A gyrodyne landing gear

Abstract

The application discloses a self-rotating rotorcraft landing gear and relates to the technical field of aircrafts. The landing gear comprises a rack, a fixed arm and a supporting arm. A shock-absorbing mechanism is arranged between the rack and the fixed arm, and an anti-impact mechanism is arranged between the rack and the supporting arm. The top of the supporting arm is hinged to the anti-impact mechanism, and the bottom of the supporting arm is hinged to the fixed arm. The landing gear has excellent anti-impact and shock-absorbing performance, and can greatly reduce the risk factors caused by impact when the self-rotating rotorcraft lands. The landing gear is provided with the shock-absorbing mechanism and the anti-impact mechanism, and utilizes composite damping, so that the expensive carbon fiber or aviation aluminum material is not needed, the mechanical structure is simple, the manufacturing and assembly are convenient, and the cost of the landing gear can be reduced again. The application also provides multiple structures which can be adjusted according to actual use conditions, and has very wide actual use.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a self-rotating rotorcraft landing gear. BACKGROUND

[0002] An autogyro, or self-rotating rotorcraft, is a rotorcraft that generates lift via unpowered rotors that spin freely. In appearance, the autogyro is similar to a helicopter rotor, but the unpowered rotors of the autogyro must have airflow passing through the rotor disc to spin, thereby generating lift. Its forward thrust is provided independently by a propulsion propeller driven by an engine.

[0003] Because the flight speed and the way of providing lift of the autogyro are quite different from common aircraft, the technical requirements of the autogyro landing gear are also different from ordinary aircraft. Compared with fixed-wing aircraft and helicopters, the lift of the autogyro for maintaining the attitude of the body is weak when landing, and the body is easy to swing and thus produce strong impact with the ground. Therefore, the landing gear of the autogyro needs to have strong impact absorbing capacity.

[0004] A Chinese patent with application number "201921401745.3" proposes a landing gear for a rotorcraft, which is an arc-shaped structure landing gear made of carbon fiber material. A Chinese patent with application number "202020207621.8" proposes a self-rotating rotorcraft landing gear, which is designed by taking advantage of the stability of the triangular structure, and the material of the main landing gear is selected as 7075T6 aviation aluminum. The above two landing gears absorb the impact of the rotorcraft take-off and landing by the elasticity of conventional materials. Although these materials have good impact absorbing performance and light weight, the landing gear designed with these materials is an overall arc-shaped structure with a certain elasticity, which is easy to bounce after being impacted when the rotorcraft lands, causing safety accidents. Moreover, the prices of the above two materials are extremely high, making the cost of the landing gear extremely high.

[0005] A Chinese patent with application number "202210855930.X" proposes a landing gear for a rotorcraft, which absorbs the impact when landing by the combined action of the mechanical structures such as connecting arms, swing arms and elastic support arms and the frame. Although this landing gear has good impact absorbing performance, the mechanical structure is complex and the manufacturing cost is still high. SUMMARY

[0006] The purpose of the present application is to provide a self-rotating rotorcraft landing gear, which solves the problems of poor safety, complex mechanical structure and high manufacturing cost of the existing self-rotating rotorcraft landing gear.

[0007] To solve the above technical problems, the present application adopts the following technical solutions:

[0008] The self-rotating rotorcraft landing gear comprises a frame, a fixed arm and a support arm, a shock-absorbing mechanism is arranged between the frame and the fixed arm, an anti-impact mechanism is arranged between the frame and the support arm, the top of the support arm is hinged on the anti-impact mechanism, and the bottom of the support arm is hinged on the fixed arm.

[0009] Further, the frame and the fixed arm are arranged vertically, and wheels are installed at the two ends of the fixed arm.

[0010] Still further, the fixed arm is arranged as an arc-shaped member.

[0011] Still further, the shock-absorbing mechanism comprises shock-absorbing blocks, a first fixed plate is arranged on the frame, a second fixed plate is arranged at the top of the fixed arm, an installation groove is formed between the first fixed plate and the second fixed plate, and the shock-absorbing blocks are arranged in the installation groove.

[0012] Still further, the shock-absorbing blocks are composite materials made of negative Poisson's ratio materials and positive Poisson's ratio materials alternately.

[0013] Still further, the anti-impact mechanism comprises a spring shock absorber, a sliding block is arranged at the bottom of the spring shock absorber, an installation support is arranged on the frame, the spring shock absorber is arranged on the installation support, the top of the support arm is hinged on the sliding block, and the bottom of the support arm is hinged on the fixed arm.

[0014] Still further, the bottom of the support arm is hinged on the end of the fixed arm.

[0015] Still further, the bottom of the support arm is hinged on the middle side wall of the fixed arm.

[0016] Compared with the prior art, the self-rotating rotorcraft landing gear has the beneficial technical effects that:

[0017] The landing gear has excellent anti-impact and shock-absorbing performance, and greatly reduces the dangerous factors caused by impact when the self-rotating rotorcraft lands. The landing gear is provided with a shock-absorbing mechanism and an anti-impact mechanism, and utilizes composite shock-absorbing, so that expensive carbon fiber or aviation aluminum material is not needed, the mechanical structure is simple, the manufacturing and assembly are convenient, and the cost of the landing gear can be reduced again. The landing gear also provides multiple structures that can be adjusted according to actual use, and has very wide actual use. BRIEF DESCRIPTION OF DRAWINGS

[0018] The self-rotating rotorcraft landing gear will be further described below in combination with the drawings.

[0019] Figure 1 It is a structure schematic view of the self-rotating rotorcraft landing gear.

[0020] Figure 2 Another angle structure diagram of the landing gear of the autorotation rotorcraft of the present application;

[0021] Figure 3 Rear view of the landing gear of the autorotation rotorcraft of the present application;

[0022] Figure 4 Sectional view of the shock absorbing block of the present application;

[0023] Marked for explanation: 1, rack; 2, fixed arm; 3, support arm; 4, spring shock absorber; 5, shock absorbing block; 6, mounting support; 7, first fixed plate; 8, second fixed plate; 9, sliding block; 51, positive Poisson ratio cell; 52, negative Poisson ratio cell. DETAILED DESCRIPTION

[0024] As Figures 1-4 shown, a landing gear of an autorotation rotorcraft, comprising a rack 1, a fixed arm 2 and a support arm 3, the rack 1 is arranged inside the rotorcraft, a shock absorbing mechanism is arranged between the rack 1 and the fixed arm 2, an anti-impact mechanism is arranged between the rack 1 and the support arm 3, the top of the support arm 3 is hinged on the anti-impact mechanism, and the bottom of the support arm 3 is hinged on the fixed arm 2; the support arm 3 is a support rod connecting the fixed arm 2 and the anti-impact mechanism, which transmits the impact of the fixed arm to the anti-impact mechanism.

[0025] Specifically, the rack 1 and the fixed arm 2 are arranged vertically, the two ends of the fixed arm 2 extend outwardly from the rack 1, and the two ends of the fixed arm 2 are provided with landing wheels. The fixed arm 2 is used to extend the width of the landing gear, so that the landing gear is arranged from the rack 1 and extends a sufficient width for landing.

[0026] The fixed arm 2 is arranged as an arcuate member; the arcuate design not only increases the height of the fixed arm 2, adjusts the height during landing of the rotorcraft, but also improves the strength of the fixed arm 2, reduces the deformation of the fixed arm 2 due to repeated take-off and landing impacts, and the high-strength fixed arm 2 in the present application does not depend on high-performance materials, and only steel can meet the strength requirements.

[0027] The shock absorbing mechanism comprises a shock absorbing block 5, a first fixed plate 7 is connected to the rack 1 by bolts, a second fixed plate 8 is connected to the top of the fixed arm 2 by bolts, an installation groove is formed between the first fixed plate 7 and the second fixed plate 8, and the shock absorbing block 5 is arranged in the installation groove; the shock absorbing block 5 is clamped by the first fixed plate 7 and the second fixed plate 8, and the shock absorbing block 5 is limited by the installation groove.

[0028] As Figure 4As shown, the shock-absorbing block 5 is a composite material made of negative Poisson's ratio material and positive Poisson's ratio material alternately, and the cell wall can be made of ordinary alloy aluminum; the filling material of the positive Poisson's ratio cell 51 can be fresh water, seawater, etc., and the loading capacity can be 100%; the filling material of the negative Poisson's ratio cell 52 can be polyurethane foam, PVC foam, phenolic foam, aluminum foam or Voronoi foam. It should be noted that the above examples of the materials of the cell walls of the positive Poisson's ratio cell 51 and the negative Poisson's ratio cell 52 and the filling materials should not be construed as a limitation of the present application, and the materials of the cell walls of the positive Poisson's ratio cell 51 and the negative Poisson's ratio cell 52 and the filling materials can also be other materials, which should be changed according to actual needs.

[0029] The shock-absorbing block 5 can absorb a large impact and only produce a small deformation, and can absorb the impact from the fixed arm 2 while stabilizing the position of the fixed arm 2 during landing, preventing the fixed arm 2 from producing excessive deformation to cause metal fatigue; the size of the shock-absorbing block 5 and the filling material can be changed according to actual performance requirements.

[0030] The anti-impact mechanism comprises a spring shock absorber 4, the bottom of the spring shock absorber 4 is provided with a sliding block 9, the rack 1 is provided with a mounting support 6 through bolt connection, the spring shock absorber 4 is mounted on the mounting support 6, the top of the support arm 3 is hinged on the sliding block 9, and the bottom of the support arm 3 is hinged on the fixed arm 2.

[0031] The support arm 3 is hinged along the tangential direction of the arc of the fixed arm 2 and the sliding block 9. This design facilitates the support arm 3 to quickly transmit the impact received by the fixed arm 2, and reduces the stress at the hinged position of the support arm 3 and the fixed arm 2; the support arm 3 arranged along the tangential direction of the arc of the fixed arm 2 can further reduce the size of the landing gear; the landing gear of the rotorcraft is arranged on the internal rack 1, so that the size of the landing gear is smaller, which is beneficial to saving the internal volume of the rotorcraft.

[0032] In order to adapt to a wider range of use scenarios, the hinged position of the support arm 3 and the fixed arm 2 can be changed, which can be hinged at the end position of the free fixed end of the fixed arm 2, or can be hinged on the side wall of the middle part of the fixed arm 2, and the hinged position is selected according to actual use requirements.

[0033] The above-described embodiments are only descriptions of the preferred modes of the present application, and do not limit the scope of the present application, and various modifications and improvements to the technical solutions of the present application made by those skilled in the art without departing from the design spirit of the present application shall fall within the protection scope determined by the claims of the present application.

Claims

1. A gyrodyne landing gear, characterized by: The utility model provides a kind of shock-absorbing mechanism and anti-impact mechanism for fixed arm and support arm, the support arm is hinged on the anti-impact mechanism at top, and is hinged on the fixed arm at bottom. The shock-absorbing mechanism includes shock-absorbing block (5), the first fixed plate (7) is provided on the rack (1), the top of the fixed arm (2) is provided with the second fixed plate (8), the first fixed plate (7) and the second fixed plate (8) form installation slot, the shock-absorbing block (5) is arranged in the installation slot, the shock-absorbing block (5) is clamped by the first fixed plate (7) and the second fixed plate (8), the shock-absorbing block (5) is limited by installation slot;The shock-absorbing block (5) is a composite material made of negative Poisson's ratio material and positive Poisson's ratio material alternately, for directional absorption vertical impact energy transmitted by the fixed arm (2); The anti-impact mechanism includes spring shock absorber (4), the bottom of the spring shock absorber (4) is provided with sliding block (9), the spring shock absorber (4) is used to provide elastic buffer force when the sliding block (9) slides, the mounting support (6) is provided on the rack (1), the spring shock absorber (4) is arranged on the mounting support (6), the top of the support arm (3) is hinged on the sliding block (9), the bottom of the support arm (3) is hinged on the fixed arm (2), the support arm (3) is arranged along the tangential direction of the fixed arm (2) arc, for converting lateral impact force transmitted by the fixed arm (2) into linear motion of the sliding block (9) along sliding groove.

2. The gyrodyne landing gear according to claim 1, characterized in that: The rack (1) and the fixed arm (2) are vertically arranged, and the fixed arm (2) is provided with landing machine wheels at both ends.

3. The gyrodyne landing gear according to claim 1, characterized in that: The fixed arm (2) is arranged as an arc member.

4. The gyrodyne landing gear according to claim 1, characterized in that: The bottom of the support arm (3) is hinged on the end of the fixed arm (2).

5. The gyrodyne landing gear according to claim 1, characterized in that: The bottom of the support arm (3) is hinged on the middle side wall of the fixed arm (2).

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