Electrorheological damping aircraft nose landing gear and aircraft

Abstract

The invention provides an electrorheological damping aircraft nose landing gear and an aircraft. The landing gear comprises a damping cylinder body; one end of the piston rod is slidably arranged in the damping cylinder, the other end of the piston rod is connected with an aircraft wheel, and a supporting shoulder is arranged in the middle of the piston rod; the electrorheological damping assembly comprises a plurality of electrorheological damping units which are stacked on the supporting shoulder; each electrorheological damping unit comprises electrorheological elastomers, a first electrode plate and a second electrode plate, and the adjacent electrorheological elastomers share one electrode plate; each first electrode plate is arranged on the inner wall of the damping cylinder body through a first insulating snap ring seat, and the end away from the snap ring seat is in sliding contact with the outer wall of the piston rod; each second electrode plate is arranged on the outer wall of the piston rod through a second insulating snap ring seat, and the end away from the snap ring seat is slidably contacted with the inner wall of the damping cylinder body; the power supply and the two electrodes are electrically connected with the piston rod and the damping cylinder body respectively to form a conductive loop; the rigidity can be adjusted in a self-adaptive mode, and the stability and comfort of aircraft operation are improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft landing devices, and in particular to an electrorheological shock-absorbing front landing gear of an aircraft and an aircraft. Background Art

[0002] The landing gear is an accessory device at the bottom of the aircraft that supports the aircraft during takeoff, landing or ground taxiing, and is used for ground movement. When the aircraft touches down or taxis at high speed on an uneven runway, it will collide violently with the ground. In addition to the small buffering effect of the pneumatic tires, most of the impact energy must be absorbed by the shock absorber. The front landing gear of the aircraft mostly uses complex oil-gas spring shock absorbers, which require good sealing performance, complex structure, and poor environmental adaptability.

[0003] Traditionally, a Chinese patent with the patent number ZL2023228585415 discloses a buffer mechanism and an aircraft landing gear, including a piston cylinder, a piston column and an elastomer. One end of the piston column is slidably arranged in the piston cylinder. The elastomer is arranged between the piston column and the piston cylinder along the sliding direction of the piston column, and the elastomer is a nonlinear elastic material; this patent utilizes the characteristics of nonlinear elastic materials to absorb impact kinetic energy, and the shock absorption performance will be improved compared to traditional linear material elastomers; however, the road conditions faced by aircraft are changeable, and the change in the elastic modulus of the selected nonlinear elastic material is also determined, and it will not make adaptive adjustments based on changes in road conditions, especially for the variable stiffness requirements of the shock absorber during aircraft landing and taxiing, which cannot improve the comfort of passengers well.

[0004] Therefore, there is an urgent need for an electrorheological shock-absorbing aircraft front landing gear and an aircraft, which can adaptively adjust its stiffness under different working environments of aircraft take-off and landing to improve the stability and comfort of aircraft operation. Summary of the invention

[0005] The purpose of the present invention is to provide an electrorheological shock-absorbing aircraft front landing gear and an aircraft, aiming to solve the technical problem that the traditional oil-gas spring shock absorber cannot well meet the different elastic stiffness requirements of take-off and landing at the same time.

[0006] To achieve the above-mentioned object, in a first aspect, the present invention provides an electrorheological damping aircraft front landing gear, comprising: Shock absorber cylinder; A piston rod, one end of which is slidably disposed inside the shock absorbing cylinder, the other end of which extends out of the shock absorbing cylinder and is connected to an aircraft wheel, and a supporting shoulder is provided in the middle thereof; An electrorheological damping assembly is arranged in the damping cylinder, and includes a plurality of electrorheological damping units, which are stacked on the supporting shoulder from top to bottom in sequence; The electrorheological damping unit comprises an electrorheological elastomer, a first electrode plate and a second electrode plate respectively contacting the upper surface or the lower surface thereof, and adjacent electrorheological elastomers share one electrode plate; each of the first electrode plates is slidably disposed on the inner wall of the damping cylinder through a first insulating snap ring seat, and the end thereof away from the first insulating snap ring seat is slidably contacting 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 snap ring seat, and its end away from the second insulating snap ring seat is slidably in contact with the inner wall of the damping cylinder body; The power source has two electrodes which are electrically connected to the piston rod and the damping cylinder respectively, and form a conductive loop, so that each of the electrorheological damping units presents different stiffness values ​​under different current intensities.

[0007] As a further improvement of the above scheme, the electrorheological shock absorbing aircraft front 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 shock absorbing component presents different stiffness values ​​according to load changes.

[0008] As a further improvement of the above solution, the first insulating clamping ring seat includes a first insulating annular body and a first annular clamping groove arranged on the inner wall of the first insulating annular body; An elastic member is provided in the first annular groove, and the outer edge of the first electrode plate can be compressibly clamped in the first annular groove; The second insulating clamping ring seat comprises a second insulating annular body and a second annular clamping groove arranged on the outer wall of the second insulating annular body; An elastic member is arranged in the second annular groove, and the inner edge of the second electrode plate can be compressed and clamped in the second annular groove.

[0009] As a further improvement of the above solution, the electrorheological elastomer is in a ring shape; The inner diameter of the electrorheological elastomer is smaller than the outer diameter of the second insulating clamping ring seat; and the outer diameter of the electrorheological elastomer is smaller than the inner diameter of the first insulating clamping ring seat.

[0010] As a further improvement of the above solution, the first electrode plate includes at least two first fan-shaped electrode plate units, and the outer edges of the first fan-shaped electrode plate units are sequentially clamped in the first annular clamping groove along the circumference of the first insulating clamping ring seat; The second electrode plate comprises at least two second sector-shaped electrode plate units, and the inner edge of each of the second sector-shaped electrode plate units is sequentially clamped in the second annular clamping groove along the circumferential direction of the second insulating clamping ring seat.

[0011] As a further improvement of the above solution, the electrorheological shock-absorbing aircraft front landing gear further comprises a cylinder cover, and the cylinder cover is detachably buckled on the end of the shock-absorbing cylinder body away from the aircraft wheel; The cylinder head comprises a connecting flange and a cylinder body integrally connected to the connecting flange, wherein the cylinder body provides a sliding accommodation space for the end of the piston rod away from the aircraft wheel.

[0012] As a further improvement of the above solution, the electrorheological shock-absorbing aircraft front 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 be connected to the fuselage frame.

[0013] As a further improvement of the above solution, the outer wall of the shock absorbing cylinder is provided with at least two connecting ears, and the connecting ears are used to be connected to the fuselage frame.

[0014] As a further improvement of the above solution, the piston rod comprises a wheel support section, the support shoulder and the electrode plate contact section which are sequentially connected and integrated, and the support shoulder and the electrode plate contact section are arranged in the shock absorbing cylinder; A first insulating guide ring is provided between the support shoulder and the inner wall of the shock absorbing cylinder; and a second insulating guide ring is provided between the wheel support section and the inner wall of the shock absorbing cylinder.

[0015] As a further improvement of the above scheme, the shock absorbing cylinder is further 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 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 cover.

[0016] As a further improvement of the above solution, the first fixed stiffness elastic element and the second fixed stiffness elastic element are both compression spring elements or elastic rubber blocks or polymer elastic blocks.

[0017] In a second aspect, the present invention further provides an aircraft, comprising the electrorheological shock absorbing aircraft front landing gear as provided in the first aspect.

[0018] Since the present invention adopts the above technical solution, the beneficial effects of this application are: 1. The present invention provides an electrorheological shock-absorbing aircraft front landing gear, comprising a shock-absorbing cylinder, a piston rod, an electrorheological shock-absorbing assembly and a power source, wherein one end of the piston rod can be slidably arranged in the shock-absorbing cylinder, and the other end extends out of the shock-absorbing cylinder and is connected to an aircraft wheel, and the portion of the piston rod located in the shock-absorbing cylinder is also provided with a supporting shoulder; the electrorheological shock-absorbing assembly comprises a plurality of electrorheological shock-absorbing units sequentially stacked on the supporting shoulder; the electrorheological shock-absorbing unit comprises an electrorheological elastomer, a first electrode plate and a second electrorheological plate respectively contacting the upper surface or the lower surface thereof An electrode plate is shared by adjacent electrorheological elastomers; each of the first electrode plates can be slidably arranged on the inner wall of the shock-absorbing cylinder through a first insulating snap ring seat, and its end away from the first insulating snap ring seat can be slidably contacted with the outer wall of the piston rod; each of the second electrode plates can be slidably arranged on the outer wall of the piston rod through a second insulating snap ring seat, and its end away from the second insulating snap ring seat can be slidably contacted with the inner wall of the shock-absorbing cylinder; a power source, whose two electrodes are electrically connected to the piston rod and the shock-absorbing cylinder respectively, and form a conductive circuit, so that each of the current-changing The shock unit presents different stiffness values ​​under different current intensities; such a setting makes the first electrode plate and the second electrode plate arranged alternately; preferably, the shock absorbing cylinder and the electrode plate in contact therewith are connected to the negative electrode of the electrorheological elastomer stack through a negative electrode wire; the piston rod and the electrode plate in contact therewith are connected to the positive electrode of the electrorheological elastomer stack through a positive electrode wire; by controlling the charge of the two electrodes, the electric field generated between the first electrode plate and the second electrode plate can be adjusted to control the stiffness change of the electrorheological elastomer, so that the stiffness is lower when the aircraft takes off, so that the aircraft travels smoothly, and the elastic body stiffness is controlled to increase when the aircraft lands, so that the aircraft lands smoothly and the rebound is reduced; thereby realizing adaptive adjustment of its stiffness and improving the stability and comfort of aircraft operation; in addition, the stacking setting of several electrorheological shock absorbing units, compared with a single large-volume electrorheological shock absorbing body, has a larger adjustable range of electrode plate capacitor voltage and a faster response, and can change the stiffness of the electrorheological elastomer faster and in a larger range; at the same time, the stacked electrorheological elastomer setting prevents the average deformation of each layer of the electrorheological elastomer from being too large when squeezed, avoiding excessive squeezing of the outer wall of the shock absorbing cylinder; In certain preferred embodiments, the electrorheological shock-absorbing aircraft front 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 shock-absorbing component presents different stiffness values ​​according to load changes; in the present invention, by controlling the output current of the power supply, the variable stiffness elastomer presents different stiffness values ​​according to load conditions. Compared with the traditional magnetorheological fluid buffer, the present invention uses electrorheological elastomer for shock absorption, which is pollution-free, environmentally friendly, highly environmentally adaptable, highly resistant to pollution, and low in cost; compared with traditional oil-gas spring shock absorbers, the present invention does not contain hydraulic oil, has low requirements on sealing performance, and avoids pollution to the environment caused by hydraulic oil leakage.

[0019] 2. In the electrorheological shock-absorbing aircraft front landing gear provided by the present invention, the first insulating clamping ring seat comprises a first insulating annular body and a first annular clamping groove arranged on the inner wall of the first insulating annular body; An elastic member is provided in the first annular groove, and the outer edge of the first electrode plate can be compressibly clamped in the first annular groove; the first electrode plate includes at least two first fan-shaped electrode plate units, and the outer edge of each of the first fan-shaped electrode plate units is sequentially clamped in the first annular groove along the circumference of the first insulating clamp ring seat; such a configuration ensures that the inner edge of the first electrode plate is in contact with the outer wall of the piston rod for electrical conduction, and at the same time, the first electrode plate is insulated from the shock-absorbing cylinder body and is not electrically conductive under the isolation of the first insulating annular body; The second insulating clamping ring seat comprises a second insulating annular body and a second annular clamping groove arranged on the outer wall of the second insulating annular body; An elastic member is provided in the second annular groove, and the inner edge of the second electrode plate can be compressibly clamped in the second annular groove. The second electrode plate includes at least two second fan-shaped electrode plate units, and the inner edges of each of the second fan-shaped electrode plate units are sequentially clamped in the second annular groove along the circumference of the second insulating clamping ring seat; such a setting ensures that the outer edge of the second electrode plate contacts the inner wall of the shock absorbing cylinder body, and at the same time, the second electrode plate is insulated and non-conductive from the piston rod under the isolation of the second insulating annular body; when the electrorheological shock absorbing assembly is working, the elastic member arranged in the annular groove is in a compressed state, thereby ensuring that the first electrode plate, the second electrode plate, the first insulating clamping ring seat and the second insulating clamping ring seat slide in the shock absorbing cylinder body and maintain a stable contact state. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0021] Figure 1 It is a three-dimensional schematic diagram of an electrorheological shock-absorbing aircraft front landing gear disclosed by the present invention; Figure 2 It is a schematic diagram of the front landing gear of an electrorheological shock-absorbing aircraft disclosed in the present invention; Figure 3 It is a partial vertical cross-sectional schematic diagram of an electrorheological shock-absorbing aircraft front landing gear disclosed by the present invention; Figure 4A schematic cross-sectional view of an electrorheological shock-absorbing aircraft front landing gear disclosed in the present invention Figure 1 ; Figure 5 A schematic cross-sectional view of an electrorheological shock-absorbing aircraft front landing gear disclosed in the present invention Figure 2 .

[0022] Reference numerals: 1. shock-absorbing cylinder; 1-1. connecting lug; 2. piston rod; 2-1. wheel support section; 2-2. support shoulder; 2-3. electrode plate contact section; 3. electrorheological shock-absorbing assembly; 3-1. electrorheological elastomer; 3-2. first electrode plate; 3-21. first fan-shaped plate unit; 3-3. second electrode plate; 3-31. second fan-shaped plate unit; 3-4. first insulating clamping ring seat; 3-5. second insulating clamping ring seat; 4. power supply; 5. cylinder head; 5-1. connecting flange; 5-2. cylinder body; 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.

[0023] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with the implementation methods and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] It should be noted that all directional indications (such as up, down, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0026] In addition, in the present invention, the descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features.

[0027] Furthermore, the technical solutions between the various embodiments of the present invention may be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in the field. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention. Example 1

[0028] See also Figure 1-Figure 5 The present invention provides an electrorheological shock-absorbing aircraft front landing gear, comprising: Shock absorber cylinder 1; A piston rod 2, one end of which is slidably disposed in the shock absorbing cylinder 1, and the other end of which extends out of the shock absorbing cylinder 1 and is connected to an aircraft wheel 11, and a supporting shoulder 2-2 is provided in the middle thereof; The electrorheological damping assembly 3 is arranged in the damping cylinder 1, and includes a plurality of electrorheological damping units, which are stacked on the supporting shoulder 2-2 from top to bottom in sequence; The electrorheological damping unit comprises an electrorheological elastomer 3-1, a first electrode plate 3-2 and a second electrode plate 3-3 respectively contacting the upper surface or the lower surface thereof, and adjacent electrorheological elastomers 3-1 share one electrode plate; each of the first electrode plates 3-2 is slidably arranged on the inner wall of the damping cylinder 1 through a first insulating clamping ring seat 3-4, and its end away from the first insulating clamping ring seat 3-4 is slidably contacting the outer wall of the piston rod 2; Each of the second electrode plates 3-3 is slidably disposed on the outer wall of the piston rod 2 through a second insulating snap ring seat 3-5, and its end away from the second insulating snap ring seat 3-5 is slidably in contact with the inner wall of the shock absorbing cylinder 1; the electrorheological elastomer 3-1 (Electrorheological 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 achieving dynamic control of its shape and stiffness. Specifically, ERE is prepared by compounding dielectrically polarizable particles and elastomers. Under the action of an electric field, the particles inside the ERE will rearrange to form a chain or columnar structure. This structural change causes the mechanical properties of the material, such as the elastic modulus, to change. With the increase of the electric field strength, the stiffness and modal loss factor of the ERE will increase, thereby effectively suppressing the vibration of the structure. In the present invention, the stacking of several electrorheological damping units has a larger adjustable range of the capacitor voltage with the electrode plate and a faster response than a single electrorheological damping body, and can change the stiffness of the electrorheological elastomer 3-1 faster and in a larger range. At the same time, the stacked electrorheological elastomer 3-1 is set so that the average deformation of each layer of the electrorheological elastomer 3-1 when squeezed is not too large, thereby avoiding excessive squeezing of the outer wall of the damping cylinder 1. A power source 4, two electrodes of which are electrically connected to the piston rod 2 and the damping cylinder 1 respectively, and form a conductive loop, so that each of the electrorheological damping units presents different stiffness values ​​under different current intensities; A controller, the controller being electrically connected to the power source 4 and configured to control an output current of the power source 4 so that the electrorheological damping assembly 3 presents different stiffness values ​​according to load changes; Such an arrangement enables the first electrode plate 3-2 and the second electrode plate 3-3 to be arranged alternately; in this embodiment, the shock absorbing cylinder 1 and the electrode plate in contact therewith 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 therewith are connected to the positive electrode of the electrorheological elastomer 3-1 stack via a positive electrode wire; by controlling the charge of the two electrodes, the electric field generated between the first electrode plate 3-2 and the second electrode plate 3-3 can be adjusted to control the stiffness change of the electrorheological elastomer 3-1, so that the stiffness is lower when the aircraft takes off, so that the aircraft travels smoothly, and when the aircraft lands, the stiffness of the elastic body is controlled to increase, so that the aircraft lands smoothly and the rebound is reduced; thereby, its stiffness can be adaptively adjusted to improve the stability and comfort of the aircraft operation; In the present invention, by controlling the output current of the power supply 4, the variable stiffness elastomer presents different stiffness values ​​according to the load conditions. Compared with the traditional magnetorheological fluid buffer, the present invention uses 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-gas spring shock absorber, the present invention does not contain hydraulic oil, has low requirements on sealing performance, and avoids the pollution of the environment caused by hydraulic oil leakage.

[0029] As a preferred embodiment, the first insulating clamping ring seat 3-4 includes a first insulating annular body and a first annular clamping groove arranged on the inner wall of the first insulating annular body; An elastic member is provided in the first annular groove, and the outer edge of the first electrode plate 3-2 can be compressed and clamped in the first annular groove; the setting of the elastic member ensures that the inner edge of the first electrode plate 3-2 is in contact with the outer wall of the piston rod 2 for electrical conduction, and at the same time, the first electrode plate 3-2 is insulated and non-conductive from the shock absorbing cylinder 1 under the isolation of the first insulating annular body; The second insulating clamping ring seat 3-5 includes a second insulating annular body and a second annular clamping groove arranged on the outer wall of the second insulating annular body; An elastic member is provided in the second annular groove, and the inner edge of the second electrode plate 3-3 can be compressed and clamped in the second annular groove; the setting of the elastic member ensures that the outer edge of the second electrode plate 3-3 contacts the inner wall of the shock absorbing cylinder 1, and at the same time, the second electrode plate 3-3 is insulated and non-conductive from the piston rod 2 under the isolation of the second insulating annular body; preferably, the elastic member is a spring leaf; when the electrorheological shock absorbing assembly 3 is working, the elastic member arranged in the annular groove is in a compressed state, thereby ensuring that the first electrode plate 3-2, the second electrode plate 3-3, the first insulating clamping ring seat 3-4 and the second insulating clamping ring seat 3-5 slide in the shock absorbing cylinder 1 and maintain a stable contact state; Alternatively, the material of the first insulating annular body and the second insulating annular body is compressible nylon. When the electrorheological shock absorbing assembly 3 is working, the insulating annular body made of nylon is in a compressed state. When the electrorheological shock absorbing assembly 3 is compressed during operation, it is ensured that the first electrode plate 3-2, the second electrode plate 3-3, the first insulating clamping ring seat 3-4 and the second insulating clamping ring seat 3-5 slide in the shock absorbing cylinder 1 and maintain a stable contact state.

[0030] As a preferred embodiment, the electrorheological elastomer 3-1 is ring-shaped; the ring-shaped 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.

[0031] As a preferred embodiment, see Figure 4 and Figure 5 The first electrode plate 3-2 includes at least two first fan-shaped plate units 3-21, and the outer edges of each of the first fan-shaped plate units 3-21 are sequentially clamped in the first annular groove along the circumference of the first insulating clamping ring seat 3-4; the second electrode plate 3-3 includes at least two second fan-shaped plate units 3-31, and the inner edges of each of the second fan-shaped plate units 3-31 are sequentially clamped in the second annular groove along the circumference of the second insulating clamping ring seat 3-5; In this embodiment, the first electrode plate 3-2 is equally divided into three first fan-shaped electrode plate units 3-21, and the second electrode plate 3-3 is equally divided into three second fan-shaped electrode plate units 3-31, which are respectively and sequentially clamped in the corresponding annular clamping grooves along the circumference of the corresponding insulating clamping ring seats. The arrangement of multiple equally divided fan-shaped electrode plate units is convenient for installation on the one hand, and can ensure sufficient and stable contact between the electrode plate and the piston rod 2 or the shock absorber cylinder 1 on the other hand.

[0032] As a preferred embodiment, the electrorheological shock-absorbing aircraft front landing gear further comprises a cylinder cover 5, and the cylinder cover 5 is detachably buckled on the end of the shock-absorbing cylinder body 1 away from the aircraft wheel 11; The cylinder head 5 includes a connecting flange 5-1 and a cylinder body 5-2 integrally connected to the connecting flange 5-1, and the cylinder body 5-2 provides a sliding accommodation space for the end of the piston rod 2 away from the aircraft wheel 11; specifically, the cylinder head 5 is fastened to the end of the shock absorbing cylinder body 1 away from the aircraft wheel 11 by bolts; the verticality of the cylinder body 5-2 provides an accommodation space for the sliding of the piston rod 2 so as to adapt to different working conditions.

[0033] As a preferred embodiment, the electrorheological shock-absorbing aircraft front landing gear further comprises 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; 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; Specifically, a U-shaped fork is provided at one end of the connecting rod 6, and the U-shaped fork is hinged to the outer wall of the piston rod 2, or the U-shaped fork is hinged to the wheel frame. The setting of the connecting rod 6 is convenient for fixed installation with the fuselage frame.

[0034] As a preferred embodiment, the outer wall of the shock absorbing cylinder body 1 is provided with at least two connecting ears 1-1, and the connecting ears 1-1 are used to connect with the fuselage frame; in this embodiment, the outer wall of the shock absorbing cylinder body 1 is symmetrically provided with two connecting ears 1-1, and the two connecting ears 1-1 cooperate with the connecting rod 6 to form a stable installation structure with the fuselage frame.

[0035] As a preferred embodiment, the piston rod 2 comprises a wheel support section 2-1, a support shoulder 2-2 and an electrode plate contact section 2-3 which are sequentially connected and integrated, and the support shoulder 2-2 and the electrode plate contact section 2-3 are arranged in the shock absorbing cylinder 1; 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; 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; a first mounting groove for installing the first insulating guide ring 7 is provided on the outer wall of the support shoulder 2-2, and a second mounting groove for installing the second insulating guide ring 8 is provided on the inner wall of the shock absorber cylinder 1; and the first insulating guide ring 7 and the second insulating guide ring 8 are arranged to avoid short circuit.

[0036] As a preferred embodiment, the damping 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 damping cylinder 1 away from the cylinder cover 5; 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 cover 5; Preferably, the first fixed stiffness elastic element 9 and the second fixed stiffness elastic element 10 are both compression spring elements or elastic rubber blocks or polymer elastic blocks; A first fixed stiffness elastic element 9 and a second fixed stiffness elastic element 10 are respectively disposed at the upper and lower ends of the electrorheological damping assembly 3 to further improve the damping performance of the front landing gear of the aircraft; It should be noted that the shock absorbing cylinder 1 is also wrapped with insulating material to avoid electrical leakage.

[0037] When the aircraft lands, when the landing gear first touches the ground and sinks, the piston rod 2 is subjected to the reaction force of the ground, the piston rod 2 retracts, and the kinetic energy is converted into elastic potential energy, part of which is fed back to the fixed stiffness elastic element and absorbed and dissipated by it; the other part of the elastic potential energy is fed back to the electrorheological elastomer 3-1, and the controller controls the electrorheological elastomer 3-1 to increase its stiffness to avoid transmitting the impact force during landing to the fuselage frame, thereby completing a smooth landing; When the aircraft is taxiing, the landing gear of the aircraft is subjected to random loads from the undulating road surface. At this time, the controller controls the electrorheological elastomer 3-1 to reduce its stiffness to increase the compression stroke, absorb more elastic potential energy under small loads, reduce the bumpy feeling caused by the uneven road surface, and improve the comfort of passengers. In addition, according to different road surface conditions or road surface unevenness, hardness, etc. (such as concrete road surface, asphalt road surface, simple earth and stone road surface, ice surface, etc.), the controller can also control the electrorheological elastomer 3-1 to adapt to the stiffness and expand the adaptability. Example 2

[0038] The present invention also provides an aircraft, comprising an electrorheological shock-absorbing aircraft front landing gear as described in Example 1; also comprising a fuselage frame, and the electrorheological shock-absorbing aircraft front landing gear arranged at the bottom of the fuselage frame; the electrorheological shock-absorbing aircraft front landing gear is provided with an electrorheological shock-absorbing assembly 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 electrorheological elastomer 3-1 is controlled to reduce its stiffness to improve the stability of the aircraft operation; when the aircraft is in landing impact, the landing gear is subjected to a huge impact force, and the electrorheological elastomer 3-1 is controlled to increase its stiffness to improve the comfort of the aircraft landing.

[0039] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. An electrorheological shock-absorbing aircraft front landing gear, characterized in that: include: Shock absorber cylinder; A piston rod, one end of which is slidably disposed inside the shock absorbing cylinder, the other end of which extends out of the shock absorbing cylinder and is connected to an aircraft wheel, and a supporting shoulder is provided in the middle thereof; An electrorheological damping assembly is arranged in the damping cylinder, and includes a plurality of electrorheological damping units, which are stacked on the supporting shoulder from top to bottom in sequence; The electrorheological damping unit comprises an electrorheological elastomer, a first electrode plate and a second electrode plate respectively contacting the upper surface or the lower surface thereof, and adjacent electrorheological elastomers share one electrode plate; each of the first electrode plates is slidably disposed on the inner wall of the damping cylinder through a first insulating snap ring seat, and the end thereof away from the first insulating snap ring seat is slidably contacting 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 snap ring seat, and its end away from the second insulating snap ring seat is slidably in contact with the inner wall of the damping cylinder body; The power source has two electrodes which are electrically connected to the piston rod and the damping cylinder respectively, and form a conductive loop, so that each of the electrorheological damping units presents different stiffness values ​​under different current intensities.

2. The electrorheological damping aircraft front landing gear according to claim 1, characterized in that: The electrorheological damping aircraft front 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 presents different stiffness values ​​according to load changes.

3. An electrorheological damping aircraft front landing gear according to claim 1 or 2, characterized in that: The first insulating clamping ring seat comprises a first insulating annular body and a first annular clamping groove arranged on the inner wall of the first insulating annular body; An elastic member is provided in the first annular groove, and the outer edge of the first electrode plate can be compressibly clamped in the first annular groove; The second insulating clamping ring seat comprises a second insulating annular body and a second annular clamping groove arranged on the outer wall of the second insulating annular body; An elastic member is arranged in the second annular groove, and the inner edge of the second electrode plate can be compressed and clamped in the second annular groove.

4. The electrorheological damping aircraft front landing gear according to claim 1 or 2, characterized in that: The electrorheological elastomer is in a ring shape; The inner diameter of the electrorheological elastomer is smaller than the outer diameter of the second insulating clamping ring seat; and the outer diameter of the electrorheological elastomer is smaller than the inner diameter of the first insulating clamping ring seat.

5. The electrorheological damping aircraft front landing gear according to claim 3, characterized in that: The first electrode plate comprises at least two first sector-shaped electrode plate units, and the outer edges of the first sector-shaped electrode plate units are sequentially clamped in the first annular clamping groove along the circumference of the first insulating clamping ring seat; The second electrode plate comprises at least two second sector-shaped electrode plate units, and the inner edge of each of the second sector-shaped electrode plate units is sequentially clamped in the second annular clamping groove along the circumferential direction of the second insulating clamping ring seat.

6. An electrorheological damping aircraft front landing gear according to claim 1 or 2, characterized in that: The electrorheological damping aircraft front landing gear also includes a cylinder cover, which is detachably buckled on the end of the damping cylinder body away from the aircraft wheel; The cylinder head comprises a connecting flange and a cylinder body integrally connected to the connecting flange, wherein the cylinder body provides a sliding accommodation space for the end of the piston rod away from the aircraft wheel.

7. An electrorheological damping aircraft front landing gear according to claim 1 or 2, characterized in that: The electrorheological damping aircraft front 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 ears, and the connecting ears are used to be connected to the fuselage frame.

8. The electrorheological damping aircraft front landing gear according to claim 6, characterized in that: The piston rod comprises a wheel support section, a support shoulder and an electrode plate contact section which are sequentially connected and integrated, and the support shoulder and the electrode plate contact section are arranged in the damping cylinder body; A first insulating guide ring is provided between the support shoulder and the inner wall of the shock absorbing cylinder; and a second insulating guide ring is provided between the wheel support section and the inner wall of the shock absorbing cylinder.

9. The electrorheological damping aircraft front landing gear according to claim 8, characterized in that: The damping cylinder 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 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 cover.

10. An aircraft, characterized in that: It comprises an electrorheological shock absorbing aircraft front landing gear as described in any one of claims 1 to 9.

Images