Visual positioning static load test tool and method moving along with airfoil deformation

Abstract

The invention provides a visual positioning static load test tool and method moving along with airfoil deformation. The visual positioning static load test tool comprises a deformation airfoil, a load distribution device, a hydraulic actuating device, a travelling crane tool and a visual positioning device. The load distribution device is arranged between the lower portion of the hydraulic actuating device and the upper portion of the deformed airfoil, the top end of the load distribution device is connected with the hydraulic actuating device, the tail end of the load distribution device is connected with the deformed airfoil, and the traveling tool is arranged above the hydraulic actuating device. The visual positioning device and the hydraulic actuating device are fixedly installed through a plurality of fasteners, and the visual positioning device is connected with the hydraulic actuating device through a tool. According to the aerodynamic force follow-up loading requirement of the airfoil of the morphing aircraft, a mode of loading the motion of the morphing airfoil through visual positioning tracking is designed, the motion trail of the morphing airfoil is calculated through visual positioning, and the follow-up trail of the loading device is given; the problem that in the prior art, a load test tool cannot meet the requirement for applying load in the airfoil unfolding dynamic process is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of mechanical environmental testing, and in particular to a visual positioning static load testing tool and method that follows the deformation movement of an airfoil. Background Art

[0002] With the rapid development of aerospace technology, the performance requirements of new aircraft are increasing, and their flight airspace and speed range are constantly expanding. In order to meet these requirements, morphing wings have emerged as an innovative wing design, which can adjust the wing shape according to different flight conditions, thereby significantly improving the performance of the aircraft. However, this high-performance morphing wing also faces a series of technical challenges in the design and application process.

[0003] During the design and development of the deformable wing, its structural integrity and working reliability must be strictly evaluated. This is usually achieved through mechanical environmental tests such as static loads and dynamic loads. Traditional mechanical environmental test methods often use the bending moment equivalence principle to simulate the aerodynamic loads on the wing when it is deployed through multi-point concentrated loading. However, for deformable wing surfaces, since they involve aerial deployment actions, traditional test methods cannot meet the requirements of applying loads during the movement and deformation of the wing surface.

[0004] Most existing load test fixtures use a fixed loading method and cannot perform dynamic loading following the deformation movement of the wing surface. This results in the inability to accurately simulate the aerodynamic loads on the deformed wing surface during actual flight during the test, thus affecting the accuracy and reliability of the test results. Therefore, it is necessary to develop a new type of load test fixture and test method to achieve dynamic loading of the deformed wing surface during the deployment movement.

[0005] In addition, the mechanical environmental test of the deformable wing surface also needs to meet the environmental requirements of the product. This requires that the test fixture not only has sufficient strength and rigidity to withstand various loads during the test, but also has good adaptability and flexibility to adapt to various deformations and motion states of the deformable wing surface. Traditional test fixtures often find it difficult to meet these requirements at the same time, so innovation and improvement are needed.

[0006] A patent document with publication number CN104677744A discloses a static loading test device for a wing, which consists of a lifting platform, a load-bearing soft sling, and a wrapping belt. The wing load is simulated by a certain amount of weights, and the load-bearing soft slings and the wrapping belts of different lengths are connected to the corresponding loading points of the wing. The lifting platform is pulled to move by a transmission mechanism composed of a motor, a reducer, a drum mechanism, a steel wire rope, etc. However, this design does not meet the test requirements of applying loads during the movement and deformation process of the wing.

[0007] Therefore, it is necessary to propose a new technical solution to improve the above technical problems. Summary of the invention

[0008] In view of the defects in the prior art, the object of the present invention is to provide a visual positioning static load test tool and method that follows the deformation movement of the wing surface.

[0009] According to the present invention, a visual positioning static load test tool that follows the deformation movement of the wing surface includes a deforming wing surface, a load distribution device, a hydraulic actuation device, a driving tool and a visual positioning device;

[0010] The deformable airfoil is assembled in a fixed test bench, and a deformation servo system inside the test bench drives the deformable airfoil to rotate in a plane, so as to unfold and lock the airfoil at any angle;

[0011] The load distribution device is arranged between the bottom of the hydraulic actuating device and the top of the deformable airfoil, and decomposes the total pulling force generated by the hydraulic actuating device into several component forces acting on the deformable airfoil;

[0012] The crane tooling is arranged above the hydraulic actuating device and is fixedly connected to the hydraulic actuating device;

[0013] The visual positioning device is connected to the hydraulic actuating device to perform real-time positioning of the positioning points on the deformable wing surface, and calculates the movement trajectory of the deformable wing through a computer to control the driving vehicle to follow the movement of the deformable wing.

[0014] Preferably, the deformable airfoil comprises a rotating shaft, a transmission rod hole and a support rod;

[0015] The deformable airfoil is connected to a deformation servo system inside the test bench through a transmission rod hole, and the deformation servo system drives the deformable airfoil to rotate around a rotation axis in a plane.

[0016] Preferably, a plurality of load loading points are arranged on the deformable airfoil, and the load loading points are connected to the load distribution device by fasteners, so that the deformable airfoil is subjected to a normal simulated aerodynamic load.

[0017] Preferably, a plurality of visual positioning points on the deformable wing surface are marked with preset shapes, and the visual positioning device performs identification and positioning through the preset shape marks.

[0018] Preferably, the load distribution device includes a primary stage, a secondary stage, a tertiary stage and a connecting device, forming a symmetrically distributed structure, and evenly decomposing the total pulling force generated by the hydraulic actuating device into multiple component forces acting on the deformable wing surface.

[0019] Preferably, a plurality of force sensors are provided on the three-stage loading rods in the load distribution device for monitoring the changes of the forces acting on the loading rods in real time.

[0020] Preferably, the hydraulic actuating device pulls the load distribution device and the deformable wing surface through the movement of the oil cylinder, so as to simulate the time-varying aerodynamic loads on the deformable wing under different ballistic conditions.

[0021] Preferably, a total load force sensor is provided on the hydraulic actuating device for measuring the total pulling force generated by the hydraulic actuating device.

[0022] Preferably, a level gauge is provided on the traction rope of the hydraulic actuating device for real-time monitoring of the inclination of the traction rope, and the direction of the load tension is always perpendicular to the deformed wing surface.

[0023] The present invention also provides a test method for a visual positioning static load test tool that follows the deformation movement of an airfoil. The method uses the visual positioning static load test tool that follows the deformation movement of an airfoil. The method comprises the following steps:

[0024] Step S1: determine the test station, assemble the deformable airfoil to a fixed test bench, and drive the deformable airfoil to rotate to a predetermined angle in a plane through a deformation servo system;

[0025] Step S2: connecting the deformable wing surface, the load distribution device, the hydraulic actuating device, the crane fixture and the visual positioning device;

[0026] Step S3: adjusting the position of the crane tooling, straightening the traction rope of the hydraulic actuating device, and adjusting the movement direction of the load distribution device;

[0027] Step S4: Load the load to the predetermined load step by step through the hydraulic actuator. At the same time, the visual positioning device locates the positioning point on the deformed wing surface in real time, and controls the crane to follow the movement of the deformed wing through the computer until the end of the test.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. According to the requirements of aerodynamic follow-up loading of the wing surface of a deformable aircraft, the present invention designs a method of visual positioning tracking loading of the deformable wing surface movement. The motion trajectory of the deformable wing is calculated in real time by a visual positioning device, and the loading device (driving tooling and hydraulic actuating device) is controlled to follow the trajectory, so as to apply load during the dynamic process of wing surface deployment. This solves the problem that the load test tooling in the prior art cannot meet the requirement of applying load during the dynamic process of wing surface deployment, and provides a new solution for the mechanical environment test of the deformable wing surface.

[0030] 2. The present invention adopts visual positioning technology, which can accurately track the motion trajectory of the deformed wing surface and control the motion of the loading device accordingly, thereby ensuring that the loading device can accurately apply simulated aerodynamic loads to the deformed wing surface, which helps to improve the accuracy of the test and make the test results closer to the aerodynamic load conditions under actual flight conditions;

[0031] 3. The tooling of the present invention adopts an open structure layout, which is convenient for operators to observe the status of the tooling and the deformed wing surface during the test. The structure design of the tooling is stable and can withstand a large load and maintain a stable working state, thereby ensuring the smooth progress of the test;

[0032] 4. The hydraulic actuator in the present invention can be designed according to the specific ballistic load to simulate the aerodynamic load on the wing surface. By accurately controlling the extension and contraction of the hydraulic actuator, it is possible to apply accurate aerodynamic simulation loads to the deformed wing surface. Force sensors are set on the hydraulic actuator and the load distribution device to monitor the total load force and the force on a single loading rod in real time, thereby further improving the loading accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0034] Figure 1 An axonometric view of a visual positioning static load test fixture that follows the wing surface deformation movement provided by the present invention;

[0035] Figure 2 A side view of the load distribution device provided by the present invention;

[0036] Figure 3 This is a top sectional view of the deformable wing provided by the present invention.

[0037] in:

[0038] Deformed airfoil 1 Secondary 22

[0039] Revolving shaft 11 Level 23

[0040] Transmission rod hole 12 Loading rod 24

[0041] Support rod 13 Hydraulic actuator 3

[0042] Load distribution device 2 Driving tooling 4

[0043] Level 21 Visual positioning device 5 DETAILED DESCRIPTION

[0044] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0045] Embodiment 1:

[0046] Reference Figure 1-Figure 3 According to the present invention, a visual positioning static load test tool for following the deformation movement of the wing surface is provided, comprising a deformable wing surface, a load distribution device, a hydraulic actuator, a crane tool and a visual positioning device; the deformable wing surface is assembled in a fixed test bench, and the deformable wing surface is driven to rotate in a plane by a deformation servo system inside the test bench to unfold and lock the wing surface at any angle; the load distribution device is arranged between the bottom of the hydraulic actuator and the top of the deformable wing surface, and the total pulling force generated by the hydraulic actuator is decomposed into several component forces to act on the deformable wing surface; the crane tool is arranged above the hydraulic actuator and fixedly connected to the hydraulic actuator; the visual positioning device is connected to the hydraulic actuator, and the positioning point on the deformable wing surface is positioned in real time, and the movement trajectory of the deformable wing is calculated by a computer to control the crane to follow the movement of the deformable wing.

[0047] The deformable wing surface includes a rotating shaft, a transmission rod hole and a support rod; the deformable wing surface is connected to the deformation servo system inside the test bench through the transmission rod hole, and the deformable wing surface is driven by the deformation servo system to rotate around the rotating shaft in the plane. A number of load loading points are set on the deformable wing surface, and the load loading points are connected to the load distribution device through fasteners. The deformable wing surface is subjected to normal simulated aerodynamic loads. A number of visual positioning points on the deformable wing surface are marked with preset shapes, and the visual positioning device recognizes and locates through the preset shape marks.

[0048] The load distribution device includes a primary stage, a secondary stage, a tertiary stage and a connecting device. The primary stage is connected to the hydraulic actuator, the tertiary stage is connected to the deformable wing surface, and the multiple stages are connected through the connecting device. The load distribution device decomposes the total pulling force generated by the hydraulic actuator into multiple component forces step by step based on the lever principle of a "seesaw", and acts on the loading points on the deformable wing surface. A number of force sensors are arranged on the loading rods of the three stages in the load distribution device to monitor the changes in the force on the loading rods in real time.

[0049] The hydraulic actuator pulls the load distribution device and the deformed wing surface through the movement of the oil cylinder to simulate the time-varying aerodynamic load on the deformed wing under different ballistic conditions. A total load force sensor is provided on the hydraulic actuator to measure the total pulling force generated by the hydraulic actuator. A level is provided on the traction rope of the hydraulic actuator to monitor the inclination of the traction rope in real time. The load pulling direction is always perpendicular to the deformed wing surface.

[0050] The present invention also provides a test method for a visual positioning static load test tool that follows the deformation movement of an airfoil. The method uses the visual positioning static load test tool that follows the deformation movement of an airfoil. The method comprises the following steps:

[0051] Step S1: determine the test station, assemble the deformable airfoil to a fixed test bench, and drive the deformable airfoil to rotate to a predetermined angle in a plane through a deformation servo system;

[0052] Step S2: connecting the deformable wing surface, the load distribution device, the hydraulic actuating device, the crane fixture and the visual positioning device;

[0053] Step S3: adjusting the position of the crane tooling, straightening the traction rope of the hydraulic actuating device, and adjusting the movement direction of the load distribution device;

[0054] Step S4: Load the load to the preset load step by step through the hydraulic actuator, and at the same time, the visual positioning device locates the positioning points on the deformed wing surface in real time, and controls the driving device to follow the deformed wing movement through the computer until the end of the test. The visual positioning device transmits the wing surface image to the computer at intervals of 1S, locates several visual positioning points on the deformed wing surface through the computer vision opencv program, calculates the movement trajectory of the deformed wing surface by comparing the positions of the pixels of the positioning points on the front and back images, plans the driving device to follow the movement trajectory by linear movement, and transmits the movement command to the driving device to follow the movement of the deformed wing.

[0055] Embodiment 2:

[0056] In view of the defects in the prior art, the purpose of the present invention is to provide a visual positioning static load test tool and test method that follows the deformation movement of the wing surface. According to the deforming wing and loading requirements, and through simulation analysis, the specific dimensions of the test device are designed in detail. This device can be used to apply load to the deforming wing surface that is undergoing expansion movement.

[0057] The present invention relates to a visual positioning static load test tool that follows the deformation movement of the wing surface and a method for carrying out a load test using the tool, comprising a deformable wing surface, a load distribution device, a hydraulic actuator, a driving tool and a visual positioning device. The load distribution device is arranged between the bottom of the hydraulic actuator and the top of the deformable wing surface, and the top of the load distribution device is connected to the hydraulic actuator, and the tail of the load distribution device is connected to the deformable wing surface. The driving tool is arranged above the hydraulic actuator and is fixedly installed with the hydraulic actuator through a number of fasteners, and the visual positioning device is connected to the hydraulic actuator through the tool. According to the requirements of the aerodynamic follow-up loading of the wing surface of the deformable aircraft, the present invention designs a method of visual positioning tracking and loading the movement of the deformable wing surface, calculates the movement trajectory of the deformable wing by using visual positioning and gives the tracking trajectory of the loading device, controls the driving to follow the movement of the deformable wing, solves the problem that the load test tool in the prior art cannot meet the requirements of applying loads in the dynamic process of the wing surface unfolding, and meets the requirements of simulated flight aerodynamic load verification test under the conditions of the deformation wing surface movement, and has the technical advantages of stable structure, accurate simulation of the deformation dynamic aerodynamic environment, and easy observation of the test process.

[0058] According to the present invention, a visual positioning static load test tool that follows the deformation movement of the airfoil includes a deformed airfoil, a load distribution device, a hydraulic actuation device, a driving tool and a visual positioning device;

[0059] The deformable airfoil is assembled in a fixed test bench, and a deformation servo system inside the test bench drives the deformable airfoil to rotate in a plane, so as to realize the deployment and locking of the airfoil at any angle;

[0060] The load distribution device is arranged between the bottom of the hydraulic actuating device and the top of the deformable airfoil, and the top end of the load distribution device is connected to the hydraulic actuating device, and the tail end of the load distribution device is connected to the deformable airfoil, so as to decompose the total pulling force generated by the hydraulic actuating device into several forces;

[0061] The crane tooling is arranged above the hydraulic actuating device and is fixedly mounted with the hydraulic actuating device through a number of fasteners; the crane tooling is a part of the crane and is driven to move in a plane under the action of the crane movement;

[0062] The visual positioning device is connected to the hydraulic actuator through the tooling. The visual positioning device performs real-time positioning of several positioning points on the deformable wing during the unfolding deformation movement, and is wirelessly connected to the computer on the vehicle. The computer calculates the movement trajectory of the deformable wing and gives the vehicle a following trajectory, thereby controlling the vehicle to follow the movement of the deformable wing.

[0063] Preferably, the deformable airfoil comprises a rotating shaft, a transmission rod hole, and a support rod; the deformable airfoil is assembled to a fixed prototype, and a deformation servo system is installed inside the prototype to drive the deformable airfoil to rotate around the rotating shaft in a plane through the transmission rod hole, so as to realize the unfolding and locking of the airfoil at any angle;

[0064] Preferably, the deformable airfoil is perforated to lay load loading points, and the load loading points are connected to the load distribution device by fasteners, so that the deformable airfoil is subjected to normal simulated aerodynamic loads.

[0065] Preferably, the plurality of visual positioning points on the deformable wing surface are marked in the shape of “X”, “*”, triangle, circle, etc., so as to facilitate accurate positioning by the visual positioning device.

[0066] Preferably, the load distribution device includes a primary stage, a secondary stage, a tertiary stage and corresponding connecting devices; a pair of secondary stages are symmetrically arranged on the left and right sides below the primary stage, and their connection and structural forms are completely symmetrical; a pair of tertiary stages are symmetrically arranged on the left and right sides below the secondary stage, and their connection and structural forms are completely symmetrical; three through holes are opened at both ends and in the middle of the primary stage, and the center lines of the through holes are on the same axis; three through holes are opened at both ends and in the middle of the secondary stage, and the center lines of the through holes are on the same axis; three through holes are opened at both ends and in the middle of the tertiary stage, and the center lines of the through holes are on the same axis; the force distribution holes at both ends of the primary stage are connected to the secondary stage through a connecting device, and the force distribution holes at both ends of the secondary stage are connected to the tertiary stage through a connecting device, so as to realize the overall connection of the primary stage, the secondary stage and the tertiary stage.

[0067] Preferably, a plurality of force sensors are provided on the three-stage loading rods in the load distribution device for measuring the forces acting on the loading rods.

[0068] Preferably, the hydraulic actuating device pulls the load distribution device and the deformable wing surface through the movement of the oil cylinder, so as to simulate the time-varying aerodynamic loads on the deformable wing under different ballistic conditions.

[0069] Preferably, the hydraulic actuating device is provided with a force sensor for measuring the total load force.

[0070] Preferably, a level is provided on the traction rope on the hydraulic actuating device for measuring the inclination of the traction rope.

[0071] Preferably, the deformation wing motion picture collected by the visual positioning device reads the coordinates and changes of the positioning points in the deformation wing motion process through a program based on a computer vision library.

[0072] According to a second aspect of the present invention, a test method for applying the visual positioning static load test fixture that follows the airfoil deformation movement is provided, comprising the following steps:

[0073] Determine the test station, assemble the deformable airfoil to a fixed test bench, and drive the deformable airfoil to rotate in a plane around the rotation axis through a deformation servo system to simulate the unfolding motion of the deformable airfoil;

[0074] Connect the deformable wing surface, the load distribution device, the hydraulic actuating device, the crane fixture and the visual positioning device in sequence;

[0075] The position of the crane tooling is adjusted to be directly above the load distribution device, the traction rope in the hydraulic actuating device is straightened, the movement direction of the load distribution device is adjusted vertically upward, the gap in the load distribution device is eliminated, and a stable working state is ensured.

[0076] The hydraulic actuator is first extended to the maximum extension position, and then slowly retracted to a tension pre-tightened state, so as to reduce the impact load generated when the hydraulic actuator starts working to a minimum.

[0077] The hydraulic actuating device is loaded, measured and recorded step by step with 10% of the design load as one level until 100% of the design load.

[0078] The visual positioning device is used to perform real-time positioning of several positioning points on the deformable wing during the unfolding deformation movement, and is wirelessly connected to the computer on the vehicle. The computer calculates the movement trajectory of the deformable wing and gives the vehicle a following trajectory, and controls the vehicle to follow the movement of the deformable wing until the end of the test.

[0079] Reference Figure 1-Figure 3 The present invention provides a case of using the visual positioning static load test tooling that follows the wing surface deformation movement to carry out a static test of a deformed wing, comprising a deformed wing surface, a load distribution device, a hydraulic actuation device, a driving tooling and a visual positioning device;

[0080] Determine the test station, assemble the deformable wing surface and the deformable servo system in a fixed test bench, and connect the external CNC, power supply, test cables and other equipment. First, no load is applied to the deformable wing surface, and the deformable wing surface is only driven by the deformable servo system to rotate in the plane to complete the deformable wing surface motion test.

[0081] The deformable wing surface is 20mm away from the outer edge and 8 evenly distributed load loading points are laid with a spacing of 200mm. The load loading points are connected to the load distribution device through bolts, nuts and other fasteners, so that the deformable wing surface is subjected to the simulated aerodynamic load in the normal upward direction. Three visual positioning points are also set on the deformable wing surface and marked in the shape of "X" to facilitate accurate positioning of the visual positioning device.

[0082] After completing the deformation wing motion test, the load distribution device and subsequent devices will be installed.

[0083] The load distribution device is arranged between the bottom of the hydraulic actuating device and the top of the deformed wing surface, and the top of the load distribution device is connected to the hydraulic actuating device. The hydraulic actuating device pulls the load distribution device and the deformed wing surface through the movement of the oil cylinder, which can simulate the time-varying aerodynamic load on the deformed wing under different ballistic conditions, and the total load force is F. The hydraulic actuating device is provided with a force sensor for real-time measurement of the total load force F. The tail end of the load distribution device is connected to the deformed wing surface and is perpendicular to the wing surface, and the total pulling force F generated by the hydraulic actuating device is decomposed into 8 component forces F1, F2, ..., F8, etc. The size of the component force depends on the structural shape of the load distribution device. There are 8 corresponding force sensors on the three-stage loading rod in the load distribution device, which are used to measure the force on the loading rod and monitor it in real time. The hydraulic actuating device is provided with a level on the traction rope of the load distribution device, which is used to measure the inclination of the traction rope and control the direction of the load pulling force to always act on the normal direction of the wing surface.

[0084] Adjust the position of the crane tooling to be directly above the load distribution device, straighten the traction rope in the hydraulic actuator, adjust the movement direction of the load distribution device vertically upward, eliminate the gap in the load distribution device, and ensure stable working state. Extend the hydraulic actuator to the maximum extension position first, and then slowly retract it to the stretched pre-tightened state, so as to reduce the impact load generated when the hydraulic actuator starts working to the minimum.

[0085] After the test officially starts, the deformation movement is controlled to the specified angle through the deformation servo system. The hydraulic actuator is loaded, measured and recorded step by step with 10% of the design load as one level until 100% of the design load. The load is maintained for at least 30 seconds and photos are taken, and then the load is unloaded to zero.

[0086] During the test, the visual positioning device locates the positioning points on the deformable wing in real time during the unfolding and deformation movement, and establishes a wireless communication connection with the computer on the vehicle. The computer calculates the movement trajectory of the deformable wing and gives the vehicle a following trajectory, controlling the vehicle to follow the movement of the deformable wing until the end of the test.

[0087] After applying the simulated aerodynamic force, the deformation servo system was cycled for 3 cycles per test.

[0088] According to the requirements of aerodynamic follow-up loading of the wing surface of a deformable aircraft, the present invention designs a method of visual positioning tracking and loading the movement of the deformed wing surface, uses visual positioning to calculate the movement trajectory of the deformed wing and gives the tracking trajectory of the loading device, controls the driving vehicle to follow the movement of the deformed wing, solves the problem that the load test tooling in the prior art cannot meet the demand for applying loads during the dynamic process of wing surface expansion. The tooling adopts an open structure layout, which is convenient for operation and test observation, and has the advantages of stable structure and accurate loading. The hydraulic actuator in the present invention can be designed according to the specific ballistic load to simulate the aerodynamic load on the wing surface, so that the load on the deformed wing surface is consistent with the actual aerodynamic load environment, and has good loading accuracy. The present invention can set force sensors on both the load distribution device and the hydraulic actuator, and can set a level on the traction rope, which meets the requirements of monitoring the total load force, the force on a single loading rod and the load inclination angle during the test.

[0089] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0090] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0091] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A visual positioning static load test tool that follows the deformation movement of the wing surface, characterized in that: It includes a deformable wing surface, a load distribution device, a hydraulic actuation device, a crane tooling and a visual positioning device; The deformable airfoil is assembled in a fixed test bench, and a deformation servo system inside the test bench drives the deformable airfoil to rotate in a plane, so as to unfold and lock the airfoil at any angle; The load distribution device is arranged between the bottom of the hydraulic actuating device and the top of the deformable airfoil, and decomposes the total pulling force generated by the hydraulic actuating device into several component forces acting on the deformable airfoil; The crane tooling is arranged above the hydraulic actuating device and is fixedly connected to the hydraulic actuating device; The visual positioning device is connected to the hydraulic actuating device to perform real-time positioning of the positioning points on the deformable wing surface, and calculates the movement trajectory of the deformable wing through a computer to control the driving vehicle to follow the movement of the deformable wing.

2. The visual positioning static load test tool that follows the wing deformation movement according to claim 1 is characterized in that: The deformable airfoil comprises a rotating shaft, a transmission rod hole and a support rod; The deformable airfoil is connected to a deformation servo system inside the test bench through a transmission rod hole, and the deformation servo system drives the deformable airfoil to rotate around a rotation axis in a plane.

3. The visual positioning static load test tool that follows the wing deformation movement according to claim 1 is characterized in that: The deformable wing surface is provided with a plurality of load loading points, and the load loading points are connected to the load distribution device through fasteners, so that the deformable wing surface is subjected to a normal simulated aerodynamic load.

4. The visual positioning static load test tool that follows the wing deformation movement according to claim 1 is characterized in that: A plurality of visual positioning points on the deformable wing surface are marked with preset shapes, and the visual positioning device performs identification and positioning through the preset shape marks.

5. The visual positioning static load test tool that follows the wing deformation movement according to claim 1 is characterized in that: The load distribution device includes a first stage, a second stage, a third stage and a connecting device. The first stage is connected to the hydraulic actuator, the third stage is connected to the deformable wing surface, and the multiple stages are connected by the connecting device; the load distribution device decomposes the total pulling force generated by the hydraulic actuator into multiple component forces, and acts on the loading points on the deformable wing surface.

6. The visual positioning static load test tool that follows the wing deformation movement according to claim 5 is characterized in that: A plurality of force sensors are provided on the three-stage loading rods in the load distribution device for real-time monitoring of the changes in the forces acting on the loading rods.

7. The visual positioning static load test tool that follows the wing deformation movement according to claim 1 is characterized in that: The hydraulic actuating device pulls the load distribution device and the deformable wing surface through the movement of the oil cylinder, simulating the time-varying aerodynamic load on the deformable wing under different ballistic conditions.

8. The visual positioning static load test tool that follows the wing deformation movement according to claim 7 is characterized in that: The hydraulic actuating device is provided with a total load force sensor for measuring the total pulling force generated by the hydraulic actuating device.

9. The visual positioning static load test tool that follows the wing deformation movement according to claim 7 is characterized in that: The traction rope of the hydraulic actuating device is provided with a level gauge for real-time monitoring of the inclination of the traction rope, and the direction of the load tension is always perpendicular to the deformed wing surface.

10. A test method for a visual positioning static load test tool that follows the deformation movement of the wing surface, characterized in that: The method uses a visual positioning static load test fixture that follows the airfoil deformation movement as described in any one of claims 1 to 9, and the method comprises the following steps: Step S1: determine the test station, assemble the deformable airfoil to a fixed test bench, and drive the deformable airfoil to rotate to a predetermined angle in a plane through a deformation servo system; Step S2: connecting the deformable wing surface, the load distribution device, the hydraulic actuating device, the crane fixture and the visual positioning device; Step S3: adjusting the position of the crane tooling, straightening the traction rope of the hydraulic actuating device, and adjusting the movement direction of the load distribution device; Step S4: Load the load to the predetermined load step by step through the hydraulic actuator. At the same time, the visual positioning device locates the positioning point on the deformed wing surface in real time, and controls the crane to follow the movement of the deformed wing through the computer until the end of the test.

Images