Steering system load simulation test device

Abstract

This utility model belongs to the technical field of testing equipment, specifically a rudder system load simulation testing device, comprising: a frame and a testing component mounted on the frame; the testing component includes a testing mechanism mounted on the frame, a load mechanism mounted on the frame and located on the side of the testing mechanism, and a mounting base mounted on the frame; the testing mechanism includes a housing mounted on the side of the frame, a motor fixed inside the housing, a drive shaft connected to the drive end of the motor, a torque sensor located in the middle of the drive shaft, and an angle encoder mounted at the end of the drive shaft. This utility model, through the testing component, can reproduce inertial loads, elastic loads, and damped loads using the magnetic powder brake, variable stiffness spring assembly, and hydraulic damper in the load mechanism. Compared with traditional fixed weight loads, the dynamic characteristic simulation is more accurate, and the test data is more comprehensive.

Description

Technical Field

[0001] This utility model relates to the field of testing equipment technology, specifically a rudder system load simulation testing device. Background Technology

[0002] The function of aircraft servos is to control the aircraft's flight attitude by adjusting the engine and various control surfaces. Specifically, servos control the engine thrust by controlling the engine intake air volume, control the aircraft's roll motion by controlling the aileron control surfaces, control the aircraft's pitch angle by controlling the horizontal tail control surfaces, and control the aircraft's yaw angle by controlling the vertical tail control surfaces.

[0003] Traditional servo motor testing uses a fixed weight load method, which has problems such as a single load type, inability to simulate dynamic characteristics, and incomplete test data.

[0004] This application proposes a control system load simulation test device, which can accurately reproduce the aerodynamic load characteristics of aircraft control surfaces through multi-dimensional load composite technology, thereby improving the accuracy and precision of the test. Utility Model Content

[0005] This utility model aims to solve one of the technical problems existing in the prior art or related technologies.

[0006] Therefore, the technical solution adopted by this utility model is as follows:

[0007] A rudder system load simulation test device includes: a frame and a test component mounted on the frame; the test component includes a test mechanism mounted on the frame, a load mechanism mounted on the frame and located on the side of the test mechanism, and a mounting base mounted on the frame; the test mechanism includes a housing mounted on the side of the frame, a motor fixed inside the housing, a drive shaft connected to the drive end of the motor, a torque sensor disposed in the middle of the drive shaft, an angle encoder mounted on the end of the drive shaft, a load disk fixed on the angle encoder, and a coupling mounted on the outside of the load disk.

[0008] In a preferred embodiment, the present invention can be further configured such that the testing mechanism also includes a main control module and a data acquisition module disposed within the housing.

[0009] In a preferred embodiment, the present invention can be further configured such that the load mechanism includes a magnetic powder brake, a variable stiffness spring assembly, and a hydraulic damper arranged symmetrically at 120° around the load disk.

[0010] The load mechanism also includes a gear ring located on the outside of the load disk, a bevel gear set connected between the load disk and the magnetic powder brake, a ball bearing located between the load disk and the hydraulic damper, a hinged swing arm connected between the load disk and the variable stiffness spring set, and a speed sensor located on the side of the load disk.

[0011] In a preferred embodiment, the present invention can be further configured such that the hydraulic damper has a built-in electro-hydraulic proportional valve and a pressure sensor, the damping coefficient adjustment range is 0.5-20 N·s / m, and the adjustment resolution reaches 0.1 N·s / m.

[0012] In a preferred embodiment, the present invention can be further configured such that a through hole is provided in the middle of the frame for the drive shaft to pass through.

[0013] The above-mentioned technical solution of this utility model has the following beneficial technical effects:

[0014] 1. This utility model, through its testing components, can reproduce inertial loads, elastic loads, and damped loads using magnetic powder brakes, variable stiffness spring groups, and hydraulic dampers in the load mechanism. Compared with traditional fixed weight loads, the dynamic characteristic simulation is more accurate, and the test data is more comprehensive.

[0015] 2. This utility model, through the testing component, can use the motor in the testing mechanism to drive the drive shaft to rotate, thereby driving the output shaft of the servo motor connected to the coupling. During the driving process, in conjunction with the load mechanism, the axial resistance torque, radial elastic force and tangential damping force applied to the load plate can accurately reproduce the aerodynamic load characteristics of the aircraft control surface, thereby improving the accuracy and precision of the test. Attached Figure Description

[0016] Figure 1 This is a cross-sectional view of the rudder system load simulation test device of this utility model;

[0017] Figure 2 This is a side view of the rudder system load simulation test device of this utility model.

[0018] Figure label:

[0019] 100. Frame; 110. Mounting base; 120. Through hole;

[0020] 200. Test components; 210. Housing; 211. Main control module; 212. Data acquisition module; 220. Motor; 230. Drive shaft; 240. Torque sensor; 250. Angle encoder; 260. Load plate; 270. Coupling;

[0021] 310. Magnetic powder brake; 320. Variable stiffness spring assembly; 330. Hydraulic damper; 340. Gear ring; 350. Bevel gear assembly; 360. Ball bearing; 370. Articulated swing arm; 380. Speed ​​sensor. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features of the present utility model can be combined with each other.

[0023] It should be understood that these descriptions are merely exemplary and not intended to limit the scope of this invention.

[0024] The following describes, with reference to the accompanying drawings, some embodiments of the present invention, a rudder system load simulation test device.

[0025] Combination Figure 1-2 As shown, the present invention provides a rudder system load simulation test device, comprising: a frame 100 and a test component 200 disposed on the frame 100; the test component 200 includes a test mechanism mounted on the frame 100, a load mechanism mounted on the frame 100 and located on the side of the test mechanism, and a mounting base 110 mounted on the frame 100; the test mechanism includes a housing 210 mounted on the side of the frame 100, a motor 220 fixed inside the housing 210, a drive shaft 230 connected to the drive end of the motor 220, a torque sensor 240 disposed in the middle of the drive shaft 230, an angle encoder 250 mounted on the end of the drive shaft 230, a load disk 260 fixed on the angle encoder 250, and a coupling 270 mounted on the outside of the load disk 260.

[0026] Furthermore, the load mechanism includes a magnetic powder brake 310, a variable stiffness spring assembly 320, and a hydraulic damper 330 arranged symmetrically at 120° around the load disk 260. The load mechanism also includes a gear ring 340 located on the outside of the load disk 260, a bevel gear assembly 350 connected between the load disk 260 and the magnetic powder brake 310, a ball bearing 360 located between the load disk 260 and the hydraulic damper 330, a hinged swing arm 370 connected between the load disk 260 and the variable stiffness spring assembly 320, and a speed sensor 380 located on the side of the load disk 260. The motor 220 in the test mechanism can drive the drive shaft 230 to rotate, thereby driving the output shaft of the servo motor connected to the coupling 270. During the drive process, the axial resistance torque, radial elastic force, and tangential damping force applied to the load disk 260 by the load mechanism can accurately reproduce the aerodynamic load characteristics of the aircraft control surface, thereby improving the accuracy and precision of the test.

[0027] Specifically, the magnetic powder brake 310 is used to apply axial resistance torque (normal direction of the plane of rotation) to the load disk 260, the variable stiffness spring group 320 is used to generate tangential damping force (opposite to the direction of rotation) to the load disk 260, and the hydraulic damper 330 applies radial elastic force (pointing towards the center) to the load disk.

[0028] Practical scenarios:

[0029] Scenario: A servo motor drives the load disk to rotate clockwise.

[0030] Magnetic powder brake 310: generates braking torque proportional to rotational speed (simulating air resistance torque).

[0031] Variable stiffness spring assembly 320: The piston rod is stretched, generating a damping force in the opposite direction to the velocity (simulating aerodynamic damping of the control surface).

[0032] Hydraulic damper 330: The swing arm compresses the spring, generating an elastic restoring force proportional to the steering angle (simulating the elastic deformation of the rudder surface).

[0033] By coordinating the spatial layout and power transmission path described above, the vector superposition of three types of loads—inertia, damping, and elasticity—is achieved, accurately simulating the load characteristics of the real control surface.

[0034] Furthermore, the magnetic powder brake 310 is located at the 12 o'clock position of the load disk 260. The magnetic powder brake 310 is vertically installed on the top of the load disk 260, and its output shaft is connected to the axis of the load disk 260 at a 90° angle through the bevel gear set 350. The variable stiffness spring set 320 and the hydraulic damper 330 are located at the 4 o'clock and 8 o'clock positions of the load disk 260, respectively. The variable stiffness spring set 320 is installed at a 45° angle on the lower right side of the load disk 260, and its piston rod end is connected to the edge of the disk surface through the ball bearing 360. The hydraulic damper 330 is horizontally arranged on the lower left side of the load disk 260, and its front end is hinged to the disk surface of the load disk 260. In this way, the load force can be transmitted when in contact without restricting the rotational freedom of the load disk.

[0035] Furthermore, the bevel gear set 350 is mounted on the frame 100 and has an adaptive adjustment function, which allows it to fit and maintain meshing as the load plate 260 is adjusted.

[0036] Specifically, the testing mechanism also includes a main control module 211 and a data acquisition module 212 installed in the housing 210. The testing operation can be controlled by the mounting base 110. It is equipped with an existing conventional CNC processing system, while the data acquisition module 212 can be connected to various sensor and other drive units. The main control module 211 has a multi-channel expansion interface (Type-C×2, aviation plug×4), an overload alarm indicator (red / yellow / green), and is directly connected to the data acquisition module 212 via a ribbon cable.

[0037] On the other hand, the hydraulic damper 330 has a built-in electro-hydraulic proportional valve and pressure sensor, and the damping coefficient adjustment range is 0.5-20 N·s / m with an adjustment resolution of 0.1 N·s / m, making it highly practical.

[0038] Furthermore, the frame 100 has a through hole 120 in the middle for the drive shaft 230 to pass through, allowing the drive shaft 230 to pass through to complete the drive test.

[0039] The working principle and usage process of this utility model are as follows: First, the servo motor under test is fixed to the mounting base 110, and the output shaft of the servo motor is connected to the load plate 260 through the coupling 270. The magnetic powder brake 310 generates a basic resistance torque on the load plate 260. The hydraulic damper 330 simulates the aerodynamic damping characteristics of the load plate 260. The variable stiffness spring group hydraulic damper 330 reproduces the elastic deformation load of the servo surface on the load plate 260. Multiple load mechanisms are coupled through the load plate 260 to form a composite load environment. Then, multiple sets of sensors collect the output parameters of the servo motor in real time for testing.

[0040] Although embodiments of the present invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A rudder system load simulation test device, characterized in that, include: A rack (100) and a test assembly (200) disposed on the rack (100); The test assembly (200) includes a test mechanism mounted on the rack (100), a load mechanism mounted on the rack (100) and located on the side of the test mechanism, and a mounting base (110) mounted on the rack (100); The testing mechanism includes a housing (210) installed on the side of the frame (100), a motor (220) fixed inside the housing (210), a drive shaft (230) connected to the drive end of the motor (220), a torque sensor (240) disposed in the middle of the drive shaft (230), an angle encoder (250) installed at the end of the drive shaft (230), a load plate (260) fixed on the angle encoder (250), and a coupling (270) installed on the outside of the load plate (260).

2. The rudder system load simulation test device according to claim 1, characterized in that, The testing mechanism also includes a main control module (211) and a data acquisition module (212) disposed within the housing (210).

3. The rudder system load simulation test device according to claim 1, characterized in that, The load mechanism includes a magnetic powder brake (310), a variable stiffness spring assembly (320), and a hydraulic damper (330) arranged symmetrically at 120° around the load disk (260). The load mechanism further includes a gear ring (340) located on the outside of the load disk (260), a bevel gear set (350) connected between the load disk (260) and the magnetic powder brake (310), a ball bearing (360) located between the load disk (260) and the hydraulic damper (330), a hinged swing arm (370) connected between the load disk (260) and the variable stiffness spring set (320), and a speed sensor (380) located on the side of the load disk (260).

4. The rudder system load simulation test device according to claim 3, characterized in that, The hydraulic damper (330) has a built-in electro-hydraulic proportional valve and pressure sensor, and the damping coefficient adjustment range is 0.5-20 N·s / m with an adjustment resolution of 0.1 N·s / m.

5. The rudder system load simulation test device according to claim 1, characterized in that, The frame (100) has a through hole (120) in the middle for the drive shaft (230) to pass through.

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