Aircraft torque motor controller in-place test tool
By designing the integrated aircraft torque motor controller in-position testing tooling, the problem of troubleshooting time and cost due to the lack of professional testing tools in the existing technology is solved, and the efficient testing of torque motor controllers is achieved, which improves the airlines operational efficiency.
Patent Information
- Application Number
- CN202421172909.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-27
- Publication Date
- 2025-01-14
- Estimated Expiration
- 2034-05-27
AI Technical Summary
In the prior art, the aging and environmental pollution of the related components of the aircraft torque motor controller lead to failure, especially the abnormal opening of the internal electromagnetic baffle valve, which leads to the failure of the gas induced system. Most domestic maintenance bases lack professional functional testing tools, resulting in Fault handling is time-consuming and costly, which affects the airline's operating efficiency.
Designed an aircraft torque motor controller in-position testing tooling, including a detection trolley, integrated pressure gauge, pressure regulating valve, DC constant power supply, nitrogen tank and power cord, connecting the test equipment through joints, simplifying wiring and transfer, providing a Integrated testing solutions.
The tooling improves the working efficiency of torque motor controller testing, has a simple structure and is easy to use, reduces production costs, shortens fault handling time, and improves the operating efficiency of airlines.
Smart Images
Figure CN222354313U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft ground maintenance, in particular to an in-situ testing tool for an aircraft torque motor controller. Background Art
[0002] As the flight time of the fleet increases, the related components of the aircraft torque motor controller (TMC) are gradually aging. Coupled with the impact of environmental pollution during long-term flight, the performance of the related components of the torque motor controller has declined and even malfunctioned. The most common failure phenomenon is the abnormal opening of the electromagnetic damper valve inside the TMC, which fails to meet the initial standard. After the failure occurs, it will trigger the failure of the bleed air system, affecting the safety margin of the aircraft bleed air system and making it impossible to guarantee the reliability of the aircraft bleed air system.
[0003] At present, most domestic aircraft maintenance bases are not equipped with professional TMC functional testing tools, which results in the inability to effectively and directly isolate the various components of the bleed air system through fault performance and quick access recorder (QAR) decoding data, and the ground parking time cannot be effectively shortened after the fault, affecting the operating efficiency of airlines. In the past, when the above faults occurred, it was necessary to borrow professional TMC functional testing tools for testing or outsource the aircraft torque motor controller (TMC) for maintenance, but the borrowing or outsourcing maintenance process was time-consuming and costly. Utility Model Content
[0004] In view of the deficiencies in the prior art, the utility model provides an in-situ test fixture for an aircraft torque motor controller to overcome the deficiencies in the prior art.
[0005] In order to achieve the above objectives, the present invention is implemented through the following technical solutions:
[0006] An aircraft torque motor controller in-situ test tool includes a test trolley. The test trolley is divided into two layers, the upper layer is provided with a first pressure gauge, a pressure regulating valve, a DC constant power supply, a flashlight charging compartment and a second pressure gauge; the lower layer is provided with a nitrogen tank, an air outlet pipe, an air return pipe, an external power cord and a plurality of joints;
[0007] The first pressure gauge is connected to the first interface of the pressure regulating valve through a docking joint, the nitrogen tank is connected to the second interface of the pressure regulating valve through a docking joint, and the first end of the gas outlet pipe is connected to the third interface of the pressure regulating valve through a docking joint;
[0008] The DC constant power supply is electrically connected to the first end of the external power line through the docking connector, and the DC constant power supply is electrically connected to the flashlight charging compartment;
[0009] The second pressure gauge is connected to the first end of the gas return pipe via a docking joint.
[0010] Furthermore, the lower space of the detection trolley is separated into a left compartment and a right compartment by a vertical partition, and the right compartment is separated into a right first compartment, a right second compartment and a right third compartment by a horizontal partition; a nitrogen tank is placed in the left compartment, an air outlet pipe is placed in the right first compartment, an air return pipe is placed in the right second compartment, and an external power cord is placed in the right third compartment.
[0011] Furthermore, a U-shaped support seat is fixedly provided in the left compartment, and the opening of the U-shaped support seat faces forward.
[0012] Furthermore, a limiting groove is horizontally provided through the U-shaped support seat in the left and right directions, and a limiting bolt is arranged in the limiting groove.
[0013] Preferably, the first pressure gauge, pressure regulating valve, DC constant power supply, flashlight charging compartment and second pressure gauge are all arranged on the rear half of the upper table of the inspection trolley, and a tool storage box is also arranged on the front half of the upper table of the inspection trolley.
[0014] Preferably, the bottom of the inspection trolley is provided with self-locking universal wheels.
[0015] Preferably, a push-pull handle is also provided on one side of the detection trolley.
[0016] Preferably, the plurality of docking joints include a pipeline docking joint, an electronic pressure gauge docking joint and a power supply docking joint.
[0017] Compared with the prior art, the beneficial effects of the utility model are:
[0018] 1) In this case, an aircraft torque motor controller in-situ test tool is provided, which integrates the test equipment, test accessories and common tools used in the in-situ test of the aircraft torque motor controller. It is easy to transport, has simple test wiring, and effectively improves work efficiency.
[0019] 2) The aircraft torque motor controller in-situ test fixture of this case has a simple structure, is easy to use, has a low production cost, and is conducive to promotion.
[0020] In order to more clearly understand the present invention, the following will describe the preferred implementation modes of the present invention in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 It is a schematic diagram of the overall structure of the utility model;
[0022] Figure 2 It is a schematic diagram of the structure of the utility model from a top view;
[0023] Figure 3 It is a schematic diagram of the testing principle of the utility model.
[0024] Figure ID:
[0025] 1-first pressure gauge, 2-pressure regulating valve, 3-DC constant power supply, 4-flashlight charging compartment, 5-second pressure gauge, 6-nitrogen tank, 7-air outlet pipe, 8-air return pipe, 9-external power cord; 100-left compartment, 101-U-shaped support seat, 102-limiting groove, 103-limiting bolt; 200-right compartment, 201-right first compartment, 202-right second compartment, 203-right third compartment. DETAILED DESCRIPTION
[0026] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In the description of the present invention, unless otherwise specified, "multiple" means two or more.
[0027] In addition, if there are terms such as "first" and "second", they are only used for descriptive purposes, mainly to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components, and cannot be understood as indicating or implying relative importance.
[0028] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installed", "provided with", "mounted / connected", "connected", etc. should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two components; for ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to specific circumstances.
[0029] See also Figure 1-3 The utility model provides an in-situ test tool for an aircraft torque motor controller, including a test trolley, which is divided into two layers, an upper layer and an lower layer; a first pressure gauge 1, a pressure regulating valve 2, a DC constant power supply 3, a flashlight charging compartment 4, and a second pressure gauge 5 are arranged on the upper layer; a nitrogen tank 6, an air outlet pipe 7, an air return pipe 8, an external power supply line 9, and a plurality of joints are placed in the lower layer space;
[0030] The first pressure gauge 1 is connected to the first interface of the pressure regulating valve 2 through a docking joint, the nitrogen tank 6 is connected to the second interface of the pressure regulating valve 2 through a docking joint, and the first end of the gas outlet pipe 7 is connected to the third interface of the pressure regulating valve 2 through a docking joint;
[0031] The DC constant power supply 3 is electrically connected to the first end of the external power line 9 through a docking connector, and the DC constant power supply 3 is electrically connected to the flashlight charging compartment 4;
[0032] The second pressure gauge 5 is connected to the first end of the gas return pipe 8 via a docking joint.
[0033] In actual working conditions, when the aircraft torque motor controller is tested with this tool: the second end of the outlet pipe 7 is connected to the inlet servo pipe of the torque motor controller through the docking joint; the second end of the return pipe 8 is connected to the outlet servo pipe of the torque motor controller through the docking joint; the second end of the external power cord 9 is connected to the power plug of the torque motor controller through the docking joint; the output pressure of the nitrogen tank 6 is adjusted by the pressure regulating valve 2 to stabilize the nitrogen pressure at the inlet end of the torque motor controller at 20PSI; then the numerical current of the DC constant current power supply is adjusted to three gears of 0-25-50MA respectively; then the air pressure value of the outlet end of the torque motor controller under each current gear is measured by the second pressure gauge 5; finally, combined with the pressure standard requirements given in the aircraft manufacturer's maintenance manual, it is judged whether the opening of the electromagnetic baffle valve inside the torque motor controller is abnormal.
[0034] Furthermore, the lower space of the inspection trolley is separated into a left compartment 100 and a right compartment 200 by vertical partitions, and the right compartment 200 is further separated into a right first compartment 201, a right second compartment 202 and a right third compartment 203 by horizontal partitions; a nitrogen tank 6 is placed in the left compartment 100, an air outlet pipe 7 is placed in the right first compartment 201, an air return pipe 8 is placed in the right second compartment 202, and an external power cord 9 is placed in the right third compartment 203.
[0035] As a preference, in this embodiment, a U-shaped support seat 101 is fixedly provided in the left compartment 100 for placing the nitrogen tank 6 , and the opening of the U-shaped support seat 101 faces forward, which facilitates operation when replacing the nitrogen tank 6 .
[0036] Preferably, in this embodiment, a limiting groove 102 is horizontally penetrated in the left and right directions on the U-shaped support seat 101, and a limiting bolt 103 is arranged in the limiting groove 102. By adjusting the position of the limiting bolt 103 in the limiting groove 102, the limiting screw can clamp the nitrogen tank 6 to ensure that the nitrogen tank 6 is stable and does not shake during transportation.
[0037] Preferably, in this embodiment, the plurality of docking joints include a pipeline docking joint standard part AS5174D0504V, an electronic pressure gauge docking joint 1 / 4UNJF thread to NPT and a power supply docking joint.
[0038] As a priority, in this embodiment, the first pressure gauge 1, the pressure regulating valve 2, the DC constant power supply 3, the flashlight charging compartment 4 and the second pressure gauge 5 are all arranged on the rear half of the upper table of the inspection trolley. A tool storage box 300 is also provided on the front half of the upper table of the inspection trolley for placing common tools used in daily inspection work, such as wrenches, screwdrivers, tapes, flashlights, connectors, connecting wires, gloves, wrenches, leakage liquids, etc.
[0039] Preferably, in this embodiment, the bottom of the inspection trolley is provided with self-locking universal wheels, and one side of the inspection trolley is also provided with a push-pull handle.
[0040] Compared with the prior art, an in-situ test tool for an aircraft torque motor controller in this case integrates the test equipment, test accessories and common tools used in the in-situ test of the aircraft torque motor controller. It is easy to transport, has simple test wiring, and effectively improves work efficiency.
[0041] The above-mentioned embodiments only express several implementation methods of the utility model, and the description is relatively specific and detailed, but it cannot be understood as limiting the scope of the utility model patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the utility model, which all belong to the protection scope of the utility model.
Claims
1. An aircraft torque motor controller in-situ test tool, comprising a test trolley, characterized in that: The detection trolley is divided into two layers, upper and lower. The upper table is provided with a first pressure gauge (1), a pressure regulating valve (2), a DC constant power supply (3), a flashlight charging compartment (4) and a second pressure gauge (5); the lower space is provided with a nitrogen tank (6), an air outlet pipe (7), an air return pipe (8), an external power supply line (9) and a plurality of joints; The first pressure gauge (1) is connected to a first interface of the pressure regulating valve (2) via a docking joint, the nitrogen tank (6) is connected to a second interface of the pressure regulating valve (2) via a docking joint, and the first end of the gas outlet pipe (7) is connected to a third interface of the pressure regulating valve (2) via a docking joint; The DC constant power source (3) is electrically connected to a first end of an external power line (9) via a docking connector, and the DC constant power source (3) is electrically connected to a flashlight charging compartment (4); The second pressure gauge (5) is connected to the first end of the return air pipe (8) via a docking joint.
2. The aircraft torque motor controller in-situ test fixture according to claim 1, characterized in that: The lower space of the detection trolley is separated into a left compartment (100) and a right compartment (200) by a vertical partition, and the right compartment (200) is further separated into a right first compartment (201), a right second compartment (202) and a right third compartment (203) by a horizontal partition; a nitrogen tank (6) is placed in the left compartment (100), an air outlet pipe (7) is placed in the right first compartment (201), an air return pipe (8) is placed in the right second compartment (202), and an external power cord (9) is placed in the right third compartment (203).
3. The aircraft torque motor controller in-situ test tool according to claim 2, characterized in that: A U-shaped support seat (101) is fixedly arranged in the left compartment (100), and the opening of the U-shaped support seat (101) faces forward.
4. The aircraft torque motor controller in-situ test tool according to claim 3, characterized in that: The U-shaped support seat (101) is provided with a limit groove (102) extending horizontally in the left and right directions, and a limit bolt (103) is arranged in the limit groove (102).
5. The aircraft torque motor controller in-situ test tool according to claim 1, characterized in that: The first pressure gauge (1), the pressure regulating valve (2), the DC constant power supply (3), the flashlight charging compartment (4) and the second pressure gauge (5) are all arranged on the rear half of the upper table of the inspection trolley, and a tool storage box (300) is also arranged on the front half of the upper table of the inspection trolley.
6. The aircraft torque motor controller in-situ test tool according to claim 1, characterized in that: The bottom of the detection trolley is provided with self-locking universal wheels.
7. The aircraft torque motor controller in-situ test tool according to claim 1, characterized in that: A push-pull handle is also provided on one side of the detection trolley.
8. The aircraft torque motor controller in-situ test tool according to claim 1, characterized in that: The plurality of docking joints include a pipeline docking joint, an electronic pressure gauge docking joint and a power supply docking joint.