Tandem type multi-strut undercarriage with load capable of being internally balanced and aircraft

Abstract

The invention provides a tandem type multi-strut undercarriage with loads capable of being internally balanced and an aircraft, and belongs to the field of aircraft undercarriages, the tandem type multi-strut undercarriage comprises at least two rocker arm type undercarriages arranged front and back, each rocker arm type undercarriage comprises a front supporting rod, an inclined strut, a buffer and a rocker arm, the front supporting rod is connected with the inclined strut, and the inclined strut is connected with the buffer; the inclined supporting column is connected with the rocker arm, the tail end of the rocker arm is connected with the airplane wheel structure, and the buffer is connected with the inclined supporting column and the rocker arm and used for buffering loads transmitted by the airplane wheel structure. And the undercarriage bracket is connected with the rocker arm of the rocker arm type undercarriage at the front end and the connecting point of the front supporting rod and the inclined supporting column of the rocker arm type undercarriage at the rear end, so that the rocker arm type undercarriages arranged front and back form a serial structure.

Description

Technical Field

[0001] The present application belongs to the field of aircraft landing gear, and in particular relates to a tandem multi-strut landing gear with internally balanced load and an aircraft. Background Art

[0002] The existing aircraft multi-strut landing gear generally installs several identical landing gears on the lower side of the fuselage to form a multi-strut landing gear. In this multi-strut landing gear structure, each landing gear is independent of each other, and each transfers the ground load it bears to the fuselage without affecting each other. However, in this structural form of multi-strut landing gear, the load of each strut cannot be internally balanced, thereby reducing part of the load transferred to the fuselage. Summary of the invention

[0003] The object of the present application is to provide a tandem multi-strut landing gear and an aircraft with internally balanced loads, so as to solve or alleviate at least one problem in the background technology.

[0004] The technical solution of the present application is: a tandem multi-strut landing gear with internally balanced load, comprising: At least two rocker-type landing gears arranged front and rear, the rocker-type landing gears comprising a front strut, an oblique strut, a buffer and a rocker arm, the front strut is connected to the oblique strut, the oblique strut is connected to the rocker arm, the end of the rocker arm is connected to the wheel structure, the buffer is respectively connected to the oblique strut and the rocker arm, and is used to buffer the load transmitted by the wheel structure; The landing gear bracket connects the rocker arm of the front rocker type landing gear and the front strut and the diagonal support connection point of the rear rocker type landing gear, thereby forming a tandem structure for the front and rear rocker type landing gears.

[0005] Preferably, the frontmost rocker landing gear further comprises a support arm, which connects the fuselage structure and a connection point between the front support rod and the diagonal support in the frontmost rocker landing gear.

[0006] Preferably, the load-bearing capacity of the two or more rocker-type landing gears is the same.

[0007] Preferably, the structural parameters of the rocker arm landing gear are the same, so as to achieve the same load-bearing capacity.

[0008] Preferably, the buffer is a hydraulic buffer.

[0009] Preferably, the landing gear support is arranged along the vertical direction.

[0010] Preferably, bearings are provided at the connection positions between the buffer, the oblique support and the rocker arm.

[0011] In addition, the present application also provides an aircraft, comprising any of the above-described tandem multi-strut landing gears capable of internally balancing loads.

[0012] The load-balanced tandem multi-strut landing gear provided in the present application utilizes the lever principle to achieve internal balance of the ground load on the landing gear bracket, thereby achieving the effect of reducing the load transferred to the body. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0014] Figure 1 It is a schematic diagram of a tandem multi-strut landing gear (three landing gears) according to an embodiment of the present application.

[0015] Figure 2 A schematic diagram of a ground load transfer path for a tandem multi-strut landing gear according to an embodiment of the present application. DETAILED DESCRIPTION

[0016] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0017] The present application provides a tandem multi-strut landing gear structure, which enables a portion of the ground load to be balanced inside the landing gear, thereby achieving the purpose of reducing the load transferred to the body and increasing the service life of the landing gear.

[0018] The tandem multi-strut landing gear structure provided by the present application includes: At least two rocker-type landing gears are arranged front and rear, each of which includes a front strut, an oblique strut, a buffer and a rocker arm, the front strut is connected to the oblique strut, the oblique strut is connected to the rocker arm, the end of the rocker arm is connected to the wheel structure, and the buffer is respectively connected to the oblique strut and the rocker arm for buffering the load transmitted by the wheel structure; The landing gear bracket connects the rocker arm of the front rocker type landing gear and the front strut and the diagonal support connection point of the rear rocker type landing gear, thereby forming a serial structure for the front and rear rocker type landing gears.

[0019] In the present application, the frontmost rocker landing gear also includes a support arm, which is connected to the fuselage structure and the connection point between the front strut and the diagonal strut, and is used to transfer the wheel structure load to the fuselage structure.

[0020] In some embodiments of the present application, bearings may be provided at the connection positions of the components that bear larger loads in each rocker landing gear, that is, the connection positions of the buffer with the diagonal struts and the rocker arms.

[0021] In a preferred embodiment of the present application, the load-bearing capacity of the plurality of tandem rocker landing gears is the same, that is, the diagonal struts, buffers and other structural dimensions of the rocker landing gears are the same. Further, in the rocker landing gear, the buffer may be a hydraulic buffer.

[0022] like Figure 1 Shown is a schematic diagram of a tandem multi-strut landing gear with three rocker arm landing gears provided in this embodiment of the present application, wherein the tandem multi-strut landing gear includes a front rocker arm landing gear 10 , an intermediate rocker arm landing gear 20 and a rear rocker arm landing gear 30 .

[0023] The front rocker arm landing gear 10, the intermediate rocker arm landing gear 20 and the rear rocker arm landing gear 30 are similar in structure. The front rocker arm landing gear 10 comprises a front landing gear front strut 11, a front landing gear oblique strut 12, a front landing gear buffer 13 and a front landing gear rocker arm 14. One end of the front landing gear front strut 11 is connected to the fuselage structure, and the other end is connected to the front landing gear oblique strut 12. The lower end of the front landing gear oblique strut 12 is connected to the front landing gear rocker arm 14. The lower end of the front landing gear rocker arm 14 is connected to the wheel structure (not shown). The front landing gear buffer 13 is arranged between the front landing gear oblique strut 12 and the front landing gear rocker arm 14 to buffer the load of the wheel structure. The front rocker arm landing gear 10 is the frontmost landing gear, and therefore, the front rocker arm landing gear 10 also includes a support arm 15 , which connects the fuselage structure and the connection point between the front landing gear front strut 11 and the front landing gear oblique strut 12 .

[0024] Similarly, the intermediate rocker arm landing gear 20 includes an intermediate landing gear front strut 21, an intermediate landing gear oblique strut 22, an intermediate landing gear buffer 23 and an intermediate landing gear rocker arm 24. The rear rocker arm landing gear 30 includes a rear landing gear front strut 31, a rear landing gear oblique strut 32, a rear landing gear buffer 33 and a rear landing gear rocker arm 34. The connection relationship between the components of the intermediate rocker arm landing gear 20 and the rear rocker arm landing gear 30 will not be described again.

[0025] The landing gear support 40 includes a first landing gear support 41, a second landing gear support 42 and a third landing gear support 43. The first landing gear support 41 is respectively connected to the front landing gear rocker arm 14 and the connection point between the middle landing gear front strut 21 and the middle landing gear oblique strut 22. The second landing gear support 42 is respectively connected to the middle landing gear rocker arm 24 and the connection point between the rear landing gear front strut 31 and the rear landing gear oblique strut 32. The third landing gear support 43 is connected to the rear landing gear rocker arm 34, thereby forming the three rocker arm landing gears into a serial structure.

[0026] In a preferred embodiment of the present application, the landing gear support 40 is arranged along the vertical direction, so that when the rocker arm transfers the load to the landing gear support 40, the component can be avoided.

[0027] like Figure 2The figure shows a schematic diagram of the ground load transfer path of a tandem multi-strut landing gear according to an embodiment of the present application, wherein the front rocker arm landing gear 10 and the intermediate rocker arm landing gear 20 are used as examples for explanation. When a ground load F0 (assuming that the load F0=1) acts on the front landing gear rocker arm 14 and the intermediate landing gear rocker arm 24, the ground load on the intermediate rocker arm landing gear 20 will take the second landing gear support 42 as the rotation point, and generate an upward support reaction force F1 (for example, the load value of the support reaction force F1 is 0.4) on the first landing gear support 41 through the intermediate landing gear rocker arm 24, the intermediate landing gear oblique strut 22, the intermediate landing gear buffer 23 and other components, and at the same time generate a downward support reaction force F2 (for example, the load value of the support reaction force F2 is 1.4) on the second landing gear support 42. Similarly, the ground load on the front rocker arm landing gear 10 will generate an upward support reaction force F1 on the front landing gear support arm 15, and a downward support reaction force F2 on the first landing gear support 41. In this way, the support reaction forces generated by the ground loads of the front rocker arm landing gear 10 and the intermediate rocker arm landing gear 20 on the first landing gear support 41 will be internally balanced, and the load transmitted to the fuselage by the first landing gear support 41 is only F2-F1=1.4-0.4=1, thereby achieving the purpose of load reduction.

[0028] The load-balanced tandem multi-strut landing gear provided in the present application utilizes the lever principle to achieve internal balance of the ground load on the landing gear bracket, thereby reducing the load transferred to the body.

[0029] The present application has strong scalability and can continue to connect the landing gears in series to achieve a landing gear arrangement with more struts.

[0030] In addition, the present application also provides an aircraft, which includes the above-mentioned tandem multi-strut landing gear with internally balanced load.

[0031] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A tandem multi-strut landing gear with internal load balance, characterized in that: include: At least two rocker-type landing gears arranged front and rear, the rocker-type landing gears comprising a front strut, an oblique strut, a buffer and a rocker arm, the front strut is connected to the oblique strut, the oblique strut is connected to the rocker arm, the end of the rocker arm is connected to the wheel structure, the buffer is respectively connected to the oblique strut and the rocker arm, and is used to buffer the load transmitted by the wheel structure; The landing gear bracket connects the rocker arm of the front rocker landing gear and the front strut and the diagonal support connection point of the rear rocker landing gear, thereby forming a tandem structure for the front and rear rocker landing gears.

2. The load-balanced tandem multi-strut landing gear according to claim 1, characterized in that: The frontmost rocker arm landing gear also includes a support arm, which connects the fuselage structure and the connection point between the front support rod and the diagonal support in the frontmost rocker arm landing gear.

3. The load-balanced tandem multi-strut landing gear according to claim 1, characterized in that: Two or more rocker arm landing gears have the same load capacity.

4. The load-balanced tandem multi-strut landing gear according to claim 3, characterized in that: The rocker-type landing gears have the same structural parameters, thereby achieving the same load-bearing capacity.

5. The load-balanced tandem multi-strut landing gear according to claim 4, characterized in that: The buffer is a hydraulic buffer.

6. The load-balanced tandem multi-strut landing gear according to claim 1, characterized in that: The landing gear support is arranged along the vertical direction.

7. The load-balanced tandem multi-strut landing gear according to claim 1, characterized in that: A bearing is provided at the connection position between the buffer, the oblique support and the rocker arm.

8. An aircraft, characterized in that: The aircraft comprises a tandem multi-strut landing gear with internally balanced load as described in any one of claims 1-7.

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