A hydraulic IBC rotor system

Abstract

The utility model relates to a hydraulic IBC rotor system, which belongs to the field of aircraft technology, and solves the problems in the prior art that the hydraulic actuator has a complex structure with many parts, a large weight, and low reliability. The utility model includes an anti-rotation rod, a drive shaft, a hub, a blade, and a hydraulic assembly, wherein the blade can be driven by the hub to rotate around the anti-rotation rod, and can also be driven by the hydraulic assembly to change pitch relative to the hub; the hydraulic assembly is located at the top of the rotor system and can rotate synchronously with the hub. The utility model uses a hydraulic assembly to drive a single blade to rotate to change its lift angle, and the hydraulic assembly is driven by the hub, so that the control of a single blade of the rotor system can be achieved without the need to set up an additional power element. It has a simple structure, a small number of parts, light weight, and high reliability.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a hydraulic IBC rotor system. Background Art

[0002] The IBC (Individual Blade Control) rotor system is an advanced helicopter rotor system that achieves precise control of the helicopter's flight performance by independently controlling the pitch of each blade.

[0003] The IBC rotor system is mainly composed of blades, hubs, control mechanisms and rotor shafts. The control mechanism is the core part of the IBC rotor system, and its layout and performance directly affect the control accuracy and flight performance of the rotor system. The control mechanism usually includes components such as actuators, sensors and controllers. The actuator is responsible for adjusting the pitch of the blades according to the instructions of the controller, and the sensor is responsible for real-time monitoring of the status and position of the blades and feeding back the information to the controller. The controller needs to have high-performance computing power and precise control algorithms to ensure accurate control of the blade pitch.

[0004] The form of the actuator can vary according to different design requirements and technical choices. Common actuator forms include electric actuators, hydraulic actuators, pneumatic actuators, and electromagnetic actuators.

[0005] The hydraulic actuator is mainly composed of a hydraulic cylinder, a hydraulic source, a control element, and an auxiliary element, and is usually arranged between the root of the blade and the rotor main shaft. Each blade is equipped with an independent hydraulic actuator to control the pitch of the blade. The piston rod of the hydraulic actuator is connected to the pitch change mechanism of the blade, and the pitch of the blade is adjusted by the reciprocating motion of the piston rod.

[0006] Existing hydraulic actuators generally use motors or engines to drive hydraulic pumps. However, using motors to drive requires additional power supply, and using engines to drive requires the pressure oil to be transmitted to the propeller hub, which requires a rotating joint structure. Both solutions increase the number of parts, weight and cost, and reduce reliability. Utility Model Content

[0007] In view of the above analysis, an embodiment of the utility model aims to provide a hydraulic IBC rotor system to solve the problems of large number of parts, heavy weight and poor reliability in the prior art.

[0008] On the one hand, the utility model provides a hydraulic IBC rotor system, including an anti-rotation rod, a drive shaft, a hub, blades and a hydraulic assembly; wherein the anti-rotation rod is fixedly arranged on the fuselage of the aircraft, the drive shaft is transmission-connected to the power system of the aircraft, and the anti-rotation rod is coaxially arranged within the drive shaft; the hub is arranged on the top periphery of the drive shaft and can be driven to rotate by the drive shaft; the blades are arranged on the hub, and the blades are driven by the hub to rotate around the anti-rotation rod, and can also be driven by the hydraulic assembly to rotate relative to the hub; the hydraulic assembly is located at the top of the rotor system and can be driven by the hub.

[0009] Furthermore, the hydraulic assembly includes a reducer, a hydraulic pump, a controller, a hydraulic motor and an oil pipe; wherein the reducer is fixedly arranged at the top end of the anti-rotation rod, the input end of the reducer is transmission-connected to the drive shaft, and the output end of the reducer is transmission-connected to the hydraulic pump; the hydraulic pump and the hydraulic motor are connected through the oil pipe, and the controller is used to control the connection or disconnection of the oil pipe.

[0010] Furthermore, the output end of the hydraulic motor can drive the blade to rotate relative to the hub around the axis of the blade.

[0011] Furthermore, the controller includes a control panel and a solenoid valve; the control panel is arranged beside or above the hydraulic pump, the inlet end of the solenoid valve is connected to the outlet end of the hydraulic pump, the solenoid valve has a first outlet end, and the first outlet end is connected to the inlet end of the hydraulic motor; the control panel can control the state of the solenoid valve.

[0012] Furthermore, the aircraft has N blades, and the controller includes N groups of the solenoid valves, and the hydraulic assembly includes N hydraulic motors, where N is a positive integer greater than or equal to 2; the solenoid valves, the hydraulic motors and the blades are arranged in a one-to-one correspondence.

[0013] Furthermore, the hydraulic pump is a gear pump.

[0014] Furthermore, the housings of the reducer, hydraulic pump and controller are fixedly connected to form a whole.

[0015] Furthermore, a bracket is fixedly arranged between the hydraulic assembly and the hub.

[0016] Furthermore, there are a plurality of brackets, which are evenly distributed around the driving shaft.

[0017] Furthermore, the controller also includes a sensing unit, which is capable of monitoring the angular velocity and pitch of each blade.

[0018] Furthermore, the sensing unit includes an RVDT sensor and a resolver sensor, both of which are arranged inside the hydraulic motor.

[0019] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0020] 1. The utility model does not require additional motor drive or rotary joint, the number of parts is reduced, the overall weight is reduced, and the system reliability is good.

[0021] 2. The utility model adopts hydraulic drive, which has abundant driving force and high reliability; the hydraulic drive structure is simple and reliable, and has strong anti-fatigue ability.

[0022] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by implementing the present invention. The purpose and other advantages of the present invention can be achieved and obtained through the contents specifically pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are only used for the purpose of illustrating specific embodiments and are not to be considered as limiting the present invention. In the entire drawings, the same reference symbols represent the same components.

[0024] Figure 1 It is a schematic diagram of the structure of the hydraulic IBC rotor system of the utility model (only one blade is shown);

[0025] Figure 2 It is a longitudinal cross-sectional schematic diagram of the hydraulic IBC rotor system of the utility model;

[0026] Figure 3 This is a working principle diagram of the hydraulic component of the utility model.

[0027] Reference numerals:

[0028] 10-anti-rotation rod; 11-drive shaft; 12-hub; 13-blade; 14-hydraulic assembly; 141-reducer; 142-hydraulic pump; 143-controller; 144-hydraulic motor; 1441-rotor; 1442-stator; 145-oil pipe. DETAILED DESCRIPTION

[0029] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0030] Example 1

[0031] The purpose of the utility model is to provide a hydraulic IBC rotor system. The hydraulic IBC rotor system of the utility model is applicable to a helicopter type aircraft. Figure 1-Figure 2 The utility model discloses a hydraulic IBC rotor system, comprising an anti-rotation rod 10, a drive shaft 11, a hub 12, blades 13 and a hydraulic assembly 14. The anti-rotation rod 10 is fixedly connected to the fuselage of the aircraft and extends vertically upward from the fuselage of the aircraft. The drive shaft 11 is transmission-connected to a power mechanism in the fuselage and can be driven to rotate by the power mechanism. The anti-rotation rod 10 is coaxially arranged with the drive shaft 11, and the anti-rotation rod 10 is located inside the drive shaft 11. The hub 12 is arranged on the top periphery of the drive shaft 11 and can be driven to rotate by the drive shaft 11. The blades 13 are arranged on the hub 12 and can be driven to rotate by the hub 12. There are usually more than two blades 13. In this embodiment, three blades 13 can be arranged on the hub 12. Only one blade 13 is shown in the accompanying drawings, and the structures of the other blades 13 are the same as the one shown.

[0032] At the same time, the blades 13 can also be driven by the hydraulic assembly 14 to rotate relative to the hub 12, and the rotation can change the pitch of the blades 13. The hydraulic assembly 14 is located at the top of the rotor system and can rotate synchronously with the hub 12.

[0033] like Figure 2 As shown, the hydraulic assembly 14 includes a reducer 141, a hydraulic pump 142, a controller 143, a hydraulic motor 144 and an oil pipe 145. The reducer 141 is fixedly arranged at the top of the anti-rotation rod 10, the input end of the reducer 141 is transmission-connected with the drive shaft 11, and the output end of the reducer 141 is transmission-connected with the hydraulic pump 142; the hydraulic pump 142 is connected to the hydraulic motor 144 through the oil pipe 145, and the controller 143 is used to control the connection or disconnection of the oil pipe 145.

[0034] Specifically, Figure 2 As shown, the reducer 141 includes a reducer seat, a reducer housing, a gear set and a reducer output end. Among them, the bottom of the reducer seat is cylindrical and fixedly connected to the top of the anti-rotation rod 10, and a gear set is arranged on the top of the reducer seat. The reducer housing is sleeved outside the reducer seat and the gear set, and the bottom of the reducer housing is connected to the reducer seat through a rolling bearing. A fixed bracket 15 is arranged on the outer peripheral surface of the reducer housing, and the fixed bracket 15 is fixedly connected to the hub 12, so that the reducer housing constitutes the input end of the reducer 141, and can transmit the movement of the hub 12 to the reducer 141. A gear ring is arranged on the inner periphery of the reducer housing, and the gear ring is meshed with one or more of the gear sets to transmit power to the gear set. The gear shaft of the central gear of the gear set protrudes axially upward, constituting the output end of the reducer 141.

[0035] Preferably, there are multiple fixing brackets 15 , the specific number of which is the same as the number of blades 13 , and they are evenly distributed along the circumference of the hub 12 .

[0036] The hydraulic pump 142 is preferably a gear pump. Specifically, a central gear is provided at the output end of the reducer 141, and a gear meshing with the central gear is also provided in the hydraulic pump 142. The liquid in the cavity of the hydraulic pump 142 is pumped from the input end of the cavity to the output end of the cavity under the action of the two gears. Obviously, the hydraulic pump 142 can also be other types of pumps such as a piston pump and a centrifugal pump.

[0037] The controller 143 includes a control panel and a solenoid valve. The control panel is arranged beside or above the hydraulic pump 142. The working principle of the controller 143 is as follows: Figure 3 As shown. The inlet end of the solenoid valve is connected to the outlet end of the hydraulic pump 142, and the solenoid valve has a first outlet end, which is connected to the inlet end of the hydraulic motor 144; the control panel can control the state of the solenoid valve. The control panel is also connected to the flight control center signal of the aircraft, and can send or receive electrical signals, and can feed back various parameters of the rotor system to the flight control center, and receive control instructions from the flight control center, control the operation of the hydraulic assembly 14, and realize the control of the single blade of the rotor system.

[0038] The output end of the hydraulic motor 144 can drive the blade 13 to rotate relative to the hub 12 around the axis of the blade 13. The rotor 1441 of the hydraulic motor is fixed to the hub 12, and the stator 1442 is connected to the blade 13. When oil is supplied to the hydraulic motor 144, the stator 1442 of the hydraulic motor 144 rotates relative to the rotor 1441, driving the blade 13 to change pitch.

[0039] The aircraft has N blades 13 , and the controller 143 includes N groups of electromagnetic valves, and the hydraulic assembly 14 includes N hydraulic motors 144 , where N is a positive integer greater than or equal to 2. The electromagnetic valves, hydraulic motors 144 and blades 13 are arranged in a one-to-one correspondence.

[0040] Generally speaking, the aircraft is provided with three blades 13, or two blades 13, or four blades 13. Regardless of how many blades 13 there are, each blade 13 is correspondingly provided with a set of hydraulic motors 144 and a solenoid valve. This arrangement ensures that each blade 13 can be driven independently.

[0041] like Figure 2 As shown, in some preferred embodiments, the housings of the reducer 141 , the hydraulic pump 142 , and the controller 143 are fixedly connected to form a whole, and the whole rotates synchronously with the hub 12 during the aircraft performing a flight mission.

[0042] A fixing bracket 15 is fixedly arranged between the hydraulic assembly 14 and the hub 12 . There are a plurality of fixing brackets 15 , which are evenly distributed around the circumference of the drive shaft 11 .

[0043] Furthermore, the controller 143 also includes a sensing unit, which can monitor the angular velocity and pitch of each blade 13. The sensing unit includes sensors such as RVDT and resolver, which are placed inside the hydraulic motor to detect the motor angle and angular velocity.

[0044] The working principle of the hydraulic IBC rotor system of the utility model is as follows:

[0045] During the flight of a helicopter, the rotation speed of the rotor relative to the fuselage is usually a constant value, and the rotor has a large moment of inertia, and the rotation speed is stable with small fluctuations. This speed is used as a power source to drive the hydraulic pump 142, and the hydraulic pump 142 pumps the hydraulic oil to the controller 143. The controller 143 includes a control panel and components such as a solenoid valve and a pressure relief valve. The hydraulic oil controls the angle of the hydraulic motor, thereby controlling the pitch of the blades.

[0046] The hydraulic motor 144 may also be replaced with a hydraulic actuator to control the pitch change of the blades or the blade clamps.

[0047] Compared with the prior art, the beneficial effects of this application are:

[0048] 1. The hydraulic assembly is driven by the propeller hub, and no additional power source is required, which makes the overall structure simple, the number of parts is small, and the reliability is high.

[0049] 2. This application adopts hydraulic drive, which has abundant driving force, high reliability and strong anti-fatigue ability.

[0050] Example 2

[0051] This embodiment 2 provides a control method for a hydraulic IBC rotor system, using the hydraulic IBC rotor system disclosed in embodiment 1. The control method specifically includes the following steps:

[0052] S1: The controller 143 obtains flight parameters and feeds back the obtained parameters to the flight control center;

[0053] S2: The flight control center calculates and obtains target parameters according to the pre-stored model, and sends the target parameters to the controller 143;

[0054] S3: The controller 143 issues a control instruction to control the action of the solenoid valve.

[0055] In step S1 , the flight parameters include the pitch of each blade 13 , the state of each solenoid valve and the state of each hydraulic motor.

[0056] In step S2 , the flight control center calculates the pitch angle that each blade should reach based on parameters such as the current attitude, target attitude, current rotor phase, etc., and sends the pitch angle to the controller 143 .

[0057] In step S3, the controller 143 calculates the solenoid valve opening according to the instruction issued by the flight control center and the current pitch of the blade, and controls the corresponding solenoid valve switch, thereby controlling each blade to reach the required pitch.

[0058] Through the technical solution of this embodiment, real-time control of the pitch of a single blade can be achieved, and the hydraulic drive has sufficient power, high reliability and strong fatigue resistance.

[0059] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. A hydraulic IBC rotor system, characterized in that: It includes an anti-rotation rod, a drive shaft, a propeller hub, a blade and a hydraulic assembly; wherein the anti-rotation rod is fixedly arranged on the fuselage of the aircraft, the drive shaft is transmission-connected to the power system of the aircraft, and the anti-rotation rod is coaxially arranged inside the drive shaft; the propeller hub is arranged on the top periphery of the drive shaft and can be driven to rotate by the drive shaft; the blade is arranged on the propeller hub, and the blade is driven by the propeller hub to rotate around the anti-rotation rod, and can also be driven by the hydraulic assembly to rotate relative to the propeller hub; the hydraulic assembly is located at the top of the rotor system and can be driven by the propeller hub.

2. The hydraulic IBC rotor system according to claim 1, characterized in that: The hydraulic assembly includes a reducer, a hydraulic pump, a controller, a hydraulic motor and an oil pipe; wherein the reducer is fixedly arranged at the top end of the anti-rotation rod, the input end of the reducer is transmission-connected to the propeller hub, and the output end of the reducer is transmission-connected to the hydraulic pump; the hydraulic pump and the hydraulic motor are connected through the oil pipe, and the controller is used to control the connection or disconnection of the oil pipe.

3. The hydraulic IBC rotor system according to claim 2, characterized in that: The controller includes a control panel and a solenoid valve; the control panel is arranged beside or above the hydraulic pump, the inlet end of the solenoid valve is connected to the outlet end of the hydraulic pump, the solenoid valve has a first outlet end, and the first outlet end is connected to the inlet end of the hydraulic motor; the control panel can control the state of the solenoid valve.

4. The hydraulic IBC rotor system according to claim 3, characterized in that: The aircraft has N blades, and the controller includes N groups of solenoid valves, and the hydraulic assembly includes N hydraulic motors, where N is a positive integer greater than or equal to 2; the solenoid valves, the hydraulic motors and the blades are arranged in a one-to-one correspondence.

5. The hydraulic IBC rotor system according to claim 3, characterized in that: The hydraulic pump is a gear pump.

6. The hydraulic IBC rotor system according to claim 2, characterized in that: The housings of the reducer, hydraulic pump and controller are fixedly connected to form a whole.

7. The hydraulic IBC rotor system according to claim 1, characterized in that: A bracket is fixedly arranged between the hydraulic assembly and the hub.

8. The hydraulic IBC rotor system according to claim 7, characterized in that: There are a plurality of brackets, which are evenly distributed around the driving shaft.

9. The hydraulic IBC rotor system according to claim 3, characterized in that: The controller also includes a sensing unit capable of monitoring the angular velocity and pitch of each of the blades.

10. The hydraulic IBC rotor system according to claim 9, characterized in that: The sensing unit comprises an RVDT sensor and a resolver sensor, both of which are arranged inside the hydraulic motor.

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