Rotor electric brake device

Abstract

The invention relates to the technical field of unmanned helicopter rotor brake systems, in particular to a rotor electric brake device which comprises an electromechanical actuating mechanism and a controller, the electromechanical actuating mechanism comprises a brake shell, a motor, a speed reducer, a lead screw, a lead screw nut, a brake pad and a force transducer, the motor is mounted on the brake shell, and the motor is mounted on the brake shell. The motor drives the speed reducer, the speed reducer is connected with the lead screw through a gear, the lead screw is sleeved with the lead screw nut, the lead screw nut is connected with the brake pads, the brake pads are installed on the two sides of the brake disc, the brake shell is further provided with the force measuring sensor, and the controller is connected with the motor and the force measuring sensor. According to the rotor wing electric brake device, the electromechanical actuating mechanism is controlled through the controller to achieve braking and brake loosening, the rotor wing electric brake device is suitable for the unmanned helicopter, traditional mechanical control type, hydraulic and pneumatic actuating type braking is replaced, full-electric automation and high-integration development of the unmanned helicopter is facilitated, the installation space is small, and maintenance is convenient.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned helicopter rotor brake systems, and in particular to a rotor electric brake device. Background Art

[0002] At present, there are three types of rotor brake devices used in domestic helicopters: mechanically controlled, hydraulically and pneumatically actuated. All of them are on manned helicopters and brakes are performed by pilots. The representatives of mechanically controlled rotor brake devices are caliper type and disc type. Braking is achieved by eliminating the brake gap through mechanical manipulation, and the brake is released by the spring after the control force is released. The hydraulic and pneumatic caliper type uses the hydraulic and pneumatic pistons in the cylinder to compress the brake disc and plate under the action of system pressure to eliminate the brake gap and brake, and the brake is released by the automatic gap adjustment return mechanism composed of springs, spring sleeves, sleeves and pull rods after the system pressure is released.

[0003] Traditional mechanically operated, hydraulic and pneumatically actuated brake devices are not suitable for unmanned helicopters. However, with the development of fully electric automation and high integration of unmanned helicopters, the development of rotor electric brake devices that can automatically execute rotor brake command operations has become an inevitable demand and development direction for unmanned helicopter rotor brake devices. Summary of the invention

[0004] In order to solve the problems mentioned in the above background technology, the present invention provides a rotor electric brake device, which performs dynamic braking on the rotor system after the engine stops when the helicopter lands or lands, and performs static braking on the rotor system when the helicopter starts in strong winds and the rotor system is folded.

[0005] The present invention discloses the following technical scheme: a rotor electric brake device, comprising an electromechanical actuating mechanism and a controller, wherein the electromechanical actuating mechanism comprises a brake housing, a motor, a reducer, a screw, a screw nut, a brake pad and a force sensor, wherein the motor is mounted on the brake housing, the motor drives the reducer, the reducer is connected to the screw via a gear, the screw is mounted on the screw, the screw nut is connected to the brake pad, the brake pad is mounted on both sides of the brake disc, the brake housing is also mounted with a force sensor, and the controller is connected to the motor and the force sensor.

[0006] Furthermore, the motor is a brushless DC motor.

[0007] Furthermore, the reducer is a planetary gear reduction mechanism.

[0008] Furthermore, the controller and the electromechanical actuating mechanism are detachably mounted as one body.

[0009] Furthermore, the controller is also connected to a Hall sensor.

[0010] Beneficial effects: Compared with the prior art, the rotor electric brake device of the present invention controls the electromechanical actuator through a controller to achieve braking and releasing the brake. The electric control method can replace manual operation. It is suitable for unmanned helicopters, has a clever design, small installation space, and easy maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a schematic diagram of the overall structure of the rotor electric brake device of the present invention; Figure 2 This is a schematic diagram of the electromechanical actuating mechanism of the present invention; Figure 3 is a functional block diagram of the rotor electric brake device of the present invention; In the figure: 1-electromechanical actuator, 2-controller, 3-brake pad, 4-brake disc, 5-motor, 6-reducer, 7-screw, 8-screw nut, 9-force sensor, 10-gear. DETAILED DESCRIPTION

[0012] like Figures 1 to 3 As shown, a rotor electric brake device includes an electromechanical actuating mechanism 1 and a controller 2. The electromechanical actuating mechanism 1 includes a brake housing, a motor 5, a reducer 6, a screw 7, a screw nut 8, a brake pad 3 and a force sensor 9. The motor 5 is installed on the brake housing. The motor 5 drives the reducer 6. The reducer 6 is connected to the screw 7 through a gear 10. The screw nut 8 is installed on the screw 7. The screw nut 8 is connected to the brake pad 3. The brake pad 3 is installed on both sides of the brake disc 4. The motor 5 drives the screw 7 to rotate through the reducer 6. The screw 7 drives the screw nut 8 to move forward and backward, pushing the brake pad 3 to approach or move away from the brake disc 4 to achieve braking or releasing the brake. The brake housing is also equipped with a force sensor 9 for real-time thrust collection and thrust closed-loop control. The controller 2 is connected to the motor 5 and the force sensor 9. The controller 2 monitors the system thrust and the current of the motor 5 in real time, performs fault processing when a fault occurs, and reports the fault to the flight control computer.

[0013] The motor 5 is a brushless DC motor with high speed, small torque and low power performance, ensuring fast response of the mechanism; the reducer 6 is a planetary gear reduction mechanism to improve work efficiency; the controller 2 and the electromechanical actuator 1 can be detachably installed as one body to reduce installation space; the controller 2 is also connected to a Hall sensor for detecting the position of the screw nut 8.

[0014] When braking, the controller 2 sends out a command, the motor 5 works to drive the reducer 6, the reducer 6 drives the screw rod 7 to rotate, the screw rod 7 drives the screw nut 8 to move, and pushes the brake pad 3 to move toward the brake disc 4, so that the brake pad 3 applies pressure to the brake disc 4 to achieve braking. When releasing the brake, the motor 5 reverses, and the screw nut 8 drives the brake pad 3 away from the brake disc 4 to achieve brake release. The electric brake device is suitable for unmanned helicopters, replacing traditional mechanically operated, hydraulic and pneumatically actuated brakes, and is conducive to the development of fully electric automation and high integration of unmanned helicopters. It has a small installation space and is easy to maintain.

[0015] 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 technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A rotor electric brake device, comprising an electromechanical actuating mechanism (1) and a controller (2), characterized in that: The electromechanical actuating mechanism (1) comprises a brake housing, a motor (5), a reducer (6), a screw (7), a screw nut (8), a brake pad (3) and a force sensor (9), wherein the motor (5) is mounted on the brake housing, the motor (5) drives the reducer (6), the reducer (6) is connected to the screw (7) via a gear (10), the screw nut (8) is mounted on the screw (7), the screw nut (8) is connected to the brake pad (3), the brake pad (3) is mounted on both sides of a brake disc (4), the brake housing is also mounted with a force sensor (9), and the controller (2) is connected to the motor (5) and the force sensor (9).

2. The rotor electric brake device according to claim 1, characterized in that: The motor (5) is a brushless DC motor.

3. The rotor electric brake device according to claim 1, characterized in that: The reducer (6) is a planetary gear reduction mechanism.

4. The rotor electric brake device according to claim 1, characterized in that: The controller (2) and the electromechanical actuating mechanism (1) are detachably mounted as a whole.

5. The rotor electric brake device according to claim 1, characterized in that: The controller (2) is also connected to a Hall sensor.

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