Impact-resistant multi-support energy-absorbing type integrated undercarriage

Abstract

The utility model relates to the technical field of aircraft take-off and landing systems, in particular to an anti-impact multi-support energy absorption type integrated undercarriage which comprises a plurality of overlapped combined springs, an anti-impact device, a supporting disc, an impact disc, a plurality of supporting devices and a pressing disc, the anti-impact device is connected with the supporting disc, the supporting devices are connected with the supporting disc, and the pressing disc is connected with the supporting disc. Impact force generated when an aircraft lands is dispersed to the multiple devices to be borne, the overlapped combined springs are placed in the anti-impact device and the multiple supporting devices, and part of huge impact force generated when the aircraft lands is converted into elastic potential energy and other forms of energy to be stored, so that the energy consumption of the aircraft is reduced, and the upper load limit of an aircraft landing gear is increased. The device is ingenious in design, novel in structure, capable of effectively improving safety, stability and energy use efficiency when the airplane takes off and lands, capable of better protecting life and property safety of passengers and unit workers, and suitable for being widely popularized and used.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft take-off and landing systems, in particular to an impact-resistant multi-support energy-absorbing integrated landing gear. Background Art

[0002] The landing gear is one of the main components of an aircraft, and is responsible for the important tasks of takeoff, landing, taxiing, ground movement and parking. Its performance is directly related to the use and safety of the aircraft. Without a good buffer system, the huge impact force may cause damage or destruction to the fuselage structure. In addition, when an emergency occurs and the aircraft needs to make an emergency landing, a good landing gear device can help the aircraft land safely and reduce the harm to passengers and crew members, thereby better fulfilling the important mission of protecting the safety of life and property.

[0003] Usually, during take-off and landing, the landing gear must withstand huge impact forces, especially during landing, when the landing gear must withstand an impact force three times the weight of the fuselage. When the aircraft is in an unpredictable situation such as overspeed or turbulence when landing, the lack of a good buffer device in the landing gear will lead to serious safety accidents. For example, the publication number CN107339360A proposes an aircraft landing gear buffer, which enhances the buffering function of the aircraft landing gear through an outer cylinder assembly, a hydraulic rod assembly and a plunger assembly, and improves the working safety of the aircraft during landing. However, the safety and stability performance of the aircraft landing gear has not been substantially improved. If the impact force is too large when the aircraft lands, it is impossible to disperse and absorb the impact force received by the landing gear, and the landing gear structure will still be damaged and destroyed. Therefore, in order to further improve the impact resistance and buffering performance of the landing gear, it is of great significance to study an impact-resistant multi-support energy-absorbing integrated landing gear. Utility Model Content

[0004] In view of the above technical problems, the utility model provides an impact-resistant multi-support energy-absorbing integrated landing gear, which has good impact resistance and buffering performance, can reduce energy loss, has a simple design, and can make aircraft take-off and landing safer and more efficient. The technical solutions adopted by the utility model are as follows:

[0005] An impact-resistant multi-support energy-absorbing integrated landing gear comprises an impact-resistant device, a support plate and at least two support devices, wherein the impact-resistant device and the support device are respectively arranged at the upper and lower ends of the support plate;

[0006] The anti-impact device and the support device both include a top support seat, a bottom support seat, an outer tube, a hydraulic rod and a superimposed combination spring. One end of the hydraulic rod is slidably arranged in the outer tube. A sealing ring is arranged between the hydraulic rod and the outer tube. A limiting structure for limiting the separation of the hydraulic rod is arranged at the outer end of the outer tube. A superimposed combination spring is arranged between the inner end of the hydraulic rod and the inner bottom of the outer tube. One end of the outer tube away from the hydraulic rod is fixedly connected to the bottom support seat. The bottom support seat is fixedly arranged on the support plate. One end of the hydraulic rod away from the outer tube is fixedly connected to the top support seat.

[0007] The top support seat of the support device is used to connect to the tire of the aircraft, and the top support seat of the impact-resistant device is used to connect to the fuselage of the aircraft.

[0008] Preferably, one end of the laminated combination spring close to the hydraulic rod is connected to a pressure plate, one end of the pressure plate is in contact with the laminated combination spring, and the other end of the pressure plate is connected to an impact plate that cooperates with the hydraulic rod.

[0009] Preferably, at least three supporting devices are provided.

[0010] Preferably, the material of the laminated combination spring is 60Si2MnA or 50CrVA.

[0011] Preferably, at least four superimposed combined springs are arranged in any of the outer cylinders.

[0012] Preferably, the support devices are arranged in a linear or non-linear distribution.

[0013] Compared with the prior art, the utility model has the following beneficial effects:

[0014] 1. The utility model utilizes multiple supporting devices and anti-impact devices to work together to disperse the impact force on the aircraft to multiple devices, has good stability on the ground, can withstand the impact force and turbulence generated when the aircraft lands at high speed, keeps the aircraft gliding smoothly on the ground, and avoids wheel bouncing.

[0015] 2. The utility model adds a composite spring to the anti-impact device and multiple supporting devices. When the wheel is impacted, the hydraulic rod moves toward the inside of the outer tube, thereby squeezing the composite spring, which greatly improves the upper limit of the bearing capacity of the aircraft landing gear structure.

[0016] 3. The aircraft landing gear of the utility model contains a plurality of superimposed combined springs, which can better absorb the vertical kinetic energy of the aircraft during landing and improve the energy absorption efficiency.

[0017] In summary, the utility model has an ingenious design and a novel structure, can effectively improve the safety and stability of an aircraft during takeoff and landing, better protect the life and property safety of passengers and crew members, and is suitable for wide promotion and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The specific implementation of the utility model will be further described in detail below with reference to the accompanying drawings.

[0019] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0020] Figure 2 It is a schematic diagram of the structure of the anti-impact device and the supporting device of the utility model;

[0021] Figure 3 It is a structural schematic diagram of the laminated combined spring of the utility model.

[0022] In the figure: 1-top support seat, 2-hydraulic rod, 3-outer cylinder, 4-sealing ring, 5-impact plate, 6-pressure plate, 7-laminated combination spring, 8-bottom support seat, 9-aircraft tire, 10-support plate, 11-anti-impact device, 12-support device, 1-1 anti-impact device top support seat, 1-2 anti-impact device hydraulic rod, 1-3 anti-impact device outer cylinder, 1-4 anti-impact device sealing ring, 1-5 anti-impact device impact plate, 1-6 anti-impact device pressure plate, 1-7 anti-impact device laminated combination spring, 1-8 anti-impact device bottom support seat, 2-1 first support device top support seat, 2-2 first support device hydraulic rod, 2-3 first support device outer cylinder, 2-4 first support device sealing ring, 2-5 first support device impact plate, 2-6 The pressure plate of the I support device, 2-7 the superimposed combination spring of the I support device, 2-8 the bottom support seat of the I support device, 3-1 the top support seat of the II support device, 3-2 the hydraulic rod of the II support device, 3-3 the outer cylinder of the II support device, 3-4 the sealing ring of the II support device, 3-5 the impact plate of the II support device, 3-6 the pressure plate of the II support device, 3-7 the superimposed combination spring of the II support device, 3-8 the bottom support seat of the II support device, 4-1 the top support seat of the III support device, 4-2 the hydraulic rod of the III support device, 4-3 the outer cylinder of the III support device, 4-4 the sealing ring of the III support device, 4-5 the impact plate of the III support device, 4-6 the pressure plate of the III support device, 4-7 the superimposed combination spring of the III support device, 4-8 the bottom support seat of the III support device. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] like Figures 1 to 3As shown, the utility model provides an impact-resistant multi-support energy-absorbing integrated landing gear device, which can disperse the huge impact force received by the aircraft during landing to multiple support devices, thereby providing a certain safety guarantee for the aircraft's overspeed forced landing.

[0025] Specifically, it includes an anti-impact device 11, a support plate 10 and a support device 12. In this embodiment, three support devices are provided. The anti-impact device is provided at the upper end of the support plate 10, and three support devices 12 are provided at the lower end of the support plate 10. The three support devices 12 can be arranged in a linear distribution or a nonlinear distribution, which is specifically distributed according to the actual situation such as the number of aircraft tires and the number of rows.

[0026] The anti-impact device 11 and the supporting device 12 both include a top supporting seat 1, a bottom supporting seat 8, an outer tube 3, a hydraulic rod 2 and a laminated combination spring 7. One end of the hydraulic rod 2 is slidably arranged in the outer tube 3. A sealing ring 4 is arranged between the hydraulic rod 2 and the outer tube 3. A hydraulic assembly is formed by the hydraulic rod 2 and the outer tube 3. The outer end of the outer tube 3 is provided with a limiting structure for limiting the detachment of the hydraulic rod 2.

[0027] A superimposed combination spring 7 is arranged between the inner end of the hydraulic rod 2 and the inner bottom of the outer tube 3. The end of the superimposed combination spring 7 close to the hydraulic rod 2 is connected to a pressure plate 6. One end of the pressure plate 6 contacts with the superimposed combination spring 7. The other end of the pressure plate 6 is connected to an impact plate 5 that cooperates with the hydraulic rod 2. The end of the outer tube 3 away from the hydraulic rod 2 is fixedly connected to the bottom support seat 8. The bottom support seat 8 is fixedly arranged on the support plate 10. The end of the hydraulic rod 2 away from the outer tube 3 is fixedly connected to the top support seat 1.

[0028] When the top support seat 1 is subjected to impact force, it pushes the hydraulic rod 2 to move into the outer tube 3, and then pushes the corresponding impact plate 5 and pressure plate 6 to move into the outer tube 3, squeezing the laminated combination spring 7, and converting the impact force into other forms of energy such as elastic potential energy and storing them.

[0029] The three support devices 12 are respectively the first support device, the second support device, and the third support device. The top support seat 1-1 of the impact-resistant device is rigidly connected to the aircraft fuselage. The top support seat 2-1 of the first support device, the top support seat 3-1 of the second support device, and the top support seat 4-1 of the third support device are rigidly connected to the axle ends of the aircraft tires.

[0030] The top support seat 1-1 of the anti-impact device, the top support seat 2-1 of the first support device, the top support seat 3-1 of the second support device, and the top support seat 4-1 of the third support device are mechanically connected to the hydraulic rod 1-2 of the anti-impact device, the hydraulic rod 2-2 of the first support device, the hydraulic rod 3-2 of the second support device, and the hydraulic rod 4-2 of the third support device respectively.

[0031] The anti-impact device sealing ring 1-4, the first support device sealing ring 2-4, the second support device sealing ring 3-4, and the third support device sealing ring 4-4 ​​are respectively installed at the bottom of the anti-impact device hydraulic rod 1-2, the first support device hydraulic rod 2-2, the second support device hydraulic rod 3-2, and the third support device hydraulic rod 4-2 and are sealed with the corresponding outer cylinder.

[0032] The anti-impact device composite spring 1-7, the first support device composite spring 2-7, the second support device composite spring 3-7, and the third support device composite spring 4-7 are respectively arranged on the inner bottom of the anti-impact device outer cylinder 1-3, the first support device outer cylinder 2-3, the second support device outer cylinder 3-3, and the third support device outer cylinder 4-3, and the inner end of the composite spring is rigidly connected to the inner bottom of the corresponding outer cylinder. The outer ends of the anti-impact device composite spring 1-7, the first support device composite spring 2-7, the second support device composite spring 3-7, and the third support device composite spring 4-7 are rigidly connected to the anti-impact device pressure plate 1-6, the first support device pressure plate 2-6, the second support device pressure plate 3-6, and the third support device pressure plate 4-6, respectively. The outer ends of the anti-impact device pressure plate 1-6, the first support device pressure plate 2-6, the second support device pressure plate 3-6, and the third support device pressure plate 4-6 are rigidly connected to the anti-impact device impact plate 1-5, the first support device impact plate 2-5, the second support device impact plate 3-5, and the third support device impact plate 4-5. The outer ends of the anti-impact device impact plate 1-5, the first support device impact plate 2-5, the second support device impact plate 3-5, and the third support device impact plate 4-5 are respectively matched with the anti-impact device hydraulic rod 1-2, the first support device hydraulic rod 2-2, the second support device hydraulic rod 3-2, and the third support device hydraulic rod 4-2. The anti-impact device bottom support seat 1-8, the first support device bottom support seat 2-8, the second support device bottom support seat 3-8, and the third support device bottom support seat 4-8 are rigidly connected to the support plate 10.

[0033] Preferably, the material of the laminated composite spring is 60Si2MnA spring steel or 50CrVA spring steel.

[0034] Preferably, at least four laminated combined springs 7 are arranged in any outer cylinder 3 .

[0035] By connecting the bottom support seat 8 of the anti-impact device 11 and the three support devices 12 with the support plate 10, the impact force during the landing of the aircraft can be dispersed to multiple devices, effectively avoiding the safety hazard caused by the damage or destruction of the landing gear structure due to excessive impact force. The composite spring 7 is rigidly connected to the bottom of the outer tube 3 of the corresponding anti-impact device 11 and the support device 12. When the wheel is impacted, the hydraulic rod 2 moves toward the inside of the outer tube 3, pushing the impact plate 5 and the pressure plate 6 to move toward the inside of the outer tube 3, and then squeezing the composite spring 7, converting the huge impact force of part of the aircraft during landing into other forms of energy such as elastic potential energy and storing it, which can reduce the energy consumption of the aircraft to a certain extent. The pressure plate is connected to the hydraulic rod through the impact plate. When the aircraft is overspeeding or makes an emergency landing under abnormal conditions, the hydraulic assembly cannot effectively buffer, and the hydraulic rod will push the pressure plate to squeeze the composite spring for secondary buffering and energy absorption.

[0036] The landing gear can be distributedly arranged in one or more sets on the front landing gear and the rear landing gear of the aircraft according to the actual speed and load conditions of the aircraft.

[0037] Working principle:

[0038] When the aircraft lands, the wheels are impacted. Due to the rigid connection between the components, the impact force will be transmitted to the tire axle end, and the top support seat 2-1 of the first support device, the top support seat 3-1 of the second support device, and the top support seat 4-1 of the third support device rigidly connected to the tire axle ends will push the anti-impact device hydraulic rod 1-2, the first support device hydraulic rod 2-2, the second support device hydraulic rod 3-2, and the third support device hydraulic rod 4-2 to move inside the outer tube respectively, and transmit part of the impact force to the anti-impact device through the support plate 10 connected to the bottom support seat 2-8 of the first support device, the bottom support seat 3-8 of the second support device, and the bottom support seat 4-8 of the third support device. In this way, the huge impact force when the aircraft lands can be buffered and dispersed from the original one device to multiple devices, thereby greatly improving the stability of the aircraft landing gear.

[0039] When the aircraft makes an emergency landing at an excessive speed, the hydraulic device cannot effectively buffer the impact, and the anti-impact device hydraulic rod 1-2, the first support device hydraulic rod 2-2, the second support device hydraulic rod 3-2, and the third support device hydraulic rod 4-2 will respectively push the anti-impact device pressure plate 1-6, the first support device pressure plate 2-6, the second support device pressure plate 3-6, and the third support device pressure plate 4-6 through the anti-impact device impact plate 1-5, the first support device impact plate 2-5, the second support device impact plate 3-5, and the third support device impact plate 4-5 to squeeze the anti-impact device superimposed combination spring 1-7, the first support device superimposed combination spring 2-7, the second support device superimposed combination spring 3-7, and the third support device superimposed combination spring 4-7 for secondary buffering and energy absorption, which can not only increase the upper limit of the bearing capacity of the aircraft landing gear structure, avoid the safety hazard caused by the damage or destruction of the landing gear structure due to excessive impact force, but also improve the energy utilization efficiency to a certain extent.

[0040] Only the preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention, and various changes should be included in the protection scope of the present invention.

Claims

1. An impact-resistant multi-support energy-absorbing integrated landing gear, characterized in that: It comprises a support plate (10), an anti-impact device (11), and a plurality of support devices (12), wherein the anti-impact device (11) and the support device (12) are respectively arranged at the upper and lower ends of the support plate (10); The anti-impact device (11) and the support device (12) both comprise a top support seat (1), a bottom support seat (8), an outer cylinder (3), a hydraulic rod (2) and a composite spring (7); one end of the hydraulic rod (2) is slidably arranged in the outer cylinder (3); a sealing ring (4) is arranged between the hydraulic rod (2) and the outer cylinder (3); a limiting structure for limiting the hydraulic rod (2) from being disengaged is arranged at the outer end of the outer cylinder (3); a composite spring (7) is arranged between the inner end of the hydraulic rod (2) and the inner bottom of the outer cylinder (3); one end of the outer cylinder (3) away from the hydraulic rod (2) is fixedly connected to the bottom support seat (8); the bottom support seat (8) is fixedly arranged on the support plate (10); and one end of the hydraulic rod (2) away from the outer cylinder (3) is fixedly connected to the top support seat (1); The top support seat (1) of the support device (12) is used to connect to an aircraft tire (9), and the top support seat (1) of the impact-resistant device is used to connect to an aircraft fuselage.

2. The impact-resistant multi-support energy-absorbing integrated landing gear according to claim 1, characterized in that: One end of the laminated combination spring (7) close to the hydraulic rod (2) is connected to a pressure plate (6), one end of the pressure plate (6) is in contact with the laminated combination spring (7), and the other end of the pressure plate (6) is connected to an impact plate (5) that matches the hydraulic rod (2).

3. The impact-resistant multi-support energy-absorbing integrated landing gear according to claim 1, characterized in that: At least three supporting devices (12) are provided.

4. The impact-resistant multi-support energy-absorbing integrated landing gear according to claim 1, characterized in that: The material of the laminated composite spring is 60Si2MnA or 50CrVA.

5. The impact-resistant multi-support energy-absorbing integrated landing gear according to claim 1, characterized in that: At least four stacked combined springs (7) are arranged in any one of the outer cylinders (3).

6. The impact-resistant multi-support energy-absorbing integrated landing gear according to claim 1, characterized in that: The support devices (12) are arranged in a linear or non-linear distribution.

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