Testing device for simulating gap of aircraft actuating system
By designing a test device that includes a housing, a fixed shaft, and a sliding shaft, the problem of insufficient simulation of clearance in aircraft actuation systems was solved, achieving efficient clearance measurement and simulation, reducing test costs, and improving verification efficiency.
Patent Information
- Application Number
- CN202422999397.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-05
- Publication Date
- 2025-11-18
- Estimated Expiration
- 2034-12-05
AI Technical Summary
Existing technologies have failed to effectively simulate clearances in ground tests of aircraft actuation systems, resulting in insufficient verification of functions and performance. Furthermore, using real aircraft control surfaces is costly and time-consuming.
Design a test device including a housing, a fixed shaft assembly and a sliding shaft assembly, to measure the clearance of a simulated aircraft actuation system in real time using a dial indicator. The device can be adjusted and connected in series to the mechanical transmission link of the actuation system to realize clearance simulation and measurement.
It enables accurate simulation and measurement of the clearances in aircraft actuation systems, reducing testing costs, shortening testing cycles, and improving the integrity of functional and performance verification.
Smart Images
Figure CN223559858U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application belongs to the technical field of aircraft transmission mechanism design, and particularly relates to a test device for simulating the gap of an aircraft actuating system. BACKGROUND
[0002] Modern aircrafts mostly adopt fly-by-wire flight control systems, and the safety and reliability thereof has been the focus of attention. Ground test of the flight control system is an important link for judging the performance of the system and components and whether the system and components can be used for flight test, and plays an important role in the whole life cycle of aircraft development, so the establishment of the ground test environment is particularly important. There is less experience in the ground test environment of aircrafts in China, especially in the test environment of large aircrafts. Therefore, in order to be closer to the real state of the aircraft, a real aircraft control surface is mostly used in the previous ground test, but if the real aircraft control surface is used, the cost of establishing the ground test environment will be greatly increased, and the test cycle will be prolonged. Especially when the flight control system actuator ratio measurement selection test is carried out in the early stage of aircraft development (the structure of the aircraft control surface is not completely determined), at this time, a ground test device of the actuating system is needed, which can simulate the gap, stiffness and mass of the aircraft control rear system.
[0003] In the previous ground test of the actuating system, only the stiffness from the fixed end of the actuator to the control point and the stiffness from the control point to the center of mass of the control surface and the simulation of the inertia of the control surface are considered, but the gap existing in the actuator system is not considered, so the function and performance verification of the actuating system may not be sufficient. CONTENT OF THE UTILITY MODEL
[0004] In order to solve the above problems, the application provides a test device for simulating the gap of an aircraft actuating system, which mainly comprises:
[0005] The shell is a cylindrical structure, one end of which has an internal thread, and the inner wall of the other end is provided with a limiting protrusion, and a micrometer is fixed on the shell;
[0006] The fixed shaft sleeve assembly is threadedly connected to one end of the shell and forms a stop end face in the shell, and the other end forms a shaft sleeve;
[0007] The sliding shaft sleeve assembly is located in the shell and slides between the limiting protrusion and the stop end face, and the other end forms a shaft body, and a measuring plate is further provided on the sliding shaft sleeve assembly, and the measuring head of the micrometer can abut against the measuring plate;
[0008] The test device is connected in series to the mechanical transmission link of the actuating system through the shaft sleeve and the shaft body.
[0009] Preferably, a first nut is threadedly connected to the fixed shaft sleeve assembly, and when the one end of the fixed shaft sleeve assembly is screwed into the shell, the first nut is rotated to abut against the end face of the shell.
[0010] Preferably, the measuring plate is slidingly arranged on the shaft body of the sliding shaft body assembly and is fixed by a fastener.
[0011] Preferably, the fastener is a second nut screwed on the shaft body of the sliding shaft body assembly, and the second nut is used to press the measuring plate against the end face of the sliding sleeve of the sliding shaft body assembly.
[0012] Preferably, the dial gauge is clamped by a clamp which is fixed on the housing by a screw.
[0013] The present application can realize the function of actuating system gap simulation. By adjusting the position of the fixed shaft body assembly in the housing, the movement range of the sliding shaft body assembly in the housing is changed, the adjustment of the simulated gap is realized, and the gap measurement value is read out by the dial gauge on the gap measurement assembly and the measuring plate on the sliding shaft body assembly. BRIEF DESCRIPTION OF DRAWINGS
[0014] Figure 1 is a structural perspective view of a preferred embodiment of the test device for simulating the actuating system gap of an aircraft according to the present application.
[0015] Figure 2 is a sectional view of the embodiment shown in the present application. Figure 1
[0016] In the figure, 1 is a fixed shaft body assembly, 11 is a shaft sleeve, 12 is a first nut, 13 is a stop end face, 2 is a housing, 21 is a limiting protrusion, 3 is a sliding shaft body assembly, 31 is a sliding sleeve, 32 is a shaft body, 33 is a second nut, 34 is a measuring plate, 4 is a gap measurement assembly, 41 is a screw, 42 is a clamp, and 43 is a dial gauge. DETAILED DESCRIPTION
[0017] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.
[0018] The present application provides a test device for simulating the actuating system gap of an aircraft, as shown in Figures 1-2 The test device mainly comprises:
[0019] The shell 2 is a cylindrical structure, one end of which is internally threaded, and the inner wall of the other end is provided with a limiting protrusion 21. A micrometer 43 is fixed to the shell 2;
[0020] The fixed shaft sleeve assembly 1 is threadedly connected to the shell 2 at one end, and forms a stop end face 13 in the shell 2, and forms a shaft sleeve 11 at the other end.
[0021] The sliding shaft sleeve assembly 3 is located in the shell 2 at one end, and slides between the limiting protrusion 21 and the stop end face 13, and forms a shaft body 32 at the other end. The sliding shaft sleeve assembly 3 is also provided with a measuring plate 34, and the measuring head of the micrometer 43 can abut against the measuring plate 34.
[0022] The test device is connected in series to the mechanical transmission link of the actuation system through the shaft sleeve 11 and the shaft body 32.
[0023] Reference Figure 2 The fixed shaft sleeve assembly 1 of the present application is threadedly connected to the shell 2, and the clearance simulation value of the test device is adjusted by changing the screwing depth of the fixed shaft sleeve assembly 1, that is, the axial distance between the right end face of the fixed shaft sleeve assembly 1 and the limiting protrusion 21 of the shell 2 is adjusted. One end of the sliding shaft sleeve assembly 3 can slide in the axial distance, and simultaneously drives the measuring plate 34 to move relative to the shell 2. The micrometer fixed to the shell 2 can measure the moving distance of the measuring plate 34 in real time, thereby measuring the specific clearance simulation value in the movement process.
[0024] Reference Figure 2 When the fixed shaft sleeve assembly 1 moves to the left, the sliding shaft sleeve assembly 3 first slides a small distance in the clearance in the shell 2. At this time, the sliding shaft sleeve assembly 3 is stationary relative to the ground reference system, and the micrometer 43 also moves relative to the measuring plate 34, and the clearance value can be read through the micrometer. When the sliding sleeve 31 contacts the limiting protrusion 21 of the shell 2, the sliding shaft sleeve assembly 3 moves to the left relative to the ground reference system. At this time, the micrometer 43 is stationary relative to the measuring plate 34, and the measurement value no longer changes. When the fixed shaft sleeve assembly 1 moves to the right again, the sliding shaft sleeve assembly 3 first slides a small distance in the clearance in the shell 2. At this time, the sliding shaft sleeve assembly 3 is stationary relative to the ground reference system, and the micrometer 43 also moves relative to the measuring plate 34, and the clearance value can be read through the micrometer. When the sliding sleeve 31 contacts the stop end face 13, the sliding shaft sleeve assembly 3 moves to the right relative to the ground reference system. At this time, the micrometer 43 is stationary relative to the measuring plate 34, and the measurement value no longer changes.
[0025] In some optional embodiments, the fixed shaft sleeve assembly 1 is threadedly connected with a first nut 12. After the fixed shaft sleeve assembly 1 is screwed into the shell 2 at one end, the first nut 12 is turned to tightly abut against the end face of the shell 2. In this embodiment, the first nut 12 is provided to prevent loosening between the fixed shaft sleeve assembly 1 and the shell 2.
[0026] In some alternative embodiments, the measuring plate 34 is slidingly arranged on the shaft body 32 of the sliding shaft body assembly 3 and is fixed by a fastener. In this embodiment, the measuring plate 34 is used to assist the dial gauge 43 in gap measurement, and is clamped on the shaft body 32 and fixed axially through the end face of the sliding sleeve 31 and the nut 33.
[0027] In some alternative embodiments, the fastener is a second nut 33 threaded on the shaft body 32 of the sliding shaft body assembly 3, and the second nut 33 is used to press the measuring plate 34 against the end face of the sliding sleeve 31 of the sliding shaft body assembly 3, and the sliding sleeve 31 is capable of sliding in the housing 2.
[0028] In some alternative embodiments, the dial gauge 43 is clamped by a clamp 42, and the clamp is fixed on the housing 2 by a screw 41. Referring to Figure 1 and Figure 2 , the screw 41, the clamp 42 and the dial gauge 43 together constitute the gap measurement assembly 4, the clamp 34 clamps and fixes the dial gauge 43 by a bolt and a nut, and then is fixed on the housing 2 by the screw 41, and the housing 2 is pre-provided with a screw mounting hole.
[0029] The present application can be connected in series in the transmission chain of the ground test bench of the actuation system to simulate the real gap existing in the air of the actuation system, and can realize gap adjustment and measurement, has complete functions, simple and practical design, clear and reliable structure, and provides strong support for examining the functions and performance of the actuation system.
[0030] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical scope disclosed in the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A test apparatus for simulating clearances in aircraft actuation systems, characterized in that, include: The housing (2) is a cylindrical structure with an internal thread at one end and a limit protrusion (21) on the inner wall of the other end. A dial indicator (43) is fixed on the housing (2). The fixed shaft assembly (1) is threaded to the housing (2) at one end and forms a stop end face (13) inside the housing (2), and forms a bushing (11) at the other end. The sliding shaft assembly (3) has one end located inside the housing and slides between the limiting protrusion (21) and the stop end face (13), and the other end forms a shaft (32). The sliding shaft assembly (3) is also provided with a measuring plate (34), and the probe of the dial indicator (43) can rest on the measuring plate (34). The test device is connected in series to the mechanical transmission link of the actuation system via a bushing (11) and a shaft (32).
2. The test apparatus for simulating clearances in an aircraft actuation system as described in claim 1, characterized in that, The fixed shaft assembly (1) is threaded with a first nut (12). After one end of the fixed shaft assembly (1) is screwed into the housing (2), the first nut (12) is rotated to press against the end face of the housing (2).
3. The test apparatus for simulating clearances in an aircraft actuation system as described in claim 1, characterized in that, The measuring plate (34) is slidably mounted on the shaft (32) of the sliding shaft assembly (3) and fixed by fasteners.
4. The test apparatus for simulating clearances in an aircraft actuation system as described in claim 3, characterized in that, The fastener is a second nut (33) threaded onto the shaft (32) of the sliding shaft assembly (3). The second nut (33) is used to press the measuring plate (34) against the end face of the sliding sleeve (31) of the sliding shaft assembly (3). The sliding sleeve (31) can slide inside the housing (2).
5. The test apparatus for simulating clearances in an aircraft actuation system as described in claim 1, characterized in that, The dial indicator (43) is clamped by a clamp (42), which is fixed to the housing (2) by a screw (41).