A tilt-mounted shock absorbing nose landing gear for a drone

Abstract

The utility model provides an unmanned plane's tilt installation shock attenuation front landing gear, its innovation has adopted tilt type installation, external rudder, and elastic buffer design, can reduce the impact load of ground to unmanned plane in the take -off and landing taxiing stage, reduces the safety risk in process, simultaneously, external rudder design scheme can provide greater space for nose internal equipment cabin, in addition still convenient installation, debugging and overhaul.

Description

Technical Field

[0001] This utility model relates to a tilt-mounted shock-absorbing front landing gear for unmanned aerial vehicles (UAVs). Background Technology

[0002] Current drone landing gear typically includes skid-type, tricycle-type, and tailwheel-type. Skid-type landing gear is only suitable for relatively flat terrain and does not provide shock absorption; tailwheel-type landing gear is less stable than tricycle-type. During landing, the ground exerts a significant impact force on the nose landing gear. Without any cushioning, this impact force is directly transmitted to the fuselage through the landing gear wheels, causing damage to the drone and jeopardizing flight safety. Utility Model Content

[0003] To address the aforementioned problems in the prior art, this utility model provides a tilt-mounted shock-absorbing front landing gear for unmanned aerial vehicles (UAVs). It innovatively adopts tilt mounting, external servo motors, and elastic buffer design, which can reduce the impact load on the UAV from the ground during the takeoff, landing, and taxiing phases, thereby reducing safety risks during the process. At the same time, the external servo motor design can provide more space for the internal equipment compartment of the nose, and it is also convenient for installation, debugging, and maintenance.

[0004] According to this utility model, a tilt-mounted shock-absorbing front landing gear for an unmanned aerial vehicle (UAV) is provided, characterized by comprising:

[0005] Inclined connecting plate, servo bracket, upper bushing, upper torque arm joint, lower bushing, hollow sleeve, upper torque arm upper pin, torque arm middle pin, lower torque arm pin, upper torque arm, lower torque arm, wheel, elastic locking pin, wheel bracket, servo, servo rocker arm, connecting rod, telescopic inner cylinder, damping spring, wheel pin.

[0006] in:

[0007] The upper end of the inclined connecting plate is provided with a first connecting plate through hole for bolt connection to the bottom plate of the drone fuselage.

[0008] The lower end of the inclined connecting plate has a second connecting plate through hole in the diameter direction, which is used to connect to the first sleeve through hole in the diameter direction at the upper end of the hollow sleeve by bolts.

[0009] The lower end of the inclined connecting plate has a third through hole in the diameter direction, which is used to connect to the second through hole in the diameter direction of the hollow sleeve at the upper end by bolts.

[0010] The servo bracket is fixed to the lower end of the hollow sleeve by bolts, wherein the bolts pass through holes in the annular clamp of the servo bracket, so that the annular clamp is clamped onto the hollow sleeve.

[0011] The servo motor is bolted to the servo motor bracket.

[0012] The servo rocker arm is connected to the upper torque arm via a connecting rod, controlling the rotation of the wheels.

[0013] The upper end of the upper torque arm is connected to the upper torque arm joint via a pin.

[0014] The upper and lower ends of the upper torque arm joint are clamped by an upper bushing and a lower bushing, respectively, allowing it to rotate only around the axis of the hollow sleeve but not to move up and down.

[0015] The upper and lower torque arms are connected by a central pivot pin.

[0016] The lower torque arm is connected to the wheel bracket via a lower torque arm pin.

[0017] The wheel bracket is fixed to the lower end of the telescopic inner cylinder.

[0018] The wheels are connected to the wheel bracket via wheel pins and flexible retaining pins.

[0019] The telescopic inner cylinder passes through the damping spring.

[0020] The upper end of the damping spring contacts the boss of the hollow sleeve, and the lower end of the damping spring contacts the wheel bracket. Attached Figure Description

[0021] Figure 1 This is an exploded view of the structural composition of the tilt-mounted shock-absorbing front landing gear of a drone according to an embodiment of the present invention.

[0022] Figure 2 This is a schematic diagram of the wheel deflection of the tilted, shock-absorbing front landing gear of a drone according to an embodiment of the present invention.

[0023] Figure 3 This is a mid-side view of the tilted-mounted shock-absorbing front landing gear of a drone according to an embodiment of the present invention.

[0024] Figure 4 This is a schematic diagram of the center position of the tilted shock-absorbing front landing gear of a drone according to an embodiment of the present invention. Detailed Implementation

[0025] The embodiments of this utility model will be described below with reference to the accompanying drawings.

[0026] like Figures 1-4As shown, the tilt-mounted shock-absorbing front landing gear of a UAV according to an embodiment of the present invention includes: a tilt connecting plate 1, a servo bracket 2, an upper bushing 3, an upper torque arm joint 4, a lower bushing 5, a hollow sleeve 6, an upper torque arm upper pin 7-a, a torque arm middle pin 7-b, a lower torque arm pin 7-c, an upper torque arm 8, a lower torque arm 9, a wheel 10, an elastic locking pin 11, a wheel bracket 12, a servo motor 13, a servo motor rocker arm 14, a connecting rod 15, a telescopic inner cylinder 16, a damping spring 17, and a wheel pin 18.

[0027] The four first connecting plate through holes 1-a at the upper end of the inclined connecting plate 1 are used to connect to the base plate 20 of the UAV fuselage by bolts. The lower end of the inclined connecting plate 1 has two sets of second connecting plate through holes 1-b and third through holes 1-c in the diameter direction, which are bolted to the two sets of first sleeve through holes 6-a and second sleeve through holes 6-b in the diameter direction at the upper end of the hollow sleeve 6, respectively.

[0028] The servo bracket 2 is fixed to two sets of bolts in the diameter direction at the lower end of the hollow sleeve 6. At the same time, the annular clamp of the servo bracket 2 can be clamped onto the hollow sleeve 6 by passing bolts through the holes.

[0029] Servo 13 is bolted to servo bracket 2. Servo rocker arm 14 is connected to upper torque arm 8 via connecting rod 15, controlling the rotation of wheel 10.

[0030] The upper end of the upper torque arm 8 is connected to the upper torque arm joint 4 via the upper torque arm pin 7-a. The upper and lower ends of the upper torque arm joint 4 are respectively pressed by the upper bushing 3 and the lower bushing 5, and can only rotate around the axis of the hollow sleeve 6 but cannot move up and down. The upper torque arm 8 and the lower torque arm 9 are connected by the middle pin 19, and the lower torque arm 9 is connected to the wheel bracket 12 via the lower torque arm pin 7-c and fixed to the lower end of the telescopic inner cylinder 16.

[0031] The wheel 11 is connected to the wheel bracket 12 via the wheel pin 18 and the elastic retaining pin 11.

[0032] The center of the damping spring 17 passes through the telescopic inner cylinder 16. The upper end of the damping spring 17 contacts the boss 6-a of the hollow sleeve 6, and the lower end contacts the wheel bracket 12.

[0033] This utility model's tilted, shock-absorbing front landing gear for drones innovatively employs tilted mounting, external servo motors, and an elastic buffer design compared to other drone front landing gears. During taxiing, the drone's taxiing direction is controlled as follows: control signals are transmitted via circuitry to the external servo motor 13, driving the servo motor rocker arm 14 and connecting rod 15 to rotate the front landing gear wheel 10, thus controlling the drone's taxiing direction. During landing, when the front landing gear wheel 10 touches the ground, the wheel support 12 moves upward, pushing the telescopic inner cylinder 16 into the hollow sleeve 6. The lower torque arm 9 rotates counterclockwise around the central pin 7-b, and the upper torque arm 8 rotates clockwise around the upper torque arm pin 7-a. Figure 3 Simultaneously, the damping spring 17 contracts to absorb the impact force. After the taxiing ends and the drone lands smoothly, the damping spring 17 gradually extends under the action of the restoring force, causing the upper and lower torque arms to move in opposite directions until the nose landing gear returns to its normal state. During landing, the impact force of the ground on the drone is converted into the elastic potential energy of the damping spring 17. By using the damping spring 17 and the upper and lower torque arms 8 and 9, the impact force exerted by the ground through the wheels on the landing gear and fuselage is greatly reduced, the stress time is extended, the impact intensity during landing is mitigated, and the safety of the drone is improved.

[0034] The advantages and beneficial effects of this utility model include:

[0035] 1) An inclined landing gear installation was adopted.

[0036] The nose landing gear of a conventional drone is usually mounted vertically to the bottom of the fuselage, with a short buffer travel. In addition, the impact load during landing exerts a net upward force on the bottom of the fuselage, which can easily damage the structure.

[0037] This utility model innovatively adopts an inclined landing gear installation design. The axis of the front landing gear telescopic inner cylinder and hollow sleeve forms a certain angle with the fuselage bottom plate. At the same height, it provides a longer buffer stroke for the damping spring and telescopic inner cylinder, and at the same time, it decomposes the impact load force transmitted to the fuselage bottom plate, reducing the impact on the bottom plate.

[0038] 2) An external steering servo was adopted.

[0039] The rudder mechanism of the nose landing gear of a conventional UAV is usually fixed to the fuselage base plate, occupying a large amount of space in the nose equipment bay and significantly affecting the installation and fixation of equipment inside the bay. In addition, the installation of the rudder mechanism inside the fuselage makes the installation, debugging and maintenance of the nose landing gear more complicated, and the maintenance and support operation more difficult.

[0040] This utility model innovatively adopts an external rudder design, with the rudder connected to the hollow sleeve of the front landing gear outside the fuselage, providing more usable space for the nose equipment compartment, while also facilitating the installation, debugging and maintenance of the rudder.

[0041] 3) An elastic buffer design was adopted.

[0042] Conventional UAVs typically have no cushioning design or use small springs in their nose landing gear, resulting in poor cushioning. During takeoff and landing, the uneven runway causes repeated loads, making the structure prone to fatigue fracture. The impact load upon landing is also significant, and the impact energy can easily cause structural damage.

[0043] This utility model innovatively adopts an elastic buffer design. The front landing gear achieves effective buffering through the relative movement of the telescopic inner cylinder and the hollow sleeve, the contraction and extension of the damping spring, and the rotation of the torque arm, thereby reducing the impact of the ground on the fuselage structure during takeoff and landing.

Claims

1. A tilt-mounted shock-absorbing front landing gear for an unmanned aerial vehicle, characterized in that... include: Inclined connecting plate (1), servo bracket (2), upper bushing (3), upper torque arm joint (4), lower bushing (5), hollow sleeve (6), upper torque arm upper pin (7-a), torque arm middle pin (7-b), lower torque arm pin (7-c), upper torque arm (8), lower torque arm (9), wheel (10), elastic locking pin (11), wheel bracket (12), servo (13), servo rocker arm (14), connecting rod (15), telescopic inner cylinder (16), damping spring (17), wheel pin (18). in: The inclined connecting plate (1) has a first connecting plate through hole (1-a) at its upper end, which is used to connect to the bottom plate (20) of the UAV fuselage by bolts. The lower end of the inclined connecting plate (1) has a second connecting plate through hole (1-b) in the diameter direction, which is used to connect to the first sleeve through hole (6-a) in the diameter direction at the upper end of the hollow sleeve (6) by bolts. The lower end of the inclined connecting plate (1) has a third through hole (1-c) in the diameter direction, which is used to connect to the second through hole (6-b) in the diameter direction of the hollow sleeve (6) by bolts. The servo bracket (2) is fixed to the lower end of the hollow sleeve (6) by bolts, wherein the bolts pass through the holes on the annular clamp of the servo bracket (2), so that the annular clamp is clamped on the hollow sleeve (6). The servo (13) is bolted to the servo bracket (2). The servo rocker arm (14) is connected to the upper torque arm (8) via a connecting rod (15) to control the rotation of the wheel (10). The upper end of the upper torque arm (8) is connected to the upper torque arm joint (4) via a pin (7-a). The upper and lower ends of the upper torque arm joint (4) are pressed together by the upper bushing (3) and the lower bushing (5) respectively, and can only rotate around the axis of the hollow sleeve (6) but cannot move up and down. The upper torque arm (8) and the lower torque arm (9) are connected by a central pin (19). The lower torque arm (9) is connected to the wheel bracket (12) via the lower torque arm pin (7-c). The wheel bracket (12) is fixed to the lower end of the telescopic inner cylinder (16). The wheel (10) is connected to the wheel bracket (12) via a wheel pin (18) and a flexible retaining pin (11). The telescopic inner cylinder (16) passes through the damping spring (17). The upper end of the damping spring (17) contacts the boss of the hollow sleeve (6), and the lower end of the damping spring (17) contacts the wheel bracket (12).

2. The tilt-mounted shock-absorbing front landing gear of the UAV according to claim 1, characterized in that: During the drone's descent, when the landing gear wheel (10) touches the ground, the wheel support (12) moves upward, pushing the telescopic inner cylinder (16) into the hollow sleeve (6). The lower torque arm (9) rotates counterclockwise around the torque arm's central pin (7-b), and the upper torque arm (8) rotates clockwise around the upper torque arm's pin (7-a). The damping spring (17) contracts to absorb the impact force. When the taxiing ends, the damping spring (17) extends under the action of the restoring force, causing the upper torsion arm (8) to move counterclockwise and the lower torsion arm (9) to move clockwise, until the front landing gear returns to normal.

3. The tilt-mounted shock-absorbing front landing gear of the UAV according to claim 1 or 2, characterized in that: When the UAV is gliding, the control signal transmitted to the external servo motor (13) drives the servo motor arm (14) and the linkage (15) to rotate the front landing gear wheel (10) and control the gliding direction of the UAV.

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