Aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system

Abstract

The invention belongs to the technical field of airplane strength ground tests, and particularly relates to an airplane strength ground test hydraulic cylinder loading stroke margin monitoring system which comprises a displacement sensor, an upper computer and a displayer. The multiple displacement sensors are connected to the hydraulic cylinders and used for monitoring the extension lengths of piston rods of the hydraulic cylinders; each displacement sensor is connected with an upper computer, the extension length of the piston rod of the hydraulic cylinder is transmitted to the upper computer, and the upper computer calculates the stroke margin of the hydraulic cylinder based on the extension length of the piston rod of the hydraulic cylinder; the upper computer is connected with the display and transmits the stroke margin of the hydraulic cylinder to the display for displaying; the displayer gives an alarm for the hydraulic cylinder with the stroke margin smaller than the safety margin threshold value.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft strength ground tests, and specifically relates to a monitoring system for the loading stroke margin of a hydraulic cylinder in an aircraft strength ground test. Background Art

[0002] In aircraft strength ground tests, force-controlled hydraulic cylinders are used for loading. The stroke of a hydraulic cylinder refers to the maximum extension of its piston rod, usually 500 mm, 1000 mm, etc. The stroke margin of a hydraulic cylinder refers to the ratio of the remaining extension of its piston rod to the maximum extension.

[0003] In aircraft strength ground tests, to ensure the accuracy and safety of load loading, it is usually specified that the stroke margin of the hydraulic cylinder cannot be less than 10%. When the stroke margin of the hydraulic cylinder is reached, the test needs to be stopped in a timely manner. Currently, this is mostly judged by visual observation, which requires manual on-site monitoring. In the case of a large number of hydraulic cylinders, it will consume a lot of labor and is prone to omissions, posing a greater safety hazard.

[0004] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0005] The purpose of this application is to provide a monitoring system for the loading stroke margin of a hydraulic cylinder in an aircraft strength ground test to overcome or mitigate at least one aspect of the known technical defects.

[0006] The technical solution of this application is as follows:

[0007] A monitoring system for the loading stroke margin of a hydraulic cylinder in an aircraft strength ground test includes displacement sensors, a host computer, and a display;

[0008] There are multiple displacement sensors, which are connected to each hydraulic cylinder to monitor the extension length of the piston rod of the hydraulic cylinder;

[0009] Each displacement sensor is connected to the host computer to transmit the extension length of the piston rod of the hydraulic cylinder to the host computer. The host computer calculates the stroke margin of the hydraulic cylinder based on the extension length of the piston rod of the hydraulic cylinder. Specifically:

[0010]

[0011] Among them,

[0012] M.S. is the stroke margin of the hydraulic cylinder, and △L x is the monitored value of the extension length of the piston rod of the hydraulic cylinder, and L x is the stroke of the hydraulic cylinder;

[0013] The host computer is connected to the display to transmit the stroke margin of the hydraulic cylinder to the display for display;

[0014] The display alarms for hydraulic cylinders with a stroke margin less than the safety margin threshold.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, the displacement sensor adopts an infrared displacement measuring device, including an infrared emission end and an infrared reflection end. Among them, the infrared emission end is connected to the cylinder block of the hydraulic cylinder, and the infrared reflection end is connected to the piston rod of the hydraulic cylinder.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, the infrared emission end of the infrared displacement measuring device is connected to the cylinder block of the hydraulic cylinder by a strong magnetic base, and the infrared reflection end adopts a light-shielding disc and is sleeved on the piston rod of the hydraulic cylinder.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, the display alarms for hydraulic cylinders with a stroke margin less than the safety margin threshold. Specifically, it can alarm through color alarm, voice alarm or lighting an abnormal button.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, the safety margin threshold is taken as 10%.

[0019] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, the loading point number of the hydraulic cylinder is simultaneously displayed on the display. Clicking on the loading point number can pop up and display the spatial installation point coordinates of the hydraulic cylinder, the piston rod extension length, the hydraulic cylinder stroke, and the hydraulic cylinder number.

[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, start and stop buttons are set on the display. When the start button is triggered, a test start instruction can be sent to the aircraft strength ground test system through the host computer, enabling the aircraft strength ground test system to start running and each hydraulic cylinder to start loading the aircraft. When the stop button is triggered, a test stop instruction can be sent to the aircraft strength ground test system through the host computer, enabling the aircraft strength ground test system to stop running and each hydraulic cylinder to stop loading the aircraft.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, a wire-pulling type displacement sensor is further included;

[0022] There are multiple wire-pulling type displacement sensors, which are connected to the aircraft structure to monitor the deformation of the aircraft structure;

[0023] Each wire-pulling displacement sensor is connected to the host computer, and transmits the deformation condition of the aircraft structure to the host computer. The host computer simulates and calculates the stroke margin of the hydraulic cylinder based on the deformation condition of the aircraft structure;

[0024] The host computer compares the stroke margin calculated based on the extended length of the piston rod of the hydraulic cylinder with the stroke margin simulated and calculated based on the deformation condition of the aircraft structure, and uses the smaller stroke margin as the stroke margin of the hydraulic cylinder, and transmits it to the display.

[0025] The present application has at least the following beneficial technical effects:

[0026] A monitoring system for the stroke margin of a hydraulic cylinder in an aircraft strength ground test is provided. The design is to monitor the extended length of the piston rod of the hydraulic cylinder with displacement sensors provided on each hydraulic cylinder, and then the host computer calculates the stroke margin of the hydraulic cylinder in real time and transmits it to the display for visual display, and can give an alarm when the stroke margin is less than the safety margin threshold, which can facilitate technicians to make on-site decisions in a timely manner, save labor, and ensure the safety of the test. Description of the Drawings

[0027] Figure 1 is a schematic diagram of a monitoring system for the stroke margin of a hydraulic cylinder in an aircraft strength ground test provided by an embodiment of the present application;

[0028] Figure 2 is a schematic diagram of the installation of a displacement sensor on a hydraulic cylinder provided by an embodiment of the present application;

[0029] Figure 3 is a schematic diagram of the display interface of a display provided by an embodiment of the present application.

[0030] For better illustration of this embodiment, some contents in the drawings are omitted, enlarged or reduced, and are only used for exemplary illustration and should not be construed as a limitation to the present application. Detailed Embodiment

[0031] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application and are not a limitation to the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The term "including" used in the description of this application means that the concept appearing before this word encompasses the concepts listed after this word and their equivalents, without excluding other related concepts.

[0033] In addition, the words indicating directions used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words such as "installed" and "connected" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable 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. Those skilled in the art can understand their specific meanings in this application according to the specific circumstances.

[0034] An aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, as Figure 1 shown, includes a displacement sensor, a host computer, and a display.

[0035] There are multiple displacement sensors, which are connected to each hydraulic cylinder to monitor the extended length of the piston rod of the hydraulic cylinder.

[0036] The displacement sensor adopts an infrared displacement measurement device, which includes an infrared emission end and an infrared reflection end. Among them, the infrared emission end is connected to the cylinder body of the hydraulic cylinder, and the infrared reflection end is connected to the piston rod of the hydraulic cylinder.

[0037] The acquisition rate of the infrared displacement measurement device is one frame per 0.01 s. The infrared emission end is connected to the cylinder body of the hydraulic cylinder by using a strong magnetic base, and the infrared reflection end adopts a light-shielding disc, which is sleeved on the piston rod of the hydraulic cylinder, as Figure 2 shown.

[0038] Each displacement sensor is connected to the host computer. Specifically, it can be connected to the host computer through a fieldbus to transmit the extended length of the piston rod of the hydraulic cylinder to the host computer. The host computer calculates the stroke margin of the hydraulic cylinder based on the extended length of the piston rod of the hydraulic cylinder.

[0039]

[0040] Among them,

[0041] M.S. is the stroke margin of the hydraulic cylinder, △L x is the monitored value of the extended length of the piston rod of the hydraulic cylinder, and L x is the stroke of the hydraulic cylinder.

[0042] The host computer is connected to the display, specifically through the fieldbus to connect to the display, and the stroke margin of the hydraulic cylinder is transmitted to the display for display.

[0043] The display alarms for hydraulic cylinders with a stroke margin less than the safety margin threshold. Specifically, it can alarm through color, voice, or lighting an abnormal button. The safety margin threshold can specifically be set to 10%.

[0044] The loading point number of the hydraulic cylinder is also displayed on the display. Clicking on the loading point number can pop up the coordinates of the spatial installation point of the hydraulic cylinder, the extended length of the piston rod, the stroke of the hydraulic cylinder, the hydraulic cylinder number, etc.

[0045] Start and stop buttons are set on the display. When the start button is triggered, the host computer can send a test start command to the aircraft strength ground test system, enabling the aircraft strength ground test system to start running, and each hydraulic cylinder starts to load the aircraft. When the stop button is triggered, the host computer can send a test stop command to the aircraft strength ground test system, enabling the aircraft strength ground test system to stop running, and each hydraulic cylinder stops loading the aircraft, facilitating the timely control of the test start and stop.

[0046] In a specific example, the display interface design of a display is as Figure 3 shown.

[0047] The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system disclosed in the above embodiment is designed to monitor the extended length of the piston rod of the hydraulic cylinder with displacement sensors set on each hydraulic cylinder, and then the host computer calculates the stroke margin of the hydraulic cylinder in real time and transmits it to the display for visual display. Moreover, it can alarm when the stroke margin is less than the safety margin threshold, which can facilitate technicians to make on-site decisions in a timely manner, save labor, and ensure the safety of the test.

[0048] It can be understood that there is a risk of failure of the displacement sensor. In order to further ensure the safety of the test, the aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system disclosed in the above embodiment includes multiple wire-type displacement sensors connected to the aircraft structure to monitor the deformation of the aircraft structure.

[0049] Each wire-type displacement sensor is connected to the host computer, specifically through the fieldbus to connect to the host computer, and transmits the deformation situation of the aircraft structure to the host computer. The host computer simulates and calculates the stroke margin of the hydraulic cylinder based on the deformation situation of the aircraft structure and corrects the stroke margin of the hydraulic cylinder in real time.

[0050] The host computer can be built with a simulation model of the aircraft strength ground test system. This simulation model takes the deformation of the aircraft structure as the input, calculates the extended length and stroke margin of the hydraulic cylinder piston rod according to the force control factor of the hydraulic cylinder, and then outputs the stroke margin of the hydraulic cylinder.

[0051] The host computer compares the deformation of the aircraft structure with the simulation calculation results, and corrects the stroke margin of the hydraulic cylinder in real time. The host computer compares the stroke margin calculated based on the extended length of the hydraulic cylinder piston rod with the stroke margin obtained by simulating and calculating based on the deformation of the aircraft structure, and takes the smaller stroke margin as the stroke margin of the hydraulic cylinder, and transmits it to the display, so as to realize the double-margin monitoring of the hydraulic cylinder stroke and ensure the safety of the test.

[0052] The wire-pulling displacement sensor can also be replaced by a strain gauge, and the strain gauge is pasted on the aircraft structure.

[0053] In addition, those skilled in the art should also be able to realize that each function of the aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software or a combination of the two. To clearly illustrate the interchangeability of hardware and software, in the present application, it is generally described according to functions. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to exceed the scope of the present application.

[0054] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. An aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system, characterized in that: Including displacement sensor, host computer and display; There are multiple displacement sensors connected to each hydraulic cylinder to monitor the extension length of the hydraulic cylinder piston rod; Each displacement sensor is connected to the host computer and transmits the extension length of the hydraulic cylinder piston rod to the host computer. The host computer calculates the stroke margin of the hydraulic cylinder based on the extension length of the hydraulic cylinder piston rod, specifically: in, MS is the stroke margin of the hydraulic cylinder, △L x is the monitoring value of the extension length of the hydraulic cylinder piston rod, L x is the stroke of the hydraulic cylinder; The upper computer is connected to the display and transmits the stroke margin of the hydraulic cylinder to the display for display; The display will alarm for hydraulic cylinders whose stroke margin is less than the safety margin threshold.

2. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 1 is characterized in that: The displacement sensor adopts an infrared displacement measuring device, including an infrared emitting end and an infrared reflecting end, wherein the infrared emitting end is connected to the cylinder body of the hydraulic cylinder, and the infrared reflecting end is connected to the piston rod of the hydraulic cylinder.

3. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 2 is characterized in that: The infrared emitting end of the infrared displacement measuring device is connected to the cylinder body of the hydraulic cylinder by using a strong magnetic base, and the infrared reflecting end adopts a light-shielding disk and is sleeved on the piston rod of the hydraulic cylinder.

4. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 3 is characterized in that: The display will alarm for hydraulic cylinders whose stroke margin is less than the safety margin threshold. The alarm can be made through color alarm, voice alarm or lighting of abnormal button.

5. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 4 is characterized in that: The safety margin threshold is 10%.

6. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 5 is characterized in that: The loading point number of the hydraulic cylinder is also displayed on the monitor. Clicking the loading point number will pop up a display showing the spatial installation point coordinates of the hydraulic cylinder, the piston rod extension length, the hydraulic cylinder stroke, and the hydraulic cylinder number.

7. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 6 is characterized in that: Start and stop buttons are set on the display. When the start button is triggered, the test start command can be sent to the aircraft strength ground test system through the host computer, so that the aircraft strength ground test system starts to run, and each hydraulic cylinder starts to load the aircraft. When the stop button is triggered, the test stop command can be sent to the aircraft strength ground test system through the host computer, so that the aircraft strength ground test system stops running, and each hydraulic cylinder stops loading the aircraft.

8. The aircraft strength ground test hydraulic cylinder loading stroke margin monitoring system according to claim 7 is characterized in that: Also included is a draw-wire displacement sensor; There are multiple wire-type displacement sensors connected to the aircraft structure to monitor the deformation of the aircraft structure; Each wire-type displacement sensor is connected to the host computer to transmit the deformation of the aircraft structure to the host computer, and the host computer simulates and calculates the stroke margin of the hydraulic cylinder based on the deformation of the aircraft structure; The upper computer compares the stroke margin calculated based on the extension length of the hydraulic cylinder piston rod and the stroke margin calculated based on the deformation simulation of the aircraft structure, and uses the smaller stroke margin as the stroke margin of the hydraulic cylinder and transmits it to the display.

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