Testing device for repairing A320 aircraft flap and slat rotary actuator

Abstract

The utility model discloses a testing device for repairing an A320 airplane flapper and slat rotary actuator, which comprises a testing table, sliding rails are arranged at the left end and the right end of the table top of the testing table, sliding sleeves are connected onto the sliding rails in a sliding manner, the sliding sleeves are fixedly connected with the sliding rails through first fixing bolts, and an output loading device and an input driving device are respectively arranged on the two sliding sleeves. A rotary actuator is connected between the output loading device and the input driving device; when an airplane flapper and slat rotation actuator is tested, a servo motor of an input driving device works to provide power drive for the flapper and slat rotation actuator, and a torque angle sensor measures the rotation speed and torque of an input shaft of the rotation actuator; the servo motor of the output loading device works to load the output end of the flaps and slats rotating actuator, so that the loading starting torque of the flaps and slats rotating actuator and the action characteristics of the torque limiter are tested, and the rotating speed, the torque and the efficiency of the output shaft are measured through the torque angle sensor.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft component repair, in particular to a test device for repairing a flap and slat rotary actuator of an A320 aircraft. Background Art

[0002] The aircraft flap and slat rotary actuator is a transmission device in the aircraft operating system. It is used for the rotational transmission of the aircraft flap and slat. It is one of the key components for aircraft flight safety. Therefore, there are high requirements for the safety of the aircraft rotary actuator. At present, the maintenance of this component in China is still in a blank area. After disassembly, repair and assembly, only certain routine tests can be performed according to the manual. There is a lack of speed and torque test devices for the rotary actuator. Some test data that affect the performance of the rotary actuator cannot be accurately obtained, which has a certain impact on the repair quality. For this reason, we propose a test device for the repair of the A320 aircraft flap and slat rotary actuator. Utility Model Content

[0003] The utility model aims to provide a test device for repairing a flap and slat rotary actuator of an A320 aircraft, so as to solve the problems raised in the above-mentioned background technology.

[0004] A test device for repairing a flap and slat rotary actuator of an A320 aircraft comprises a test bench, wherein slide rails are installed at the left and right ends of the test bench table, a sliding sleeve is slidably connected to the slide rail, the sliding sleeve is fixedly connected to the slide rail by a first fixing bolt, and after the first fixing bolt is removed, the sliding sleeve can slide and move on the slide rail, an output loading device and an input driving device are respectively installed on two of the sliding sleeves, and a rotary actuator is connected between the output loading device and the input driving device;

[0005] The input drive device comprises a second servo motor, the output shaft of the second servo motor is connected to one end of the second torque angle sensor, the other end of the second torque angle sensor is connected to the rotary actuator, and the lower ends of the second servo motor and the second torque angle sensor are mounted on a sliding sleeve, so that the input drive device can slide and move on the test bench;

[0006] The output loading device comprises a first servo motor, the output shaft of the first servo motor is connected to one end of a reducer, the other end of the reducer is connected to one end of a first torque angle sensor, the other end of the first torque angle sensor is connected to one end of an angle sensor, and the other end of the angle sensor is connected to the other end of a rotary actuator through a coupling; the lower ends of the first servo motor, the reducer, the first torque angle sensor and the angle sensor are mounted on a sliding sleeve, so that the output loading device can also slide and move on the test bench;

[0007] Preferably, the first servo motor and the second servo motor are electrically connected to a PLC controller, and the PLC controller is also electrically connected to a first torque angle sensor, an angle sensor, and a second torque angle sensor. The PLC controller controls the working parameters of the first servo motor and the second servo motor, and collects signals from the first torque angle sensor, the angle sensor, and the second torque angle sensor. After the PLC controller is connected to an industrial computer, the signal is processed and displayed to obtain test data.

[0008] Preferably, two ends of the rotary actuator are respectively inserted into the coupling and the rotating shaft of the second torque angle sensor and fixedly connected by second fixing bolts, so that the rotary actuator is firmly connected.

[0009] Compared with the prior art, the beneficial effects of the utility model are:

[0010] When testing the aircraft flap and slat rotary actuator, the second servo motor is controlled to work according to the speed and torque required by the repair manual test specifications to provide power drive for the flap and slat rotary actuator, and the speed and torque of the input shaft of the rotary actuator are measured by the second torque angle sensor. The technical parameters of the input end are: 0-80Nm, speed 0-1500rpm;

[0011] At the same time, the first servo motor is controlled to work, the output end of the tested flap slat rotary actuator is loaded, the loading starting torque of the flap slat rotary actuator and the torque limiter action characteristics are tested, and the speed, torque and efficiency of the output shaft of the rotary actuator are measured through the first torque angle sensor. The technical parameters of the output end are: 0-700Nm, the speed is 0-1500rpm, and the output end angle sensor can be used for backlash measurement of the gear pair;

[0012] Finally, complete the data collection, calculate and analyze the test data, judge the test results and existing faults, effectively ensure the quality of repairs, and obtain greater economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is the front view of the utility model;

[0014] Figure 2 This is a front view of the connection position of the rotary actuator of the utility model;

[0015] Figure 3 This is a working principle diagram of the utility model.

[0016] In the figure: 1. test bench, 2. slide rail, 3. sleeve, 4. first fixing bolt, 5. output loading device, 51. first servo motor, 52. reducer, 53. first torque angle sensor, 54. angle sensor, 55. connector, 6. rotary actuator, 61. second fixing bolt, 7. input drive device, 71. second servo motor, 72. second torque angle sensor, 721. rotating shaft, 8. PLC controller. DETAILED DESCRIPTION

[0017] 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.

[0018] See also Figure 1-3 A test device for repairing a flap and slat rotary actuator of an A320 aircraft comprises a test bench 1, wherein slide rails 2 are installed at the left and right ends of the test bench 1, and a sliding sleeve 3 is slidably connected to the slide rail 2. The sliding sleeve 3 is fixedly connected to the slide rail 2 by a first fixing bolt 4. After the first fixing bolt 4 is removed, the sliding sleeve 3 can slide and move on the slide rail 2. An output loading device 5 and an input driving device 7 are respectively installed on the two sliding sleeves 3, and a rotary actuator 6 is connected between the output loading device 5 and the input driving device 7;

[0019] The input drive device 7 includes a second servo motor 71, the output shaft of the second servo motor 71 is connected to one end of a second torque angle sensor 72, the other end of the second torque angle sensor 72 is connected to the rotary actuator 6, and the lower ends of the second servo motor 71 and the second torque angle sensor 72 are installed on the sliding sleeve 3, so that the input drive device 7 can slide and move on the test bench 1; by controlling the second servo motor 71 to work, power is provided for the flap rotary actuator, and the speed and torque of the input shaft of the rotary actuator are measured by the second torque angle sensor 72, and the technical parameters of the input end are: 0-80Nm, speed 0-1500rpm.

[0020] The output loading device 5 includes a first servo motor 51, the output shaft of the first servo motor 51 is connected to one end of a reducer 52, the other end of the reducer 52 is connected to one end of a first torque angle sensor 53, the other end of the first torque angle sensor 53 is connected to one end of an angle sensor 54, the other end of the angle sensor 54 is connected to the other end of a rotary actuator 6 through a connector 55, the two ends of the rotary actuator 6 are respectively inserted into the connector 55 and the rotating shaft 721 of the second torque angle sensor 72 and are fixedly connected by a second fixing bolt 61, so that the connection of the rotary actuator 6 is firm; the first The lower ends of the servo motor 51, the reducer 52, the first torque angle sensor 53 and the angle sensor 54 are installed on the sliding sleeve 3, so that the output loading device 5 can also slide and move on the test bench 1; the first servo motor 51 is controlled to work, and the output end of the flap and slat rotary actuator under test is loaded, so as to realize the test of the loading starting torque and the torque limiter action characteristics of the flap and slat rotary actuator, and the speed, torque and efficiency of the output shaft of the rotary actuator are measured by the first torque angle sensor 53. The technical parameters of the output end are: 0-700Nm, the speed is 0-1500rpm, and the output end angle sensor can be used for the backlash measurement of the gear pair.

[0021] The first servo motor 51 and the second servo motor 71 are electrically connected to the PLC controller 8, and the PLC controller 8 is also electrically connected to the first torque angle sensor 53, the angle sensor 54, and the second torque angle sensor 72. The PLC controller 8 controls the working parameters of the first servo motor 51 and the second servo motor 71, and collects signals from the first torque angle sensor 53, the angle sensor 54, and the second torque angle sensor 72. After the PLC controller 8 is connected to an industrial computer, the signal is processed and displayed to obtain test data.

[0022] Working principle: When testing the aircraft flap and slat rotary actuator, the second servo motor 71 is controlled to work according to the speed and torque required by the repair manual test specifications to provide power drive for the flap and slat rotary actuator, and the speed and torque of the input shaft of the rotary actuator are measured by the second torque angle sensor 72. The technical parameters of the input end are: 0-80Nm, speed 0-1500rpm; at the same time, the first servo motor 51 is controlled to work to load the output end of the tested flap and slat rotary actuator to achieve the test of the loading starting torque and torque limiter action characteristics of the flap and slat rotary actuator, and the speed, torque and efficiency of the output shaft of the rotary actuator are measured by the first torque angle sensor 53. The technical parameters of the output end are: 0-700Nm, speed 0-1500rpm. The output end angle sensor can be used for backlash measurement of gear pairs.

[0023] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-restrictive from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

[0024] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A test device for repairing a flap and slat rotary actuator of an A320 aircraft, comprising a test bench (1), characterized in that: Slide rails (2) are installed at the left and right ends of the tabletop of the test bench (1); a slide sleeve (3) is slidably connected to the slide rail (2); the slide sleeve (3) is fixedly connected to the slide rail (2) via a first fixing bolt (4); an output loading device (5) and an input driving device (7) are respectively installed on the two slide sleeves (3); a rotary actuator (6) is connected between the output loading device (5) and the input driving device (7); The input drive device (7) comprises a second servo motor (71), the output shaft of the second servo motor (71) is connected to one end of a second torque angle sensor (72), the other end of the second torque angle sensor (72) is connected to the rotary actuator (6), and the lower ends of the second servo motor (71) and the second torque angle sensor (72) are mounted on the sliding sleeve (3); The output loading device (5) comprises a first servo motor (51), the output shaft of the first servo motor (51) is connected to one end of a reducer (52), the other end of the reducer (52) is connected to one end of a first torque angle sensor (53), the other end of the first torque angle sensor (53) is connected to one end of an angle sensor (54), and the other end of the angle sensor (54) is connected to the other end of a rotary actuator (6) via a connector (55); the lower ends of the first servo motor (51), the reducer (52), the first torque angle sensor (53) and the angle sensor (54) are mounted on the sliding sleeve (3).

2. A test device for repairing the A320 aircraft flap and slat rotary actuator according to claim 1, characterized in that: The first servo motor (51) and the second servo motor (71) are electrically connected to a PLC controller (8), and the PLC controller (8) is also electrically connected to a first torque angle sensor (53), an angle sensor (54), and a second torque angle sensor (72).

3. The A320 aircraft flap and slat rotary actuator repair test device according to claim 1, characterized in that: The two ends of the rotary actuator (6) are respectively inserted into the coupling (55) and the rotating shaft (721) of the second torque angle sensor (72) and are fixedly connected by a second fixing bolt (61).

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