Frame type static test undercarriage

Abstract

The invention discloses a frame type undercarriage for a static test. The frame type undercarriage comprises an undercarriage body, two stable buffers and four hinge seats, the stable buffer comprises a buffer pipe, a first spring, a second spring, a balance column, a pull rod, a first hinge lug and a second hinge lug. According to the invention, the stability and precision of the frame type undercarriage in a static test can be obviously improved, the manufacturing, mounting and dismounting of the buffer become more convenient through the simplified structural design, and the labor intensity of operators is reduced. Meanwhile, a non-hydraulic element is adopted as a buffer core, so that the buffer is more reliable to use, performance fluctuation and maintenance difficulty possibly brought by the hydraulic element are avoided, and the efficiency and accuracy of the test process are improved.

Description

Technical Field

[0001] The invention relates to a landing gear test, in particular to a frame-type static test landing gear. Background Art

[0002] During the static test of the frame-type landing gear, the frame structure has a certain degree of pitch freedom, which can easily cause the landing gear to move unnecessarily during the test, thus affecting the accuracy and stability of the test. In order to solve this problem, it is usually necessary to install a stabilizing buffer between the frame and the support to limit the pitch freedom and ensure the stability of the frame during the test.

[0003] However, the existing frame-type landing gear stabilizer designs mainly use hydraulic buffers or similar complex components. Although these hydraulic buffers can provide the required buffering and stabilizing effects to a certain extent, their structures are relatively complex and inconvenient to disassemble and maintain, which increases the inconvenience and cost during use. In addition, the working state of the hydraulic buffer may be affected by factors such as temperature and pressure, resulting in unstable buffering effect, which in turn affects the accuracy of the test data. Summary of the invention

[0004] In order to solve the problems of complex design, inconvenient disassembly and maintenance of hydraulic buffers in the prior art, the present invention proposes a frame-type static test landing gear, which solves the problem of limiting the pitch freedom of the frame by optimizing the stable buffer between the frame and the pillar and adopting a simplified structure and high-efficiency materials, while improving the stability, disassembly and maintenance convenience of the buffer.

[0005] The present invention adopts the following technical solutions to solve the above technical problems: A frame-type static test landing gear comprises a landing gear body, first to second stabilizing buffers, and first to fourth articulated seats; The first to second stable buffers have the same structure, and both include a buffer tube, a first spring, a second spring, a balance column, a pull rod, a first hinge ear, and a second hinge ear; The buffer tube comprises a tube body and an end cover, wherein the tube body and the tube cover are both hollow cylinders with one end open and the other end closed, an outer thread is provided on the outer wall of the open end of the tube body, an inner thread matching the outer thread on the tube body is provided on the inner wall of the open end of the tube cover, and the tube cover and the tube body are connected by threads; a through hole for matching with the pull rod is provided at the center of the closed end of the tube cover; The balance column is a cylinder, which is arranged in the tube body and can slide freely along the tube body; The first spring is disposed in the tube body, one end of the first spring is fixedly connected to the closed end of the tube body, and the other end of the first spring is fixedly connected to one end of the balance column; One end of the pull rod is coaxially fixedly connected to an end of the balance column away from the first spring, and the other end extends out of the through hole of the tube cover. The diameter of the pull rod is smaller than the diameter of the balance column. The pull rod and the tube cover are clearance-matched at the through hole of the tube cover and can slide freely relative to the tube cover. The second spring is sleeved outside the pull rod and is located in the tube body, one end of the second spring is fixedly connected to the balance column, and the other end is fixedly connected to the closed end of the end cover; The first hinge ear is arranged at an end of the pull rod away from the balance column, and the second hinge ear is arranged at an end of the tube body away from the end cover; The first stabilizing buffer and the second stabilizing buffer are arranged in parallel, the first hinge ear of the first stabilizing buffer is hinged to the piston rod of the landing gear body through the first hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the second hinge seat, the first hinge ear of the second stabilizing buffer is hinged to the piston rod of the landing gear body through the third hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the fourth hinge seat, so that the piston rod of the landing gear body is located between the first stabilizer and the anti-torsion arm of the landing gear body.

[0006] As a further optimization solution of the frame-type static test landing gear of the present invention, the first spring and the second spring are both made of carbon steel.

[0007] As a further optimization scheme of a frame-type static test landing gear of the present invention, the shear modulus G of the first spring and the second spring is 79000 MPa, the length is 420 mm, the wire diameter is 25 mm, the total number of turns is 10 turns, and the outer diameter is 180 mm.

[0008] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects: The present invention uses two stable buffers designed in parallel to improve the overall stiffness, provide effective preload, and significantly improve the stability and accuracy of the frame-type landing gear in the static test. Its simplified structural design makes the manufacture, installation and removal of the buffer more convenient, reducing the labor intensity of the operator. At the same time, the use of non-hydraulic components as the buffer core makes the use of the buffer more reliable, avoiding the performance fluctuations and maintenance difficulties that may be caused by hydraulic components, thereby improving the efficiency and accuracy of the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 is a schematic structural diagram of a first stabilizing buffer in the present invention; Figure 3 It is a schematic diagram of the matching structure of the first and second stabilizing buffers and the landing gear body in the present invention.

[0010] In the figure, 1-landing gear body, 2-first stabilizing buffer, 3-second stabilizing buffer, 4-first articulated seat, 5-third articulated seat, 6-tube body, 7-end cover, 8-balance column, 9-first spring, 10-second spring, 11-pull rod, 12-first hinge ear, 13-second hinge ear, 14-piston rod of the landing gear body, 15-anti-torsion arm of the landing gear body, 16-frame of the landing gear body, 17-second articulated seat, 18-fourth articulated seat. DETAILED DESCRIPTION

[0011] The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings: The present invention can be implemented in many different forms and should not be considered to be limited to the embodiments described herein. On the contrary, these embodiments are provided to make this disclosure thorough and complete, and will fully express the scope of the present invention to those skilled in the art. In the accompanying drawings, components are enlarged for clarity.

[0012] As attached Figure 1 As shown, the present invention discloses a frame-type static test landing gear, comprising a landing gear body, first to second stabilizing buffers, and first to fourth articulated seats; like Figure 2 As shown, the first to second stable buffers have the same structure, and both include a buffer tube, a first spring, a second spring, a balance column, a pull rod, a first hinge ear, and a second hinge ear; The buffer tube comprises a tube body and an end cover, wherein the tube body and the tube cover are both hollow cylinders with one end open and the other end closed, an outer thread is provided on the outer wall of the open end of the tube body, an inner thread matching the outer thread on the tube body is provided on the inner wall of the open end of the tube cover, and the tube cover and the tube body are connected by threads; a through hole for matching with the pull rod is provided at the center of the closed end of the tube cover; The balance column is a cylinder, which is arranged in the tube body and can slide freely along the tube body; The first spring is disposed in the tube body, one end of the first spring is fixedly connected to the closed end of the tube body, and the other end of the first spring is fixedly connected to one end of the balance column; One end of the pull rod is coaxially fixedly connected to an end of the balance column away from the first spring, and the other end extends out of the through hole of the tube cover. The diameter of the pull rod is smaller than the diameter of the balance column. The pull rod and the tube cover are clearance-matched at the through hole of the tube cover and can slide freely relative to the tube cover. The second spring is sleeved outside the pull rod and is located in the tube body, one end of the second spring is fixedly connected to the balance column, and the other end is fixedly connected to the closed end of the end cover; The first hinge ear is arranged at an end of the pull rod away from the balance column, and the second hinge ear is arranged at an end of the tube body away from the end cover; like Figure 3As shown, the first stabilizing buffer and the second stabilizing buffer are arranged in parallel, the first hinge ear of the first stabilizing buffer is hinged to the piston rod of the landing gear body through the first hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the second hinge seat, the first hinge ear of the second stabilizing buffer is hinged to the piston rod of the landing gear body through the third hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the fourth hinge seat, so that the piston rod of the landing gear body is located between the first stabilizer and the anti-torsion arm of the landing gear body.

[0013] The first spring and the second spring are both made of carbon steel, with a shear modulus G of 79000MPa, a length of 420mm, a wire diameter of 25mm, a total number of turns of 10 turns, and an outer diameter of 180mm; the pitch of the 1-2 section and the 9-10 section is set to 30mm, the pitch of the 3-8 section is 50mm, and the spring stiffness is 66000N / m; The two stabilizing buffers are connected in parallel, doubling the stiffness.

[0014] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as generally understood by those skilled in the art in the art to which the present invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0015] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A frame-type static test landing gear, characterized in that: It includes a landing gear body, first to second stabilizing buffers, and first to fourth articulated seats; The first to second stable buffers have the same structure, and both include a buffer tube, a first spring, a second spring, a balance column, a pull rod, a first hinge ear, and a second hinge ear; The buffer tube comprises a tube body and an end cover, wherein the tube body and the tube cover are both hollow cylinders with one end open and the other end closed, an outer thread is provided on the outer wall of the open end of the tube body, an inner thread matching the outer thread on the tube body is provided on the inner wall of the open end of the tube cover, and the tube cover and the tube body are connected by threads; a through hole for matching with the pull rod is provided at the center of the closed end of the tube cover; The balance column is a cylinder, which is arranged in the tube body and can slide freely along the tube body; The first spring is disposed in the tube body, one end of the first spring is fixedly connected to the closed end of the tube body, and the other end of the first spring is fixedly connected to one end of the balance column; One end of the pull rod is coaxially fixedly connected to an end of the balance column away from the first spring, and the other end extends out of the through hole of the tube cover. The diameter of the pull rod is smaller than the diameter of the balance column. The pull rod and the tube cover are clearance-matched at the through hole of the tube cover and can slide freely relative to the tube cover. The second spring is sleeved outside the pull rod and is located in the tube body, one end of the second spring is fixedly connected to the balance column, and the other end is fixedly connected to the closed end of the end cover; The first hinge ear is arranged at an end of the pull rod away from the balance column, and the second hinge ear is arranged at an end of the tube body away from the end cover; The first stabilizing buffer and the second stabilizing buffer are arranged in parallel, the first hinge ear of the first stabilizing buffer is hinged to the piston rod of the landing gear body through the first hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the second hinge seat, the first hinge ear of the second stabilizing buffer is hinged to the piston rod of the landing gear body through the third hinge seat, and the second hinge ear is hinged to the frame of the landing gear body through the fourth hinge seat, so that the piston rod of the landing gear body is located between the first stabilizer and the anti-torsion arm of the landing gear body.

2. The frame-type static test landing gear according to claim 1, characterized in that: The first spring and the second spring are both made of carbon steel.

3. The frame-type static test landing gear according to claim 1, characterized in that: The shear modulus G of the first spring and the second spring is 79000 MPa, the length is 420 mm, the wire diameter is 25 mm, the total number of turns is 10, and the outer diameter is 180 mm.

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