] Figure 4 It is a schematic diagram of the rotating frame structure in the embodiment of the present disclosure.

[0022] Figure 5 It is a cross-sectional view of the first cylinder in the embodiment of the present disclosure.

[0023] Figure 6 It is a cross-sectional view of the second cylinder in the embodiment of the present disclosure.

[0024] Figure 7 In the embodiment of the present disclosure Figure 1 Enlarged schematic diagram at point A in the middle.

[0025] Figure 8 It is a cross-sectional view of the first fixing ring in the embodiment of the present disclosure.

[0026] Reference numerals: linear moving assembly 1, supporting tube 11, limiting groove 111, fixing block 112, first telescopic rod 113, third triangular block 114, connecting tube 115, second telescopic rod 116, sleeve 12, first gear 121, second gear 122, first motor 123, first limiting slider 13, movable seat 14, supporting frame 15, auxiliary rotating assembly 2, cockpit 21, first rotating shaft 22, third gear 221, fourth gear 222, second motor 223, slider 23, screw rod 231 ，The third motor 232, the main rotating assembly 3, the second rotating shaft 31, the fifth gear 311, the sixth gear 312, the fourth motor 313, the rotating frame 32, the driving assembly 4, the first cylinder 41, the first piston head 42, the first push rod 43, the limiter 44, the second fixing ring 441, the second movable rod 442, the second spring 443, the second fixing plate 444, the second triangular block 445, the electric push rod 45, the energy recovery assembly 5, the second cylinder 51, the second piston head 52, the second push rod 53, the second limiter slider 54, the first fixing ring 55, the first movable rod 56, the first spring 57, the first fixing plate 58, the first triangular block 59, and the air guide pipe 510. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0028] Example 1, reference Figure 1-Figure 4 and Figure 6 This embodiment provides an auxiliary simulation device for an aviation aircraft, including a linear motion component 1, a secondary rotation component 2, a main rotation component 3 and an energy recovery component 5. The linear motion component 1 includes a support tube 11, a sleeve 12, a first limit slider 13, a movable seat 14 and a support frame 15. Both ends of the support tube 11 are respectively installed on the ground through the support frame 15. A limit groove 111 is provided on the support tube 11. The inner wall of the limit groove 111 is slidably connected to the first limit slider 13. The first limit slider 13 is fixedly connected to the inner wall of the sleeve 12. The sleeve 12 is slidably connected to the support tube 11. The outer wall of the sleeve 12 is rotatably connected to the movable seat 14.

[0029] In this embodiment, preferably, both ends of the support tube 11 are respectively installed on the ground through the support frame 15, which can fix the support tube 11, and the sleeve 12 can slide on the support tube 11. The sleeve 12 can drive the first limit slider 13 to slide on the inner wall of the limit groove 111, which can prevent the sleeve 12 and the support tube 11 from rotating relative to each other, and the movable seat 14 can rotate on the sleeve 12. In one embodiment, a rocket engine is mounted on the sleeve 12 to push the sleeve 12 to slide on the support tube 11, and the sleeve 12 is accelerated to simulate the gravity acceleration during the flight acceleration process.

[0030] The auxiliary rotating assembly 2 includes a cabin 21, a first rotating shaft 22 and a slider 23. Both ends of the cabin 21 are fixedly connected to the first rotating shaft 22, and the first rotating shaft 22 is rotatably connected to the slider 23.

[0031] In this embodiment, preferably, a movable door is provided on the cockpit 21. After opening the movable door, the pilot can enter the cockpit 21. An existing seat is fixedly installed inside the cockpit 21, and the pilot can be fixed on the seat. When the first rotating shaft 22 rotates, it can drive the cockpit 21 to rotate, simulating the rotation of the pilot with himself as the axis.

[0032] The main rotating assembly 3 includes a second rotating shaft 31 and a rotating frame 32. The inner wall of the rotating frame 32 is slidably connected to the slider 23. The rotating frame 42 is fixedly connected to one end of the second rotating shaft 31. The other end of the second rotating shaft 31 is rotatably connected to the movable seat 14. The main rotating assembly 3 and the auxiliary rotating assembly 2 are respectively provided with two groups, which are respectively located on both sides of the movable seat 14.

[0033] Preferably in this embodiment, the slider 23 can slide on the inner wall of the rotating frame 32 to adjust the positions of the slider 23, the first rotating shaft 22 and the cabin 21. The rotating frame 32 can rotate around the second rotating shaft 31 to simulate the flipping movement during flight.

[0034] Furthermore, the movable seat 14 can rotate on the sleeve 12, thereby driving the second rotating shaft 31, the rotating frame 32, the cockpit 21, the first rotating shaft 22 and the slider 23 to rotate with the support tube 11 as the axis, simulating the rotational movement of the pilot at a certain turning radius. Moreover, the rotation of the movable seat 14, the cockpit 21 and the rotating frame 32 does not affect each other, and the direction adjustment is more flexible.

[0035] The energy recovery component 5 includes a second cylinder 51, a second piston head 52, a second push rod 53 and a second limit slider 54. The inner wall of the second cylinder 51 is slidably connected to the second piston head 52, the second piston head 52 is fixedly connected to one end of the second push rod 53, the other end of the second push rod 53 is fixedly connected to the second limit slider 54, and the second limit slider 54 is slidably connected to the limit groove 111.

[0036] In this embodiment, preferably, when the movable seat 14 and the sleeve 12 drive the first limiting slider 13 to hit the second limiting slider 54, the first limiting slider 13 pushes the second limiting slider 54 to move, and the second limiting slider 54 pushes the second piston head 52 to slide in the second cylinder 51 through the second push rod 53, compressing Figure 6 The gas inside the second cylinder 51 on the right side of the second piston head 52 decelerates the sleeve 12 and the movable seat 14 under the action of the gas. At the same time, the gas inside the second cylinder 51 can be compressed to store energy and recover the energy after acceleration, which is more environmentally friendly.

[0037] Example 2, reference Figure 1-Figure 8 This embodiment is based on the previous embodiment, and differs from the previous embodiment in that.

[0038] Reference Figure 2The outer wall of the sleeve 12 is fixedly connected to the first gear 121 , the first gear 121 is meshedly connected to the second gear 122 , the second gear 122 is fixedly connected to the first motor 123 , and the first motor 123 is fixedly connected to the movable seat 14 .

[0039] In this embodiment, preferably, the first motor 123 can drive the second gear 122 to rotate when working, and the second gear 122 can drive the first gear 121 to rotate when rotating, and the first gear 121 drives the sleeve 12 to rotate, and the sleeve 12 drives the movable seat 14 to rotate, thereby driving the second rotating shaft 31, the rotating frame 32, the cockpit 21, the first rotating shaft 22 and the slider 23 to rotate with the support tube 11 as the axis, simulating the rotation movement of the pilot at a certain turning radius. Moreover, the rotation of the movable seat 14, the cockpit 21 and the rotating frame 32 does not affect each other, and the direction adjustment is more flexible.

[0040] Reference Figure 3 The first rotating shaft 22 is fixedly connected to the third gear 221 , the third gear 221 is meshedly connected to the fourth gear 222 , the fourth gear 222 is fixedly connected to the second motor 223 , and the second motor 223 is fixedly connected to the slider 23 .

[0041] Preferably in this embodiment, when the second motor 223 is working, it can drive the fourth gear 222 to rotate, the fourth gear 222 drives the third gear 221 to rotate, the third gear 221 drives the first rotating shaft 22 to rotate, and the first rotating shaft 22 drives the cockpit 21 to rotate, simulating the rotation of the pilot with himself as the axis.

[0042] Reference Figure 4 The slider 23 is threadedly connected to the screw rod 231 , one end of the screw rod 231 is rotatably connected to the rotating frame 32 , and the other end of the screw rod 231 is fixedly connected to the third motor 232 , and the third motor 232 is fixedly connected to the rotating frame 32 .

[0043] Preferably, in this embodiment, when the third motor 232 is working, it drives the screw rod 231 to rotate, and the screw rod 231 drives the slider 23 to move under the action of the thread, and the slider 23 drives the cockpit 21 to move closer to or away from the movable seat 14 through the first rotating shaft 22, simulating the rotational movement of the pilot at different turning radii.

[0044] Reference Figure 4 The second rotating shaft 31 is fixedly connected to the fifth gear 311 , the fifth gear 311 is meshedly connected to the sixth gear 312 , the sixth gear 312 is fixedly connected to the fourth motor 313 , and the fourth motor 313 is fixedly connected to the movable seat 14 .

[0045] Preferably, in this embodiment, when the fourth motor 313 is working, it can drive the sixth gear 312 to rotate, the sixth gear 312 drives the fifth gear 311 to rotate, the fifth gear 311 drives the second rotating shaft 31 to rotate, and the second rotating shaft 31 drives the rotating frame 32 to rotate, which can simulate the flipping movement during flight.

[0046] Reference Figure 5 , and also includes a driving component 4, which includes a first cylinder 41, a first piston head 42 and a first push rod 43. The inner wall of the first cylinder 41 is slidingly connected to the first piston head 42, one end of the first piston head 42 is fixedly connected to the first push rod 43, and the other end of the first push rod 43 faces the support tube 11.

[0047] In this embodiment, preferably, the gas inside the first cylinder 41 can push the first piston head 42 to Figure 5 The first piston head 42 moves to the right side, the first push rod 43 moves, the first push rod 43 pushes the first limit slider 13 to slide on the inner wall of the limit groove 111, and the limit slider 13 drives the sleeve 12 and the movable seat 14 to move, giving the sleeve 12 and the movable seat 14 an initial velocity, thereby reducing the energy consumption of the sleeve 11 and the movable seat 42 when accelerating from 0.

[0048] Reference Figure 6 and Figure 8 The energy recovery assembly 5 further includes a first fixed ring 55, a first movable rod 56, a first spring 57, a first fixed disk 58, a first triangular block 59 and an air duct 510. The first fixed ring 55 is fixedly connected to the second cylinder 51, and the inner wall of the first fixed ring 55 is slidably connected to the first movable rod 56. One end of the first movable rod 56 is fixedly connected to the first triangular block 59, and the other end of the first movable rod 56 is fixedly connected to the first fixed disk 58. The first movable rod 56 is sleeved with a first spring 57, one end of the first spring 57 is fixedly connected to the first fixed ring 55, and the other end of the first spring 57 is fixedly connected to the first fixed disk 58. The second cylinder 51 is connected to the first cylinder 41 through the air duct 510. A sealing ring is arranged on the inner wall of the first fixed ring 55, which is conducive to improving the sealing between the first fixed ring 55 and the first movable rod 56.

[0049] In this embodiment, preferably, under the action of the pulling force of the first spring 57, the first triangular block 59 is located Figure 6 The second piston head 52 can be stuck in the middle position. Figure 6 The position of the second piston head 52 is locked on the left side of the first triangular block 59. When the first fixed plate 58 moves upward, the first fixed plate 58 pulls the first movable rod 56 and the first triangular block 59 to move upward. At this time, the position of the second piston head 52 is unlocked. When the first limiting slider 13 pushes the second limiting slider 54 to move, the second limiting slider 54 pushes the second piston head 52 to slide in the second cylinder 51 through the second push rod 53, compressing Figure 6 The gas inside the second cylinder 51 on the right side of the second piston head 52 decelerates the sleeve 12 and the movable seat 14 under the action of the gas. At the same time, the gas inside the second cylinder 51 can be compressed to store energy and recover the energy after acceleration, which is more environmentally friendly.

[0050] Reference Figure 5 A limiting member 44 is provided on the first cylinder 41, and the limiting member 44 includes a second fixed ring 441, a second movable rod 442, a second spring 443, a second fixed disk 444 and a second triangular block 445. The second fixed ring 441 is fixedly connected to the first cylinder 41, and the inner wall of the second fixed ring 441 is slidably connected to the second movable rod 442, one end of the second movable rod 442 is fixedly connected to the second fixed disk 444, and the other end of the second movable rod 442 is fixedly connected to the second triangular block 445. A second spring 443 is sleeved on the second movable rod 442, one end of the second spring 443 is fixedly connected to the second fixed ring 441, and the other end of the second spring 443 is fixedly connected to the second fixed disk 444.

[0051] In this embodiment, preferably, under the action of the pulling force of the second spring 443, the second triangular block 445 is located Figure 5 The first piston head 42 can be stuck in the middle position. Figure 5 The left side of the first piston head 42 is locked. When the second fixed plate 444 moves upward, the second movable rod 442 and the second triangular block 445 are pulled upward. At this time, the position of the first piston head 42 is unlocked, and the gas inside the first cylinder 41 can push the first piston head 42 to Figure 5 The first piston head 42 moves to the right side, the first push rod 43 moves, the first push rod 43 pushes the first limit slider 13 to slide on the inner wall of the limit groove 111, and the limit slider 13 drives the sleeve 12 and the movable seat 14 to move, giving the sleeve 12 and the movable seat 14 an initial velocity, thereby reducing the energy consumption of the sleeve 11 and the movable seat 42 when accelerating from 0.

[0052] Reference Figure 7 The outer wall of the support tube 11 is fixedly connected to the fixed block 112, the fixed block 112 is fixedly connected to the first telescopic rod 113, one end of the first telescopic rod 113 is fixedly connected to the third triangular block 114, the third triangular block 114 is located above the limiting groove 111, the other end of the first telescopic rod 113 is fixedly connected to the second telescopic rod 116 through the connecting tube 115, the bottom end of the second telescopic rod 116 is fixedly connected to the outer wall of the second cylinder 51, and the second telescopic rod 116 is against the lower surface of the first fixed plate 58.

[0053] In this embodiment, preferably, the position of the first telescopic rod 113 can be fixed by the fixing block 112, and the radial dimension of the first telescopic rod 113 is greater than that of the second telescopic rod 116, that is, when the first telescopic rod 113 is compressed a short distance, after the connecting tube 115 acts on the second telescopic rod 116, the second telescopic rod 116 will extend a long distance. In one embodiment, the first telescopic rod 113, the connecting tube 115, and the second telescopic rod 116 are filled with hydraulic oil. Due to the incompressibility of the hydraulic oil, when the first telescopic rod 113 is compressed a short distance, after the connecting tube 115 acts on the second telescopic rod 116, the second telescopic rod 116 will extend a long distance. The extension of the second telescopic rod 116 pushes the first fixed plate 58 to move upward. Installation of the third triangular block 114 Figure 7 In the shape setting, when the first limiting slider 13 passes through the third triangular block 114, the first limiting slider 13 pushes the third triangular block 114 to compress the first telescopic rod 113.

[0054] Reference Figure 8 The outer wall of the first cylinder 41 is fixedly connected to one end of the electric push rod 45 , and the other end of the electric push rod 45 is against the lower surface of the second fixed plate 444 .

[0055] Preferably, in this embodiment, when the electric push rod 45 is controlled to extend, the electric push rod 45 pushes the second fixed plate 444 to move upward, and the second fixed plate 444 pulls the second movable rod 442 and the second triangular block 445 to move upward, and the position of the first piston head 42 is unlocked.

[0056] Working principle: When in use, an air pump is arranged in the middle of the air guide pipe 510 to pump a small amount of gas inside the second cylinder 51 into the first cylinder 41, and at this time, the first piston head 42 is stuck by the second triangular block 445. Figure 5 The second piston head 52 is stuck by the first triangular block 59 on the left side. Figure 6 The left side of the second piston head 52 is negative pressure, and there is a large air pressure inside the first cylinder 41 on the left side of the first piston head 42. When the electric push rod 45 is controlled to extend, the electric push rod 45 pushes the second fixed plate 444 to move upward, and the second fixed plate 444 pulls the second movable rod 442 and the second triangular block 445 to move upward. At this time, the position of the first piston head 42 is unlocked, and the gas inside the first cylinder 41 can push the first piston head 42 to Figure 5 The first piston head 42 moves to the right side, the first push rod 43 moves, the first push rod 43 pushes the first limit slider 13 to slide on the inner wall of the limit groove 111, and the limit slider 13 drives the sleeve 12 and the movable seat 14 to move, giving the sleeve 12 and the movable seat 14 an initial velocity, thereby reducing the energy consumption of the sleeve 11 and the movable seat 42 when accelerating from 0.

[0057] By adding a rocket engine to the sleeve 12, the sleeve 12 is pushed to slide on the support tube 11. The sleeve 12 is accelerated and the acceleration of gravity during the flight acceleration process is simulated. When the sleeve 12 slides on the support tube 11: the first motor 123 can drive the second gear 122 to rotate when it works, and the second gear 122 can drive the first gear 121 to rotate when it rotates. The first gear 121 drives the sleeve 12 to rotate, and the sleeve 12 drives the movable seat 14 to rotate, thereby driving the second rotating shaft 31, the rotating frame 32, the cockpit 21, the first rotating shaft 22 and the slider 23 to rotate with the support tube 11 as the axis, simulating the rotational movement of the pilot at a certain turning radius. Moreover, the rotations among the movable seat 14, the cockpit 21 and the rotating frame 32 do not affect each other, and the direction adjustment is more flexible; when the second motor 223 is working, it drives the fourth gear 222 to rotate, the fourth gear 222 drives the third gear 221 to rotate, the third gear 221 drives the first rotating shaft 22 to rotate, and the first rotating shaft 22 drives the cockpit 21 to rotate, simulating the rotation of the pilot with itself as the axis; when the third motor 232 is working, it drives the screw rod 231 to rotate, the screw rod 231 drives the slider 23 to move under the action of the thread, and the slider 23 drives the cockpit 21 to approach or move away from the movable seat 14 through the first rotating shaft 22, simulating the rotational movement of the pilot under different turning radii; when the fourth motor 313 is working, it can drive the sixth gear 312 to rotate, the sixth gear 312 drives the fifth gear 311 to rotate, the fifth gear 311 drives the second rotating shaft 31 to rotate, and the second rotating shaft 31 drives the rotating frame 32 to rotate, which can simulate the flipping movement during flight. The rotations among the movable seat 14, cockpit 21 and rotating frame 32 do not affect each other, and the direction adjustment is more flexible, which facilitates the simulation of various flight states and improves the effect of simulation training.

[0058] When the sleeve 12 drives the first limit slider 13 to pass through the third triangular block 114, the first limit slider 13 pushes the third triangular block 114 to compress the first telescopic rod 113. After the first telescopic rod 113 is compressed and acts on the second telescopic rod 116 through the connecting tube 115, the second telescopic rod 116 extends and pushes the first fixed plate 58 to move upward. The first fixed plate 58 pulls the first movable rod 56 and the first triangular block 59 to move upward. At this time, the position of the second piston head 52 is unlocked. Under the action of negative pressure, the second piston head 52 pulls the second push rod 53 and the second limit slider 54 to move upward. Figure 7 The first limiting slider 13 moves to the right side to prevent the high-speed moving first limiting slider 13 from directly contacting the static second limiting slider 54, which may cause the device to be damaged or a safety accident. When the first limiting slider 13 and the second limiting slider 54 contact, the first limiting slider 13 pushes the second limiting slider 54 to move, and the second limiting slider 54 pushes the second piston head 52 to slide in the second cylinder 51 through the second push rod 53, compressing Figure 6The gas inside the second cylinder 51 on the right side of the second piston head 52 decelerates the sleeve 12 and the movable seat 14 under the action of the gas. At the same time, the gas inside the second cylinder 51 is compressed and enters the first cylinder 41 through the air guide pipe 510, so that the inside of the first cylinder 41 has a large air pressure, recovering the energy after acceleration, which is more environmentally friendly.

[0059] The air pump in the middle of the air guide pipe 510 can drive the first push rod 43 to move at the first piston head 42, and the first push rod 43 pushes the first limit slider 13 to slide on the inner wall of the limit groove 111, and the limit slider 13 drives the sleeve 12 and the movable seat 14 to move, giving the sleeve 12 and the movable seat 14 an initial velocity, reducing the energy consumption of the sleeve 11 and the movable seat 42 when accelerating from 0, and then firstly pumping the gas in the first cylinder 41 into the second cylinder 51, so that the first piston head 42 is again stuck in the second triangular block 445. Figure 5 The left side of the second cylinder 51 is drawn into the first cylinder 41 after the gas flows naturally in the air duct 510, so that the second cylinder 51 has a negative pressure. Preferably, a valve is provided on the air duct 510 to open or close the air duct 510. After the gas in the second cylinder 51 is compressed, it enters the first cylinder 41 through the air duct 510. The first cylinder 41 has a large air pressure. After the energy after acceleration is recovered, the valve is closed to prevent the gas in the first cylinder 41 from returning to the second cylinder 51.

Claims

1. An auxiliary simulation device for an aircraft, characterized in that: include A linear motion assembly (1), the linear motion assembly (1) comprising a support tube (11), a sleeve (12), a first limiting slider (13), a movable seat (14) and a support frame (15), the two ends of the support tube (11) are respectively installed on the ground through the support frame (15), a limiting groove (111) is provided on the support tube (11), the inner wall of the limiting groove (111) is slidably connected to the first limiting slider (13), the first limiting slider (13) is fixedly connected to the inner wall of the sleeve (12), the sleeve (12) is slidably connected to the support tube (11), and the outer wall of the sleeve (12) is rotatably connected to the movable seat (14); A secondary rotating assembly (2), the secondary rotating assembly (2) comprising a cabin (21), a first rotating shaft (22) and a slider (23), the two ends of the cabin (21) are respectively fixedly connected to the first rotating shaft (22), and the first rotating shaft (22) is rotatably connected to the slider (23); A main rotating assembly (3), the main rotating assembly (3) comprising a second rotating shaft (31) and a rotating frame (32), the inner wall of the rotating frame (32) being slidably connected to a slider (23), the rotating frame (42) being fixedly connected to one end of the second rotating shaft (31), the other end of the second rotating shaft (31) being rotatably connected to a movable seat (14), the main rotating assembly (3) and the auxiliary rotating assembly (2) being respectively provided with two groups, which are respectively located on both sides of the movable seat (14); An energy recovery component (5), the energy recovery component (5) comprising a second cylinder (51), a second piston head (52), a second push rod (53) and a second limit slider (54), the inner wall of the second cylinder (51) is slidably connected to the second piston head (52), the second piston head (52) is fixedly connected to one end of the second push rod (53), the other end of the second push rod (53) is fixedly connected to the second limit slider (54), and the second limit slider (54) is slidably connected to the limit groove (111).

2. The auxiliary simulation device for aircraft according to claim 1, characterized in that: The outer wall of the sleeve (12) is fixedly connected to the first gear (121), the first gear (121) is meshedly connected to the second gear (122), the second gear (122) is fixedly connected to the first motor (123), and the first motor (123) is fixedly connected to the movable seat (14).

3. The auxiliary simulation device for aircraft according to claim 1, characterized in that: The first rotating shaft (22) is fixedly connected to the third gear (221), the third gear (221) is meshedly connected to the fourth gear (222), the fourth gear (222) is fixedly connected to the second motor (223), and the second motor (223) is fixedly connected to the sliding block (23).

4. The auxiliary simulation device for aircraft according to claim 1, characterized in that: The slider (23) is threadedly connected to a screw rod (231), one end of the screw rod (231) is rotatably connected to a rotating frame (32), the other end of the screw rod (231) is fixedly connected to a third motor (232), and the third motor (232) is fixedly connected to the rotating frame (32).

5. The auxiliary simulation device for aircraft according to claim 1, characterized in that: The second rotating shaft (31) is fixedly connected to the fifth gear (311), the fifth gear (311) is meshedly connected to the sixth gear (312), the sixth gear (312) is fixedly connected to the fourth motor (313), and the fourth motor (313) is fixedly connected to the movable seat (14).

6. The auxiliary simulation device for aircraft according to claim 5, characterized in that: The invention also comprises a driving assembly (4), wherein the driving assembly (4) comprises a first cylinder (41), a first piston head (42) and a first push rod (43), wherein the inner wall of the first cylinder (41) is slidably connected to the first piston head (42), one end of the first piston head (42) is fixedly connected to the first push rod (43), and the other end of the first push rod (43) faces the support tube (11).

7. The auxiliary simulation device for aircraft according to claim 6, characterized in that: The energy recovery component (5) further comprises a first fixed ring (55), a first movable rod (56), a first spring (57), a first fixed disk (58), a first triangular block (59) and an air duct (510); the first fixed ring (55) is fixedly connected to the second cylinder (51), and the inner wall of the first fixed ring (55) is slidably connected to the first movable rod (56); one end of the first movable rod (56) is fixedly connected to the first triangular block (59), and the other end of the first movable rod (56) is fixedly connected to the first fixed disk (58); a first spring (57) is sleeved on the first movable rod (56), one end of the first spring (57) is fixedly connected to the first fixed ring (55), and the other end of the first spring (57) is fixedly connected to the first fixed disk (58); the second cylinder (51) is connected to the first cylinder (41) via the air duct (510).

8. The auxiliary simulation device for aircraft according to claim 7, characterized in that: A limiting member (44) is provided on the first cylinder (41), and the limiting member (44) comprises a second fixed ring (441), a second movable rod (442), a second spring (443), a second fixed disk (444) and a second triangular block (445); the second fixed ring (441) is fixedly connected to the first cylinder (41); the inner wall of the second fixed ring (441) is slidably connected to the second movable rod (442); one end of the second movable rod (442) is fixedly connected to the second fixed disk (444); the other end of the second movable rod (442) is fixedly connected to the second triangular block (445); a second spring (443) is sleeved on the second movable rod (442); one end of the second spring (443) is fixedly connected to the second fixed ring (441); and the other end of the second spring (443) is fixedly connected to the second fixed disk (444).

9. The auxiliary simulation device for aircraft according to claim 8, characterized in that: The outer wall of the support tube (11) is fixedly connected to a fixed block (112), the fixed block (112) is fixedly connected to a first telescopic rod (113), one end of the first telescopic rod (113) is fixedly connected to a third triangular block (114), the third triangular block (114) is located above the limiting groove (111), the other end of the first telescopic rod (113) is fixedly connected to a second telescopic rod (116) via a connecting tube (115), the bottom end of the second telescopic rod (116) is fixedly connected to the outer wall of the second cylinder (51), and the second telescopic rod (116) is against the lower surface of the first fixed plate (58).

10. The auxiliary simulation device for aircraft according to claim 9, characterized in that: The outer wall of the first cylinder (41) is fixedly connected to one end of an electric push rod (45), and the other end of the electric push rod (45) abuts against the lower surface of the second fixed plate (444).

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