A test device for testing the anti-interference capability of aircraft training

Abstract

This application discloses a test device for anti-interference capability of aircraft training, relating to the technical field of aircraft test devices. It includes a workbench, a soft pad, a hydraulic base, a test module, and a simulation test mechanism. The simulation test mechanism consists of a base, a test cylinder, a central shaft, a vertical plate, a movable sleeve, a top shaft sleeve, a secondary base, a pull rope, and an annular bladder. Through the cooperation of the electric telescopic rod, the movable column, and the top shaft sleeve, it simulates sudden pulling force on the aircraft and tests its fuselage stability and response capability under interference conditions. The device also has angle adjustment and airflow interference functions, which can simulate obstacle pulling and airflow interference scenarios in various real environments, improving the realism of the test and the comprehensiveness of the data.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing equipment technology, and in particular to an aircraft training anti-interference capability testing device. Background Technology

[0002] Currently, testing the anti-interference capabilities of aircraft in complex environments largely relies on actual flight tests, which suffers from high costs, significant risks, and poor repeatability. Existing testing equipment often cannot simulate various dynamic interference conditions, such as sudden pulling, elastic obstacle fluctuations, and airflow disturbances, resulting in incomplete test data that fails to accurately reflect the stability and control performance of aircraft under sudden interference. Therefore, there is an urgent need for a device capable of simulating multiple interference scenarios and facilitating systematic testing in a laboratory environment. Summary of the Invention

[0003] This application provides a test device for testing the anti-interference capability of aircraft training, which solves the technical problems of the single anti-interference test environment and insufficient realism in the prior art. By simulating sudden tension and dynamic interference through multi-mechanism collaboration, it achieves the technical effect of comprehensive, realistic and repeatable testing of the anti-interference capability of aircraft.

[0004] This application provides a test device for testing the anti-interference capability of aircraft training, including a workbench, on which a soft pad and multiple hydraulic bases are installed, and a simulation test mechanism is installed at the output end of the hydraulic bases.

[0005] The test module is installed on the aircraft fuselage and is not shown in the figure. The test module can be various sensor structures and is mainly used to detect the flight status of the aircraft. The specific structure of the test module is based on existing technology and will not be described in detail here.

[0006] The simulation testing mechanism includes: a base, a test cylinder, a central shaft, a vertical plate, a movable sleeve, a top shaft sleeve, a secondary base, a pull rope, and an annular bladder; the base is fixed to the output end of the hydraulic base, the test cylinder and the secondary base are fixed on the base, and the vertical plate is provided on the secondary base;

[0007] The movable sleeve is set at one end of the test cylinder, and the annular bladder and the central shaft are fixed inside the test cylinder; the top shaft sleeve is set inside the central shaft, and an electric telescopic rod is fixed on the vertical plate; a horizontal column is fixed at the output end of the electric telescopic rod, and a movable column is fixed at the bottom of the horizontal column; a through hole is opened at the center of the vertical plate, and one end of the pull rope is fixed to one end of the movable sleeve, and a claw is fixed at the other end.

[0008] The movable sleeve is slidably connected to one end of the test cylinder, and the annular bladder is wrapped around the central axis; the top shaft sleeve is slidably connected inside the central axis; the movable column is slidably connected to the other end of the top shaft sleeve.

[0009] The base has a sliding groove, and a micro motor is installed on the side of the base near the sliding groove. A roller screw is fixed to the output end of the micro motor, and the bottom of the sub-base is fixed to the outer ring of the roller screw. Arc-shaped guides are fixed to both ends of the through hole to guide the pull rope to move towards the arc-shaped concave stable point of the guide.

[0010] The movable column has a U-shaped structure, with both ends fixed to the bottom of the horizontal column and the middle end slidably connected to the middle of the other end of the top shaft sleeve;

[0011] The vertical plate and the test cylinder are not fitted together; there is a gap between them to allow for the extension and retraction of the electric telescopic rod and to prevent jamming.

[0012] The upright plate is detachably fixed to the sub-base by bolts, so that the position of the upright plate can be adjusted on the sub-base;

[0013] The annular bladder is also equipped with a connecting tube, which passes through the test cylinder and is connected to an external air pump device. The air pump is existing technology and is not shown in the figure, so it will not be described in detail here.

[0014] Furthermore, a circular base is fixed at the center of one side of the upright plate, and a rotating circular component is rotatably connected to the circular base; the outer cross section of the rotating circular component is provided with teeth; a micro motor II is fixed on one side of the upright plate and close to the circular base, and its output end is fixed with a gear that meshes with the teeth of the rotating circular component; a vibrator is installed inside the wave crest of the interference bag to simulate the slight shaking of the obstacle or to ensure the continuity of the interference force between the pull rope and the interference bag; the interference bag is composed of multiple connected cavities, each cavity corresponding to an inflation hole, and there is a gap between two cavities, the gap distance being greater than the diameter of the pull rope;

[0015] Furthermore, the main air pipe also includes multiple auxiliary air pipes, the number of which corresponds to the limiting component. One end of the auxiliary air pipe is connected to the main air pipe, and the other end passes through the corresponding limiting component, then is laid along the pull rope, and extends to the vicinity of the claw. Its opening points towards the aircraft to provide airflow interference.

[0016] Beneficial effects: By driving the moving column 203 and the top shaft sleeve 161 through the electric telescopic rod 201, the sudden pulling force on the aircraft can be simulated, which can effectively test its emergency stability capability, simulate the pulling of real obstacles, and provide accurate test data and flexible and adjustable operation.

[0017] By using the interference capsule 222 and the vibrator 225 to generate waves in tandem, the continuous interference of elastic obstacles on the aircraft fuselage is simulated, which improves the realism and coherence of the test scenario and is more in line with actual flight obstacles.

[0018] By combining airflow jets and wave interference, it simulates a complex environment where airflow and obstacles interact, enhancing the testing dimensions and providing more comprehensive anti-interference performance data, making it suitable for high-end testing needs. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural schematic diagram of an aircraft training anti-interference capability testing device according to the present invention;

[0020] Figure 2 This is a half-sectional view of the test cylinder of the aircraft training anti-interference capability testing device of the present invention;

[0021] Figure 3 This is a schematic diagram of the guide structure of an aircraft training anti-interference capability testing device according to the present invention;

[0022] Figure 4 This is a schematic diagram of the rotating circular component structure of a second embodiment of the aircraft training anti-interference capability testing device of the present invention;

[0023] Figure 5 This is a schematic diagram of the vibrator position in Embodiment 2 of the aircraft training anti-interference capability testing device of the present invention;

[0024] Figure 6 This is a schematic diagram of the main air pipe position in Embodiment 3 of the aircraft training anti-interference capability testing device of the present invention.

[0025] In the picture:

[0026] 100. Workbench; 110. Soft pad; 120. Hydraulic base; 130. Base; 131. Sliding groove; 132. Micro motor one; 140. Test cylinder; 141. Central shaft; 150. Vertical plate; 151. Perforation; 160. Moving sleeve; 161. Top shaft sleeve; 170. Sub-base; 180. Pull rope; 200. Annular bladder; 201. Electric telescopic rod; 202. Horizontal column; 203. Moving column; 210. Guide; 220. Round seat; 221. Rotating round part; 222. Interference bladder; 223. Micro motor two; 224. Bladder cavity; 225. Vibrator; 230. Round sleeve; 231. Main air pipe; 232. Limiting component; 233. Sub-air pipe. Detailed Implementation

[0027] To facilitate understanding of the present invention, a more complete description of this application will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the invention. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to enable a more thorough and complete understanding of the disclosure of the present invention.

[0028] It should be noted that the terms "vertical," "horizontal," "up," "down," "left," "right," and similar expressions used in this article are for illustrative purposes only and do not represent the only possible implementation.

[0029] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains; the terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to limit the invention; the term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0030] Example 1: As Figures 1 to 3 As shown, this application discloses an aircraft training anti-interference capability testing device, including a workbench 100, on which a soft pad 110 and multiple hydraulic bases 120 are installed, and a simulation testing mechanism is installed at the output end of the hydraulic bases 120.

[0031] The test module is installed on the aircraft fuselage and is not shown in the figure. The test module can be various sensor structures and is mainly used to detect the flight status of the aircraft. The specific structure of the test module is based on existing technology and will not be described in detail here.

[0032] The simulation testing mechanism includes: a base 130, a test cylinder 140, a central shaft 141, a vertical plate 150, a movable sleeve 160, a top shaft sleeve 161, a secondary base 170, a pull rope 180, and an annular bladder 200; the base 130 is fixed to the output end of the hydraulic base 120, the test cylinder 140 and the secondary base 170 are fixed on the base 130, and the vertical plate 150 is provided on the secondary base 170.

[0033] A movable sleeve 160 is disposed at one end of a test cylinder 140, and an annular bladder 200 and a central shaft 141 are fixed inside the test cylinder 140; a top shaft sleeve 161 is disposed inside the central shaft 141, and an electric telescopic rod 201 is fixed on a vertical plate 150; a horizontal column 202 is fixed at the output end of the electric telescopic rod 201, and a movable column 203 is fixed at the bottom of the horizontal column 202; a through hole 151 is opened at the center of the vertical plate 150, and one end of a pull rope 180 is fixed to one end of the movable sleeve 160, and the other end is fixed with a claw.

[0034] The movable sleeve 160 is slidably connected to one end of the test cylinder 140, and the annular bladder 200 is wrapped around the central shaft 141; the top shaft sleeve 161 is slidably connected inside the central shaft 141; and the movable column 203 is slidably connected to the other end of the top shaft sleeve 161.

[0035] The base 130 has a sliding groove 131. A micro motor 132 is installed on the side end of the base 130 near the sliding groove 131. A roller screw is fixed to the output end of the micro motor 132. The bottom of the sub-base 170 is fixed to the outer ring of the roller screw. Arc-shaped guides 210 are fixed to both ends of the through hole 151 to guide the pull rope 180 to move towards the arc-shaped concave stable point of the guide 210.

[0036] The movable column 203 has a U-shaped structure, with both ends fixed to the bottom of the horizontal column 202, and the middle end slidably connected to the middle of the other end of the top shaft sleeve 161.

[0037] The vertical plate 150 and the test cylinder 140 are not attached to each other, and there is a gap between them for the extension and retraction of the electric telescopic rod 201 to prevent jamming.

[0038] The upright plate 150 is detachably fixed to the sub-base 170 by bolts, so that the position of the upright plate 150 can be adjusted on the sub-base 170.

[0039] The annular bladder 200 is also provided with a connecting tube, which passes through the test cylinder 140 and is connected to an external air pump device. The air pump is existing technology and is not shown in the figure, so it will not be described in detail here.

[0040] Specific implementation: First, connect and fix the claws on the pull rope 180 to components such as the aircraft fuselage or wings. Then, inflate the annular bladder 200 (inflation or deflating is also possible during testing). Next, fix the upright plate 150 to the sub-base 170 with bolts (the position of the upright plate 150 is adjustable before the test simulation). After completing the above steps, conduct an anti-interference simulation test. During the flight movement of the aircraft, pull the pull rope 180. At this time, the pull rope 180 is in a taut state. Activate the electric telescopic rod 201 at the corresponding position of the pull rope 180. The electric telescopic rod 201 extends, driving the horizontal column 202 to move. The horizontal column 202 drives the moving column 203 to move. The moving column 203 then drives the top shaft sleeve 161 to press against the moving sleeve 161. 60, to give the aircraft a sudden pulling force, simulating a real aircraft getting stuck on a tree branch or other obstacle, thereby forcing the aircraft to make a quick stabilizing maneuver, and the data is recorded by the test module. During the simulation test, the micro motor 132 can be activated to adjust the angle of the stand plate 150 relative to the test cylinder 140. The movement of the stand plate 150 causes the perforation 151 to move together. The perforation 151 moves to press against the pull rope 180, causing the pull rope 180 to pull in the direction of the movement of the stand plate 150. When the electric telescopic rod 201 is activated, the pull rope 180 pulls the aircraft in different angles of tension, achieving the effect of fine-tuning the test. Through the above, various external tension test data can be simulated.

[0041] Beneficial effects: By driving the moving column 203 and the top shaft sleeve 161 through the electric telescopic rod 201, the basic sudden pulling force of the aircraft can be simulated, which can effectively test its emergency stability capability, provide a basic test scenario for simulating the pulling of real obstacles, and the test data is accurate and the operation is flexible and adjustable.

[0042] Example 2: To simulate the wave-like motion of an aircraft when it is pulled by an elastic obstacle, and to test the aircraft's motion data in this scenario, this application proposes the following technical solution to address the aforementioned technical problem:

[0043] like Figure 4 and Figure 5 As shown, a circular base 220 is fixed at the center of one side of the upright plate 150, and a rotating circular component 221 is rotatably connected to the circular base 220; the outer cross section of the rotating circular component 221 is provided with teeth; an interference bladder 222 is fixed inside the rotating circular component 221; a micro motor 223 is fixed on one side of the upright plate 150 and close to the circular base 220, and its output end is fixed with a gear that cooperates with the teeth of the rotating circular component 221.

[0044] The interference bladder 222 is composed of multiple bladder cavities 224 connected together. Each bladder cavity 224 corresponds to an inflation hole. There is a gap between two bladder cavities 224, and the gap distance is greater than the diameter of the pull rope 180.

[0045] A vibrator 225 is installed inside the crest of the interference capsule 222 to simulate the slight shaking of an obstacle or to ensure the continuity of the interference force between the pull rope 180 and the interference capsule 222.

[0046] Specific implementation: In order to simulate the wave scenario when the aircraft is pulled by an elastic obstacle, after the aircraft is taut by the pull rope 180, the electric telescopic rod 201 is activated, giving the aircraft a sudden pulling force. At this time, the micro motor 223 and the vibrator 225 are activated. The micro motor 223 rotates, which drives the interference bag 222 to rotate and come into contact with the pull rope 180. The pull rope 180 continuously moves in contact with the crests and troughs of the interference bag 222. The vibrator 225 performs secondary vibrations during the process of the pull rope 180 moving from the crest or trough to the trough or crest, improving the wave continuity and making the wave closer to the external real environment test. Through the above, the wave scenario when the aircraft is pulled by an elastic obstacle (tree branch or other obstacle) can be simulated.

[0047] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0048] Based on the static tension simulated in Example 1, the interference capsule 222 and the vibrator 225 are used to generate waves in coordination to simulate the dynamic and continuous wave interference of elastic obstacles on the aircraft fuselage, which greatly improves the realism and coherence of the test scenario and is more in line with actual flight obstacles.

[0049] Example 3: To simulate the impact of airflow on an aircraft during adjustment when it is caught on an obstacle, and to test the data on the aircraft's response actions; this application proposes the following technical solution to address the above-mentioned technical problem, specifically:

[0050] like Figure 6 As shown, a circular sleeve 230 is fixed at the center of one side of the upright plate 150, and a main air pipe 231 is installed on the outer cross section of the circular sleeve 230, which is close to the upright plate 150.

[0051] The outer cross-section of the circular sleeve 230 is provided with multiple limiting elements 232.

[0052] The main air pipe 231 also includes a plurality of auxiliary air pipes 233, the number of which corresponds to the limiting member 232. One end of the auxiliary air pipe 233 is connected to the main air pipe 231, and the other end passes through the corresponding limiting member 232, and then is laid along the pull rope 180 and extends to the vicinity of the claw. Its opening points towards the aircraft to provide airflow interference.

[0053] Specific implementation: To simulate the impact of airflow on an aircraft during its adjustment process when it is caught on an obstacle; after the aircraft pulls the rope 180 taut, the electric telescopic rod 201 actuates, giving the aircraft a sudden pulling force. At this time, the micro motor 223 and vibrator 225 are activated. The rotation of the micro motor 223 drives the interference bag 222 to rotate and contact the rope 180. The rope 180 moves between the crests and troughs of the interference bag 222. The vibrator 225 performs secondary vibrations as the rope 180 moves from a crest or trough to a trough or crest. At this time, the external air pump is activated to inflate the main air pipe 231. Airflow is jetted from the auxiliary air pipe 233 onto the aircraft to interfere with the airflow. After the airflow interference, the aircraft needs to make more complex response actions to balance its fuselage, thus obtaining data on the fuselage adjustment process affected by airflow when caught on an obstacle. The combined effect of wave interference and airflow interference further improves the realism of the scene, making the wave and airflow interference closer to the actual external environment test.

[0054] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0055] By further integrating airflow jets with the wave interference of Example 2, a complex test environment is constructed that involves multiple factors such as mechanical tension, obstacle wave fluctuations, and airflow disturbances. This enhances the test dimensions and ultimately enables a comprehensive evaluation of the aircraft's anti-interference performance under extremely complex conditions, making it suitable for high-end testing needs.

[0056] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A test device for testing the anti-interference capability of aircraft training, characterized in that, Includes a workbench, on which a soft pad and multiple hydraulic bases are mounted, and a simulation testing mechanism is installed at the output end of the hydraulic bases; The test module is installed on the aircraft fuselage; The simulation testing mechanism includes: a base, a test cylinder, a central shaft, a vertical plate, a movable sleeve, a top shaft sleeve, a secondary base, a pull rope, and an annular bladder; the base is fixed to the output end of the hydraulic base, the test cylinder and the secondary base are fixed on the base, and the vertical plate is provided on the secondary base; A movable sleeve is installed at one end of the test cylinder, and the annular bladder and central shaft are fixed inside the test cylinder. A top shaft sleeve is installed inside the central shaft, and an electric telescopic rod is fixed on the vertical plate. A horizontal column is fixed at the output end of the electric telescopic rod, and a movable column is fixed at the bottom of the horizontal column. The movable column has a U-shaped structure, with both ends fixed to the bottom of the horizontal column and the middle end slidably connected to the middle of the other end of the top shaft sleeve. A through hole is opened at the center of the vertical plate, and one end of the pull rope is fixed to one end of the movable sleeve, while the other end is fixed to a pawl. By driving the movable column and the top shaft sleeve with the electric telescopic rod, a basic sudden tension of the aircraft is simulated to test its emergency stability capability. A circular base is fixed at the center of one side of the upright plate, and a rotating circular component is rotatably connected to the circular base; the outer cross section of the rotating circular component has teeth; an interference bladder is fixed inside the rotating circular component; a micro motor is fixed to one side of the upright plate, close to the circular base, and its output end is fixed with a gear that meshes with the teeth of the rotating circular component; the interference bladder is composed of multiple connected cavities, each cavity corresponding to an inflation hole, and there is a gap between two cavities, the gap distance being greater than the diameter of the pull rope; a vibrator is installed inside the crest of the interference bladder; the rotation of the micro motor drives the interference bladder to rotate and contact the pull rope, and the pull rope continuously contacts and moves with the crest and trough of the interference bladder, and the vibrator performs secondary vibration as the pull rope moves from the crest or trough to the trough or crest; A circular sleeve is fixed at the center of one side of the upright plate. The outer cross section of the circular sleeve is fitted with a main air pipe and is close to the upright plate. Multiple limiting components are provided around the outer cross section of the circular sleeve. The main air pipe also includes multiple auxiliary air pipes, the number of which corresponds to the limiting components. One end of the auxiliary air pipe is connected to the main air pipe, and the other end passes through the corresponding limiting component. Then it is laid along the pull rope and extends to the vicinity of the chuck. Its opening points towards the aircraft to provide airflow interference, inflating the main air pipe. The airflow is jetted from the auxiliary air pipes onto the aircraft to interfere with the airflow.

2. The aircraft training anti-interference capability testing device as described in claim 1, characterized in that, The movable sleeve is slidably connected to one end of the test cylinder, and the annular bladder is wrapped around the central axis; the top shaft sleeve is slidably connected inside the central axis; and the movable column is slidably connected to the other end of the top shaft sleeve.

3. The aircraft training anti-interference capability testing device as described in claim 2, characterized in that, The base has a sliding groove, and a micro motor is installed on the side of the base near the sliding groove. A roller screw is fixed to the output end of the micro motor, and the bottom of the sub-base is fixed to the outer ring of the roller screw. Arc-shaped guides are fixed to both ends of the through hole.

4. The aircraft training anti-interference capability testing device as described in claim 1, characterized in that, The vertical plate and the test cylinder are not fitted together; there is a gap between them to provide movable space for the extension and retraction of the electric telescopic rod and to prevent jamming.

5. The aircraft training anti-interference capability testing device as described in claim 1, characterized in that, The upright plate is detachably fixed to the sub-base by bolts, allowing the upright plate to be adjusted in position on the sub-base; the annular bladder is also provided with a connecting pipe, which passes through the test cylinder and is connected to an external air pump device.

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