A torsion device for aircraft front landing gear return-to-center test

Abstract

The invention discloses a torsion device for a test of the front landing gear of an aircraft returning to the center. The base is fixed on the upper end surface of the bracket; a V-shaped support groove of the aircraft landing gear axle is arranged in the middle of the upper end of the rotating support frame, and a step shaft matching the step hole of the base is arranged at the lower end thereof, and a small diameter shaft at the lower end of the step shaft is provided with a central blind hole, and a spline is arranged at the lower end of the central blind hole, and the step shaft is rotatably installed in the step hole of the base; the output shaft of the reduction motor of the torsion motor is connected with the spline of the rotating support frame through a clutch; the angle sensor is installed on the base, and its contact contacts the outer circle of the step shaft of the rotating support frame, and the angle sensor itself has a display screen; the angle sensor sets the angle at which the aircraft landing gear axle needs to rotate. The invention can automatically rotate the landing gear to the required angle value, can directly display the angle during the process of the landing gear returning to the center, has high control accuracy, saves time and labor, has high efficiency, and has a wide range of applications.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft landing gear performance detection test equipment and relates to a torsion device for a front landing gear return-to-center test of an aircraft. Background Art

[0002] Aircraft landing gear needs to have accurate return-to-center performance during flight and ground operations to ensure safe takeoff and landing and ground taxiing stability. At present, the front landing gear return-to-center test generally compresses the front landing gear piston rod to the required position first, then manually rotates the landing gear to the required angle value, and after removing the compression force, allows the landing gear piston rod to automatically return to the center, thereby measuring the angle and time of the landing gear return-to-center process. Manually rotating the landing gear to complete the twisting angle is not only time-consuming and laborious, but also the twisting angle control is not accurate. During the twisting angle process, the landing gear is under stress, which poses a safety hazard to operation. Summary of the invention

[0003] The purpose of the present invention is to solve the above-mentioned problems existing in the prior art and to provide a torsion device for the return-to-center test of the front landing gear of an aircraft, which can automatically rotate the landing gear to a required angle value, can directly display the angle during the return-to-center process of the landing gear, has high control accuracy, saves time and effort, and has high efficiency; and can be applied to the return-to-center performance test of landing gear of various models of aircraft, and has a wide range of applications.

[0004] To achieve the above-mentioned purpose, the technical solution of the present invention is: a torsion device for a centering test of a front landing gear of an aircraft, comprising a bracket, a torsion motor, a base, an angle sensor and a rotating support frame; the base is fixed on the upper end surface of the bracket, and a step hole is opened in the center thereof; a V-shaped support groove of an aircraft landing gear axle is arranged in the middle of the upper end of the rotating support frame, and a step shaft matching the step hole of the base is arranged at the lower end thereof, and a small diameter shaft at the lower end of the step shaft is opened with a central blind hole, and a spline is arranged at the lower end of the central blind hole, and the step shaft is rotatably mounted in the step hole of the base; the torsion motor comprises a motor and a reduction motor, and the output shaft of the reduction motor is connected to one end of a clutch; a spline is arranged at the other end of the clutch, and the end passes through the upper end surface of the bracket and the step hole of the base and is connected to the spline of the rotating support frame; the angle sensor is installed on the base, and its contact contacts the outer circle of the step shaft of the rotating support frame, and the angle sensor itself has a display screen; the angle sensor sets the angle at which the aircraft landing gear axle needs to rotate.

[0005] Further preferably, the step shaft 52 of the rotating support frame is rotatably mounted in the step hole of the base 3 via a bearing 6 .

[0006] Further preferably, the side of the rotating support frame is also provided with a weight-reducing groove 53 which is vertically connected to the V-shaped support groove 51. The weight-reducing groove 53 also has the function of avoiding interference with other components on the axle of the aircraft landing gear.

[0007] When in use, the bracket 1 of the present invention is fixed to a suitable position of the aircraft landing gear return performance test equipment, and then the aircraft landing gear axle is placed in the V-shaped support groove 51 of the rotating support frame. In this way, as long as the front landing gear piston rod is compressed to the required position, the motor is started, and the rotating support frame 5 drives the aircraft landing gear axle to rotate to the set angle, the clutch automatically disengages, and the compression force is removed at the same time, the landing gear piston rod automatically returns to the center, and the angle sensor 4 displays the angle during the landing gear return process. Compared with the prior art, the present invention can automatically rotate the landing gear to the required angle value, and can directly display the angle during the landing gear return process, with high control accuracy, time and labor saving, and high efficiency; and can be applied to various types of aircraft landing gear return performance tests, with a wide range of applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 It is a structural schematic diagram of the present invention; Figure 2 It is a schematic diagram of the structure of the rotating support frame in the present invention. DETAILED DESCRIPTION

[0009] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0010] like Figure 1 and Figure 2 As shown, this embodiment includes a bracket 1, a torsion motor 2, a base 3, an angle sensor 4 and a rotating support frame 5. The base 3 is fixed to the upper end surface of the bracket 1, and a step hole is opened in the center thereof. A V-shaped support groove 51 of the aircraft landing gear axle is arranged in the middle of the upper end of the rotating support frame 5, and a step shaft 52 matching the step hole of the base 3 is arranged at the lower end thereof, and a small diameter shaft at the lower end of the step shaft 52 is opened with a central blind hole, and a spline is arranged at the lower end of the central blind hole, and the step shaft 52 is rotatably mounted in the step hole of the base 3. Preferably, the step shaft 52 of the rotating support frame is rotatably mounted in the step hole of the base 3 through a bearing 6. Preferably, a weight reduction groove 53 which is vertically connected to the V-shaped support groove 51 is also opened on the side of the rotating support frame. The weight reduction groove 53 also has the function of avoiding interference with other components on the aircraft landing gear axle. The torsion motor 2 includes a motor and a reduction motor, and the output shaft of the reduction motor is connected to one end of the clutch. The other end of the clutch is provided with a spline, which passes through the upper end surface of the bracket 1 and the step hole of the base and is connected to the spline of the rotating support frame 5. The angle sensor 4 is installed on the base 3, and its contact contacts the outer circle of the step shaft 52 of the rotating support frame. The angle sensor 4 itself has a display screen. The angle sensor 4 sets the angle at which the aircraft landing gear axle needs to rotate.

[0011] When in use, the bracket 1 of the present invention is fixed to a suitable position of the aircraft landing gear return performance test equipment, and then the aircraft landing gear axle is placed in the V-shaped support groove 51 of the rotating support frame. In this way, as long as the front landing gear piston rod is compressed to the required position, the motor is started, and the rotating support frame 5 drives the aircraft landing gear axle to rotate to the set angle, the clutch is automatically disengaged, and the compression force is released at the same time, the landing gear piston rod automatically returns to the center, and the angle sensor 4 displays the angle of the landing gear during the return process.

[0012] Of course, the present invention has many other embodiments. Without violating the spirit and essence of the present invention, technicians familiar with the field can make corresponding changes and deformations based on the present invention, but these corresponding changes and deformations should be regarded as improvements of equivalent technologies and belong to the protection scope of the claims of the present invention.

Claims

1. A torsion device for a centering test of a front landing gear of an aircraft, characterized in that: It includes a bracket, a torsion motor, a base, an angle sensor and a rotating support frame; the base is fixed on the upper end face of the bracket, and a step hole is opened in the center of the base; a V-shaped support groove of the aircraft landing gear axle is arranged in the middle of the upper end of the rotating support frame, and a step shaft matching the step hole of the base is arranged at the lower end, and the small diameter shaft at the lower end of the step shaft has a central blind hole, and a spline is arranged at the lower end of the central blind hole, and the step shaft can be rotatably installed in the step hole of the base; the torsion motor includes a motor and a reduction motor, and the output shaft of the reduction motor is connected to one end of the clutch; the other end of the clutch is provided with a spline, and the end passes through the upper end face of the bracket and the step hole of the base and is connected with the spline of the rotating support frame; the angle sensor is installed on the base, and its contact contacts the outer circle of the step shaft of the rotating support frame, and the angle sensor itself has a display screen; the angle required to rotate the aircraft landing gear axle is set on the angle sensor.

2. The aircraft front landing gear return-to-center test torsion device according to claim 1, characterized in that: The step shaft of the rotating support frame is rotatably installed in the step hole of the base through a bearing.

3. The aircraft front landing gear return-to-center test torsion device according to claim 1 or 2, characterized in that: The side surface of the rotating support frame is also provided with a weight-reducing groove which is vertically connected with the V-shaped support groove.

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