Aircraft cockpit control panel switch synchronism test equipment

Abstract

The utility model discloses equipment for testing the switch synchronism of a control panel of an aircraft cockpit. The test equipment comprises a working platform, a switch fixing device and a switch pulling device. The switch fixing device is provided with a fixing device guide rail sliding block pair, a fixing device movable seat and a fixing device mounting plate. The switch wrenching device is provided with a wrenching device first guide rail sliding block pair, a wrenching device second guide rail sliding block pair, a wrenching device movable seat and a wrenching device tail end executing mechanism. The beneficial effects of the utility model are that the test device can be adaptively adjusted according to the specific specification of the control panel switch of the aircraft cabin to be tested, so as to realize the test task of the control panel switches of the aircraft cabin with more specifications.

Description

Technical Field

[0001] The utility model relates to a test device for switches of an aircraft cockpit control panel, in particular to a test device for the synchronicity of switches of an aircraft cockpit control panel. Background Art

[0002] The synchronization of cockpit control panel switches is crucial to flight safety. When pilots operate cockpit control panel switches according to operating specifications, if the switches' internal synchronization fails to meet technical specifications, the aircraft's next maneuver can be impacted.

[0003] The current aircraft cockpit control panel switch synchronization test equipment has the following disadvantages: the test equipment is customized and only adapts to aircraft cockpit control panel switches of specified specifications, and cannot test aircraft cockpit control panel switches of other specifications. Utility Model Content

[0004] The utility model aims to solve the existing technical problems and provide a device for testing the synchronism of switches in an aircraft cockpit control panel.

[0005] In order to achieve this purpose, the technical solution of the present invention is as follows: an aircraft cockpit control panel switch synchronization test device, comprising: a working platform, a switch fixing device and a switch pulling device; the switch fixing device comprises a fixing device guide rail slider pair, a fixing device movable seat and a fixing device mounting plate, the guide rail of the fixing device guide rail slider pair is fixed to the top surface of the working platform, the guide rail portion of the fixing device guide rail slider pair extends along the front-back direction, and the slider portion of the fixing device guide rail slider pair is fixedly connected to the fixing device movable seat; the fixing device mounting plate is fixed to the fixing device movable seat, the fixing device mounting plate has mounting plate fixing holes, the mounting plate fixing holes are arranged along the left-right direction, and the mounting plate fixing holes are used to fix the aircraft cockpit control panel switch; the switch The pulling device includes a first guide rail slider pair of the pulling device, a second guide rail slider pair of the pulling device, a movable seat of the pulling device and an end actuator of the pulling device; the guide rail portion of the first guide rail slider pair of the pulling device is fixed to the top surface of the working platform, the guide rail portion of the first guide rail slider pair of the pulling device extends along the left and right directions, the slider portion of the first guide rail slider pair of the pulling device is fixedly connected to the guide rail portion of the second guide rail slider pair of the pulling device, the guide rail portion of the second guide rail slider pair of the pulling device extends along the up and down directions, the slider portion of the second guide rail sliding pair of the pulling device is fixedly connected to the movable seat of the pulling device; the end actuator of the pulling device is fixed to the movable seat of the pulling device, and the end actuator of the pulling device is used to pull or lift the switch of the aircraft cabin control panel.

[0006] As a preferred solution for the aircraft cockpit control panel switch synchronization test equipment, the switch fixing device has a fixing device screw nut pair and a fixing device servo motor, the screw portion of the fixing device screw nut pair is parallel to the guide rail portion of the fixing device guide rail slider pair, the nut portion of the fixing device screw nut pair is fixedly connected to the slider portion of the fixing device guide rail slider pair or the fixing device movable seat, and the fixing device servo motor is used to drive the screw portion of the fixing device screw nut pair to move, thereby adjusting the front and rear position of the fixing device movable seat.

[0007] As a preferred solution for the aircraft cockpit control panel switch synchronization test equipment, the switch triggering device has a first screw-nut pair of the triggering device and a first servo motor of the triggering device. The screw portion of the first screw-nut pair of the triggering device is parallel to the guide rail portion of the first guide rail slider pair of the triggering device. The nut portion of the first screw-nut pair of the triggering device is fixedly connected to the guide rail portion of the second guide rail slider pair of the triggering device or the slider portion of the first guide rail slider pair of the triggering device. The first servo motor of the triggering device is used to drive the screw portion of the first screw-nut pair of the triggering device to move, thereby adjusting the left and right positions of the movable seat of the triggering device.

[0008] As a preferred solution for the aircraft cockpit control panel switch synchronization testing equipment, the switch triggering device has a second screw-nut pair of the triggering device and a second servo motor of the triggering device. The screw portion of the second screw-nut pair of the triggering device is parallel to the guide rail portion of the second guide rail slider pair of the triggering device. The nut portion of the second screw-nut pair of the triggering device is fixedly connected to the nut portion of the second screw-nut pair of the triggering device or the movable seat of the triggering device. The second servo motor of the triggering device is used to drive the screw portion of the second screw-nut pair of the triggering device to move, thereby adjusting the upper and lower positions of the movable seat of the triggering device.

[0009] As a preferred solution of the aircraft cockpit control panel switch synchronization test equipment, the trigger device end actuator has a clamping claw, and the clamping claw is used to clamp the switch shaft of the aircraft cockpit control panel switch.

[0010] As a preferred solution for the aircraft cockpit control panel switch synchronization test equipment, it also includes: a host computer device; the host computer device has a host and a display, and the host is inside the host cabinet below the working platform; the display is fixed to the working platform or the host cabinet below the working platform through a display bracket.

[0011] Compared to the prior art, the present invention offers at least the following advantages: because the front-to-back position of the movable base of the fixing device and the vertical and horizontal positions of the movable base of the triggering device are adjustable, the testing equipment can be adaptively adjusted according to the specific specifications of the aircraft cockpit control panel switches to be tested, thereby enabling testing of a wider range of aircraft cockpit control panel switches. Furthermore, the testing equipment has a simple overall structure and is easy to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a structural schematic diagram of an embodiment of the present utility model.

[0013] Figure 2 It is a structural diagram of a working platform according to an embodiment of the present utility model.

[0014] Figure 3 It is a structural schematic diagram of a switch fixing device according to an embodiment of the present utility model.

[0015] Figure 4 It is a structural schematic diagram of a switch pulling device according to an embodiment of the present utility model.

[0016] Figure 5 It is a structural diagram of the host computer device of an embodiment of the utility model. DETAILED DESCRIPTION

[0017] The present invention will be further described in detail below through specific embodiments in conjunction with the accompanying drawings. It should be noted that the description of these embodiments is intended to facilitate understanding of the present invention and does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0018] See also Figure 1 The figure shows an aircraft cockpit control panel switch synchronization test device. The device is used to test the synchronization of aircraft cockpit control panel switches 100. The device comprises a work platform 1, a switch fixing device 2, a switch actuating device 3, and a host computer 4.

[0019] See also Figure 2 , shown in the figure is the work platform 1. A main cabinet 11 is provided below the work platform 1.

[0020] See also Figure 1 and Figure 3, the switch fixing device 2 is on the top surface of the working platform 1. The switch fixing device 2 has a fixing device guide rail slider pair 21, a fixing device movable seat 22 and a fixing device mounting plate 23. The guide rail of the fixing device guide rail slider pair 21 is fixed to the top surface of the working platform 1. The guide rail portion of the fixing device guide rail slider pair 21 extends along the front-to-back direction. The slider portion of the fixing device guide rail slider pair 21 is fixedly connected to the fixing device movable seat 22. As a result, the fixing device movable seat 22 can adjust its position along the front-to-back direction. The fixing device mounting plate 23 is fixed to the fixing device movable seat 22. The fixing device mounting plate 23 has mounting plate fixing holes 230. The mounting plate fixing holes 230 are arranged along the left-right direction. The mounting plate fixing holes 230 are used to fix the aircraft cockpit control panel switch 100.

[0021] In a specific embodiment, the switch fixture 2 further comprises a fixture screw-nut pair 24 and a fixture servo motor (not shown). The screw portion of the fixture screw-nut pair 24 is parallel to the guide rail portion of the fixture guide rail slider pair 21. The nut portion of the fixture screw-nut pair 24 is fixedly connected to the slider portion of the fixture guide rail slider pair 21 or the fixture movable seat 22. The fixture servo motor is used to drive the screw portion of the fixture screw-nut pair 24, thereby adjusting the front-back position of the fixture movable seat 22.

[0022] See also Figure 1 and Figure 4 The switch trigger device 3 is located on the top surface of the work platform 1. The switch trigger device 3 comprises a first guide rail slider pair 31, a second guide rail slider pair 32, a movable seat 33, and an end-effector 34. The guide rail portion of the first guide rail slider pair 31 is fixed to the top surface of the work platform 1. The guide rail portion of the first guide rail slider pair 31 extends horizontally. The slider portion of the first guide rail slider pair 31 is fixedly connected to the guide rail portion of the second guide rail slider pair 32. The guide rail portion of the second guide rail slider pair 32 extends vertically. The slider portion of the second guide rail slider pair is fixedly connected to the movable seat 33. Thus, the movable seat 33 can be adjusted horizontally and vertically. The end-effector 34 is fixed to the movable seat 33. The end-effector 34 is located above the aircraft cockpit control panel switch 100. The triggering device end actuator 34 is used to perform a triggering or lifting action on the aircraft cockpit control panel switch 100 .

[0023] In a specific embodiment, the switch actuating device 3 further comprises a first screw-nut pair of the actuating device and a first servo motor of the actuating device. The screw portion of the first screw-nut pair of the actuating device is parallel to the guide rail portion of the first guide rail slider pair 31 of the actuating device. The nut portion of the first screw-nut pair of the actuating device is fixedly connected to the guide rail portion of the second guide rail slider pair 32 of the actuating device or the slider portion of the first guide rail slider pair 31 of the actuating device. The first servo motor of the actuating device is used to drive the screw portion of the first screw-nut pair of the actuating device to move, thereby adjusting the left and right position of the movable seat 33 of the actuating device.

[0024] In a specific embodiment, the switch actuating device 3 further comprises a second screw-nut pair and a second servo motor. The screw portion of the second screw-nut pair is parallel to the guide rail portion of the second guide rail slider pair 32. The nut portion of the second screw-nut pair is fixedly connected to the nut portion of the second screw-nut pair or the movable seat 33 of the actuating device. The second servo motor is used to drive the screw portion of the second screw-nut pair, thereby adjusting the vertical position of the movable seat 33.

[0025] In a specific implementation, the actuator end 34 of the triggering device has a clamping claw. The clamping claw is used to clamp the switch shaft of the aircraft cockpit control panel switch 100. The clamping claw performs a triggering or pulling action.

[0026] See also Figure 5 The host device 4 includes a host (not shown) and a display 41. The host is located inside the host cabinet 11 below the work platform 1. The display 41 is fixed to the work platform 1 or the host cabinet 11 below the work platform 1 via a display bracket 42. Preferably, the display bracket 42 has a bracket extension platform 421. The bracket extension platform 421 has an input keyboard and mouse 43. The host is connected to the display 41, the input keyboard and mouse 43, the control part of the switch fixing device 2, the control part of the switch triggering device 3, etc. in a wired or wireless manner.

[0027] While the above merely describes the embodiments of the present invention, and while the description is relatively specific and detailed, it should not be construed as limiting the scope of the utility model patent. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the concept of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present utility model patent shall be determined by the appended claims.

Claims

1. An aircraft cockpit control panel switch synchronization test device, characterized in that: The invention comprises: a working platform, a switch fixing device and a switch triggering device; the switch fixing device comprises a fixing device guide rail slider pair, a fixing device movable seat and a fixing device mounting plate, the guide rail of the fixing device guide rail slider pair is fixed to the top surface of the working platform, the guide rail portion of the fixing device guide rail slider pair extends along the front-back direction, and the slider portion of the fixing device guide rail slider pair is fixedly connected to the fixing device movable seat; the fixing device mounting plate is fixed to the fixing device movable seat, the fixing device mounting plate has mounting plate fixing holes, the mounting plate fixing holes are arranged along the left-right direction, and the mounting plate fixing holes are used to fix the aircraft cabin control panel switch; the switch triggering device comprises a triggering device first guide rail slider pair, a triggering device A second guide rail slider pair, a pulling device movable seat and a pulling device end actuator are provided; the guide rail portion of the first guide rail slider pair of the pulling device is fixed to the top surface of the working platform, the guide rail portion of the first guide rail slider pair of the pulling device extends along the left and right directions, the slider portion of the first guide rail slider pair of the pulling device is fixedly connected to the guide rail portion of the second guide rail slider pair of the pulling device, the guide rail portion of the second guide rail slider pair of the pulling device extends along the up and down directions, the slider portion of the second guide rail sliding pair of the pulling device is fixedly connected to the pulling device movable seat; the pulling device end actuator is fixed to the pulling device movable seat, and the pulling device end actuator is used to pull or lift the aircraft cabin control panel switch.

2. The aircraft cockpit control panel switch synchronization test equipment according to claim 1, characterized in that: The switch fixing device includes a fixing device screw nut pair and a fixing device servo motor, the screw portion of the fixing device screw nut pair is parallel to the guide rail portion of the fixing device guide rail slider pair, the nut portion of the fixing device screw nut pair is fixedly connected to the slider portion of the fixing device guide rail slider pair or the fixing device movable seat, and the fixing device servo motor is used to drive the screw portion of the fixing device screw nut pair to move, thereby adjusting the front and rear position of the fixing device movable seat.

3. The aircraft cockpit control panel switch synchronization test equipment according to claim 1, characterized in that: The switch trigger device includes a first screw-nut pair of the trigger device and a first servo motor of the trigger device. The screw portion of the first screw-nut pair of the trigger device is parallel to the guide rail portion of the first guide rail slider pair of the trigger device. The nut portion of the first screw-nut pair of the trigger device is fixedly connected to the guide rail portion of the second guide rail slider pair of the trigger device or the slider portion of the first guide rail slider pair of the trigger device. The first servo motor of the trigger device is used to drive the screw portion of the first screw-nut pair of the trigger device to move, thereby adjusting the left and right positions of the movable seat of the trigger device.

4. The aircraft cockpit control panel switch synchronization test equipment according to claim 3, characterized in that: The switch trigger device includes a second screw-nut pair of the trigger device and a second servo motor of the trigger device. The screw portion of the second screw-nut pair of the trigger device is parallel to the guide rail portion of the second guide rail slider pair of the trigger device. The nut portion of the second screw-nut pair of the trigger device is fixedly connected to the nut portion of the second screw-nut pair of the trigger device or the movable seat of the trigger device. The second servo motor of the trigger device is used to drive the screw portion of the second screw-nut pair of the trigger device to move, thereby adjusting the upper and lower positions of the movable seat of the trigger device.

5. The aircraft cockpit control panel switch synchronization test equipment according to claim 1, characterized in that: The end actuator of the trigger device has a clamping claw, and the clamping claw is used to clamp the switch shaft of the aircraft cockpit control panel switch.

6. The aircraft cockpit control panel switch synchronization test equipment according to claim 1, characterized in that: Also includes: The host computer device comprises a host computer and a display, and the host computer is located inside the host cabinet below the working platform; The display is fixed to the work platform or the main cabinet below the work platform through a display bracket.

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