Mechanical brake structure suitable for aircraft wing

Abstract

The utility model relates to the technical field of unmanned aerial vehicle propeller braking, in particular to a mechanical brake structure suitable for an aircraft wing, which comprises a motor, a brake disc, a steering engine, a steering engine rocker arm and a tension spring, the brake disc is composed of an annular brake pad, a flexible brake pad and a traction arm, the brake pad is arranged in front of a rotor of the motor, the steering engine rocker arm swings, the brake pad is pushed through the traction arm, and the flexible brake pad is separated from the rotor of the motor; the rear end of the traction arm is further connected with a tension spring, the tension spring is in a stretched state, and the brake pad is pulled through the traction arm so that the flexible brake pad can make contact with a rotor of the motor. The electric energy loss of the brake device is reduced, the endurance time and the cruising distance of the aircraft are increased, the locking mode and the working mode of the motor can be freely switched according to requirements, and the reliability of a mechanical structure is larger than that of an electromagnetic brake structure.

Description

Technical Field

[0001] The utility model relates to the technical field of propeller brakes for unmanned aerial vehicles, and specifically provides a mechanical brake structure suitable for use on aircraft wings. Background Art

[0002] When flying, the aircraft usually has two states: vertical and level flight. In the level flight mode, the motor will stop or start according to the situation. In the stopped state, due to the existence of aerodynamic force, the propeller will continue to rotate, which will cause turbulence on the surface of the aircraft, seriously affecting the aerodynamic efficiency of the aircraft in the level flight state. Usually, to solve this problem, the motor will be powered on and the problem will be solved by electromagnetic braking, but this method will increase energy consumption and reduce the endurance of the aircraft, especially at higher speeds, in order to offset the aerodynamic force, more electricity will be consumed or the aerodynamic force cannot be offset and reverses.

[0003] Compared with electromagnetic brakes, mechanical brakes can effectively reduce the consumption of electrical energy, especially for long-range and long-endurance aircraft. Mechanical brakes have the advantages of lower energy consumption, can effectively increase aerodynamic efficiency, and can greatly increase the endurance of aircraft. However, mechanical brakes are currently usually used in the automotive field, and the mechanical brake structure suitable for aircraft is not yet mature, so mechanical brakes are rarely used in aircraft.

[0004] For example, the Chinese utility model patent with announcement number CN215293341U discloses a motor brake device for an electric vehicle, which can brake the motor through a mechanical braking mode. However, the braking is achieved by gear meshing, and a gear structure needs to be provided on the rotating shaft. However, the gear structure on the rotating shaft is prone to failure, which will cause the entire system to fail. The braking stability is low, and this structure is only suitable for motors with the rotating mechanism inside the cabin, and cannot be applied to fixed-wing aircraft.

[0005] For example, the Chinese utility model patent with publication number CN115473378A discloses a method of stopping a rotating shaft through a motor brake device through a gear structure. This structure can avoid interference from electromagnetic brakes, but the transmission structure requires high precision. When the small motor brakes, there are too many small structural components. It is also only applicable to motors with rotating mechanisms inside the cabin and cannot be used on fixed-wing aircraft. Utility Model Content

[0006] In order to solve the above-mentioned problems, the utility model provides a mechanical brake structure suitable for the wings of aircraft, which replaces the traditional electromagnetic brake method on the aircraft with a mechanical brake method, effectively improving the braking reliability, especially at a higher speed, the mechanical brake has a better effect in offsetting the aerodynamic force and avoids the problem of reversal of the electromagnetic brake. At the same time, the mechanical brake also reduces the power loss during braking.

[0007] The utility model provides a mechanical brake structure suitable for use on an aircraft wing, comprising: a motor, a brake disc, a steering gear, a steering gear rocker arm and a tension spring;

[0008] The rotor of the motor is connected to a propeller outside the aircraft, and the stator of the motor is fixed inside the aircraft;

[0009] The brake disc includes a brake pad and at least two pulling arms. The brake pad is annular, and the pulling arm is vertically connected to the ring surface of the brake pad. The brake pad is correspondingly arranged in front of the rotor of the motor and is parallel to the front end surface of the rotor. A flexible brake pad is arranged on the inner side of the brake pad.

[0010] The servo is connected to one end of the servo rocker arm, and the other end of the servo rocker arm is connected to the pulling arm; the servo rocker arm swings, and the brake pad is pushed through the pulling arm, so that the flexible brake pad is separated from the rotor of the motor;

[0011] The rear end of the pulling arm is also connected to a tension spring, and the tension spring is in a stretched state. The brake pad is pulled by the pulling arm, so that the flexible brake pad contacts the rotor of the motor.

[0012] Preferably, it also includes a motor seat and a brake disc rocker arm, the motor seat is arranged on the port of the propeller power cabin, and the stator of the motor is fixed on the motor seat;

[0013] A plurality of through holes are opened on the motor seat, through which the pulling arm passes, and the brake disc rocker arm is vertically connected to the rear end of the pulling arm, and the tension spring and the steering gear rocker arm are connected to the pulling arm through the brake disc rocker arm.

[0014] Preferably, the steering gear rocker arm is a Z-shaped rocker arm.

[0015] Preferably, the brake disc rocker arm is a T-shaped connecting plate, a waist hole is opened on the brake disc rocker arm, and the swing end of the servo rocker arm is movably connected in the waist hole.

[0016] Preferably, the flexible brake pad is made of rubber material.

[0017] Preferably, it also includes a steering gear seat, which is vertically connected by a horizontal plate and a vertical plate, the steering gear is fixed on the horizontal plate, and the vertical plate is connected to the motor seat.

[0018] An aircraft is provided with a mechanical brake structure suitable for the wing of the aircraft.

[0019] Compared with the prior art, the utility model can achieve the following beneficial effects:

[0020] The utility model replaces the traditional electromagnetic brake method on the aircraft with a mechanical brake method, and designs a reliable mechanical brake structure. The mechanical brake can increase the endurance time and cruising distance, especially when high speed or afterburner is not required, the mechanical brake can reduce energy consumption, thereby extending the operation time of the aircraft in the air, and then increasing its achievable cruising distance; the design of the mechanical brake structure allows the locking mode and working mode of the motor to be freely switched according to demand. In the locking mode, the brake disc and the motor are locked by a tension spring, and no electricity is required to maintain it; in the working mode, the brake disc is separated from the motor by a steering gear for power output, so that the braking system can maintain a low energy consumption level without sacrificing performance; the mechanical brake has higher reliability, a simpler mechanical structure, and is not easily affected by external factors such as temperature, humidity and electromagnetic interference; in addition, compared with the mechanical brake structure exposed to the outside, the steering gear and the tension spring in the utility model are both arranged in the propeller power compartment, which can better resist external interference. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the assembly relationship between the mechanical brake structure applicable to the wing of an aircraft and the aircraft according to an embodiment of the utility model;

[0022] Figure 2 It is a structural schematic diagram of a mechanical brake structure applicable to an aircraft wing provided according to an embodiment of the utility model;

[0023] Figure 3 It is a structural schematic diagram of a brake disc and a brake disc rocker arm provided according to an embodiment of the utility model;

[0024] Figure 4 It is a structural schematic diagram of a motor base provided according to an embodiment of the utility model;

[0025] Figure 5 It is a structural schematic diagram of a steering gear seat provided according to an embodiment of the utility model.

[0026] Reference numerals include:

[0027] Propeller power compartment 1, mechanical brake structure 2 suitable for aircraft wing, motor 21, brake disc 22, brake pad 221, pulling arm 222, flexible brake pad 223, servo 23, servo rocker arm 24, tension spring 25, motor seat 26, pulling arm through hole 261, motor wiring hole 262, brake disc rocker arm 27, waist hole 271, tension spring fixing hole 272, servo seat 28, horizontal plate 281, vertical plate 282, tension spring fixing bolt 29. DETAILED DESCRIPTION

[0028] Hereinafter, embodiments of the present utility model will be described with reference to the accompanying drawings. In the following description, the same modules are represented by the same reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, the detailed description thereof will not be repeated.

[0029] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and do not constitute a limitation of the utility model.

[0030] like Figure 1 and Figure 2 As shown, the embodiment of the utility model provides a mechanical brake structure 2 suitable for aircraft wings, which is used to brake the propeller on the aircraft wing, and is arranged at the front end of the propeller power compartment 1, and is mainly composed of a motor 21, a brake disc 22, a steering gear 23, a steering gear rocker arm 24, a tension spring 25, a motor seat 26, a brake disc rocker arm 27, a steering gear seat 28 and a tension spring fixing bolt 29, wherein the motor 21 drives the propeller to rotate in the vertical climbing step of the aircraft to provide the power required for climbing. The motor 21 is mainly divided into a rotor and a stator, and the rotor is connected to the propeller outside the propeller power compartment 1 to drive the propeller to rotate; the stator is fixed to the fixing part inside the propeller power compartment 1 to achieve the fixing of the motor 21.

[0031] like Figure 3 As shown, the brake disc 22 is mainly composed of a brake pad 221, a pulling arm 222 and a flexible brake pad 223, wherein the brake pad 221 is annular, arranged in front of the rotor of the motor 21, and corresponds to the position of the rotor. A flexible brake pad 223 is attached to the inner side of the brake pad 221, and the shape of the flexible brake pad 223 is also annular, and its preparation material is rubber. There are two pulling arms 222, which are respectively arranged at the two ends of the same side of the brake pad 221 and vertically connected to the annular surface of the brake pad 221. The connection method between the brake pad 221 and the pulling arm 222 can be welding or integrated processing injection molding. The brake pad 221 is arranged at the front end of the rotor of the motor 21, and the output shaft of the motor 21 passes through the inner diameter of the ring of the brake pad 221 and is connected to the propeller; the pulling arm 222 is arranged on the outside of the motor 21 parallel to the axial direction of the motor 21.

[0032] like Figure 4As shown, the motor seat 26 is a circular cap-shaped structure, specifically including a cap cover and a brim. The brim is provided with a lateral opening, and the motor seat 26 is installed on the front end port of the propeller power compartment 1 by means of a bolt and nut structure. The cap of the motor seat 26 is provided with two pulling arm through holes 261, one motor wiring hole 262, a threaded hole for fixing the motor 21, and a threaded hole for fixing the servo seat 28. The rear end of the stator of the motor 1 is fixed to the cap of the motor seat 26 through a threaded hole. The motor wiring hole 262 is used to pass the power cord of the motor 21. The two pulling arms 222 respectively pass through the two pulling arm through holes 261 to extend into the interior of the propeller power compartment 1 and are connected to the brake disc rocker arm 27, and the pulling arm 222 can move axially along the pulling arm through hole 261.

[0033] like Figure 5 As shown, the servo seat 28 is composed of a horizontal plate 281 and a vertical plate 282. The vertical plate 282 is installed on the inner side of the motor seat 26 by bolts passing through threaded holes. The servo 23 is installed on the horizontal plate 281 through the threaded holes of the bolts. The servo rocker arm 24 is a Z-shaped rocker arm. One end of the servo rocker arm 24 is connected to the servo 23, and the other end of the servo rocker arm 24 is connected to the brake disc rocker arm 27. Specifically, a vertical waist hole 271 is opened on the brake disc rocker arm 27. The upper end of the servo rocker arm 24 extends into the waist hole 271. Through the swing of the servo rocker arm 24, the brake disc rocker arm 27 and the brake disc 22 are driven to move. One end of the tension spring 25 is connected to the rear side of the servo rocker arm 24, and the other end of the tension spring 25 is fixed to the tension spring fixing bolt 29. The tension spring fixing bolt 29 is fixed to the servo seat 28 through the threaded holes on the servo seat 28. In the level flight stage of the aircraft, the tension spring 25 is always in a stretched state.

[0034] Based on the above structure, the process and principle of braking and unlocking the motor 21 by the mechanical brake structure 2 applied to the wing of the aircraft are described as follows:

[0035] The motor 21 needs to output power only during the vertical climb phase of the aircraft to drive the propellers on the wings of the aircraft to rotate, so as to provide the lift required for the aircraft to climb; during the level flight phase of the aircraft, it is not only necessary to shut down the motor 21, but also to lock the motor 21 to prevent the propellers from rotating due to wind and other factors, which will cause turbulence on the surface of the aircraft and seriously affect the aerodynamic efficiency of the aircraft in the level flight state. Therefore, the traditional brake system uses electromagnetic braking, which not only requires motor output power during the vertical climb phase, but also requires electromagnetic brakes to resist propeller rotation during the level flight phase of the aircraft. Therefore, the electromagnetic brake system also needs to be powered on during the level flight phase of the aircraft to resist propeller rotation, which greatly increases energy consumption and reduces the endurance time and cruising distance of the aircraft.

[0036] For the mechanical brake structure 2 applied to the wing of the aircraft in the embodiment of the utility model, the propeller on the wing is required to provide lift during the vertical climbing stage of the aircraft, so the motor 21 is powered on and is in the starting state. At this time, the steering gear 23 is powered on, and the steering gear rocker arm 24 is driven to swing through the internal driving gear, and the brake disc 22 is pushed forward through the brake disc rocker arm 27, so that the flexible brake pad 223 is separated from the rotor of the motor 21. At this time, the motor 21 can drive the propeller to rotate to provide lift for the aircraft.

[0037] After the aircraft enters the level flight stage from the vertical climb stage, the propeller on the wing is no longer needed to provide lift, so the motor 21 is powered off and in a shutdown state. At this time, the servo 23 is also powered off, and the tension spring 25 is in a stretched state. Under the action of elastic force, the tension spring 25 pulls the brake disc 22 backward through the servo rocker arm 24, so that the flexible brake pad 223 contacts the rotor of the motor 21. The friction between the flexible brake pad 223 and the rotor of the motor 21 locks the rotor of the motor 21, preventing the propeller from rotating in the level flight stage and affecting the airflow on the surface of the aircraft. The mechanical brake structure 2 on the wing of the aircraft in the embodiment of the utility model is applicable. The motor 21 and the servo 23 need to be powered on only in the vertical climb stage, and the time of the vertical climb stage is relatively short; in the level flight stage of the aircraft, braking can be achieved only through the mechanical structure, without power loss, which greatly reduces power loss.

[0038] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

[0039] The above specific implementation methods of the utility model do not constitute a limitation on the protection scope of the utility model. Any other corresponding changes and modifications made according to the technical concept of the utility model should be included in the protection scope of the claims of the utility model.

Claims

1. A mechanical brake structure suitable for use on an aircraft wing, characterized in that: include: Motor, brake disc, servo, servo rocker arm and tension spring; Wherein, the rotor of the motor is connected to a propeller outside the aircraft, and the stator of the motor is fixed inside the aircraft; The brake disc comprises a brake pad and at least two pulling arms, the brake pad is annular, and the pulling arm is vertically connected to the annular surface of the brake pad; the brake pad is correspondingly arranged in front of the rotor of the motor and is parallel to the front end surface of the rotor; a flexible brake pad is arranged on the inner side of the brake pad; The steering gear is connected to one end of the steering gear rocker arm, and the other end of the steering gear rocker arm is connected to the pulling arm; the steering gear rocker arm swings, and the brake pad is pushed by the pulling arm, so that the flexible brake pad is separated from the rotor of the motor; The rear end of the pulling arm is also connected to the tension spring, and the tension spring is in a stretched state. The brake pad is pulled by the pulling arm to make the flexible brake pad contact with the rotor of the motor.

2. The mechanical brake structure suitable for use on an aircraft wing as claimed in claim 1, characterized in that: It also includes a motor seat and a brake disc rocker arm, wherein the motor seat is arranged on the port of the propeller power cabin, and the stator of the motor is fixed on the motor seat; The motor seat is provided with a plurality of through holes, the pulling arm passes through the through holes, the brake disc rocker arm is vertically connected to the rear end of the pulling arm, and the tension spring and the steering gear rocker arm are connected to the pulling arm through the brake disc rocker arm.

3. The mechanical brake structure suitable for use on an aircraft wing as claimed in claim 2, characterized in that: The steering gear rocker arm is a Z-shaped rocker arm.

4. The mechanical brake structure suitable for use on an aircraft wing as claimed in claim 3, characterized in that: The brake disc rocker arm is a T-shaped connecting plate, a waist hole is opened on the brake disc rocker arm, and the swing end of the steering gear rocker arm is movably connected in the waist hole.

5. The mechanical brake structure suitable for use on an aircraft wing as claimed in claim 1, characterized in that: The flexible brake pad is made of rubber material.

6. The mechanical brake structure suitable for use on an aircraft wing as claimed in claim 2, It is characterized in that It also includes a steering gear seat, which is vertically connected by a horizontal plate and a vertical plate. The steering gear is fixed on the horizontal plate, and the vertical plate is connected to the motor seat.

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