Electrorheological shock-absorbing aircraft front landing gear and aircraft

Abstract

This invention provides an electrorheological damping aircraft nose landing gear and an aircraft. The landing gear includes: a damping cylinder; a piston rod, one end of which is slidably disposed within the damping cylinder, and the other end connected to an aircraft wheel, with a supporting shoulder in the middle; an electrorheological damping assembly, including a plurality of electrorheological damping units stacked on the supporting shoulder; each electrorheological damping unit includes an electrorheological elastomer, a first electrode plate, and a second electrode plate, with adjacent electrorheological elastomers sharing a single electrode plate; each first electrode plate is disposed on the inner wall of the damping cylinder via a first insulating retaining ring seat, with the end away from the retaining ring seat slidably contacting the outer wall of the piston rod; each second electrode plate is disposed on the outer wall of the piston rod via a second insulating retaining ring seat, with the end away from the retaining ring seat slidably contacting the inner wall of the damping cylinder; and a power supply, with the two electrodes electrically connected to the piston rod and the damping cylinder respectively, forming a conductive circuit; this invention can adaptively adjust its stiffness, improving the stability and comfort of aircraft operation.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing device technology, and in particular to an electrorheological damping aircraft nose landing gear and an aircraft. Background Technology

[0002] Landing gear is an accessory device located under an aircraft, used to support the aircraft during takeoff, landing, or taxiing, and for ground movement. When an aircraft touches down or taxis at high speed on an uneven runway, it experiences a violent impact with the ground. While pneumatic tires provide some cushioning, most of the impact energy is absorbed by shock absorbers. The nose landing gear of most aircraft uses complex hydropneumatic spring shock absorbers, which require excellent sealing performance, have complex structures, and poor environmental adaptability.

[0003] A traditional Chinese patent, ZL2023228585415, discloses a buffer mechanism and aircraft landing gear, including a piston cylinder, a piston rod, and an elastomer. One end of the piston rod is slidably disposed within the piston cylinder. The elastomer, made of a nonlinear elastic material, is disposed between the piston rod and the piston cylinder along the sliding direction of the piston rod. This patent utilizes the characteristics of nonlinear elastic materials to absorb impact kinetic energy, which improves shock absorption performance compared to traditional linear material elastomers. However, the road conditions faced by aircraft are variable, and the change in the elastic modulus of the selected nonlinear elastic material is fixed, without adaptive adjustments based on changes in road conditions. This is particularly problematic for the variable stiffness requirements of the shock absorber during aircraft landing and taxiing, failing to effectively improve passenger comfort.

[0004] Therefore, there is an urgent need for an electrorheological damping aircraft nose landing gear and aircraft that can adaptively adjust its stiffness under different operating environments during takeoff and landing, thereby improving the stability and comfort of aircraft operation. Summary of the Invention

[0005] The purpose of this invention is to provide an electro-variable damping aircraft nose landing gear and aircraft, which aims to solve the technical problem that traditional oil-gas spring dampers cannot simultaneously meet the different elastic stiffness requirements for takeoff and landing.

[0006] To achieve the above objectives, in a first aspect, the present invention provides an electrorheological damping aircraft nose landing gear, comprising:

[0007] Shock-absorbing cylinder block;

[0008] The piston rod has one end slidably mounted in the shock absorber cylinder, and the other end extends out of the shock absorber cylinder and is connected to an aircraft wheel, and a support shoulder is provided in the middle.

[0009] An electrorheological damping assembly is disposed in the damping cylinder and includes several electrorheological damping units, which are stacked sequentially from top to bottom on the support shoulder.

[0010] The electrorheological damping unit includes an electrorheological elastomer, a first electrode plate and a second electrode plate that are respectively in contact with the upper and lower surfaces of the electrorheological elastomer, and adjacent electrorheological elastomers share a common electrode plate; each first electrode plate is slidably disposed on the inner wall of the damping cylinder through a first insulating retaining ring seat, and its end away from the first insulating retaining ring seat is slidably in contact with the outer wall of the piston rod.

[0011] Each of the second electrode plates is slidably disposed on the outer wall of the piston rod via a second insulating retaining ring seat, and its end away from the second insulating retaining ring seat is slidably in contact with the inner wall of the shock-absorbing cylinder.

[0012] The power supply has two electrodes that are electrically connected to the piston rod and the damping cylinder respectively, forming a conductive circuit, so that each of the current-varying damping units exhibits different stiffness values ​​under different current intensities.

[0013] As a further improvement to the above solution, the electrorheological damping aircraft nose landing gear also includes a controller, which is electrically connected to the power supply and is used to control the output current of the power supply so that the electrorheological damping component exhibits different stiffness values ​​according to load changes.

[0014] As a further improvement to the above solution, the first insulating ring seat includes a first insulating annular body and a first annular groove disposed on the inner wall of the first insulating annular body.

[0015] The first annular groove is provided with an elastic element, and the outer edge of the first electrode plate can be compressed and locked in the first annular groove;

[0016] The second insulating retaining ring seat includes a second insulating annular body and a second annular retaining groove disposed on the outer wall of the second insulating annular body;

[0017] The second annular groove is provided with an elastic element, and the inner edge of the second electrode plate can be compressed and locked in the second annular groove.

[0018] As a further improvement to the above scheme, the electrovariable elastomer is ring-shaped;

[0019] The inner diameter of the electrorheological elastomer is smaller than the outer diameter of the second insulating retainer seat; and the outer diameter of the electrorheological elastomer is smaller than the inner diameter of the first insulating retainer seat.

[0020] As a further improvement to the above solution, the first electrode plate includes at least two first sector-shaped electrode plate units, and the outer edges of each first sector-shaped electrode plate unit are sequentially engaged in the first annular groove along the circumferential direction of the first insulating retaining ring seat.

[0021] The second electrode plate includes at least two second sector-shaped electrode plate units, and the inner edges of each second sector-shaped electrode plate unit are sequentially engaged in the second annular groove along the circumferential direction of the second insulating retaining ring seat.

[0022] As a further improvement to the above solution, the electrorheological damping aircraft nose landing gear also includes a cylinder head, which is detachably fastened to the damping cylinder body at the end away from the aircraft wheel.

[0023] The cylinder head includes a connecting flange and a cylindrical body integrally connected to the connecting flange, the cylindrical body providing sliding accommodation space for the piston rod at the end away from the aircraft wheel.

[0024] As a further improvement to the above solution, the electro-variable damping aircraft nose landing gear also includes a connecting rod, one end of which is hinged to the aircraft wheel end of the piston rod, and the other end is used to connect to the fuselage frame.

[0025] Alternatively, one end of the connecting rod is hinged to the wheel frame of the aircraft wheel, and the other end is used to connect to the fuselage frame.

[0026] As a further improvement to the above solution, the outer wall of the shock-absorbing cylinder is provided with at least two connecting lugs, which are used to connect with the fuselage frame.

[0027] As a further improvement to the above solution, the piston rod includes a wheel support section, a support shoulder and an electrode plate contact section that are sequentially connected as a single unit, and the support shoulder and the electrode plate contact section are disposed in the damping cylinder body;

[0028] Furthermore, a first insulating guide ring is provided between the support shoulder and the inner wall of the shock-absorbing cylinder; a second insulating guide ring is provided between the wheel support section and the inner wall of the shock-absorbing cylinder.

[0029] As a further improvement to the above solution, the damping cylinder body is also provided with a first fixed stiffness elastic element and a second fixed stiffness elastic element; the first fixed stiffness elastic element is sleeved on the outer wall of the wheel support section and is located between the support shoulder and the end of the damping cylinder body away from the cylinder head.

[0030] The second fixed stiffness elastic element is sleeved on the outer wall of the electrode plate contact section and is located between the electrorheological damping assembly and the cylinder head.

[0031] As a further improvement to the above scheme, both the first fixed stiffness elastic element and the second fixed stiffness elastic element are compression spring elements, elastic rubber blocks, or polymer elastic blocks.

[0032] In a second aspect, the present invention also provides an aircraft including an electrorheological damping aircraft nose landing gear as described in the first aspect.

[0033] Because the present invention adopts the above technical solutions, the beneficial effects of this application are as follows:

[0034] 1. The present invention provides an electrorheological damping aircraft nose landing gear, comprising a damping cylinder, a piston rod, an electrorheological damping assembly, and a power supply. One end of the piston rod is slidably disposed within the damping cylinder, and the other end extends out of the damping cylinder and is connected to an aircraft wheel. The portion of the piston rod located within the damping cylinder also has a support shoulder. The electrorheological damping assembly comprises a plurality of electrorheological damping units stacked sequentially on the support shoulder. Each electrorheological damping unit comprises an electrorheological elastomer, a first electrode plate in contact with its upper and lower surfaces respectively, and a second electrode plate. The electrode plates are shared by adjacent electrorheological bodies. Each first electrode plate is slidably disposed on the inner wall of the damping cylinder via a first insulating retaining ring, and its end away from the first insulating retaining ring is slidably in contact with the outer wall of the piston rod. Each second electrode plate is slidably disposed on the outer wall of the piston rod via a second insulating retaining ring, and its end away from the second insulating retaining ring is slidably in contact with the inner wall of the damping cylinder. A power supply has two electrodes electrically connected to the piston rod and the damping cylinder respectively, forming a conductive circuit to enable each electrorheological body to... The vibration unit exhibits different stiffness values ​​under different current intensities; this arrangement allows the first and second electrode plates to be staggered; preferably, the damping cylinder and the electrode plate in contact with it are connected to the negative electrode of the electrorheological elastomer stack via a negative electrode wire; the piston rod and the electrode plate in contact with it are connected to the positive electrode of the electrorheological elastomer stack via a positive electrode wire; by controlling the charge on the two electrodes, the electric field generated between the first and second electrode plates can be adjusted, thereby controlling the stiffness change of the electrorheological elastomer, so that the stiffness is lower during aircraft takeoff, making the aircraft run smoothly, and the stiffness of the elastomer is increased during aircraft landing, making the aircraft land smoothly and reducing rebound; thus, the stiffness can be adaptively adjusted, improving the stability and comfort of aircraft operation; in addition, the stacked arrangement of several electrorheological damping units, compared with a single large-volume electrorheological damping body, has a larger adjustable range of voltage of the electrode plate capacitor and a faster response, and can change the stiffness of the electrorheological elastomer more quickly and over a larger range; at the same time, the stacked electrorheological elastomer arrangement ensures that the average deformation of each layer of electrorheological elastomer under compression is not too large, avoiding excessive compression of the outer wall of the damping cylinder.

[0035] In some preferred embodiments, the electrorheological damping aircraft nose landing gear further includes a controller electrically connected to the power supply for controlling the output current of the power supply so that the electrorheological damping component exhibits different stiffness values ​​according to load changes. In this invention, by controlling the magnitude of the output current of the power supply, the variable stiffness elastomer exhibits different stiffness values ​​according to load conditions. Compared to the traditional magnetorheological fluid damper, this invention uses electrorheological elastomer damping, which is pollution-free, environmentally friendly, highly adaptable to the environment, highly resistant to pollution, and low in cost. Compared to traditional oil-air spring dampers, this invention does not contain hydraulic oil, has lower requirements for sealing performance, and avoids pollution caused by hydraulic oil leakage.

[0036] 2. The present invention provides an electrorheological damping aircraft nose landing gear, wherein the first insulating retainer includes a first insulating annular body and a first annular retainer groove disposed on the inner wall of the first insulating annular body.

[0037] The first annular groove is provided with an elastic element, and the outer edge of the first electrode plate can be compressed and locked in the first annular groove; the first electrode plate includes at least two first sector-shaped electrode plate units, and the outer edges of each first sector-shaped electrode plate unit are sequentially locked in the first annular groove along the circumference of the first insulating retaining ring seat; this arrangement ensures that the inner edge of the first electrode plate is in contact with the outer wall of the piston rod and conducts electricity, while the first electrode plate is insulated from the shock-absorbing cylinder body and does not conduct electricity under the isolation of the first insulating annular body;

[0038] The second insulating retaining ring seat includes a second insulating annular body and a second annular retaining groove disposed on the outer wall of the second insulating annular body;

[0039] The second annular groove is provided with an elastic element, and the inner edge of the second electrode plate is compressibly engaged in the second annular groove. The second electrode plate includes at least two second sector-shaped electrode plate units, and the inner edges of each second sector-shaped electrode plate unit are sequentially engaged in the second annular groove along the circumference of the second insulating retaining ring seat. This arrangement ensures that the outer edge of the second electrode plate is in contact with the inner wall of the damping cylinder, and the second electrode plate is insulated from the piston rod and is non-conductive under the isolation of the second insulating annular body. When the electrorheological damping assembly is working, the elastic element provided in the annular groove is under pressure, thereby ensuring that the first electrode plate, the second electrode plate, the first insulating retaining ring seat and the second insulating retaining ring seat slide in the damping cylinder and maintain a stable contact state. Attached Figure Description

[0040] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0041] Figure 1 This is a three-dimensional schematic diagram of an electrorheological damping aircraft nose landing gear disclosed in this invention.

[0042] Figure 2 This is a front view schematic diagram of an electrorheological damping aircraft nose landing gear disclosed in this invention;

[0043] Figure 3 This is a partial vertical sectional view of the front landing gear of an aircraft with electrorheological damping disclosed in this invention.

[0044] Figure 4 This is a schematic lateral cross-sectional view of an electrorheological damping aircraft nose landing gear disclosed in this invention. Figure 1 ;

[0045] Figure 5 This is a schematic lateral cross-sectional view of an electrorheological damping aircraft nose landing gear disclosed in this invention. Figure 2 .

[0046] Figure label:

[0047] 1. Shock-absorbing cylinder body; 1-1. Connecting lug; 2. Piston rod; 2-1. Wheel support section; 2-2. Support shoulder; 2-3. Electrode plate contact section; 3. Current-varying shock-absorbing assembly; 3-1. Current-varying elastomer; 3-2. First electrode plate; 3-21. First sector-shaped electrode plate unit; 3-3. Second electrode plate; 3-31. Second sector-shaped electrode plate unit; 3-4. First insulating retaining ring seat; 3-5. Second insulating retaining ring seat; 4. Power supply; 5. Cylinder head; 5-1. Connecting flange; 5-2. Cylinder body;

[0048] 6. Connecting rod; 7. First insulating guide ring; 8. Second insulating guide ring; 9. First fixed stiffness elastic element; 10. Second fixed stiffness elastic element; 11. Aircraft wheel.

[0049] The realization of the objective, functional characteristics and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0050] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0051] It should be noted that all directional indicators (such as up, down, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0052] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature.

[0053] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention. Example

[0054] See Figure 1-Figure 5 The present invention provides an electro-variable shock-absorbing aircraft nose landing gear, comprising:

[0055] Shock absorber cylinder 1;

[0056] The piston rod 2 has one end slidably disposed inside the shock-absorbing cylinder 1, and the other end extends out of the shock-absorbing cylinder 1 and is connected to the aircraft wheel 11, and a support shoulder 2-2 is provided in the middle.

[0057] The electrorheological damping assembly 3 is disposed inside the damping cylinder 1 and includes several electrorheological damping units, which are stacked sequentially from top to bottom on the support shoulder 2-2.

[0058] The electrorheological damping unit includes an electrorheological elastomer 3-1, a first electrode plate 3-2 and a second electrode plate 3-3 respectively in contact with the upper and lower surfaces of the electrorheological elastomer 3-1, and adjacent electrorheological elastomers 3-1 share a common electrode plate; each first electrode plate 3-2 is slidably disposed on the inner wall of the damping cylinder 1 through a first insulating retaining ring seat 3-4, and its end away from the first insulating retaining ring seat 3-4 is slidably in contact with the outer wall of the piston rod 2;

[0059] Each of the second electrode plates 3-3 is slidably disposed on the outer wall of the piston rod 2 via the second insulating retaining ring seat 3-5, and its end away from the second insulating retaining ring seat 3-5 is slidably in contact with the inner wall of the shock-absorbing cylinder 1; the electrorheological elastomer 3-1 Elastomer (ERE) is a smart material. Under the action of an electric field, the mechanical properties of ERE, such as hardness and elastic modulus, can change significantly, thereby enabling dynamic control of its shape and stiffness. Specifically, ERE is prepared by combining dielectrically polarizable particles with an elastomer. Under the action of an electric field, the particles inside ERE will rearrange to form chain-like or columnar structures. This structural change leads to changes in the mechanical properties of the material, such as elastic modulus. As the electric field strength increases, the stiffness and modal loss factor of ERE will increase, thereby effectively suppressing structural vibration. In this invention, the stacked arrangement of several current-varying damping units, compared to a single current-varying damper, has a larger adjustable voltage range and faster response of the electrode plate capacitor, enabling faster and larger-scale changes in the stiffness of the current-varying elastomer 3-1. At the same time, the stacked arrangement of the current-varying elastomer 3-1 ensures that the average deformation of each layer of current-varying elastomer 3-1 under compression is not too large, avoiding excessive compression of the outer wall of the damping cylinder 1.

[0060] Power supply 4, whose two electrodes are electrically connected to the piston rod 2 and the damping cylinder 1 respectively, forming a conductive circuit, so that each of the current-varying damping units exhibits different stiffness values ​​under different current intensities;

[0061] The controller is electrically connected to the power supply 4 and is used to control the output current of the power supply 4 so that the current-variable damping component 3 exhibits different stiffness values ​​according to load changes.

[0062] This arrangement results in the first electrode plate 3-2 and the second electrode plate 3-3 being staggered. In this embodiment, the shock-absorbing cylinder 1 and the electrode plate in contact with it are connected to the negative electrode of the electrorheological elastomer 3-1 stack via a negative electrode wire; the piston rod 2 and the electrode plate in contact with it are connected to the positive electrode of the electrorheological elastomer 3-1 stack via a positive electrode wire. By controlling the charge on the two electrodes, the electric field generated between the first electrode plate 3-2 and the second electrode plate 3-3 can be adjusted, thereby controlling the stiffness change of the electrorheological elastomer 3-1. This results in lower stiffness during aircraft takeoff, ensuring smooth aircraft operation, and increased stiffness during aircraft landing, ensuring smooth landing and reducing rebound. This achieves adaptive adjustment of its stiffness, improving the stability and comfort of aircraft operation.

[0063] In this invention, by controlling the output current of the power supply 4, the variable stiffness elastomer can exhibit different stiffness values ​​according to the load conditions. Compared with the traditional magnetorheological fluid damper, this invention uses an electrorheological elastomer 3-1 for shock absorption, which is pollution-free, environmentally friendly, highly adaptable to the environment, highly resistant to pollution, and low in cost. Compared with the traditional oil-air spring shock absorber, this invention does not contain hydraulic oil, has low requirements for sealing performance, and avoids pollution to the environment caused by hydraulic oil leakage.

[0064] In a preferred embodiment, the first insulating ring seat 3-4 includes a first insulating ring-shaped body and a first annular groove disposed on the inner wall of the first insulating ring-shaped body;

[0065] An elastic element is provided in the first annular groove, and the outer edge of the first electrode plate 3-2 can be compressed and locked in the first annular groove. The elastic element ensures that the inner edge of the first electrode plate 3-2 is in contact with the outer wall of the piston rod 2 and conducts electricity. At the same time, the first electrode plate 3-2 is insulated from the shock-absorbing cylinder 1 and does not conduct electricity under the isolation of the first insulating annular body.

[0066] The second insulating ring seat 3-5 includes a second insulating ring-shaped body and a second annular groove disposed on the outer wall of the second insulating ring-shaped body;

[0067] An elastic element is provided in the second annular groove, and the inner edge of the second electrode plate 3-3 can be compressibly locked in the second annular groove. The elastic element ensures that the outer edge of the second electrode plate 3-3 is in contact with the inner wall of the damping cylinder 1, and the second electrode plate 3-3 is insulated from the piston rod 2 and is non-conductive under the isolation of the second insulating annular body. Preferably, the elastic element is a spring. When the electrorheological damping assembly 3 is working, the elastic element provided in the annular groove is under pressure, thereby ensuring that the first electrode plate 3-2, the second electrode plate 3-3, the first insulating retaining ring seat 3-4 and the second insulating retaining ring seat 3-5 slide in the damping cylinder 1 and maintain a stable contact state.

[0068] Alternatively, the first and second insulating ring bodies may be made of compressible nylon. When the current-varying damping assembly 3 is working, the nylon insulating ring bodies are under pressure. When compressed during operation, the first electrode plate 3-2, the second electrode plate 3-3, the first insulating retaining ring seat 3-4, and the second insulating retaining ring seat 3-5 slide within the damping cylinder 1 and maintain a stable contact state.

[0069] In a preferred embodiment, the electrorheological elastomer 3-1 is annular; the annular electrorheological elastomer 3-1 is sleeved on one end of the piston rod 2, and the inner diameter of the electrorheological elastomer 3-1 is smaller than the outer diameter of the second insulating retaining ring seat 3-5; and the outer diameter of the electrorheological elastomer 3-1 is smaller than the inner diameter of the first insulating retaining ring seat 3-4.

[0070] As a preferred embodiment, see Figure 4 and Figure 5 The first electrode plate 3-2 includes at least two first sector-shaped electrode plate units 3-21, and the outer edges of each first sector-shaped electrode plate unit 3-21 are sequentially engaged in the first annular groove along the circumferential direction of the first insulating retaining ring seat 3-4; the second electrode plate 3-3 includes at least two second sector-shaped electrode plate units 3-31, and the inner edges of each second sector-shaped electrode plate unit 3-31 are sequentially engaged in the second annular groove along the circumferential direction of the second insulating retaining ring seat 3-5.

[0071] In this embodiment, the first electrode plate 3-2 is divided into three first sector-shaped electrode plate units 3-21, and the second electrode plate 3-3 is divided into three second sector-shaped electrode plate units 3-31. They are respectively locked in the corresponding annular slots along the circumference of the corresponding insulating ring seat. The arrangement of multiple equally divided sector-shaped electrode plate units facilitates installation and ensures sufficient and stable contact between the electrode plate and the piston rod 2 or the shock-absorbing cylinder 1.

[0072] As a preferred embodiment, the electrorheological damping aircraft nose landing gear also includes a cylinder head 5, which is detachably fastened to the end of the damping cylinder 1 away from the aircraft wheel 11.

[0073] The cylinder head 5 includes a connecting flange 5-1 and a cylindrical body 5-2 integrally connected to the connecting flange 5-1. The cylindrical body 5-2 provides sliding accommodation space for the piston rod 2 at the end away from the aircraft wheel 11. Specifically, the cylinder head 5 is fastened to the end of the shock-absorbing cylinder 1 away from the aircraft wheel 11 by bolts. The verticality of the cylindrical body 5-2 provides accommodation space for the sliding of the piston rod 2 so as to adapt to different working conditions.

[0074] In a preferred embodiment, the electrorheological damping aircraft nose landing gear further includes a connecting rod 6, one end of which is hinged to the aircraft wheel 11 end of the piston rod 2, and the other end is used to connect to the fuselage frame;

[0075] Alternatively, one end of the connecting rod 6 is hinged to the wheel frame of the aircraft wheel 11, and the other end is used to connect to the fuselage frame;

[0076] Specifically, one end of the connecting rod 6 is provided with a U-shaped fork, which is hinged to the outer wall of the piston rod 2, or the U-shaped fork is hinged to the wheel frame. The connecting rod 6 is provided to facilitate its fixed installation with the machine frame.

[0077] In a preferred embodiment, the outer wall of the shock-absorbing cylinder 1 is provided with at least two connecting lugs 1-1, which are used to connect with the fuselage frame. In this embodiment, the outer wall of the shock-absorbing cylinder 1 is symmetrically provided with two connecting lugs 1-1, and the two connecting lugs 1-1, together with the connecting rod 6, form a stable installation structure with the fuselage frame.

[0078] In a preferred embodiment, the piston rod 2 includes a wheel support section 2-1, a support shoulder 2-2, and an electrode plate contact section 2-3 that are sequentially connected as a single unit. The support shoulder 2-2 and the electrode plate contact section 2-3 are disposed inside the shock-absorbing cylinder 1.

[0079] Furthermore, a first insulating guide ring 7 is provided between the support shoulder 2-2 and the inner wall of the shock-absorbing cylinder 1; a second insulating guide ring 8 is provided between the wheel support section 2-1 and the inner wall of the shock-absorbing cylinder 1.

[0080] Specifically, the outer diameter of the support shoulder 2-2 is larger than the outer diameter of the wheel support section 2-1, and the outer diameter of the wheel support section 2-1 is larger than the outer diameter of the electrode plate contact section 2-3; the outer wall of the support shoulder 2-2 is provided with a first mounting groove for the first insulating guide ring 7 to be installed, and the inner wall of the shock-absorbing cylinder 1 is provided with a second mounting groove for the second insulating guide ring 8 to be installed; and the arrangement of the first insulating guide ring 7 and the second insulating guide ring 8 avoids short circuits.

[0081] In a preferred embodiment, the shock-absorbing cylinder 1 is further provided with a first fixed stiffness elastic element 9 and a second fixed stiffness elastic element 10; the first fixed stiffness elastic element 9 is sleeved on the outer wall of the wheel support section 2-1 and is located between the support shoulder 2-2 and the end of the shock-absorbing cylinder 1 away from the cylinder head 5.

[0082] The second fixed stiffness elastic element 10 is sleeved on the outer wall of the electrode plate contact section 2-3 and is located between the electrorheological damping assembly 3 and the cylinder head 5;

[0083] Preferably, the first fixed stiffness elastic element 9 and the second fixed stiffness elastic element 10 are both compression spring elements, elastic rubber blocks, or polymer elastic blocks;

[0084] A first fixed stiffness elastic element 9 and a second fixed stiffness elastic element 10 are respectively provided at the upper and lower ends of the electrorheological damping component 3 to further improve the damping performance of the aircraft's nose landing gear.

[0085] It should be noted that the shock-absorbing cylinder 1 is also wrapped with insulating material to prevent leakage.

[0086] When the aircraft lands, as the landing gear first touches the ground and sinks, the piston rod 2 is subjected to the reaction force from the ground. The piston rod 2 retracts, and the kinetic energy is converted into elastic potential energy. Part of the elastic potential energy is fed back to the fixed stiffness elastic element and absorbed and dissipated by it; another part of the elastic potential energy is fed back to the electrovariable elastomer 3-1. The controller controls the electrovariable elastomer 3-1 to increase its stiffness to avoid transmitting the impact force during landing to the fuselage frame, thus completing a smooth landing.

[0087] When an aircraft taxis, its landing gear is subjected to random loads from the uneven pavement surface. At this time, the controller adjusts the stiffness of the electrorheological elastomer 3-1 to increase its compression stroke. Under small loads, it can absorb more elastic potential energy, reducing the bumpiness caused by uneven pavement and improving passenger comfort. Furthermore, depending on different pavement conditions or unevenness and hardness (e.g., concrete pavement, asphalt pavement, simple dirt pavement, ice surface, etc.), the controller can also adjust the stiffness of the electrorheological elastomer 3-1 to an appropriate level, expanding its adaptability. Example

[0088] The present invention also provides an aircraft, including a current-variable damping aircraft nose landing gear as described in Embodiment 1; it also includes a fuselage frame, and the current-variable damping aircraft nose landing gear disposed at the bottom of the fuselage frame; the current-variable damping aircraft nose landing gear is provided with a current-variable damping component 3. When the aircraft is running on the ground, the landing gear is subjected to a small static load or fluctuates near the static load, and the current-variable elastomer 3-1 is controlled to reduce its stiffness to improve the stability of the aircraft operation; when the aircraft is impacted during landing, the landing gear is subjected to a huge impact force, and the current-variable elastomer 3-1 is controlled to increase its stiffness to improve the landing comfort of the aircraft.

[0089] The above are merely preferred embodiments of the present invention and do not limit the patent scope of the present invention. All equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A current-variable shock-absorbing aircraft nose landing gear, characterized in that, include: Shock-absorbing cylinder block; The piston rod has one end slidably mounted in the shock absorber cylinder, and the other end extends out of the shock absorber cylinder and is connected to an aircraft wheel, and a support shoulder is provided in the middle. An electrorheological damping assembly is disposed in the damping cylinder and includes several electrorheological damping units, which are stacked sequentially from top to bottom on the support shoulder. The electrorheological damping unit includes an electrorheological elastomer, a first electrode plate and a second electrode plate that are respectively in contact with the upper and lower surfaces of the electrorheological elastomer, and adjacent electrorheological elastomers share a common electrode plate; each first electrode plate is slidably disposed on the inner wall of the damping cylinder through a first insulating retaining ring seat, and its end away from the first insulating retaining ring seat is slidably in contact with the outer wall of the piston rod. Each of the second electrode plates is slidably disposed on the outer wall of the piston rod via a second insulating retaining ring seat, and its end away from the second insulating retaining ring seat is slidably in contact with the inner wall of the shock-absorbing cylinder. The power supply has two electrodes that are electrically connected to the piston rod and the damping cylinder respectively, forming a conductive circuit, so that each of the current-varying damping units exhibits different stiffness values ​​under different current intensities. A controller, electrically connected to the power supply, is used to control the output current of the power supply so that the current-variable damping component exhibits different stiffness values ​​according to load changes; The first insulating retaining ring seat includes a first insulating annular body and a first annular retaining groove disposed on the inner wall of the first insulating annular body; The first annular groove is provided with an elastic element, and the outer edge of the first electrode plate can be compressed and locked in the first annular groove; The second insulating retaining ring seat includes a second insulating annular body and a second annular retaining groove disposed on the outer wall of the second insulating annular body; The second annular groove is provided with an elastic element, and the inner edge of the second electrode plate can be compressed and locked in the second annular groove; The electrovariable elastomer is ring-shaped; The inner diameter of the electrorheological elastomer is smaller than the outer diameter of the second insulating retainer seat; and the outer diameter of the electrorheological elastomer is smaller than the inner diameter of the first insulating retainer seat. The first electrode plate includes at least two first sector-shaped electrode plate units, and the outer edges of each first sector-shaped electrode plate unit are sequentially engaged in the first annular groove along the circumferential direction of the first insulating retaining ring seat. The second electrode plate includes at least two second sector-shaped electrode plate units, and the inner edges of each second sector-shaped electrode plate unit are sequentially engaged in the second annular groove along the circumferential direction of the second insulating retaining ring seat.

2. The electrorheological damping aircraft nose landing gear according to claim 1, characterized in that, The electrorheological damping aircraft nose landing gear also includes a cylinder head, which is detachably fastened to the damping cylinder body at the end away from the aircraft wheels. The cylinder head includes a connecting flange and a cylindrical body integrally connected to the connecting flange, the cylindrical body providing sliding accommodation space for the piston rod at the end away from the aircraft wheel.

3. The electrorheological damping aircraft nose landing gear according to claim 1, characterized in that, The electrorheological damping aircraft nose landing gear also includes a connecting rod, one end of which is hinged to the aircraft wheel end of the piston rod, and the other end is used to connect to the fuselage frame; Alternatively, one end of the connecting rod is hinged to the wheel frame of the aircraft wheel, and the other end is used to connect to the fuselage frame; The outer wall of the shock-absorbing cylinder is provided with at least two connecting lugs, which are used to connect to the fuselage frame.

4. The electrorheological damping aircraft nose landing gear according to claim 2, characterized in that, The piston rod includes a wheel support section, a support shoulder, and an electrode plate contact section that are connected in sequence as one piece. The support shoulder and the electrode plate contact section are disposed in the damping cylinder body. Furthermore, a first insulating guide ring is provided between the support shoulder and the inner wall of the shock-absorbing cylinder; a second insulating guide ring is provided between the wheel support section and the inner wall of the shock-absorbing cylinder.

5. The electrorheological damping aircraft nose landing gear according to claim 4, characterized in that, The shock-absorbing cylinder body is also provided with a first fixed stiffness elastic element and a second fixed stiffness elastic element; the first fixed stiffness elastic element is sleeved on the outer wall of the wheel support section and is located between the support shoulder and the end of the shock-absorbing cylinder body away from the cylinder head. The second fixed stiffness elastic element is sleeved on the outer wall of the electrode plate contact section and is located between the electrorheological damping assembly and the cylinder head.

6. An aircraft, characterized in that, Including the electrorheological damping aircraft nose landing gear as described in any one of claims 1-5.

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