Undercarriage and aircraft

Abstract

The utility model discloses an undercarriage and an aircraft, and relates to the technical field of equipment. The frame body is used for being installed at the bottom of the aircraft, the frame body comprises an arch-shaped beam used for being connected with the aircraft and skid pipes connected with the two ends of the arch-shaped beam, the skid pipes are used for making contact with a supporting face, and a boosting assembly is arranged on the frame body and used for applying thrust in the direction opposite to the descending direction of the aircraft so as to reduce the descending speed of the aircraft. According to the undercarriage provided by the invention, the boosting assembly is arranged on the frame body of the undercarriage, and the thrust can be applied in the direction opposite to the descending direction of the aircraft through the boosting assembly, so that the descending speed of the aircraft is reduced, and the risk that the aircraft is damaged when falling to the ground can be reduced.

Description

Technical Field

[0001] This application relates to the field of equipment technology, and more specifically, to a landing gear and an aircraft. Background Technology

[0002] In this field, aircraft typically rely on rotors to generate lift, and both takeoff and landing require rotors to provide lift. However, during the use of aircraft, vibrations, component failures, and other reasons may cause the aircraft to lose power during flight, resulting in a crash and varying degrees of damage.

[0003] Therefore, how to reduce the risk of damage to the aircraft itself when it crashes has become a technical problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0004] In view of this, the purpose of this application is to provide a landing gear to reduce the risk of damage to the aircraft itself when it crashes to the ground.

[0005] Another object of this application is to provide an aircraft having the aforementioned landing gear.

[0006] To achieve the above objectives, this application provides the following technical solution:

[0007] A landing gear, comprising:

[0008] A frame for mounting on the bottom of an aircraft, the frame including an arcuate beam for connection to the aircraft and skid tubes connected to both ends of the arcuate beam, the skid tubes for contacting a support surface, and a booster assembly provided on the frame for applying thrust in the opposite direction of the aircraft's descent to reduce the descent speed of the aircraft.

[0009] Optionally, in the aforementioned landing gear, the bow-shaped beam includes a horizontal tube for connection with the aircraft and a bent tube for connection with the skid tube, wherein the angle between the bent tube and the horizontal tube is 120° to 150°.

[0010] Optionally, in the above-mentioned landing gear, two connecting pipes are connected between the bend of the bow-shaped beam and the skid tube, and the two connecting pipes are arranged symmetrically along the bend of the bow-shaped beam.

[0011] Optionally, in the above-mentioned landing gear, both ends of the bow-shaped beam are provided with the booster assembly, and the booster assembly includes two thrusters that apply thrust in opposite directions, and the two thrusters are respectively located in the two connecting pipes on the same side of the bow-shaped beam.

[0012] Optionally, in the landing gear described above, the two thrusters are located at ports of the two connecting pipes that are far apart from each other, and the end of the thruster away from the port is provided with a pipe blockage, while the end of the thruster near the port is provided with a sealed catapult, which is linked to the thruster.

[0013] Optionally, in the above-mentioned landing gear, the included angle between the connecting tube and the skid tube is 30° to 60°.

[0014] Optionally, in the aforementioned landing gear, the control end of each of the thrusters is used to connect to the flight control system of the aircraft, so as to control the thrust applied by the thrusters through the flight control system.

[0015] Optionally, in the above-mentioned landing gear, there are one or more bow-shaped beams, and each bow-shaped beam is connected at both ends to two parallel skid tubes.

[0016] Optionally, in the aforementioned landing gear, a buffer pad is provided on the skid tube.

[0017] An aircraft comprising landing gear as described in any of the preceding claims.

[0018] The landing gear provided in this application is connected to the aircraft via an arched beam in the frame, and the skid tube can contact the support surface to achieve takeoff and landing of the aircraft. Furthermore, a booster assembly is installed on the frame. When the aircraft malfunctions and crashes, the booster assembly can apply thrust in the opposite direction of the aircraft's descent to reduce the aircraft's descent speed, thereby reducing the risk of damage to the aircraft upon impact. As can be seen from the above example, the landing gear provided in this application, by installing a booster assembly on the landing gear frame, can apply thrust in the opposite direction of the aircraft's descent to reduce the aircraft's descent speed, thereby reducing the risk of damage to the aircraft upon impact.

[0019] The technical features mentioned above, those to be mentioned below, and those shown individually in the accompanying drawings can be combined arbitrarily, provided that the combined technical features are not contradictory. All feasible combinations of features are the technical content explicitly described herein. Any one of the multiple sub-features contained in the same statement can be applied independently, without necessarily being applied together with other sub-features. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0021] Figure 1 An isometric view of the landing gear provided in an embodiment of this application;

[0022] Figure 2 A top view of the landing gear provided in an embodiment of this application;

[0023] Figure 3 A front view of the landing gear provided in an embodiment of this application;

[0024] Figure 4 A cross-sectional view of the thrust member provided in an embodiment of this application;

[0025] Figure 5 This is a schematic diagram showing the distribution of the thrust element provided in an embodiment of this application.

[0026] Among them, 100 is the frame, 10 is the bow beam, 20 is the skid tube, 30 is the booster assembly, and 40 is the connecting tube;

[0027] 11 is a horizontal pipe, and 12 is a bent pipe;

[0028] 21 is a straight section, and 22 is a raised section;

[0029] 31 is the propulsion unit, 311 is the sealing catapult, and 312 is the pipeline plug. Detailed Implementation

[0030] The core of this application is to provide a landing gear that reduces the risk of damage to the aircraft itself when it crashes.

[0031] Another core aspect of this application is to provide an aircraft with the aforementioned landing gear.

[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0033] In related fields, aircraft such as helicopters and drones typically rely on rotors to generate lift, and both takeoff and landing require rotors to provide lift. However, during the use of aircraft, vibrations, component failures, and other reasons may cause the aircraft to lose power during flight, resulting in a crash and varying degrees of damage.

[0034] Therefore, such as Figure 1 As shown in the figure, this application discloses a landing gear, including a frame 100. By providing a booster assembly 30 on the landing gear frame 100, the booster assembly 30 can apply thrust in the direction opposite to the descent of the aircraft, thereby reducing the descent speed of the aircraft and thus reducing the risk of damage to the aircraft itself when it crashes to the ground.

[0035] The following will combine Figures 1 to 5 The landing gear disclosed in the embodiments of this application will be explained and described in detail.

[0036] The frame 100 can be installed on the bottom of the aircraft. For example... Figure 1 As shown, the frame 100 may include an arcuate beam 10 and skid tubes 20 connected to both ends of the arcuate beam 10. The arcuate beam 10 and the skid tubes 20 may be fixed together by welding or bolting to form the landing gear frame 100. The arcuate beam 10 can be connected to the aircraft, while the skid tubes 20 can contact the ground or other supporting surfaces to realize the take-off and landing actions of the aircraft.

[0037] like Figure 1 As shown, a booster assembly 30 is installed on the frame 100. When the aircraft malfunctions and crashes, the booster assembly 30 can apply thrust in the opposite direction to the aircraft's descent to reduce the aircraft's descent speed, thereby reducing the risk of damage to the aircraft upon impact.

[0038] In some embodiments, such as Figure 1 As shown, the bow-shaped beam 10 may include a horizontal tube 11 and bent tubes 12 located at both ends of the horizontal tube 11, and the included angle between the bent tubes 12 and the horizontal tube 11 may be 120° to 150°. The horizontal tube 11 may be connected to the aircraft, and the bent tubes 12 may be connected to the skid tube 20. Preferably, the horizontal tube 11 and the bent tubes 12 may be an integral structure, and the included angle between the bent tubes 12 and the horizontal tube 11 may be 135°, thereby reducing the instantaneous impact and vibration when the landing gear lands, ensuring the stability of the aircraft upon landing. It should be noted that the bent tubes 12 and the horizontal tube 11 may also be separate structures, and the bent tubes 12 and the horizontal tube 11 may be fixed by welding.

[0039] like Figures 1 to 5As shown, there are two connecting pipes 40 connecting the bend of the bow beam 10, i.e. the connection between the bend tube 12 and the horizontal tube 11, and the skid tube 20. The two connecting pipes 40 can be symmetrically arranged on both sides of the bend tube 12 of the bow beam 10, which can strengthen the connection between the bow beam 10 and the skid tube 20 and improve the overall stability of the landing gear.

[0040] In some embodiments, such as Figure 1 and Figure 2 As shown, one end of the connecting pipe 40 can be welded to the bend of the arched beam 10, and the other end of the connecting pipe 40 can be welded to the skid pipe 20. Furthermore, as... Figure 3 As shown, the included angle β between the connecting pipe 40 and the horizontal pipe 11 of the bow beam 10 can be 120° to 150°, and at the same time, as Figure 5 As shown, the included angle γ between the connecting pipe 40 and the skid pipe 20 can be 30° to 60°. Preferably, as shown... Figure 3 and Figure 5 As shown, the included angle β between the connecting pipe 40 and the horizontal pipe 11 of the bow beam 10 can be 135°, and the included angle γ between the connecting pipe 40 and the skid pipe 20 can be 45°, so that the two connecting pipes 40 can be set perpendicular to each other, thereby effectively reducing the instantaneous impact and vibration when the landing gear lands and ensuring the stability of the aircraft when it lands.

[0041] To ensure a smooth landing in the event of a malfunction, booster components 30 can be installed at both ends of the bow-shaped beam 10 to guarantee stability during landing and prevent skewing. For example, Figure 1 and Figure 4 As shown, the booster assembly 30 may include two thrusters 31 that apply thrust in opposite directions, and the two thrusters 31 may be located in two connecting pipes 40 on the same side of the bow beam 10, respectively. When the aircraft malfunctions and crashes, one of the thrusters 31 can apply a reverse thrust to reduce the aircraft's falling speed and reduce the risk of damage to the aircraft upon landing; when the aircraft malfunctions and crashes in the opposite direction, the other thruster 31 can apply a reverse thrust to reduce the aircraft's falling speed in the opposite direction and reduce the risk of damage to the aircraft upon landing in the opposite direction.

[0042] In some embodiments, such as Figure 4 As shown, the two thrusters 31 can be located at the ports of the two connecting pipes 40 that are far apart from each other. That is, one thruster 31 is located at the bend of the connecting pipe 40 near the bow beam 10, and the other thruster 31 is located at the bend of the other connecting pipe 40 away from the bow beam 10, so that the two thrusters 31 can apply thrust in opposite directions.

[0043] In some embodiments, such as Figure 4As shown, a pipe plug 312 is provided at the end of the thruster 31 furthest from the connecting pipe 40 to block the thrust of the thruster 31. Simultaneously, to ensure that the thruster 31 does not interfere with the normal operation of the landing gear, a sealed ejector 311 is provided at the end of the thruster 31 closest to the connecting pipe 40, and the sealed ejector 311 is linked to the thruster 31. When the aircraft is operating normally, the sealed ejector 311 can seal the port of the connecting pipe 40, allowing the aircraft to take off and land normally via the landing gear. When the aircraft malfunctions and crashes, the thruster 31 activates, and the sealed ejector 311 opens. At this time, the thruster 31 applies thrust in the opposite direction of the aircraft's descent, thereby reducing the aircraft's descent speed and lowering the risk of damage upon impact.

[0044] In the above embodiments, the thruster 31 can be a rocket thruster, which uses fuel combustion to generate high-pressure airflow, thereby generating reverse thrust. Of course, the thruster 31 can also be a propeller thruster, which uses rotating blades to generate reverse thrust.

[0045] In some embodiments, the control terminal of each thruster 31 can be connected to the flight control system of the aircraft. In the flight control system, the attitude angle of the aircraft can be determined by the gyroscope of the aircraft. In the event of an emergency, the thrusters 31 in the corresponding directions can be activated for different landing attitudes to slow down the landing speed of the aircraft.

[0046] In some embodiments, such as Figure 1 and Figure 2 As shown, one, two, three or more bow-shaped beams 10 can be used to improve the overall stability of the landing gear. At the same time, the two skid tubes 20 can be set in parallel, and the two ends of each bow-shaped beam 10 are connected to the two parallel skid tubes 20 respectively to ensure the smoothness of the aircraft landing through the landing gear.

[0047] In some embodiments, such as Figure 2 As shown, two bow-shaped beams 10 can be used, and two thrusters 31 are provided at both ends of each bow-shaped beam 10. The positions of each thruster 31 are symmetrically distributed along the bow-shaped beam 10 and the skid tube 20 to ensure the stability of the thrusters 31 applying reverse thrust, thereby reducing the risk of damage to the aircraft when it crashes.

[0048] In some embodiments, such as Figure 1 As shown, the skid tube 20 may include a straight section 21 and a raised section 22 that curves away from the support surface. The straight section 21 and the raised section 22 may be an integral structure or separate structures, and are connected by welding. The raised section 22 of the skid tube 20 reduces the impact upon landing, providing a cushioning effect.

[0049] Of course, in order to reduce the risk of damage to the aircraft itself when it crashes, buffer pads can also be installed on the skid tube 20. The buffer pads can be made of elastic materials, such as rubber, so as to reduce the impact of the aircraft crashing and reduce the risk of damage to the aircraft itself when it crashes.

[0050] The landing gear disclosed in this application is connected to the aircraft via the arched beam 10 of the frame 100, and the skid tube 20 can contact the support surface to realize the take-off and landing of the aircraft. Furthermore, a booster assembly 30 is provided on the frame 100. When the aircraft malfunctions and crashes, the booster assembly 30 can apply thrust in the opposite direction to the aircraft's descent to reduce the aircraft's descent speed, thereby reducing the risk of damage to the aircraft upon impact.

[0051] The landing gear disclosed in this application embodiment, by providing a booster assembly 30 on the landing gear frame 100, can apply thrust in the opposite direction to the descent of the aircraft through the booster assembly 30, thereby reducing the descent speed of the aircraft and thus reducing the risk of damage to the aircraft itself when it crashes to the ground.

[0052] This application also discloses an aircraft including the landing gear disclosed in the above embodiments. Therefore, the aircraft has all the technical effects of the above landing gear, which will not be repeated here.

[0053] The terms "first" and "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, not to describe a specific order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units may include steps or units not listed, but rather not listed.

[0054] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A landing gear, characterized in that, include: A frame (100) is used to be installed on the bottom of the aircraft. The frame (100) includes an arc-shaped beam (10) for connection with the aircraft and skid tubes (20) connected to both ends of the arc-shaped beam (10). The skid tubes (20) are used to contact the support surface. A booster assembly (30) is provided on the frame (100). The booster assembly (30) is used to apply thrust in the opposite direction of the aircraft's descent to reduce the descent speed of the aircraft.

2. The landing gear according to claim 1, characterized in that, The bow beam (10) includes a horizontal tube (11) for connection with the aircraft and a bent tube (12) for connection with the skid tube (20), the angle between the bent tube (12) and the horizontal tube (11) being 120° to 150°.

3. The landing gear according to claim 2, characterized in that, Two connecting pipes (40) are connected between the bend of the bow beam (10) and the skid tube (20), and the two connecting pipes (40) are arranged symmetrically along the bend of the bow beam (10) (12).

4. The landing gear according to claim 3, characterized in that, Both ends of the bow beam (10) are provided with the booster assembly (30), and the booster assembly (30) includes two thrusters (31) that apply thrust in opposite directions. The two thrusters (31) are located in the two connecting pipes (40) on the same side of the bow beam (10).

5. The landing gear according to claim 4, characterized in that, The two thrusters (31) are located at ports of the two connecting pipes (40) that are far apart from each other. The end of the thruster (31) away from the port is provided with a pipe plug (312), and the end of the thruster (31) close to the port is provided with a sealing catapult (311). The sealing catapult (311) is linked with the thruster (31).

6. The landing gear according to claim 5, characterized in that, The angle between the connecting pipe (40) and the skid pipe (20) is 30° to 60°.

7. The landing gear according to claim 4, characterized in that, The control terminal of each of the thrusters (31) is used to connect to the flight control system of the aircraft to control the thrust applied by the thruster (31) through the flight control system.

8. The landing gear according to claim 1, characterized in that, There are one or more bow beams (10), and each bow beam (10) is connected at both ends to two parallel skid tubes (20).

9. The landing gear according to any one of claims 1 to 8, characterized in that, The skid tube (20) is provided with a buffer pad.

10. An aircraft, characterized in that, Including the landing gear as described in any one of claims 1 to 9.

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