Damping device for preventing rough and violent manipulation of aircraft accelerator

Abstract

According to the technical scheme, the damping device for preventing the aircraft accelerator from roughly and fiercely operating is characterized in that the damping device comprises an operating table, an operating rod is rotationally installed on the top of the operating table, and an operating head is fixedly installed at the top end of the operating rod; the damping assembly is arranged on the top face of the operation table and used for buffering the operation rod, and the damping assembly comprises two installation plates. When the damping device is used, when an operator operates the operation rod, the movable rod moves in the cylinder body, the first arc-shaped plate and the second arc-shaped plate pressurize damping liquid, and the damping liquid flows into the cylinder body; the pressurized damping liquid flows to the upper portion through a gap between the first arc-shaped plate and the second arc-shaped plate, when an operator operates the operating rod in the opposite direction, the first arc-shaped plate and the second arc-shaped plate apply pressure to the damping liquid above, the damping liquid flows to the lower portion again, and therefore the situation that the operator often draws the operating rod roughly and fiercely is relieved, and the operating efficiency is improved. Meanwhile, position change of the operating rod due to vibration of the airplane is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of damping equipment, in particular to a damping device for preventing rough and violent operation of an aircraft throttle. Background Art

[0002] Rough operation of the throttle (moving the throttle lever too quickly) will firstly cause a sharp change in aircraft power, making the aircraft state change too quickly to be difficult to control or even out of control; secondly, it will cause excessive force on the engine, increasing the risk of engine failure; thirdly, it will cause improper matching of engine oil and gas (the residual air coefficient is too large or too small), making the engine unable to respond effectively or even stall; therefore, every flight instructor will repeatedly ask flight trainees to operate the throttle gently and consistently. It takes three to five seconds to push the throttle lever from the slow position to the forward position. However, flight trainees or inexperienced pilots often roughly increase or decrease the throttle, especially when encountering special situations. The frequency of rough increase or decrease in the throttle is higher, posing a hidden danger to flight safety.

[0003] For general aircraft, the engines used usually do not have full-authority digital engine controllers, and the engine power needs to be directly controlled by the pilot using the throttle lever. Although the tightness adjustment knob of the throttle lever can adjust the resistance of throttle increase or decrease, it is more about preventing the control force from being too large or too small, and the throttle position from changing due to aircraft vibration. It is ineffective for excessive power changes caused by rough control by the pilot. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a damping device for preventing rough throttle operation of an aircraft, which solves the problem that flight trainees or inexperienced pilots often make rough throttle adjustments, especially when encountering special situations, the frequency of rough throttle adjustments is higher, posing a hidden danger to flight safety.

[0005] The above technical objectives of the utility model are achieved through the following technical solutions:

[0006] A damping device for preventing rough throttle operation of an aircraft comprises: an operating table, an operating rod is rotatably mounted on the top of the operating table, and an operating head is fixedly mounted on the top of the operating rod;

[0007] A damping assembly, wherein the damping assembly is arranged on the top surface of the operating table and is used to buffer the operating rod. The damping assembly comprises: two mounting plates, both of which are fixedly mounted on the top surface of the operating table, a cylinder is arranged between the mounting plates, a damping fluid is arranged inside the cylinder, a sealing ring is arranged inside the cylinder, a movable rod is arranged in a movable sleeve inside the cylinder, a through hole is arranged on the bottom surface of the cylinder, one end of the movable rod passes through the through hole and extends to the outside, a hinged plate is fixedly mounted on the outer circular wall surface of the operating rod, and rotating plates are arranged on both sides of the hinged plate. The movable hole is a movable rod, and one end of the movable rod away from the cylinder is hinged with the hinge plate. A hinge hole is opened on one side of the mounting plate. A hinge shaft is fixedly installed on the outer circular wall of the cylinder. The hinge shaft is hinged with the hinge hole. A first arc plate is fixedly sleeved on the outer circular wall of the movable rod. A rotating sleeve is rotatably installed on the outer circular wall of the movable rod. The rotating sleeve is rotatably sleeved on the inner wall of the sealing block ring. The bottom end of the rotating sleeve is fixedly sleeved with a second arc plate in contact with the first arc plate. A driving mechanism for driving the rotating sleeve to rotate is installed on the side of the movable rod.

[0008] Preferably, the driving mechanism includes a mounting block fixedly mounted on the side of the movable rod, a motor is fixedly mounted on the bottom of the mounting block, a rotating shaft is fixedly connected to the output end of the motor, a small gear is fixedly mounted on the end of the rotating shaft, a large gear is fixedly sleeved on the outer circular wall surface of the rotating sleeve, and the large gear is meshed with the small gear.

[0009] Preferably, a disc is fixedly sleeved on the rotating shaft, an annular groove is formed on the outer circumferential wall of the disc, a rotating ring is fixedly sleeved on the outer circumferential wall of the rotating sleeve, and a side portion of the rotating ring extends into the annular groove.

[0010] Preferably, an injection nozzle is provided on the bottom surface of the cylinder.

[0011] Preferably, an anti-overflow groove is provided on the top surface of the cylinder, and a sealing ring for sealing the sealing ring is provided inside the anti-overflow groove.

[0012] Preferably, a replacement hole is provided on the bottom surface of the cylinder, and a blocking bolt is connected to the internal thread of the replacement hole.

[0013] Preferably, the outer sides of the first arc plate and the second arc plate are in contact with the annular inner wall of the cylinder, the inner wall of the rotating sleeve and the outer circular wall of the movable rod are provided with a first sealing ring, the through hole and the outer circular wall of the movable rod are provided with a second sealing ring, and the outer circular wall of the rotating sleeve and the inner wall of the sealing ring are provided with a third sealing ring.

[0014] Preferably, a connecting hole is provided on the outer circumferential wall surface of the cylinder, a connecting bolt is connected to the internal thread of the connecting hole, a thread groove is provided on the outer circumferential wall surface of the sealing ring, and the bottom end of the connecting bolt is threadedly installed in the thread groove.

[0015] In summary, the utility model mainly has the following beneficial effects:

[0016] When the utility model is in use, when the operator manipulates the operating lever, the movable rod moves in the cylinder, so that the first arc plate and the second arc plate pressurize the damping fluid, and the pressurized damping fluid flows upward through the gap between the first arc plate and the second arc plate; when the operator manipulates the operating lever in the opposite direction, the first arc plate and the second arc plate pressurize the damping fluid above, so that the damping fluid flows downward again, thereby alleviating the situation that the operator often pulls the operating lever roughly, and at the same time preventing the operating lever from changing position due to the vibration of the aircraft.

[0017] In the utility model, the operator can start the motor, and the output end of the motor drives the rotating shaft to rotate, thereby causing the small gear to rotate, and the rotation of the small gear drives the large gear and the rotating sleeve to rotate, and the rotation of the rotating sleeve drives the second arc plate to rotate, so that the position of the second arc plate gradually overlaps or separates with the position of the first arc plate, and the circulation rate of the damping fluid can be increased or decreased to adapt to the strength of different operators. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0019] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0020] Figure 3 It is a first-angle stereoscopic view of the cylinder of the utility model after being cut open;

[0021] Figure 4 It is a stereoscopic diagram of the utility model after the cylinder body is cut open from the second viewing angle.

[0022] Figure numerals: 1. operating table; 2. operating lever; 3. operating head; 4. cylinder; 5. movable rod; 6. hinged plate; 7. rotating hole; 8. mounting plate; 9. hinged hole; 10. hinged shaft; 11. first arc plate; 12. second arc plate; 13. large gear; 14. mounting block; 15. sealing ring; 16. injection nozzle; 17. sealing ring; 18. motor; 19. blocking bolt; 20. small gear; 21. connecting bolt; 22. anti-overflow groove; 23. through hole; 24. rotating sleeve; 25. disc; 26. rotating ring. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] Embodiment 1

[0025] refer to Figure 1-Figure 4 , a damping device for preventing rough and violent operation of an aircraft throttle, an operating platform 1, an operating rod 2 is rotatably mounted on the top of the operating platform 1, and an operating head 3 is fixedly mounted on the top of the operating rod 2;

[0026] A damping assembly is arranged on the top surface of the operating platform 1 and is used to buffer the operating rod 2. The damping assembly comprises: two mounting plates 8, both mounting plates 8 are fixedly mounted on the top surface of the operating platform 1, a cylinder 4 is arranged between the mounting plates 8, a damping fluid is arranged inside the cylinder 4, a sealing ring 17 is arranged inside the cylinder 4, a movable rod 5 is arranged in a movable sleeve inside the cylinder 4, a through hole is arranged on the bottom surface of the cylinder 4, one end of the movable rod 5 passes through the through hole and extends to the outside, a hinge plate 6 is fixedly mounted on the outer circumferential wall surface of the operating rod 2, rotating holes 7 are arranged on both sides of the hinge plate 6, one end of the movable rod 5 away from the cylinder 4 is hinged to the hinge plate 6, a hinge hole 9 is arranged on one side of the mounting plate 8, and the cylinder The outer circular wall surface of the body 4 is fixedly mounted with a hinge shaft 10, and the hinge shaft 10 is hinged with the hinge hole 9. The outer circular wall surface of the movable rod 5 is fixedly sleeved with a first arc plate 11, and the outer circular wall surface of the movable rod 5 is rotatably mounted with a rotating sleeve 24, and the rotating sleeve 24 is rotatably sleeved on the inner wall of the sealing ring 17. The bottom end of the rotating sleeve 24 is fixedly sleeved with a second arc plate 12 in contact with the first arc plate 11. A driving mechanism for driving the rotating sleeve 24 to rotate is installed on the side of the movable rod 5. The area of ​​the first arc plate 11 is larger than half of the cross-sectional area between the movable rod 5 and the cylinder body 4, and the area of ​​the second arc plate 12 is larger than half of the cross-sectional area between the rotating sleeve 24 and the cylinder body 4, which helps to seal.

[0027] During use, when the operator manipulates the operating lever 2, the movable rod 5 moves in the cylinder 4, so that the first curved plate 11 and the second curved plate 12 pressurize the damping fluid, and the pressurized damping fluid flows upward through the gap between the first curved plate 11 and the second curved plate 12. When the operator manipulates the operating lever 2 in the opposite direction, the first curved plate 11 and the second curved plate 12 pressurize the damping fluid above, so that the damping fluid flows downward again, thereby alleviating the situation where the operator often pulls the operating lever 2 roughly, and at the same time avoiding the position change of the operating lever 2 due to the vibration of the aircraft.

[0028] Embodiment 2

[0029] Based on the above embodiment 1, reference Figure 2 The driving mechanism includes a mounting block 14 fixedly mounted on the side of the movable rod 5, a motor 18 fixedly mounted on the bottom of the mounting block 14, a rotating shaft fixedly connected to the output end of the motor 18, a pinion 20 fixedly mounted on the end of the rotating shaft, a large gear 13 fixedly sleeved on the outer circumferential wall of the rotating sleeve 24, and the large gear 13 meshes with the pinion 20; a disc 25 fixedly sleeved on the rotating shaft, an annular groove 23 is provided on the outer circumferential wall of the disc 25, a rotating ring 26 fixedly sleeved on the outer circumferential wall of the rotating sleeve 24, and the side of the rotating ring 26 extends into the annular groove 23. The operator can start the motor 18, and the output end of the motor 18 drives the shaft to rotate, thereby causing the small gear 20 to rotate. The rotation of the small gear 20 drives the large gear 13 and the rotating sleeve 24 to rotate. The rotation of the rotating sleeve 24 drives the second arc plate 12 to rotate, so that the position of the second arc plate 12 gradually overlaps or separates from the position of the first arc plate 11, which can increase or decrease the circulation rate of the damping fluid. The relative positions of the first arc plate 11 and the second arc plate 12 change, and the circulation rate of the damping fluid changes. When the first arc plate 11 and the second arc plate 12 are completely separated, the damping reaches the maximum, so that the staff can adjust the circulation rate of the damping fluid to adjust the damping size to adapt to the strength of different operators.

[0030] Embodiment 3

[0031] Based on the above embodiments 1 and 2, reference Figure 2 and Figure 3The bottom surface of the cylinder 4 is provided with an injection nozzle 16. By providing the injection nozzle 16, when the damping liquid in the cylinder 4 is consumed more, it is convenient for maintenance personnel to inject damping liquid into the cylinder 4 through the injection nozzle 16; the top surface of the cylinder 4 is provided with an anti-overflow groove 22, and the internal fixed sleeve of the anti-overflow groove 22 is provided with a sealing ring 15 for sealing the sealing ring 17. By providing the sealing ring 15, the damping liquid is prevented from overflowing from the top of the cylinder 4; the bottom surface of the cylinder 4 is provided with a replacement hole, and the internal thread of the replacement hole is connected with a blocking bolt 19. By providing the blocking bolt 19, when the damping liquid is used for a long time, the maintenance personnel can unscrew the blocking bolt 19 to make the damping liquid in the cylinder 4 flow out for replacement; the first arc plate 11 and the second arc plate 11 are provided with a replacement hole. The outer sides of the plates 12 are in contact with the annular inner wall of the cylinder 4; a first sealing ring is installed between the inner wall of the rotating sleeve 24 and the outer cylindrical wall of the movable rod 5; a second sealing ring is installed between the through hole and the outer cylindrical wall of the movable rod 5; a third sealing ring is installed between the outer cylindrical wall of the rotating sleeve 24 and the inner wall of the sealing ring 17; a connecting hole is provided on the outer cylindrical wall of the cylinder 4; a connecting bolt 21 is connected to the internal thread of the connecting hole; a thread groove is provided on the outer cylindrical wall of the sealing ring 17; the bottom end thread of the connecting bolt 21 is installed in the thread groove; when parts in the cylinder 4 need to be maintained or replaced, maintenance personnel can disassemble the sealing ring 17 through the connecting bolt 21, thereby facilitating maintenance and replacement of parts in the cylinder 4.

[0032] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A damping device for preventing rough throttle operation of an aircraft, characterized in that: include: An operating table (1), wherein an operating rod (2) is rotatably mounted on the top of the operating table (1), and an operating head (3) is fixedly mounted on the top of the operating rod (2); A damping assembly, wherein the damping assembly is arranged on the top surface of an operating table (1) and is used for buffering an operating rod (2), wherein the damping assembly comprises: two mounting plates (8), wherein the two mounting plates (8) are fixedly mounted on the top surface of the operating table (1), wherein a cylinder (4) is arranged between the mounting plates (8), wherein a damping fluid is arranged inside the cylinder (4), wherein a sealing ring (17) is arranged inside the cylinder (4), wherein a movable rod (5) is movably sleeved inside the cylinder (4), wherein a through hole is provided on the bottom surface of the cylinder (4), wherein one end of the movable rod (5) passes through the through hole and extends to the outside, wherein a hinged plate (6) is fixedly mounted on the outer circumferential wall surface of the operating rod (2), wherein rotation holes (7) are provided on both sides of the hinged plate (6), wherein the movable rod (5) One end away from the cylinder (4) is hinged to the hinge plate (6), a hinge hole (9) is opened on one side of the mounting plate (8), a hinge shaft (10) is fixedly mounted on the outer circular wall of the cylinder (4), the hinge shaft (10) is hinged to the hinge hole (9), a first arc plate (11) is fixedly sleeved on the outer circular wall of the movable rod (5), a rotating sleeve (24) is rotatably mounted on the outer circular wall of the movable rod (5), the rotating sleeve (24) is rotatably sleeved on the inner wall of the sealing ring (17), a second arc plate (12) in contact with the first arc plate (11) is fixedly sleeved on the bottom end of the rotating sleeve (24), and a driving mechanism for driving the rotating sleeve (24) to rotate is installed on the side of the movable rod (5).

2. A damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: The driving mechanism comprises a mounting block (14) fixedly mounted on the side of the movable rod (5); a motor (18) is fixedly mounted on the bottom of the mounting block (14); an output end of the motor (18) is fixedly connected to a rotating shaft; a pinion (20) is fixedly mounted on the end of the rotating shaft; a large gear (13) is fixedly sleeved on the outer circular wall surface of the rotating sleeve (24); and the large gear (13) is meshed with the small gear (20).

3. A damping device for preventing rough throttle operation of an aircraft according to claim 2, characterized in that: A disc (25) is fixedly sleeved on the rotating shaft, an annular groove (23) is formed on the outer circumferential wall surface of the disc (25), a rotating ring (26) is fixedly sleeved on the outer circumferential wall surface of the rotating sleeve (24), and a side portion of the rotating ring (26) extends into the annular groove (23).

4. The damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: The bottom surface of the cylinder (4) is provided with an injection nozzle (16).

5. The damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: An anti-overflow groove (22) is provided on the top surface of the cylinder (4), and a sealing ring (15) for sealing the sealing ring (17) is fixedly sleeved inside the anti-overflow groove (22).

6. The damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: A replacement hole is provided on the bottom surface of the cylinder (4), and a blocking bolt (19) is threadedly connected to the interior of the replacement hole.

7. The damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: The outer sides of the first arc plate (11) and the second arc plate (12) are in contact with the annular inner wall of the cylinder (4); the inner wall of the rotating sleeve (24) and the outer circular wall of the movable rod (5) are provided with a first sealing ring; the through hole and the outer circular wall of the movable rod (5) are provided with a second sealing ring; and the outer circular wall of the rotating sleeve (24) and the inner wall of the sealing ring (17) are provided with a third sealing ring.

8. The damping device for preventing rough throttle operation of an aircraft according to claim 1, characterized in that: The outer circumferential wall surface of the cylinder (4) is provided with a connecting hole, the inner thread of the connecting hole is connected with a connecting bolt (21), the outer circumferential wall surface of the sealing ring (17) is provided with a thread groove, and the bottom end of the connecting bolt (21) is threadedly installed in the thread groove.

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