Braking main wheel of unmanned aerial vehicle

Abstract

The invention relates to the technical field of airplane braking, in particular to an unmanned aerial vehicle braking main wheel which comprises an airplane wheel assembly and a braking assembly, the braking assembly comprises a braking shell assembly and a gap adjusting force return assembly, and a heat reservoir assembly and a cylinder base assembly are installed on the braking shell assembly. The cylinder base assembly is used for driving a friction disc of the heat reservoir assembly to make contact with a movable disc for friction braking. The gap adjusting return force assembly is arranged between the cylinder base assembly and the pressing ring and used for adjusting the size of the brake gap. The brake clearance is prevented from becoming large, it is guaranteed that the stroke needed by the piston is increased during braking, the problems of low braking efficiency and short airplane wheel service life caused by too high temperature are solved, and the reliability of the braking main airplane wheel is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft braking, and particularly to a brake main wheel for an unmanned aerial vehicle (UAV). Background Art

[0002] The brake main wheel is composed of a wheel assembly and a brake device, and is installed on the wheel axle of the main landing gear of the aircraft. During parking, taxiing, and landing, it bears the dynamic and static loads of the aircraft and supports the aircraft. When the aircraft taxis, the wheel assembly rolls on the ground, and the moving disk assembly on the brake device rotates synchronously with the wheel. The pressing disk, static disk, and pressure-bearing disk installed on the brake housing are relatively stationary and do not rotate, and the moving disk assembly and the static disk rotate relatively. When the aircraft brakes, under the action of the brake pressure, the piston moves forward, pressing the stationary pressing disk, static disk, and pressure-bearing disk against the rotating moving disk assembly. At this time, a frictional torque is generated between the brake disks and is transmitted to the wheel assembly through the concave key groove of the moving disk assembly, braking and stopping the aircraft during takeoff, landing, and parking, and converting the kinetic energy of the aircraft into heat energy through friction. When the brake is released, the piston retracts under the action of the return spring, the moving and static disks are released, and the wheel releases the brake.

[0003] At present, the UAV industry at home and abroad has developed rapidly. Generally speaking, UAVs are characterized by small size and light weight. Most UAVs weigh between 500 kg and 3 t, and some existing technologies cannot be directly applied to the brake main wheel of UAVs. Existing UAVs generally adopt an electro-hydrostatic braking system. The oil capacity in the system is limited. During the landing process of the aircraft, the vibration and impact are relatively large, which may push the piston back to the initial position, resulting in a larger brake clearance, an increased stroke required for the piston during braking, and a situation of insufficient oil, leading to the problem that the piston cannot press the brake disk and cause brake failure. At the same time, during the braking process, due to the small size of the brake main wheel of the UAV, the temperature of the brake disk is relatively high during braking, and the heat will be transferred to the oil through heat conduction and heat radiation, resulting in too high an oil temperature, a problem of reduced brake pressure, affecting the braking efficiency, and moreover, too high a temperature will affect the service life of the wheel assembly and increase the failure rate of the brake main wheel.

[0004] Therefore, it is necessary to provide a brake main wheel for a UAV to solve the above problems. Summary of the Invention

[0005] To solve the problems of the electro-hydrostatic braking system, where the oil capacity in the system is limited, the vibration and impact during aircraft landing are large, which may push the piston back to the initial position, increasing the braking gap, increasing the required stroke of the piston during braking, resulting in insufficient oil and causing the piston to fail to press the brake disc, leading to brake failure. At the same time, during braking, due to the small volume of the main brake wheel of the UAV, the temperature of the brake disc is relatively high during braking, and heat will be transferred to the oil through heat conduction and heat radiation, resulting in too high oil temperature and a problem of reduced braking pressure, affecting braking efficiency. Moreover, too high a temperature will affect the service life of the wheel assembly and increase the failure rate of the main brake wheel. The present invention provides a main brake wheel for a UAV to solve the existing problems.

[0006] The main brake wheel for a UAV of the present invention adopts the following technical solutions, including: It includes a wheel assembly and a brake assembly. The brake assembly includes: A brake housing assembly, on which a heat reservoir assembly and a cylinder seat assembly are installed. The cylinder seat assembly is used to drive the friction disc of the heat reservoir assembly to contact the moving disc for frictional braking; And a gap adjustment and return force assembly, which is arranged between the cylinder seat assembly and the pressing ring and is used to adjust the size of the braking gap; Among them, the gap adjustment and return force assembly includes: A pull rod, one end of which is arranged in the installation cavity provided between every two piston cavities, and the other end is connected to the pressing ring; A spring sleeve, which is sleeved and fixed on the pull rod in the installation cavity; A limit assembly, which is used to limit the movement of the spring sleeve on the pull rod; And a spring seat, which is sleeved on the outer peripheries of the limit assembly and the spring sleeve, and a spring is arranged between its outer periphery and the inner wall of the installation cavity. The spring is used for the reset of the pull rod.

[0007] A further technical solution of the present invention is that an insulating gasket ring is arranged between the piston output end on the cylinder seat assembly and the pressing ring. Among them, the insulating gasket ring is installed in the circular groove provided on the piston end face.

[0008] A further technical solution of the present invention is that the limit assembly includes: a limit sleeve, which is sleeved on the pull rod, one end of which faces the end of the spring sleeve, and the other end is provided with a limit lug, and the limit lug is restricted in the installation cavity by an elastic retaining ring.

[0009] A further technical solution of the present invention is that the spring seat includes: a cylinder body, one end of the cylinder body is a closed end, the closed end is penetrated through the pull rod, the inside of the closed end contacts the end of the spring sleeve facing away from the limit lug, and a limit disc is arranged on the outer periphery of the other end of the cylinder body. Among them, the spring is arranged between the limit disc and the end wall of the installation cavity penetrating the pull rod.

[0010] A further technical solution of the present invention is that the wheel assembly includes: A hub, on the outer peripheral surface of which a plurality of thermal plugs are provided, and on the inner ring thereof a plurality of guide rail bosses are evenly distributed. Guide rails are provided on the guide rail bosses, and a full-circle heat shield is installed on the guide rails. A valve assembly is installed on one side of the web hole of the hub; A movable rim, installed on the hub, with a sealing assembly provided between the movable rim and the hub, and the movable rim is used to limit the position of the main tire; And two semi-circular snap rings, arranged in the snap ring grooves provided on the hub, and the opposite ends of the two semi-circular snap rings are connected by a connecting piece to form an integral snap ring, and the integral snap ring is used to limit the axial movement of the movable rim.

[0011] A further technical solution of the present invention is that two bearing chambers are provided at the center of the hub. Tapered roller bearings are installed in the bearing chambers, and on the side of the two tapered roller bearings facing away from each other, there is an oil retaining ring that fits against the end face of the inner ring of the bearing. The oil retaining ring is used to prevent grease from being thrown out and contaminants from entering the bearing.

[0012] A further technical solution of the present invention is that the heat reservoir assembly is matched with the keyway on the brake housing assembly, and the circular hole on the pressure-bearing disc of the heat reservoir assembly is matched with the corresponding pressure-bearing cup on the brake housing assembly.

[0013] A further technical solution of the present invention is that the cylinder block assembly and the brake housing assembly are connected by high-strength bolts, and a washer is provided between the high-strength bolts and the cylinder block assembly.

[0014] A further technical solution of the present invention is that the piston is installed in the piston cavity, and a sealing ring and a protective ring are provided between the piston and the inner wall of the piston cavity.

[0015] A further technical solution of the present invention is that a bent pipe joint is connected to the pipeline interface of the cylinder block assembly, a plug is installed on the bent pipe joint, and the plug and the bent pipe joint are sealed to prevent oil leakage. A taper pin and a plug sleeve are installed at the end of the oil passage hole of the cylinder block assembly, and the taper pin and the plug sleeve are used to seal the oil passage hole of the cylinder block assembly.

[0016] The beneficial effects of the present invention are: Through the clearance-adjusting and back-force component provided by the present invention, when the vibration and impact are large during the aircraft landing process, the clearance-adjusting and back-force component reduces the vibration and impact during the landing of the main wheels of the aircraft, preventing the piston of the cylinder seat assembly from returning to the initial position, thereby avoiding an increase in the braking clearance, ensuring an increase in the required stroke of the piston during braking, and achieving stable braking. Secondly, by providing a heat insulation gasket ring between the piston output end and the pressing ring, the heat radiation of the hydraulic oil is isolated through the heat insulation gasket ring, reducing the influence of heat conduction on braking, thus solving the problems of low braking efficiency and low wheel life caused by excessive temperature, improving the reliability of the main braking wheels, and can be widely applied to the electro-hydrostatic braking system of unmanned aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0018] Figure 1 It is a schematic structural diagram of the main braking wheel of the present invention.

[0019] Figure 2 is Figure 1 The A-A cross-sectional structural diagram of the main braking wheel.

[0020] Figure 3 is Figure 1 The structural diagram of the wheel assembly of the main braking wheel.

[0021] Figure 4 is Figure 3 The B-B cross-sectional schematic diagram of the wheel assembly.

[0022] Figure 5 is Figure 1 The structural diagram of the braking assembly of the main braking wheel.

[0023] Figure 6 is Figure 5 The C-C cross-sectional structural diagram of the braking assembly.

[0024] Figure 7 is Figure 5 The structural diagram of the cylinder seat assembly of the braking assembly.

[0025] Figure 8 is Figure 7 The D-D cross-sectional schematic diagram of the cylinder seat assembly.

[0026] Figure 9 is Figure 7 The E-E cross-sectional schematic diagram of the cylinder seat assembly.

[0027] In the figure: 1. Wheel assembly; 2. Brake assembly; 3. Hub; 4. Movable wheel rim; 5. Semi-circular snap ring; 6. Guide rail; 7. Sealing ring; 8. Heat insulation screen; 9. Fusible plug; 10. Valve assembly; 11. Connecting piece; 12. Tapered roller bearing; 13. Oil baffle ring; 14. Guide rail screw; 15. Screw; 16. Cylinder block assembly; 17. Heat reservoir assembly; 18. Brake housing assembly; 19. High-strength bolt; 20. Washer; 21. Cylinder block; 22. Piston; 23. Pad ring; 24. Compression ring; 25. Elbow joint; 26. Sealing ring; 27. Protective ring; 28. Locking nut; 29. Taper pin; 30. Plug sleeve; 32. Pull rod; 33. Spring seat; 34. Spring; 35. Spring sleeve; 36. Limit sleeve; 37. Circlip. Specific implementation manner

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0029] An embodiment of a brake main wheel of a drone according to the present invention, as Figure 1 and Figure 2 shown, includes: a wheel assembly 1 and a brake assembly 2. The brake assembly 2 includes: a brake housing assembly 18 and a clearance adjustment and return force assembly. A heat reservoir assembly 17 and a cylinder block assembly 16 are installed on the brake housing assembly 18. The cylinder block assembly 16 is used to drive the friction disc of the heat reservoir assembly 17 to contact the moving disc for frictional braking; the clearance adjustment and return force assembly is arranged between the cylinder block assembly 16 and the compression ring 24 and is used to adjust the size of the brake clearance. In this embodiment, the clearance adjustment and return force assembly includes: a pull rod 32, a spring sleeve 35, a limit assembly, and a spring seat 33. One end of the pull rod 32 is arranged in an installation cavity provided on the cylinder block assembly 16 between every two piston cavities, and the other end of the pull rod 32 is connected to the compression ring 24; the spring sleeve 35 is sleeved and fixed on the pull rod 32 in the installation cavity, that is, in this embodiment, the spring sleeve 35 and the pull rod 32 are in an interference fit, and a frictional force is formed between the spring sleeve 35 and the pull rod 32; the limit assembly is used to limit the movement of the spring sleeve 35 on the pull rod 32; the spring seat 33 is sleeved on the outer periphery of the limit assembly and the spring sleeve 35, and a spring 34 is arranged between the outer periphery of the spring seat 33 and the inner wall of the installation cavity. The spring 34 is used for the reset of the pull rod 32. Among them, the limit assembly is used to limit the movement of the spring sleeve 35 to avoid abnormal movement due to the vibration of the aircraft during landing.

[0030] Exemplarily, as Figure 7 、 Figure 8 andFigure 9 As shown, in this embodiment, the cylinder block assembly 16 includes: a cylinder block 21, a piston 22, a spacer ring 23, a compression ring 24, an elbow joint 25, a sealing ring 26, a protective ring 27, a lock nut 28, a taper pin 29, a plug sleeve 30, and a plug cover 31. Among them, a heat insulation spacer ring 23 is provided between the output end of the piston 22 and the compression ring 24. In this embodiment, the heat insulation spacer ring 23 is installed in a circular groove provided on the end face of the piston 22 to ensure that the oil is less affected by heat radiation and heat conduction. The piston 22 is installed in the piston cavity, and a sealing ring 16 and a protective ring 27 are provided between the piston 22 and the inner wall of the piston cavity. The elbow joint 25 is connected to the pipeline interface of the cylinder block assembly 16 through the lock nut 28. The angle of the elbow joint 25 can be adjusted by using the lock nut 28. A plug cover 31 is installed on the elbow joint 25, and the plug cover 31 and the elbow joint 25 are sealed to prevent oil leakage. A taper pin 29 and a plug sleeve 30 are installed at the end of the oil hole of the cylinder block assembly 16, and the taper pin 29 and the plug sleeve 30 are used to seal the oil hole of the cylinder block assembly 16.

[0031] Exemplarily, in a specific embodiment, the limiting assembly includes: a limiting sleeve 36, which is sleeved on the pull rod 32, one end of which faces the end of the spring sleeve 35, and the other end of which is provided with a limiting lug, and the limiting lug is restricted in the installation cavity by an elastic retaining ring 37.

[0032] Exemplarily, in a specific embodiment, the spring seat 33 includes: a cylinder body, one end of the cylinder body is a closed end, the closed end is penetrated through the pull rod 32, the inside of the closed end contacts the end of the spring sleeve 35 facing away from the limiting lug, and a limiting disc is provided on the outer periphery of the other end of the cylinder body. Among them, the spring 34 is provided between the limiting disc and the end wall of the installation cavity penetrating the pull rod 32.

[0033] Exemplarily, as Figure 3 and Figure 4As shown, in a specific embodiment, the wheel assembly 1 includes: a hub 3, a movable rim 4, and two semi-circular snap rings 5. Three hot melt plugs 9 are arranged on the outer peripheral surface of the hub 3. Five guide rail bosses are evenly distributed on the inner ring of the hub 3. A guide rail 6 is fixedly installed on the guide rail bosses through guide rail screws 14. An integral heat insulation screen 8 is installed on the guide rail 6, that is, the integral heat insulation screen 8 is installed between the guide rail 5 and the hub 3 by using its own elasticity and is axially limited through a relief groove arranged on the guide rail boss. A valve assembly 10 is installed on one side of the web hole of the hub 3; the movable rim 4 is installed on the hub 3, and a sealing assembly is arranged between the movable rim 4 and the hub 3. The movable rim 4 is used to limit the position of the main tire, that is, there is a sealing ring groove designed on the hub 3, and a sealing ring 7 is installed in the sealing ring groove to seal the movable rim 4 and the hub 3; a snap ring groove is arranged on the hub 3, and the snap ring groove is an annular groove. The opposite ends of the two semi-circular snap rings 5 are connected through a connecting piece 11 to form an integral snap ring, and the integral snap ring is installed in the snap ring groove. The integral snap ring is used to limit the axial movement of the movable rim 4 on the hub 3 to prevent the main tire from slipping out of the hub 3. Among them, each connecting piece 11 is fixed on the semi-circular snap ring 5 by using two screws 15, and the two screws 15 are loosening-proofed by using a fuse.

[0034] Exemplarily, as Figure 4 As shown, in a specific embodiment, two bearing chambers are arranged at the center of the hub 3. Tapered roller bearings 12 are installed in the bearing chambers, and an oil retaining ring 13 that fits with the end face of the bearing inner ring is arranged on the side of the two tapered roller bearings 12 facing away from each other. The oil retaining ring 13 is used to prevent grease from being thrown out and contaminants from entering the bearings.

[0035] Exemplarily, as Figure 5 and Figure 6 As shown, in a specific embodiment, the heat reservoir assembly 17 is matched with the keyway on the brake housing assembly 18. The circular holes on the pressure-bearing disc of the heat reservoir assembly 17 are matched with the corresponding pressure-bearing cups on the brake housing assembly 18. The cylinder block assembly 16 and the brake housing assembly 18 are connected by high-strength bolts 19, and a washer 10 is arranged between the high-strength bolts 19 and the cylinder block assembly 16. That is, in this embodiment, eight circular holes are arranged on the pressure-bearing disc, and the eight circular holes are matched with the eight pressure-bearing cups on the brake housing assembly 18. Six high-strength bolts 19 sequentially pass through the washer 20 and the cylinder block assembly 16, and then are screwed into the bolt holes on the brake housing assembly. The high-strength bolts 19 are used to connect the cylinder block assembly 16 and the brake housing assembly 18. After the six high-strength bolts 19 are installed, they are loosening-proofed in pairs by using a fuse.

[0036] Working principle When the main landing gear vibrates and is impacted greatly during the aircraft landing process, the cylinder seat assembly 16 on the brake assembly 2 is impacted and vibrates. Since the clearance adjusting return force assembly is arranged between the cylinder seat assembly 16 and the pressing ring 24, and the pull rod 32 of the clearance adjusting return force assembly is arranged in the installation cavity of the cylinder seat assembly 16, when the cylinder seat assembly 16 vibrates, there is a tendency for the pull rod 32 and the spring sleeve 35 on it to move as a whole, that is, it will drive the pressing ring 24 to move, resulting in the piston 22 retracting and the brake clearance becoming larger. Designing the limit sleeve 36 can effectively prevent the overall movement of the pull rod 32 and the spring sleeve 35, avoid the piston 22 of the cylinder seat assembly 16 from returning to the initial position, and further avoid the increase of the brake clearance, ensure that the oil displacement during braking meets the consumption of the required stroke of the piston, and achieve stable braking.

[0037] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An unmanned aerial vehicle braking main wheel, comprising a wheel assembly and a braking assembly, characterized in that, Brake components include: The brake housing assembly is mounted with a heat storage assembly and a cylinder seat assembly. The cylinder seat assembly is used to drive the friction disc of the heat storage assembly to contact the moving disc for friction braking. and a gap adjustment return force assembly, which is arranged between the cylinder seat assembly and the clamping ring and is used to adjust the brake gap size; Among them, the gap adjustment and return force components include: A pull rod, one end of which is arranged in a mounting cavity provided between every two piston cavities, and the other end of which is connected to the clamping ring; A spring sleeve, which is fixed on the pull rod in the installation cavity; A limit assembly, used to limit the movement of the spring sleeve on the pull rod; And a spring seat, which is sleeved on the outer periphery of the limiting component and the spring sleeve, and a spring is arranged between the outer periphery and the inner wall of the installation cavity, and the spring is used for resetting the pull rod.

2. The main wheel of the drone brake according to claim 1, characterized in that A heat-insulating gasket is provided between the piston output end and the clamping ring on the cylinder seat assembly, wherein the heat-insulating gasket is installed in a circular groove provided on the piston end surface.

3. A main wheel for an unmanned aerial vehicle brake according to claim 1, wherein The limiting assembly includes: a limiting sleeve, which is sleeved on the pull rod, with one end facing the end of the spring sleeve and the other end provided with a limiting lug, which is limited in the installation cavity by an elastic retaining ring.

4. The main wheel of the drone brake according to claim 1, characterized in that The spring seat includes: The cylinder body has one end which is a closed end and is passed through the pull rod. The interior of the closed end contacts the end of the spring sleeve which is away from the limiting lug. A limiting disk is provided on the outer periphery of the other end of the cylinder body, wherein the spring is provided between the limiting disk and the end wall of the pull rod which is passed through the mounting cavity.

5. A main wheel of an unmanned aerial vehicle brake according to claim 1, characterized in that, The wheel assembly includes: The wheel hub has multiple thermal plugs on its outer circumference, multiple guide rail bosses evenly distributed on its inner ring, guide rails on the guide rail bosses, and a full-circle heat shield installed on the guide rails. A valve assembly is installed on one side of the web hole of the wheel hub; A movable rim is mounted on the wheel hub, a sealing assembly is provided between the movable rim and the wheel hub, and the movable rim is used to limit the position of the main tire; And two semicircular snap rings are arranged in the snap ring grooves arranged on the wheel hub, and the opposite ends of the two semicircular snap rings are connected by a connecting piece to form an integral snap ring, which is used to limit the axial movement of the movable wheel rim.

6. The main wheel of a drone brake according to claim 5, characterized in that There are two bearing chambers in the center of the wheel hub, and tapered roller bearings are installed in the bearing chambers. Oil retaining rings that fit with the end faces of the inner rings of the bearings are provided on the opposite sides of the two tapered roller bearings. The oil retaining rings are used to prevent grease from being thrown out and contaminants from entering the bearings.

7. The main wheel of a drone brake according to claim 1, characterized in that, The heat storage assembly cooperates with the keyway on the brake housing assembly, and the circular hole on the pressure plate of the heat storage assembly cooperates with the corresponding pressure cup on the brake housing assembly.

8. A main wheel for braking an unmanned aerial vehicle according to claim 7, characterized in that, The cylinder seat assembly and the brake housing assembly are connected by high-strength bolts, and washers are provided between the high-strength bolts and the cylinder seat assembly.

9. The main wheel of an unmanned aerial vehicle brake according to claim 1, wherein, The piston is installed in the piston cavity, and a sealing ring and a protective ring are provided between the piston and the inner wall of the piston cavity.

10. The main wheel of the drone brake according to claim 1, characterized in that, An elbow joint is connected to the pipeline interface of the cylinder seat assembly, and a plugging cover is installed on the elbow joint. The plugging cover and the elbow joint are sealed to prevent oil leakage. A tapered pin and a plugging sleeve are installed at the end of the oil passage hole of the cylinder seat assembly. The tapered pin and the plugging sleeve are used to seal the oil passage hole of the cylinder seat assembly.

Images