An auxiliary simulation device for an aerial vehicle

Abstract

The application relates to the technical field of simulation training, in particular to an auxiliary simulation device for an aviation aircraft, which comprises a linear movement assembly, a secondary rotating assembly, a primary rotating assembly and an energy recovery assembly, the linear movement assembly comprises a supporting pipe, a sleeve pipe, a first limiting sliding block, a movable seat and a supporting frame, the supporting pipe is installed on the ground through the supporting frame at two ends respectively, a limiting groove is formed in the supporting pipe, the first limiting sliding block is slidably connected to the inner wall of the limiting groove, the first limiting sliding block is fixedly connected to the inner wall of the sleeve pipe, the sleeve pipe is slidably connected to the supporting pipe, and the outer wall of the sleeve pipe is rotatably connected to the movable seat; the movable seat can rotate on the sleeve pipe, thereby driving the second rotating shaft, the rotating frame, the cabin, the first rotating shaft and the sliding block to rotate around the supporting pipe, and the rotating movement of a pilot under a certain turning radius is simulated. Moreover, the rotation between the movable seat, the cabin and the rotating frame does not affect each other, and the direction adjustment is more flexible.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of simulation training, in particular to an auxiliary simulation device for an aviation aircraft. BACKGROUND

[0002] With the rapid development of aerospace industry, the aviation aircraft is constantly updated and replaced, and the auxiliary simulation device for the aerospace aircraft is a typical simulation system, which is a flight motion simulation device based on flight kinematics, and combines virtual reality technology, three-dimensional real-time rendering technology, computer graphics technology, computer interface technology and multimedia technology.

[0003] The existing auxiliary simulation device for the aerospace aircraft has been widely applied, has the advantages of simple operation, safety and comfort, and can simulate the real flight state of the aircraft on the ground. The device is not restricted by many factors such as site, environment, weather, air traffic control and the like, so that the training is efficient and convenient. When the pilot uses the auxiliary simulation device for flight training, the pilot can repeatedly practice difficult projects according to his own conditions, so as to improve the training efficiency. The auxiliary simulation device can avoid safety hazards caused by operation errors of the pilot, and ensures the safety of personnel and equipment.

[0004] At present, the Chinese invention with the application number 201410814354.X discloses a flight simulation training device, which comprises a vertical main shaft and a cantilever beam arranged on the main shaft through a bearing. One end of the cantilever beam is provided with a training cabin. Although the flight simulation training device can adjust the body posture of the pilot or astronaut to be consistent with the direction of the force that the pilot or astronaut bears the super load, so as to improve the real sense of the simulation flight, the direction adjustment is not flexible enough, and it is difficult to recover the energy after acceleration, so the energy consumption is high and the device is not environmentally friendly. SUMMARY

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

[0006] To solve the above technical problems, the application provides the following technical scheme: an auxiliary simulation device for an aerial vehicle, comprising a linear movement assembly, a secondary rotation assembly, a primary rotation assembly and an energy recovery assembly, the linear movement assembly comprises a support pipe, a sleeve pipe, a first limiting sliding block, a movable seat and a support frame, the support pipe is installed on the ground through the support frame at both ends, a limiting groove is formed in the support pipe, the first limiting sliding block is slidably connected to the inner wall of the limiting groove, the first limiting sliding block is fixedly connected to the inner wall of the sleeve pipe, the sleeve pipe is slidably connected to the support pipe, and the outer wall of the sleeve pipe is rotatably connected to the movable seat; the secondary rotation assembly comprises a cabin, a first rotating shaft and a sliding block, the cabin is fixedly connected to the first rotating shaft at both ends, and the first rotating shaft is rotatably connected to the sliding block; the primary rotation assembly comprises a second rotating shaft and a rotating frame, the sliding block is slidably connected to the inner wall of the rotating frame, one end of the second rotating shaft is fixedly connected to the rotating frame, and the other end of the second rotating shaft is rotatably connected to the movable seat, and the primary rotation assembly and the secondary rotation assembly are provided with two groups respectively and are located on both sides of the movable seat; the energy recovery assembly comprises a second cylinder, a second piston head, a second push rod and a second limiting sliding block, the second piston head is slidably connected to the inner wall of the second cylinder, one end of the second piston head is fixedly connected to the second push rod, the other end of the second push rod is fixedly connected to the second limiting sliding block, and the second limiting sliding block is slidably connected to the limiting groove.

[0007] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the outer wall of the sleeve pipe is fixedly connected to a first gear, the first gear is meshingly connected to a second gear, the second gear is fixedly connected to a first motor, and the first motor is fixedly connected to the movable seat.

[0008] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the first rotating shaft is fixedly connected to a third gear, the third gear is meshingly connected to a fourth gear, the fourth gear is fixedly connected to a second motor, and the second motor is fixedly connected to the sliding block.

[0009] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the sliding block is threadedly connected to a lead screw, one end of the lead screw is rotatably connected to the rotating frame, the other end of the lead screw is fixedly connected to a third motor, and the third motor is fixedly connected to the rotating frame.

[0010] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the second rotating shaft is fixedly connected to a fifth gear, the fifth gear is meshingly connected to a sixth gear, the sixth gear is fixedly connected to a fourth motor, and the fourth motor is fixedly connected to the movable seat.

[0011] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the auxiliary simulation device further comprises a driving assembly, the driving assembly comprises a first cylinder, a first piston head and a first push rod, the first piston head is slidably connected to the inner wall of the first cylinder, one end of the first piston head is fixedly connected to the first push rod, and the other end of the first push rod is directed towards the support pipe.

[0012] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the energy recovery assembly further comprises a first fixed ring, a first movable rod, a first spring, a first fixed disc, a first triangular block and a gas guide pipe, the first fixed ring is fixedly connected with the second cylinder, the inner wall of the first fixed ring is slidably connected with the first movable rod, one end of the first movable rod is fixedly connected with the first triangular block, the other end of the first movable rod is fixedly connected with the first fixed disc, the first movable rod is sleeved with the first spring, one end of the first spring is fixedly connected with the first fixed ring, and the other end of the first spring is fixedly connected with the first fixed disc, and the second cylinder is communicated with the first cylinder through the gas guide pipe.

[0013] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the first cylinder is provided with a limiting piece, the limiting piece comprises a second fixed ring, a second movable rod, a second spring, a second fixed disc and a second triangular block, the second fixed ring is fixedly connected with the first cylinder, the inner wall of the second fixed ring is slidably connected with the second movable rod, one end of the second movable rod is fixedly connected with the second fixed disc, the other end of the second movable rod is fixedly connected with the second triangular block, the second movable rod is sleeved with the second spring, one end of the second spring is fixedly connected with the second fixed ring, and the other end of the second spring is fixedly connected with the second fixed disc.

[0014] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the outer wall of the supporting pipe is fixedly connected with a fixed block, the fixed block is fixedly connected with a first telescopic rod, one end of the first telescopic rod is fixedly connected with a third triangular block, the third triangular block is located above the limiting groove, the other end of the first telescopic rod is fixedly connected with a second telescopic rod through a connecting pipe, the bottom end of the second telescopic rod is fixedly connected with the outer wall of the second cylinder, and the second telescopic rod abuts against the lower surface of the first fixed disc.

[0015] As a preferred scheme of the auxiliary simulation device for the aerial vehicle, the outer wall of the first cylinder is fixedly connected with one end of the electric push rod, and the other end of the electric push rod abuts against the lower surface of the second fixed disc.

[0016] The beneficial effects of the present application are as follows: the movable seat in the present application can rotate on the sleeve, thereby driving the second rotating shaft, the rotating frame, the cockpit, the first rotating shaft and the sliding block to rotate around the supporting pipe as the axis, and simulating the rotary motion of the pilot under a certain turning radius. Moreover, the rotation between 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 limiting slider to collide with the second limiting slider, the first limiting slider pushes the second limiting slider to move, the second limiting slider pushes the second piston head to slide in the second cylinder through the second push rod, the gas in the right side of the second cylinder inside the second piston head in the drawing is compressed, the sleeve and the movable seat are decelerated under the action of the gas, and the gas in the second cylinder can be stored after compression, the energy after acceleration is recovered, and the energy is more environmentally friendly. BRIEF DESCRIPTION OF DRAWINGS

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

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

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

[0024] Figure 7 It is a schematic diagram of the first fixed ring in the embodiment of the present disclosure. Figure 1 It is an enlarged schematic diagram of A in the embodiment of the present disclosure.

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

[0026] The drawings show that the straight line moving assembly 1, the support pipe 11, the limiting groove 111, the fixed block 112, the first telescopic rod 113, the third triangular block 114, the connecting pipe 115, the second telescopic rod 116, the sleeve 12, the first gear 121, the second gear 122, the first motor 123, the first limiting slider 13, the movable seat 14, the support frame 15, the auxiliary rotating assembly 2, the cabin 21, the first rotating shaft 22, the third gear 221, the fourth gear 222, the second motor 223, the slider 23, and the 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 limiting piece 44, the second fixed ring 441, the second movable rod 442, the second spring 443, the second fixed disc 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 limiting slide 54, the first fixed ring 55, the first movable rod 56, the first spring 57, the first fixed disc 58, the first triangular block 59, the air duct 510. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned objectives, characteristics and advantages of the present application more apparent and easy to understand, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0028] Embodiment 1, with reference to Figures 1-4 and Figure 6 This embodiment provides an auxiliary simulation device for an aerial vehicle, which comprises a linear moving assembly 1, a secondary rotating assembly 2, a main rotating assembly 3 and an energy recovery assembly 5. The linear moving assembly 1 comprises a support pipe 11, a sleeve pipe 12, a first limiting slide 13, a movable seat 14 and a support frame 15. The support pipe 11 is installed on the ground through the support frame 15 at both ends, and a limiting groove 111 is formed on the support pipe 11. The first limiting slide 13 is slidably connected to the inner wall of the limiting groove 111, and the first limiting slide 13 is fixedly connected to the inner wall of the sleeve pipe 12. The sleeve pipe 12 is slidably connected to the support pipe 11, and the outer wall of the sleeve pipe 12 is rotatably connected to the movable seat 14.

[0029] In this embodiment, the support pipe 11 is installed on the ground through the support frame 15 at both ends, which can fix the support pipe 11. The sleeve pipe 12 can slide on the support pipe 11, and the sleeve pipe 12 can drive the first limiting slide 13 to slide on the inner wall of the limiting groove 111, which can prevent relative rotation between the sleeve pipe 12 and the support pipe 11. The movable seat 14 can rotate on the sleeve pipe 12. In one embodiment, a rocket engine is hung on the sleeve pipe 12 to push the sleeve pipe 12 to slide on the support pipe 11, and the acceleration of the sleeve pipe 12 simulates the gravitational acceleration in the process of flight acceleration.

[0030] The secondary rotating assembly 2 comprises a cabin 21, a first rotating shaft 22 and a slide 23. The cabin 21 is fixedly connected to the first rotating shaft 22 at both ends, and the first rotating shaft 22 is rotatably connected to the slide 23.

[0031] In this preferred embodiment, the cockpit 21 is equipped with a movable door. 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 secured in the seat. When the first rotating shaft 22 rotates, it can drive the cockpit 21 to rotate, simulating the pilot's rotation around 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 a 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 in two sets, located on both sides of the movable seat 14.

[0033] In this preferred embodiment, the slider 23 can slide on the inner wall of the rotating frame 32 to adjust the position of the slider 23, the first rotating shaft 22 and the cockpit 21. The rotating frame 32 can rotate around the second rotating shaft 31 as the axis, which can simulate the flipping motion 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 around the support tube 11 as the axis, simulating the rotational movement of a pilot within 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, making directional adjustment more flexible.

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

[0036] In this preferred embodiment, when the movable seat 14 and the sleeve 12 cause the first limiting slider 13 to contact the second limiting slider 54, the first limiting slider 13 pushes the second limiting slider 54 to move. The second limiting slider 54 then pushes the second piston head 52 to slide in the second cylinder 51 via 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, refer to Figures 1-8 This embodiment is based on the previous embodiment, but differs from the previous embodiment in that...

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

[0039] In the embodiment, the first motor 123 can drive the second gear 122 to rotate when the first motor 123 works, the second gear 122 can drive the first gear 121 to rotate when the second gear 122 rotates, the first gear 121 drives the sleeve 12 to rotate, the sleeve 12 drives the movable seat 14 to rotate, thereby driving the second rotating shaft 31, the rotating frame 32, the cabin 21, the first rotating shaft 22 and the sliding block 23 to rotate with the support pipe 11 as the axis, and the rotation of the pilot under a certain turning radius is simulated. Moreover, the rotation between the movable seat 14, the cabin 21 and the rotating frame 32 does not affect each other, and the direction adjustment is more flexible.

[0040] With reference to Figure 3 The first rotating shaft 22 is fixedly connected with a third gear 221, the third gear 221 is in meshing connection with a fourth gear 222, the fourth gear 222 is fixedly connected with a second motor 223, and the second motor 223 is fixedly connected with the sliding block 23.

[0041] In the embodiment, the second motor 223 can drive the fourth gear 222 to rotate when the second motor 223 works, 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 cabin 21 to rotate, thereby simulating the rotation of the pilot with the self as the axis.

[0042] With reference to Figure 4 The sliding block 23 is threadedly connected with a lead screw 231, one end of the lead screw 231 is rotatably connected with the rotating frame 32, the other end of the lead screw 231 is fixedly connected with a third motor 232, and the third motor 232 is fixedly connected with the rotating frame 32.

[0043] In the embodiment, the third motor 232 drives the lead screw 231 to rotate when the third motor 232 works, the lead screw 231 drives the sliding block 23 to move under the action of the thread, the sliding block 23 drives the cabin 21 to move close to or away from the movable seat 14 through the first rotating shaft 22, thereby simulating the rotation of the pilot under different turning radii.

[0044] With reference to Figure 4 The second rotating shaft 31 is fixedly connected with a fifth gear 311, the fifth gear 311 is in meshing connection with a sixth gear 312, the sixth gear 312 is fixedly connected with a fourth motor 313, and the fourth motor 313 is fixedly connected with the movable seat 14.

[0045] In the preferred embodiment, when the fourth motor 313 is working, the sixth gear 312 is driven to rotate, the fifth gear 311 is driven to rotate by the sixth gear 312, the second rotating shaft 31 is driven to rotate by the fifth gear 311, and the rotating frame 32 is driven to rotate by the second rotating shaft 31, so as to simulate the overturning movement in flight.

[0046] With reference to Figure 5 The driving assembly 4 comprises a first cylinder 41, a first piston head 42, and a first push rod 43. The first piston head 42 is slidably connected to the inner wall of the first cylinder 41, and the first piston head 42 is fixedly connected to one end of the first push rod 43. The other end of the first push rod 43 faces the support pipe 11.

[0047] In the preferred embodiment, the gas inside the first cylinder 41 can push the first piston head 42 to move to the right side of the first cylinder 41, and the first piston head 42 drives the first push rod 43 to move. Figure 5

[0048] With reference to Figure 6 and Figure 8 The energy recovery assembly 5 further comprises a first fixed ring 55, a first movable rod 56, a first spring 57, a first fixed disc 58, a first triangular block 59, and a gas guide pipe 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 disc 58. The first movable rod 56 is sleeved with the 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 disc 58. The second cylinder 51 is connected to the first cylinder 41 through the gas guide pipe 510. A sealing ring is arranged on the inner wall of the first fixed ring 55, which is beneficial to improve the sealing performance between the first fixed ring 55 and the first movable rod 56.

[0049] In the preferred embodiment, under the action of the pulling force of the first spring 57, the first triangular block 59 is located at the position in the first fixed ring 55, and at this time, the second piston head 52 can be clamped to the left side of the first triangular block 59 in the first fixed ring 55, so as to lock the position of the second piston head 52. Figure 6 Figure 6 In the preferred embodiment, under the action of the pulling force of the first spring 57, the first triangular block 59 is located at the position in the first fixed ring 55, and at this time, the second piston head 52 can be clamped to the left side of the first triangular block 59 in the first fixed ring 55, so as to lock the position of the second piston head 52.​​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 component 44 is provided on the first cylinder 41. The limiting component 44 includes a second fixed ring 441, a second movable rod 442, a second spring 443, a second fixed plate 444, and a second triangular block 445. The second fixed ring 441 is fixedly connected to the first cylinder 41. The second movable rod 442 is slidably connected to the inner wall of the second fixed ring 441. One end of the second movable rod 442 is fixedly connected to the second fixed plate 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 plate 444.

[0051] In this preferred embodiment, the second triangular block 445 is positioned under the tension of the second spring 443. Figure 5 In the middle position, the first piston head 42 can be locked in place. Figure 5 On the left side, the position of the first piston head 42 is locked. When the second fixed plate 444 moves upward, it pulls the second movable rod 442 and the second triangular block 445 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 towards... Figure 5 The first piston head 42 moves to the right, which drives the first push rod 43 to move. The first push rod 43 pushes the first limiting slider 13 to slide on the inner wall of the limiting groove 111. The limiting 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 when the sleeve 11 and the movable seat 42 accelerate from 0.

[0052] Reference Figure 7 The outer wall of the support tube 11 is fixedly connected to the fixing block 112, the fixing 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 abuts against the lower surface of the first fixing plate 58.

[0053] The first telescopic rod 113 is 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 by a short distance, the second telescopic rod 116 is elongated by a long distance through the action of the connecting pipe 115 on the second telescopic rod 116. In one embodiment, the first telescopic rod 113, the connecting pipe 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 by a short distance, the second telescopic rod 116 is elongated by a long distance through the action of the connecting pipe 115 on the second telescopic rod 116, and the second telescopic rod 116 elongates to push the first fixed disc 58 to move upward. Figure 7 The third triangular block 114 is installed in the shape of the first limiting sliding block 13 passing through the third triangular block 114, the first limiting sliding block 13 pushes the third triangular block 114 to compress the first telescopic rod 113.

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

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

[0056] Working principle: when in use, a suction pump is arranged in the middle of the air guide pipe 510, a small part of the gas in the second cylinder 51 is sucked into the first cylinder 41, and at this time, the first piston head 42 is clamped on the left side of Figure 5 by the second triangular block 445, the second piston head 52 is clamped on the left side of Figure 6 by the first triangular block 59, the right side of the second piston head 52 is under negative pressure, and there is a large gas pressure in the first cylinder 41 on the left side of the first piston head 42. When the electric push rod 45 is controlled to elongate, the electric push rod 45 pushes the second fixed disc 444 to move upward, the second fixed disc 444 pulls the second movable rod 442 and the second triangular block 445 to move upward, and at this time, the position of the first piston head 42 is unlocked, the gas in the first cylinder 41 can push the first piston head 42 to move to the right side of Figure 5 , the first piston head 42 drives the first push rod 43 to move, the first push rod 43 pushes the first limiting sliding block 13 to slide in the inner wall of the limiting groove 111, and the limiting sliding block 13 drives the sleeve 12 and the movable seat 14 to move, thereby giving the sleeve 12 and the movable seat 14 an initial speed, reducing the energy consumption when the sleeve 11 and the movable seat 42 start to accelerate from 0.

[0057] By attaching a rocket engine to the sleeve 12, the sleeve 12 is pushed to slide on the support tube 11. By accelerating the sleeve 12, the gravitational acceleration during flight acceleration is simulated. During the sliding of the sleeve 12 on the support tube 11: when the first motor 123 works, it can drive the second gear 122 to rotate. When the second gear 122 rotates, it can drive the first gear 121 to rotate. The first gear 121 drives the sleeve 12 to rotate. 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 around the support tube 11 as the axis, simulating the rotational motion of the pilot under a certain turning radius. Furthermore, the rotation of the movable seat 14, cockpit 21, and rotating frame 32 does not affect each other, making directional adjustment 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 pilot's rotation around himself. When the third motor 232 is working, it drives the lead screw 231 to rotate, and the lead screw 231 drives the slider 23 to move under the action of the thread. 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 pilot's rotational movement at 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, simulating the roll motion during flight. The rotation of the movable seat 14, the cockpit 21 and the rotating frame 32 does not affect each other, the direction adjustment is more flexible, it is easier to complete the simulation of various flight states and improve the effect of simulation training.

[0058] When the sleeve 12 drives the first limiting slider 13 past the third triangular block 114, the first limiting slider 13 pushes the third triangular block 114 to compress the first telescopic rod 113. The compressed first telescopic rod 113, through the connecting pipe 115, acts on the second telescopic rod 116, causing the second telescopic rod 116 to extend and push the first fixed plate 58 upwards. The first fixed plate 58 pulls the first movable rod 56 and the first triangular block 59 upwards. At this time, the position of the second piston head 52 is unlocked. Under negative pressure, the second piston head 52 pulls the second push rod 53 and the second limiting slider 54 towards... Figure 7 The first limiting slider 13 moves to the right to prevent the high-speed moving first limiting slider 13 from directly contacting the stationary second limiting slider 54, which could damage the device or cause a safety accident. When the first limiting slider 13 and the second limiting slider 54 come into contact, the first limiting slider 13 pushes the second limiting slider 54 to move. The second limiting slider 54, through the second push rod 53, pushes the second piston head 52 to slide in the second cylinder 51, compressing... Figure 6The gas in the second cylinder 51 right side of the second piston head 52 inside, under the action of the gas to the sleeve 12 and the movable seat 14 deceleration, while the second cylinder 51 inside the gas compression through the gas pipe 510 into the first cylinder 41, make the first cylinder 41 inside has a very big gas pressure, recovery after the energy of acceleration, more environmentally friendly.

[0059] And the gas pump in the middle of the gas pipe 510, can move in the first piston head 42 drive the first push rod 43, the first push rod 43 push the first limit slide 13 in the limit slot 111 wall sliding, limit slide 13 drive in the sleeve 12 and the movable seat 14 move, give the sleeve 12 and the movable seat 14 a initial velocity, reduce the energy consumption to the sleeve 11 and the movable seat 42 from 0 start to accelerate after, first into the cylinder 41 gas in the second cylinder 51 inside, make the first piston head 42 is re second triangular block 445 card in Figure 5 The left side, then after the gas in the gas pipe 510 natural flow, the second cylinder 51 inside a small part of the gas into the first cylinder 41, make the second cylinder 51 inside has negative pressure, preferably on the gas pipe 510 set valve, used to open or close the gas pipe 510, in the second cylinder 51 inside the gas compression through the gas pipe 510 into the first cylinder 41, the first cylinder 41 inside has a very big gas pressure, recovery after the energy of acceleration, close the valve, prevent the first cylinder 41 inside the gas back into the second cylinder 51 inside.

Claims

1. An auxiliary simulation device for an aerial vehicle, characterized by: Comprising The linear moving assembly (1) comprises a support pipe (11), a sleeve pipe (12), a first limiting sliding block (13), a movable seat (14) and a support frame (15), the support pipe (11) is installed on the ground through the support frame (15) at both ends respectively, a limiting groove (111) is formed on the support pipe (11), the first limiting sliding block (13) is slidably connected to the inner wall of the limiting groove (111), the first limiting sliding block (13) is fixedly connected to the inner wall of the sleeve pipe (12), the sleeve pipe (12) is slidably connected to the support pipe (11), and the outer wall of the sleeve pipe (12) is rotatably connected to the movable seat (14); The auxiliary rotating assembly (2) comprises a cabin (21), a first rotating shaft (22) and a sliding block (23), the cabin (21) is fixedly connected to the first rotating shaft (22) at both ends respectively, and the first rotating shaft (22) is rotatably connected to the sliding block (23); The main rotating assembly (3) comprises a second rotating shaft (31) and a rotating frame (32), the sliding block (23) is slidably connected to the inner wall of the rotating frame (32), one end of the rotating frame (32) is fixedly connected to the second rotating shaft (31), and 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 provided with two groups respectively and are located on both sides of the movable seat (14); The energy recovery assembly (5) comprises a second cylinder (51), a second piston head (52), a second push rod (53) and a second limiting sliding block (54), the second cylinder (51) is slidably connected to the second piston head (52), one end of the second piston head (52) is fixedly connected to the second push rod (53), the other end of the second push rod (53) is fixedly connected to the second limiting sliding block (54), and the second limiting sliding block (54) is slidably connected to the limiting groove (111).

2. The supplemental simulation device for an aerospace vehicle of claim 1, wherein: The outer wall of the sleeve pipe (12) is fixedly connected to the first gear (121), the first gear (121) is meshingly 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 supplemental simulation device for an aerospace vehicle as recited in claim 1, wherein: The first rotating shaft (22) is fixedly connected to the third gear (221), the third gear (221) is meshingly 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 supplemental simulation device for an aerospace vehicle as described in claim 1 wherein: The sliding block (23) is threadedly connected to a lead screw (231), one end of the lead screw (231) is rotatably connected to the rotating frame (32), the other end of the lead screw (231) is fixedly connected to a third motor (232), and the third motor (232) is fixedly connected to the rotating frame (32).

5. The supplemental simulation device for an aerospace vehicle as described in claim 1 wherein: The second rotating shaft (31) is fixedly connected to the fifth gear (311), the fifth gear (311) is meshingly 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 supplemental simulation device for an aerospace vehicle as recited in claim 5, wherein: Also include drive assembly (4), the drive assembly (4) includes first cylinder (41), first piston head (42) and first push rod (43), the first cylinder (41) inner wall is connected with first piston head (42) slidingly, one end of first piston head (42) is fixedly connected with first push rod (43), the other end of first push rod (43) is towards support tube (11).

7. The supplemental simulation device for an aerospace vehicle as recited in claim 6, wherein: The energy recovery assembly (5) further comprises a first fixed ring (55), a first movable rod (56), a first spring (57), a first fixed disc (58), a first triangular block (59) and a gas guide tube (510), the first fixed ring (55) is fixedly connected with the second cylinder (51), and the inner wall of the first fixed ring (55) is slidably connected with the first movable rod (56), one end of the first movable rod (56) is fixedly connected with the first triangular block (59), the other end of the first movable rod (56) is fixedly connected with the first fixed disc (58), the first movable rod (56) is provided with the first spring (57), one end of the first spring (57) is fixedly connected with the first fixed ring (55), the other end of the first spring (57) is fixedly connected with the first fixed disc (58), and the second cylinder (51) is communicated with the first cylinder (41) through the gas guide tube (510).

8. The supplemental simulation device for an aerospace vehicle as recited in claim 7, wherein: The first cylinder (41) is provided with a limiting piece (44), the limiting piece (44) comprises a second fixed ring (441), a second movable rod (442), a second spring (443), a second fixed disc (444) and a second triangular block (445), the second fixed ring (441) is fixedly connected with the first cylinder (41), the inner wall of the second fixed ring (441) is slidably connected with the second movable rod (442), one end of the second movable rod (442) is fixedly connected with the second fixed disc (444), the other end of the second movable rod (442) is fixedly connected with the second triangular block (445), the second movable rod (442) is provided with the second spring (443), one end of the second spring (443) is fixedly connected with the second fixed ring (441), and the other end of the second spring (443) is fixedly connected with the second fixed disc (444).

9. The supplemental simulation device for an aerospace vehicle as recited in claim 8, wherein: The outer wall of the support tube (11) is fixedly connected with a fixed block (112), the fixed block (112) is fixedly connected with a first telescopic rod (113), one end of the first telescopic rod (113) is fixedly connected with 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 with a second telescopic rod (116) through a connecting pipe (115), the bottom end of the second telescopic rod (116) is fixedly connected with the outer wall of the second cylinder (51), and the second telescopic rod (116) abuts against the lower surface of the first fixed disc (58).

10. The supplemental simulation device for an aerospace vehicle as recited in claim 9, wherein: The outer wall of the first cylinder (41) is fixedly connected with one end of the electric push rod (45), and the other end of the electric push rod (45) abuts against the lower surface of the second fixed disc (444).

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