Aircraft front wheel turning test device

Abstract

The utility model provides an airplane front wheel turning test device. The airplane front wheel turning test device comprises a fixture, a lifting hanging basket and a loading cylinder used for driving the lifting hanging basket to lift in the fixture, and the outer surface of the bottom of the lifting hanging basket is provided with a main rotating shaft support used for corresponding to the position of a main rotating shaft of an undercarriage and a supporting rod support used for corresponding to the position of a supporting rod of the undercarriage. A turning base is arranged on the inner surface of the bottom of the fixture, and a turning clamp used for being connected with an airplane wheel axle of the undercarriage is arranged at the upper end of the turning base. According to the utility model, the main rotating shaft support and the supporting rod support are arranged on the lifting hanging basket capable of ascending and descending, so that the problem that the degree of freedom in the vertical direction in the test of the existing test device is limited is solved, the airplane body load can be really simulated, and the pressure change under different temperature conditions can be adapted.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft landing gear testing, in particular to an aircraft front wheel turning test device; the utility model is suitable for aircraft front wheel turning tests, in particular for turning tests with large displacement in up and down directions and large body load during the front wheel turning test. Background Art

[0002] Before any aircraft model is put into use, the front wheels of the aircraft must be subjected to a turning test, which is mainly used to evaluate the durability of the turning mechanism, the sealing performance of the circumferential movement of the sealing device, etc.

[0003] like Figure 1 As shown, a conventional aircraft landing gear includes a main rotating shaft 100, a strut 200, an outer tube 300, a rotating mechanism 400, an anti-torsion arm 500 and a wheel axle 600. The main rotating shaft 100, the strut 200 and the outer tube 300 are connected as a whole, one end of the rotating mechanism 400 is fixedly connected to the outer tube 300, and the other end is connected to the anti-torsion arm 500 through a gear, and the anti-torsion arm 500 is connected to the wheel axle 600.

[0004] like Figure 2 As shown, the existing test device includes a jig 1, on which an actuator support 12, a main rotating shaft support 6, a strut support 7, a turning clamp 9 and a turning base 10 are provided. When the landing gear is conducting a turning test, the main rotating shaft 100 is connected to the main rotating shaft support 6 on the jig 1, the strut 200 is connected to the strut support 7 on the jig 1, and the actuator is connected to the actuator support 12 on the jig 1. When the rotating mechanism 400 supplies hydraulic pressure, the anti-torsion arm 500 and the wheel axle 600 are driven to rotate through gears to achieve turning. The turning clamp 9 is used to fix the wheel axle 600 and adjust the different compression amounts caused by the use load. The turning base 10 is used to establish load and drive turning.

[0005] When the test device is tested, it is necessary to design the tooling to compensate for the compression through the turning clamp 9. The freedom in the up and down directions is constrained, and the simulated aircraft fuselage load is somewhat different from the actual load. Especially under high and low temperature conditions, the air pressure causes the load to change, and it is impossible to truly simulate the aircraft usage status, and the versatility is poor. Utility Model Content

[0006] The utility model aims to provide an aircraft front wheel turning test device, which can apply corresponding loads to landing gears of different models in a simple and convenient way to truly simulate the turning state of the aircraft.

[0007] The technical solution of the utility model is: an aircraft front wheel turning test device, comprising a jig, a lifting basket and a loading cylinder for driving the lifting basket to rise and fall in the jig, the bottom outer surface of the lifting basket is provided with a main rotating shaft support corresponding to the main rotating shaft position of the landing gear and a strut support corresponding to the strut position of the landing gear, the bottom inner surface of the jig is provided with a turning base, and the upper end of the turning base is provided with a turning clamp for connecting with the wheel axle of the landing gear.

[0008] Preferably, two loading cylinders are symmetrically arranged on the lifting basket.

[0009] Preferably, the loading cylinder includes a first base arranged at the end of the piston rod and a second base arranged at the end of the cylinder barrel, and the second base is arranged close to the piston rod; the piston rod of the loading cylinder is arranged upward, so that the first base is connected to the lifting basket, and the second base is connected to the frame.

[0010] Preferably, a displacement sensor for sensing the lifting position of the lifting basket is provided between the lifting basket and the frame.

[0011] Preferably, the displacement sensor comprises a pull rope arranged vertically, the lower end of the pull rope is connected to the sensing end, the upper end of the pull rope is connected to the lifting basket, and the sensing end is connected to the frame.

[0012] Preferably, the frame is provided with a vertically extending guide rail, and the lifting basket is provided with a guide rail seat adapted to the guide rail.

[0013] Preferably, a counterweight is installed on the top of the lifting basket.

[0014] Compared with the related art, the beneficial effects of the utility model are:

[0015] 1. The main rotary shaft support and the strut support are arranged on a lifting basket that can be raised and lowered, so as to solve the problem that the freedom of the existing test device in the up and down directions is limited during the test, and the load of the aircraft fuselage can be truly simulated to adapt to the pressure changes under different temperature conditions;

[0016] Second, the loading cylinder can be adjusted dynamically in real time to adjust the load and compression requirements of different types of aircraft on the landing gear, which can truly simulate the actual state of the aircraft turning, and is easy to replace, with high versatility and repeatability;

[0017] 3. Improve test efficiency, facilitate implementation and have wide adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a structural diagram of a certain type of aircraft landing gear;

[0019] Figure 2It is a structural schematic diagram of an existing aircraft nose wheel turning test device;

[0020] Figure 3 A schematic structural diagram of a first viewing angle of the aircraft front wheel turning test device provided by the utility model;

[0021] Figure 4 A schematic structural diagram of a second viewing angle of the aircraft front wheel turning test device provided by the utility model;

[0022] Figure 5 for Figure 3 Schematic diagram of the frame, turning clamp and turning base removed.

[0023] In the accompanying drawings: 1, jig; 101, first flange; 102, second flange; 2, loading cylinder; 21, first base; 22, second base; 3, lifting basket; 4, guide rail; 5, guide rail seat; 6, main rotary shaft support; 7, strut support; 8, test piece; 9, turning clamp; 10, turning base; 11, displacement sensor; 111, pull rope; 112, sensing end; 12, actuator support; 100, main rotary shaft; 200, strut; 300, outer cylinder; 400, rotating mechanism; 500, anti-torsion arm; 600, wheel axle. DETAILED DESCRIPTION

[0024] The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments. It should be noted that the embodiments and features in the embodiments of the present invention can be combined with each other without conflict. For the convenience of description, if the words "upper", "lower", "left" and "right" appear in the following text, they only indicate that the upper, lower, left and right directions are consistent with the drawings themselves, and do not limit the structure.

[0025] like Figure 3 , Figure 4 , Figure 5 As shown, an aircraft front wheel turning test device provided in this embodiment includes a jig 1, a loading cylinder 2, a lifting basket 3, a guide rail 4, a guide rail seat 5, a main rotating shaft support 6, a strut support 7, a turning clamp 9, a turning base 10 and a displacement sensor 11.

[0026] The jig 1 is a frame structure built according to the test requirements, which can be divided into an upper layer and a lower layer. A guide rail 4 is provided on the side wall of the upper layer. The lifting basket 3 is an assembled box-shaped structure, and a guide rail seat 5 is provided on its outer periphery to slide with the guide rail 4, so that the lifting basket 3 can be raised and lowered inside the upper layer of the jig 1. A counterweight block (not shown) is installed on the top of the lifting basket 3 by bolts, and the counterweight block is used to maintain the stability of the lifting basket 3.

[0027] like Figure 5As shown, a main rotating shaft support 6 corresponding to the main rotating shaft 100 of the landing gear and a strut support 7 corresponding to the strut 200 of the landing gear are provided on the bottom outer surface of the jig 1. Two main rotating shaft supports 6 are provided in the Y direction of the lifting cradle 3, and the strut support 7 is provided on the side of the main rotating shaft support 6 in the X direction.

[0028] like Figure 5 As shown, two loading cylinders 2 are symmetrically arranged on the lifting basket 3. The two ends of the Y direction of the bottom outer surface of the frame 1 are also provided with first flanges 101. The loading cylinder 2 includes a first base 21 arranged at the end of the piston rod and a second base 22 arranged at the end of the cylinder barrel. The second base 22 is arranged close to the piston rod. The piston rod of the loading cylinder 2 is arranged upward, so that the first base 21 is hinged to the first flange 101 of the lifting basket 3 by bolts. Figure 3 As shown, the lower surface of the top beam of the lower layer of the frame 1 is provided with a second flange 102, one end of the second flange 102 is connected to the frame 1, and the other end is cantilevered for the cylinder barrel of the loading cylinder 2 to pass through. The second base 22 is fixedly connected to the second flange 102 by bolts.

[0029] like Figure 4 As shown, a turning base 10 is provided on the inner surface of the bottom of the jig 1. A turning clamp 9 for connecting to the wheel axle 600 of the landing gear is provided at the upper end of the turning base 10. The turning base 10 is used to establish load and drive turning.

[0030] like Figure 3 As shown, a displacement sensor 11 for sensing the lifting position of the lifting basket is provided between the lifting basket 3 and the frame 1. The displacement sensor 11 comprises a vertically arranged pull rope 111, the lower end of the pull rope 111 is connected to a sensing end 112, the upper end of the pull rope 111 is connected to the lifting basket 3, and the sensing end 112 is connected to the frame 1.

[0031] like Figure 1 , Figure 3 , Figure 4 As shown, before the test, the main rotating shaft 100 of the test piece 8 is fixed on the main rotating shaft support 6, the strut 200 is fixed on the strut support 7, and the wheel axle 600 is fixed on the turning clamp 9. The loading cylinder 2 is used to simulate the load of the body itself and adapt to the load changes caused by the pressure changes in different temperature environments, and dynamically adjust the tensile and compressive loads through the lifting and lowering loading method. When the compression amount is adjusted, the compression amount of the test piece 8 is adjusted accordingly. The displacement sensor 11 dynamically monitors and feeds back the compression amount to output a signal, and the control unit outputs an instruction on whether to adjust the compression amount to the loading cylinder 2 for execution.

[0032] The utility model studies the turning loading characteristics of different landing gear products, applies corresponding loads to landing gears of different models in a simple and convenient way, and truly simulates the turning state of the aircraft.

[0033] The above description is only an embodiment of the present invention, and does not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the contents of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. An aircraft front wheel turning test device, characterized in that: The invention comprises a jig (1), a lifting basket (3) and a loading cylinder (2) for driving the lifting basket (3) to move up and down in the jig (1); a main rotating shaft support (6) corresponding to the main rotating shaft position of the landing gear and a strut support (7) corresponding to the strut position of the landing gear are provided on the bottom outer surface of the jig (1); a turning base (10) is provided on the bottom inner surface of the jig (1); and a turning clamp (9) for connecting to the wheel axle of the landing gear is provided on the upper end of the turning base (10).

2. The aircraft front wheel turning test device according to claim 1, characterized in that: Two loading cylinders (2) are symmetrically arranged on the lifting basket (3).

3. The aircraft front wheel turning test device according to claim 1, characterized in that: The loading cylinder (2) comprises a first base (21) arranged at the end of a piston rod and a second base (22) arranged at the end of a cylinder barrel, wherein the second base (22) is arranged close to the piston rod; the piston rod of the loading cylinder (2) is arranged upward, so that the first base (21) is connected to the lifting basket (3), and the second base (22) is connected to the frame (1).

4. The aircraft front wheel turning test device according to claim 1, characterized in that: A displacement sensor (11) for sensing the lifting position of the lifting basket (3) is provided between the lifting basket (3) and the frame (1).

5. The aircraft front wheel turning test device according to claim 4, characterized in that: The displacement sensor (11) comprises a pull rope (111) arranged vertically, the lower end of the pull rope (111) being connected to a sensing end (112), the upper end of the pull rope (111) being connected to a lifting basket (3), and the sensing end (112) being connected to a frame (1).

6. The aircraft front wheel turning test device according to claim 1, characterized in that: The frame (1) is provided with a vertically extending guide rail (4), and the lifting basket (3) is provided with a guide rail seat (5) adapted to the guide rail (4).

7. The aircraft front wheel turning test device according to claim 1, characterized in that: A counterweight is installed on the top of the lifting basket (3).

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