Damping structure for helicopter

Abstract

The utility model relates to the technical field of helicopter rotors, in particular to a damping structure for a helicopter, which comprises a connecting shaft, a damping bearing and a swing identification structure, the damping bearing is used for reducing vibration in the operation process of the helicopter, and the swing identification structure is used for identifying the centrifugal force of blades on the connecting shaft. The damping bearing comprises a shell, damping blades, a damping body and an inner shaft sleeve, the inner shaft sleeve is used for containing a rotating shaft of the blades, the rotating shaft is rotationally connected with the inner shaft sleeve, and the damping blades are concentrically and evenly distributed along the axis of the inner shaft sleeve. The problem that an existing shimmy damping structure for the helicopter is complex and not easy to maintain or replace is effectively solved. The damping bearing composed of the shell, the damping blade, the damping body, the inner shaft sleeve and the limiting ring is adopted, deflection generated by the blade can be swung under the action of the damping body and the damping blade, and vibration generated by the blade can be absorbed by the damping body in the swinging process.

Description

Technical Field

[0001] This utility model relates to the field of helicopter rotor technology, specifically to a shock-absorbing structure for helicopters. Background Technology

[0002] During the rotation of a helicopter rotor, the helicopter takes off, lands, and hovers by changing the angle of the blades. During the rotor rotation, the blades will vibrate with different intensities when they encounter unstable airflow. Existing methods for damping the vibrations generated by the rotor use air springs or hydraulic cylinders.

[0003] However, the air springs or hydraulic cylinders mounted on the blade shaft require corresponding auxiliary structures to be installed simultaneously, which makes the surrounding structure of the blade shaft more complex and difficult to repair or replace. Utility Model Content

[0004] In view of the above situation and to overcome the defects of the prior art, the purpose of this utility model is to provide a shock-absorbing structure for helicopters, which effectively solves the problem that the existing anti-sway structures for helicopters are relatively complex and difficult to repair or replace.

[0005] The technical solution provided by this utility model is a shock-absorbing structure for helicopters, including a connecting shaft, a shock-absorbing bearing, and a swing recognition structure. The shock-absorbing bearing is located at one end of the connecting shaft and connected to the helicopter blades to reduce vibration during helicopter operation. The swing recognition structure is located on the connecting shaft to identify the magnitude of the centrifugal force exerted on the connecting shaft by the blades.

[0006] The damping bearing includes a housing, damping blades, a damping body, and an inner bushing. The inner bushing is located inside the housing to accommodate the rotating shaft of the blades. The rotating shaft is rotatably connected to the inner bushing. The damping blades are evenly distributed concentrically along the axis of the inner bushing. The damping body is an elastic structure and fills the space between the housing, the inner bushing, and the damping blades to dampen the blades.

[0007] Preferably, the diameters of two adjacent damping blades are staggered.

[0008] Preferably, the swing recognition structure includes a cylinder and an oil pump. The end of the connecting shaft away from the shock-absorbing bearing is inserted into the cylinder and is provided with a piston. The cylinder has through holes on both sides of the piston for hydraulic oil to enter and exit. The oil pump is located outside the cylinder and communicates with the through holes for inputting or outputting hydraulic oil into or out of the cylinder.

[0009] Preferably, the swing recognition structure further includes a sensor, which is located between the oil pump and the cylinder to detect the pressure value when hydraulic oil flows in or out.

[0010] Preferably, the sidewall of the cylinder body that contacts the connecting shaft is provided with a plurality of first oil seals evenly distributed along the axial direction of the connecting shaft, and the outer edge surface of the piston that contacts the cylinder body is provided with a plurality of second oil seals evenly distributed along the axial direction of the connecting shaft.

[0011] The beneficial effects of this utility model are as follows:

[0012] This utility model uses a shock-absorbing bearing composed of a shell, shock-absorbing blades, shock-absorbing body, inner bushing and limiting ring. Under the action of the shock-absorbing body and shock-absorbing blades, the deflection of the blades can be oscillated, and the shock-absorbing body can absorb the vibration generated by the blades during the oscillation.

[0013] This invention detects the movement of the connecting shaft through a cylinder, connecting shaft, piston, oil pump, and sensors. The sensors detect the speed and pressure of the hydraulic oil entering or exiting the through-hole. Through an algorithm, this can be converted into a current signal and transmitted back to the avionics system. The avionics system will determine whether to reduce engine power based on the current value, thereby reducing altitude or prompting human intervention to increase altitude and avoid turbulence areas, so as to ensure the safe operation of the blades and the safety of the aircraft flight. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0015] Figure 2 This is a cross-sectional front view schematic diagram of the present invention;

[0016] Figure 3 This is a utility model Figure 2 Enlarged view of A in the middle;

[0017] Figure 4 This is a cross-sectional structural diagram of the shock-absorbing bearing in this utility model;

[0018] In the diagram, 1-connecting shaft; 2-outer shell; 3-damping blade; 4-damping body; 5-inner bushing; 7-cylinder; 8-oil pump; 9-piston; 10-through hole; 11-sensor; 12-first oil seal; 13-second oil seal. Detailed Implementation

[0019] The specific embodiments of this utility model will be further described in detail below with reference to the accompanying drawings.

[0020] Refer to the instruction manual appendix Figure 1-4A vibration damping structure for helicopters includes a connecting shaft 1, a vibration damping bearing, and a oscillation recognition structure. The vibration damping bearing is located at one end of the connecting shaft 1 and connected to the helicopter blades to reduce vibration during helicopter operation. The oscillation recognition structure is located on the connecting shaft 1 to identify the magnitude of the centrifugal force exerted on the connecting shaft 1 by the blades. By setting the oscillation recognition structure, the power of the blades and the pressure they experience during rotation can be identified. When the vibration intensity exceeds a set value, the sensor will send a signal to the avionics system, which will then issue an alarm. The pilot will then manually adjust the engine power based on their judgment to ensure safe rotor operation and aircraft flight safety.

[0021] The shock-absorbing bearing includes a housing 2, shock-absorbing blades 3, a shock-absorbing body 4, and an inner bushing 5. The inner bushing 5 is located inside the housing 2 and is used to accommodate the rotating shaft of the blades. The rotating shaft is rotatably connected to the inner bushing 5. The shock-absorbing blades 3 are evenly distributed concentrically along the axis of the inner bushing 5. The shock-absorbing body 4 is an elastic structure and fills the space between the housing 2, the inner bushing 5, and the shock-absorbing blades 3 to dampen the blades. When the rotating shaft of the blades rotates under the drive of the engine, the blades at different angles will apply different degrees of external force to the bearing. The shock-absorbing body 4, which fills the housing 2, the inner bushing 5, and the shock-absorbing blades 3, absorbs the angle of the blade rotating shaft swing. At the same time, the shock-absorbing blades 3 support the shock-absorbing body 4 on the one hand, and absorb some of the vibration when the rotating shaft swings on the other hand, thereby improving the damping effect.

[0022] The diameters of two adjacent damping blades 3 are staggered, and the arrangement of the two adjacent damping blades 3 allows the inner bushing 5 to provide a larger swing amplitude for the shaft when it swings.

[0023] The swing recognition structure includes a cylinder 7 and an oil pump 8. The end of the connecting shaft 1 away from the shock-absorbing bearing is inserted into the cylinder 7 and is equipped with a piston 9. The cylinder 7 has through holes 10 on both sides of the piston 9 for hydraulic oil to enter and exit. The oil pump 8 is located on the outside of the cylinder 7 and communicates with the through holes 10 to input or output hydraulic oil to the cylinder 7. Through the sliding of the cylinder 7 and the connecting shaft 1, feedback can be given according to the state of the connecting shaft 1 under different pressure environments. After feedback, the signal is converted into an electrical signal by the circuit module in the helicopter and displayed on the instrument panel in the helicopter through a suitable algorithm.

[0024] When the vibration amplitude is too large, there will be stretching on both sides, and the cylinder body 7 and the connecting shaft 1 will slide left and right. The hydraulic oil in the cylinder body 7 will enter or be forced out of the cylinder body 7 through the through hole 10.

[0025] The swing recognition structure also includes a sensor 11, which is located between the oil pump 8 and the cylinder 7 to detect the pressure value when hydraulic oil flows in or out.

[0026] Hydraulic oil entering or exiting cylinder 7 passes through hydraulic sensor 11. Sensor 11 uses an algorithm to convert the hydraulic oil's flow rate and pressure into a current signal, which is then transmitted back to the avionics system. The avionics system uses the current value to determine whether to reduce engine power, thereby reducing altitude or prompting human intervention to increase altitude and avoid turbulent areas, in order to ensure the safe operation of the blades and the safety of the aircraft's flight.

[0027] The side wall of the cylinder body 7 that contacts the connecting shaft 1 is provided with a plurality of first oil seals 12 evenly distributed along the axial direction of the connecting shaft 1, and the outer edge surface of the piston 9 that contacts the cylinder body 7 is provided with a plurality of second oil seals 13 evenly distributed along the axial direction of the connecting shaft 1. Under the action of the first oil seals 12 and the second oil seals 13, the relative displacement between the connecting shaft 1 and the cylinder body 7 is not affected by a large frictional force.

[0028] When this utility model is in use, one end of the cylinder 7 is installed inside the helicopter, and the other end is used to accommodate the connecting shaft 1 and the piston 9 thereon. The end of the connecting shaft 1 away from the piston 9 is provided with a ring-shaped fixing ring. The outer shell 2 is inserted into the fixing ring, and the rotating shaft of the blade is inserted into the inner bushing 5 and rotates relative to the inner bushing 5.

[0029] When the shaft rotates with the blades, the helicopter can take off or hover by adjusting the angle of the blades. When the blades are adjusted, they will swing and squeeze the inner bushing 5 by rotating. During the process of squeezing the inner bushing 5, the shock absorber 4 is compressed. At the same time, under the action of the limiting ring 6 and the shock absorber blades 3, the shock absorber 4 will not move out of the outer shell 2, so the vibration of the shaft can be absorbed.

[0030] During the rotation of the blade, the rotating shaft swings and squeezes the inner bushing 5, and at the same time, it generates a certain axial force on the connecting shaft 1. The axial force on the connecting shaft 1 will cause the connecting shaft 1 to move relative to the cylinder body 7, and the piston 9 on the connecting shaft 1 will cause the hydraulic oil on both sides of the piston 9 to enter or be forced out of the cylinder body 7 through the through hole 10.

[0031] When hydraulic oil enters or exits cylinder 7, it passes through sensor 11. Sensor 11 identifies the flow rate and pressure value of the hydraulic oil. Through an algorithm, it is converted into a current signal and transmitted back to the avionics system. The avionics system determines whether to reduce engine power based on the current value, thereby reducing altitude or prompting human intervention to increase altitude and avoid turbulence areas, so as to ensure the safe operation of the blades and the flight safety of the aircraft.

[0032] This utility model adopts a shock-absorbing bearing composed of a shell 2, shock-absorbing blades 3, shock-absorbing body 4, inner bushing 5 and limiting ring 6. Under the action of shock-absorbing body 4 and shock-absorbing blades 3, the deflection generated by the blades can be oscillated, and during the oscillation, shock-absorbing body 4 can absorb the vibration generated by the blades.

[0033] This invention detects the movement of the connecting shaft 1 through the cylinder 7, connecting shaft 1, piston 9, oil pump 8, and sensor 11. The sensor 11 detects the speed and pressure of the hydraulic oil entering or exiting the through hole 10. Through an algorithm, this can be converted into a current signal and transmitted back to the avionics system. The avionics system will determine whether to reduce engine power based on the current value, thereby reducing altitude or prompting human intervention to increase altitude and avoid turbulence areas, so as to ensure the safe operation of the blades and the flight safety of the aircraft.

Claims

1. A shock-absorbing structure for a helicopter, comprising a connecting shaft (1), a shock-absorbing bearing, and a swing recognition structure, wherein the shock-absorbing bearing is disposed at one end of the connecting shaft (1) and connected to the blades of the helicopter to reduce vibration during helicopter operation, and the swing recognition structure is disposed on the connecting shaft (1) to identify the magnitude of the centrifugal force exerted on the connecting shaft (1) by the blades. Its features are, The shock-absorbing bearing includes a housing (2), shock-absorbing blades (3), a shock-absorbing body (4), and an inner bushing (5). The inner bushing (5) is located inside the housing (2) to accommodate the rotating shaft of the blades. The rotating shaft is rotatably connected to the inner bushing (5). The shock-absorbing blades (3) are evenly distributed concentrically along the axis of the inner bushing (5). The shock-absorbing body (4) is an elastic structure and fills the space between the housing (2), the inner bushing (5), and the shock-absorbing blades (3) to dampen the blades.

2. The shock-absorbing structure for helicopters according to claim 1, characterized in that: The diameters of two adjacent damping blades (3) are staggered.

3. The shock-absorbing structure for helicopters according to claim 1, characterized in that: The swing recognition structure includes a cylinder (7) and an oil pump (8). The end of the connecting shaft (1) away from the shock-absorbing bearing is inserted into the cylinder (7) and a piston (9) is provided. The cylinder (7) has through holes (10) on both sides of the piston (9) for hydraulic oil to enter and exit. The oil pump (8) is located outside the cylinder (7) and communicates with the through holes (10) for inputting or outputting hydraulic oil into or out of the cylinder (7).

4. A shock-absorbing structure for helicopters according to claim 3, characterized in that: The swing recognition structure also includes a sensor (11), which is located between the oil pump (8) and the cylinder (7) to detect the pressure value when hydraulic oil flows in or out.

5. A shock-absorbing structure for helicopters according to claim 4, characterized in that: The side wall of the cylinder (7) that contacts the connecting shaft (1) is provided with a plurality of first oil seals (12) evenly distributed along the axial direction of the connecting shaft (1), and the outer edge surface of the piston (9) that contacts the cylinder (7) is provided with a plurality of second oil seals (13) evenly distributed along the axial direction of the connecting shaft (1).

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