A method and device for detecting the closure of a lock of a thrust reverser of an aeroengine

Abstract

The application discloses an aero-engine reverse thrust device closed lock detection method and device, and belongs to the field of aircraft maintenance. The device comprises a rack assembly, a transmitter placing box, a pressure transmitter, a support, a tension spring, a test assembly, a lifting ring, a counterweight assembly and a rotating shaft. The counterweight assembly is used for simulating design load, the handle of the test assembly is rotated to make the pressure sensor contact the closed lock trigger or the handle mark, force signals are transmitted to the pressure transmitter, and the opening force and the closing force are detected respectively. The problems of large size, complex operation, low safety and insufficient measurement accuracy of the detection device in the prior art are solved. Through optimization of the mechanical structure and sensor integration, fine measurement of the closing force in the range of 2210N-2230N is realized, and direct contact of personnel with the closed lock trigger is avoided, so that operation safety is ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft maintenance, in particular to a method and device for detecting the closed lock of an aircraft engine reverse thrust device. BACKGROUND

[0002] The closed lock of an aircraft engine reverse thrust device is a key locking mechanism to ensure that the reverse thrust device remains closed when the engine is working, and its failure may cause serious safety accidents. Currently, the detection devices for the closed lock produced by professional manufacturers are usually large in size and complex in hardware and software design, which are difficult to install and use in aircraft engine repair factories. The existing technology lacks a detection scheme that is compact in structure, easy to move and simple to operate, resulting in the inability to effectively verify whether the closing force of the closed lock meets the design requirements during the repair process. In addition, the traditional detection method has the safety hazard of direct contact between personnel and the trigger, and the measurement accuracy is insufficient, which cannot meet the fine repair requirements. SUMMARY

[0003] The purpose of the present application is to provide a method and device for detecting the closed lock of an aircraft engine reverse thrust device, which aims to solve the problems of large size, complex operation, low safety and insufficient measurement accuracy of the detection device in the prior art, and to provide a method and device for detecting the closing force of the closed lock of an aircraft engine reverse thrust device, which are compact in structure, reliable in fixation, easy to move, simple to operate and accurate in measurement. By optimizing the mechanical structure and integrating the sensor, fine measurement of the closing force in the range of 2210N~2230N is realized, and direct contact between personnel and the trigger of the closed lock is avoided to ensure operation safety.

[0004] The present application is implemented by the following technical scheme: a detection device for the closed lock of an aircraft engine reverse thrust device, comprising a rack assembly, a test assembly, a pressure transmitter and a counterweight assembly; the test assembly is rotatably arranged on the rack assembly and integrated with a pressure sensor; the counterweight assembly is connected to the hook end of the closed lock through a lifting ring; the pressure transmitter is in communication connection with the pressure sensor for detecting and displaying the closing force signal.

[0005] Further, the test assembly comprises a handle, a mounting plate and a pressure sensor; the mounting plate is hinged to a support through a rotating shaft, and the handle is fixed to the tail of the mounting plate; two mounting stations are arranged on the mounting plate, including a mounting station one for testing the opening force of the closed lock and a mounting station two for testing the closing force of the closed lock.

[0006] Further, a transmitter placement box is further included, and the pressure transmitter is arranged in the transmitter placement box; the test assembly is hinged to the support through a rotating shaft and a shaft stop ring, and a tension spring is provided to provide a reset spring force.

[0007] Further, the counterweight assembly is composed of multiple adjustable counterweights, and the total weight is adjustable in the range of 2210N to 2230N; the lifting ring is connected with the counterweight assembly at one end, and connected with the lifting ring of the closed lock through the crane at the other end.

[0008] Further, the rack assembly comprises a bottom plate, a column, a beam and a reinforcing rib plate which are welded; the support is welded with the rack assembly to form an integral support structure.

[0009] An aero-engine reverse thrust device closed lock detection method comprises the following steps:

[0010] Step one, connect the pin hole end of the closed lock with the test assembly through the quick-release latch;

[0011] Step two, connect the counterweight assembly with the hook end of the closed lock through the lifting ring, and adjust the weight of the counterweight to the design value in the range of 2210N to 2230N;

[0012] Step three, rotate the handle of the test assembly so that the contact of the pressure sensor contacts the trigger of the closed lock, opens the closed lock, and reads the opening force value displayed by the pressure transmitter;

[0013] Step four, rotate the handle of the test assembly again so that the contact of the pressure sensor contacts the 25.4mm mark away from the edge of the handle, closes the closed lock, and reads the closing force value displayed by the pressure transmitter.

[0014] Further, the opening force value is qualified in the range of 30N to 50N, and the closing force value is qualified in the range of 176N to 245N; during the test, first place the test head assembly in the installation station one to test the opening force, and then move to the installation station two to test the closing force.

[0015] Further, in steps three and four, the automatic return of the test assembly is realized through the tension spring; and the weight of the counterweight assembly is finely adjusted in the range of 2210N to 2230N according to the specification of the closed lock.

[0016] The aero-engine reverse thrust device closed lock detection method and device have the following beneficial effects:

[0017] The counterweight assembly is composed of multiple adjustable counterweights, and the total weight is adjustable in the range of 2210N to 2230N. The counterweight assembly is connected with the closed lock through the lifting ring, which simulates the actual working load and ensures the authenticity of the test conditions, and the weight adjustment interval is small, which is suitable for different lock specifications.

[0018] The pressure sensor is directly integrated in the test head and is in communication connection with the pressure transmitter, which converts the force signal into an electrical signal in real time and displays it. This design eliminates human reading errors, and the accuracy of the closure force measurement can reach the level of refinement within the range of 2210N~2230N.

[0019] By rotating the handle of the test assembly, the pressure sensor contacts the trigger or handle mark of the closure lock indirectly, avoiding direct contact with the pre-tightening force component and preventing the risk of injury.

[0020] Two installation stations are provided on the mounting plate of the test assembly: installation station one is used to test the opening force, and installation station two is used to test the closing force. This modular station allows step-by-step testing, avoids cross interference, and improves testing efficiency.

[0021] The test assembly is hinged to the bracket through a rotating shaft and integrated with a tension spring to provide a reset spring force. This rotating design allows the handle to easily operate the test assembly, and the spring automatic return function ensures the consistency of multiple tests, reducing manual intervention. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or prior art description will be briefly introduced as follows. The drawings in the following description are only some embodiments of the present application, and other drawings can be obtained from the structures shown in these drawings without creative labor for those skilled in the art.

[0023] Figure 1 is a structural schematic diagram of the present application;

[0024] Figure 2 is Figure 1 is a sectional view in the direction of K-K in FIG. 1;

[0025] Figure 3 is Figure 1 is a partial sectional view in the direction of B-B in FIG. 1;

[0026] Figure 4 is a structural diagram of the test assembly;

[0027] In the figure, 1 is a bracket assembly, 2 is a transmitter placement box, 3 is a pressure transmitter, 4 is a bracket, 5 is a tension spring, 6 is a test assembly, 7 is a lifting ring, 8 is a counterweight assembly, 9 is a rotating shaft, 61 is a handle, 62 is a mounting plate, 63 is installation station one, 64 is installation station two, and 65 is a pressure sensor. DETAILED DESCRIPTION

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention. Example

[0030] like Figures 1-4 As shown, this embodiment of the invention provides a method and apparatus for detecting the closed latch of an aero-engine thrust reverser device. The apparatus mainly consists of a frame assembly 1, a transmitter housing 2, a pressure transmitter 3, a bracket 4, a tension spring 5, a test assembly 6, a lifting ring 7, a counterweight assembly 8, and a rotating shaft 9. The test assembly 6 further includes a handle 61, a mounting plate 62, a first mounting station 63, a second mounting station 64, and a pressure sensor 65. The mounting plate 62 is rotatably connected to the bracket 4 via the rotating shaft 9. The handle 61 is fixedly located at the rear of the mounting plate 62 for manual operation. The mounting plate 62 has a first mounting station 63 and a second mounting station 64 for placing the probe assembly. The pressure sensor 65 is integrated into the test head for detecting the closing force.

[0031] Specifically, the rack assembly 1 is fixedly connected with the support 4 by welding to form an integral support structure. The rack assembly 1 itself is welded from a bottom plate, a stand, a lifting ring bolt, a cross beam, a reinforcing rib plate and the like to ensure structural stability. One end of each of the two tension springs 5 is connected with the rack assembly 1, and the other end is connected with the mounting plate 62 of the test assembly 6 to provide a reset elastic force, so that the test assembly 6 can automatically reset after operation. The rotating shaft 9 passes through corresponding shaft pin holes on the support 4 and the rack assembly 1, is hingedly connected with the mounting plate 62 of the test assembly 6, and is axially fixed by a shaft blocking ring to ensure the stability of the rotating movement. The pressure transmitter 3 is placed in the transmitter placing box 2, and the inside of the transmitter placing box 2 is connected with a spring stand, a hexagon nut, a wrench seat, an internal hexagonal cylindrical head screw, a flat washer, a handle, a handle ball, a cylindrical pin, a sleeve, a pressure sensor 65, an end cover and a test head and the like through threads and pins. The pressure sensor 65 is fixed by the sleeve and the end cover and is connected with the test head for converting a mechanical signal into an electrical signal. One end of the lifting ring 7 is connected with the counterweight assembly 8, and the counterweight assembly 8 is composed of a plurality of counterweights, the total weight of which can be accurately adjusted within a range of 2210N to 2230N with an interval of 0.98N to meet the requirement of fine measurement. The other end of the lifting ring 7 is connected with the lifting ring of the closed shackle to be measured through an external crane. The quick-release latch is used to quickly connect the pin hole end of the closed shackle with the test assembly 6, and auxiliary components such as the cylindrical pin and the spring pull column are threadedly or pin-holed matched to ensure reliable fixation between the components.

[0032] The device is used for detecting the closing force of the closed shackle of the reverse thrust device of an aero-engine, and the specific process is as follows:

[0033] First, the pin hole end of the closed shackle is connected with the mounting plate 62 of the test assembly 6 through the quick-release latch, and the hook end is connected with the counterweight assembly 8 through the lifting ring 7. The weight of the counterweight assembly 8 is pre-set to a design value between 2210N and 2230N. The other end of the lifting ring 7 is suspended by the crane to make the closed shackle in a test state.

[0034] During the test, the operator manually rotates the handle 61 of the test assembly 6 to drive the mounting plate 62 to rotate around the rotating shaft 9. Initially, the test head assembly is manually removed and placed on the mounting station one 63. The handle 61 is rotated downward by 90° to make the test head contact the trigger of the closed shackle, trigger the switch mechanism of the closed shackle, and realize the opening and closing torque test. At this time, the contact of the pressure sensor 65 is pressed on the trigger, the handle of the closed shackle is opened, the force value is read through the pressure transmitter 3, and if the value is within a range of 30N to 50N, the product is qualified.

[0035] Subsequently, the handle 61 is loosened, and the elastic force of the tension spring 5 makes the mounting plate 62 return to the original position. The probe assembly is manually removed and placed on the mounting station two 64. The handle 61 is rotated downward by 90° again, so that the test head contacts the handle edge of the closed lock at the 25.4 mm mark, and is pressed until the closed lock is closed. The contact of the pressure sensor 65 is pressed at the handle mark, the closed lock handle is closed, the force value is read by the pressure transmitter 3, and if the value is in the range of 176N to 245N, the product is qualified.

[0036] During the whole process, the pressure sensor 65 transmits the detected force signal to the pressure transmitter 3 for signal conversion and display, ensuring accurate measurement. The structural design of the device avoids direct contact of personnel with the trigger of the closed lock, preventing the risk of injury caused by pre-tightening force. By adjusting the weight of the counterweight block assembly 8, fine measurement of the closing force in the range of 2210N to 2230N can be achieved. The device is compact in structure, reliable in fixation, easy to move, and suitable for aircraft engine repair sites.

[0037] The detection device realizes efficient and safe detection of the closing force of the closed lock through the combination of mechanical and sensing technologies. The rotational movement of the test assembly 6 is controlled by the rotating shaft 9 and the tension spring 5, ensuring smooth operation. The design of the mounting station one 63 and the mounting station two 64 allows step-by-step testing of the opening and closing force, improving test accuracy. The use of the pressure transmitter 3 and the pressure sensor 65 digitizes the measurement data, reducing human error. The welded structure of the rack assembly 1 ensures overall rigidity, and the adjustability of the counterweight block assembly 8 adapts to different testing requirements. Therefore, the embodiment not only has simple operation, but also has good measurement repeatability, safety and reliability, effectively solving the problem of closed lock detection in aircraft engine repair.

[0038] In the above embodiments, the basic principles and main features of the present application and the advantages of the present application are described. It should be understood by those skilled in the art that the present application is not limited by the above embodiments, and the above embodiments and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, modifications and changes made by those skilled in the art do not deviate from the spirit and scope of the present application, and should be within the protection scope of the claims of the present application.

Claims

1. An aircraft engine reverse thrust device closed lock detection device characterized by, The utility model relates to a kind of test device of closure lock, including rack assembly (1), test assembly (6), pressure transmitter (3) and counterweight assembly (8);The test assembly (6) is rotatably arranged on rack assembly (1), and is integrated with pressure sensor (65);The counterweight assembly (8) is connected with the hook end of closed lock by lifting ring (7) and closed shackle;The pressure transmitter (3) is connected with pressure sensor (65), for detecting and displaying closing force signal;The test assembly (6) includes handle (61), mounting plate (62) and pressure sensor (65);The mounting plate (62) is hinged with support (4) by pivot (9), and the handle (61) is fixed to the tail of mounting plate (62);Two mounting stations are provided on the mounting plate (62), including installation station one (63) for testing the opening force of closed lock and installation station two (64) for testing the closing force of closed lock;The support (4) is welded with rack assembly (1) and forms integral support structure.

2. A closure lock detection device for a jet engine reverse thrust device as set forth in claim 1, characterized in that, It also includes transmitter placing box (2), and the pressure transmitter (3) is arranged in the transmitter placing box (2);The test assembly (6) is hinged with support (4) by pivot (9) and shaft stopper, and is provided with tension spring (5) for providing reset elastic force.

3. A closure lock detection device for a jet engine reverse thrust device as set forth in claim 1, characterized in that, The counterweight assembly (8) is composed of multiple adjustable counterweights, and the total weight is adjustable within the range of 2210N to 2230N;One end of the lifting ring (7) is connected with the counterweight assembly (8), and the other end is connected with the lifting ring of the closed lock through a crane.

4. A closure lock detection device for a jet engine reverse thrust device as set forth in claim 1, characterized in that, The rack assembly (1) includes a bottom plate, a vertical column, a cross beam and a reinforcing rib plate connected by welding.

5. An aircraft engine reverse thrust device closed lock detection method using the detection device of any one of claims 1 to 4, characterized in that, The utility model includes the following steps: Step one, connect the pin hole end of the closed lock with the test assembly (6) through the quick-release latch; Step two, connect the counterweight assembly (8) with the hook end of the closed lock through the lifting ring (7), and adjust the weight of the counterweight to the design value within the range of 2210N to 2230N; Step three, rotate the handle (61) of the test assembly (6) to make the contact of the pressure sensor (65) contact the trigger of the closed lock, open the closed lock, and read the opening force value displayed by the pressure transmitter (3); Step four, rotate the handle (61) of the test assembly (6) again to make the contact of the pressure sensor (65) contact the 25.4mm mark on the edge of the handle of the closed lock, close the closed lock, and read the closing force value displayed by the pressure transmitter (3).

6. A method of detecting the closure of a lock of a turbofan engine reverse thrust device according to claim 5, characterized in that, The qualified range of the opening force value is 30N to 50N, and the qualified range of the closing force value is 176N to 245N;During testing, first place the measuring head assembly in the installation station one (63) to test the opening force, and then move to the installation station two (64) to test the closing force.

7. The method of detecting the closure of a lock of a thrust reverser of a gas turbine engine as set forth in claim 5, wherein, In steps three and four, the test assembly (6) is automatically returned by the tension spring (5);The weight of the counterweight assembly (8) is finely adjusted within the range of 2210N to 2230N according to the specifications of the closed lock.

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