High-aspect-ratio wing follow-up loading device

Abstract

The invention discloses a high aspect ratio wing follow-up loading device, which comprises a force direction control assembly, a displacement control assembly, a position monitoring assembly and a servo control assembly, and is characterized in that the force direction control assembly comprises a clamping plate, a pull pressure sensor, a connecting rod and a spherical hinge, and the clamping plate is clamped and fixed on a load loading point of a high aspect ratio wing; the connecting rod is connected with the tension-pressure sensor and the spherical hinge; the displacement control assembly comprises a connecting ring, an electric servo cylinder and a lead screw linear sliding table. The position monitoring assembly comprises a vertical displacement sensor and a horizontal displacement sensor. And the servo control assembly performs movement control on the lead screw linear sliding table according to the displacement detected by the two displacement sensors until a force value displayed by the tension and pressure sensor is a calibration force value, so that follow-up loading of the high-aspect-ratio wing is realized. According to the invention, follow-up loading of the high-aspect-ratio wing can be realized, the requirement on a laboratory site is reduced, and the risk in the test process is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft structure static test, and in particular relates to a large aspect ratio wing follower loading device. Background Art

[0002] The high aspect ratio wing layout can reduce the influence of wingtip vortices during low-speed flight, which is beneficial to reduce induced drag, improve lift-to-drag ratio, thereby reducing fuel consumption and extending flight endurance, and can serve the performance requirements of high-altitude long-duration flight. In order to prevent the occurrence of safety accidents, the physical properties of the wing need to be controlled before the aircraft is put into use. Usually, the lift load on the wing during flight is analyzed by obtaining the load spectrum in the actual flight test. The strain method is used to realize the correspondence between load and strain, and a load calibration test is carried out on the high aspect ratio wing. A load model between the load on the measuring section and the strain signal at the measuring section is established. The load model is used to convert the measured strain time history into the load time history during the flight test.

[0003] The high aspect ratio wing is highly flexible and will deform greatly under the ground load calibration conditions, resulting in inaccurate load acquisition in the ground load calibration test. At present, the main solution to the loading error caused by wing deformation is to use a gantry structure with double actuators to control the load loading and displacement, control the horizontal displacement of the other actuator through the lateral actuator at the top of the gantry, and achieve follow-up loading through hinges and sensors. This loading method has high requirements for the laboratory, requiring the laboratory to have sufficient space to place the gantry and to fix the top actuator. Using this device in a small laboratory may cause experimental risks. Summary of the invention

[0004] The purpose of the present invention is to provide a high aspect ratio wing follower loading device, which can realize the follower loading of the high aspect ratio wing, reduce the requirements for laboratory sites, and reduce the risks in the test process.

[0005] In order to achieve the above-mentioned object, one aspect of the present invention provides a high aspect ratio wing follower loading device, comprising a force direction control component, a displacement control component, a position monitoring component and a servo control component.

[0006] The force direction control component includes a clamping card plate, a tension pressure sensor, a connecting rod, and a ball joint. The clamping card plate is clamped and fixed on the load loading point of the large aspect ratio wing, including an upper clamping card plate arranged above the large aspect ratio wing and a lower clamping card plate arranged below the large aspect ratio wing. The tension pressure sensor is fixed on the lower clamping card plate. The connecting rod is fixed on the lower side of the tension pressure sensor and is used to connect the tension pressure sensor and the ball joint. The direction of the force at the load loading point is consistent with the direction of the tension pressure sensor, and the component force of the tension of the ball joint on the tension pressure sensor along the direction of the tension pressure sensor is the force value displayed by the tension pressure sensor.

[0007] The displacement control assembly includes a connecting ring, an electric servo cylinder and a lead screw linear slide, wherein the connecting ring is fixed to the lower side of the ball joint and is used to connect the ball joint and the electric servo cylinder, the electric servo cylinder is fixed to the lower side of the connecting ring and is used to bend the large aspect ratio wing downward by contraction and pulling, and the lead screw linear slide is connected to the electric servo cylinder and is used to control the horizontal displacement of the electric servo cylinder;

[0008] The position monitoring component includes a vertical displacement sensor and a horizontal displacement sensor, the vertical displacement sensor is used to detect the vertical displacement caused by the contraction of the electric servo cylinder, and the horizontal displacement sensor is used to detect the horizontal displacement of the electric servo cylinder controlled by the lead screw linear slide;

[0009] The servo control component is used to control the movement of the lead screw linear slide according to the vertical displacement detected by the vertical displacement sensor and the horizontal displacement detected by the horizontal displacement sensor until the force value displayed by the tension and pressure sensor is the calibrated force value, thereby realizing the follow-up loading of the large aspect ratio wing.

[0010] Preferably, the servo control component controls the movement of the lead screw linear slide, and the vertical displacement detected by the vertical displacement sensor and the horizontal displacement detected by the horizontal displacement sensor satisfy the following formula:

[0011] (xX) 2 +(yY) 2 =X 2 +Y 2 ,

[0012] Among them, x is the horizontal displacement detected by the horizontal displacement sensor, y is the vertical displacement detected by the vertical displacement sensor, X is the distance between the load loading point of the high aspect ratio wing and the wing root, and Y is the distance between the high aspect ratio wing and the bottom of the ball joint.

[0013] Preferably, the clamping card further comprises:

[0014] A plurality of wooden blocks are arranged between the upper clamping plate and the lower clamping plate and the surface of the high aspect ratio wing, and each wooden block matches the surface of the high aspect ratio wing;

[0015] The connecting rod is connected with the upper clamping plate and the lower clamping plate, so that the upper clamping plate and the lower clamping plate clamp the large aspect ratio wing through the multiple wooden blocks.

[0016] The high aspect ratio wing follower loading device according to the above aspects of the present invention can realize the follower loading of the high aspect ratio wing, reduce the requirements for laboratory sites, and reduce the risks in the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solution of the present invention, the following briefly introduces the drawings used in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work:

[0018] Figure 1 2 is a schematic structural diagram of a high aspect ratio wing follower loading device according to an embodiment of the present invention;

[0019] Figure 2 is a schematic structural diagram of a force direction control assembly according to an embodiment of the present invention;

[0020] Figure 3 is a schematic structural diagram of a displacement control assembly according to an embodiment of the present invention;

[0021] Figure 4 It is a schematic diagram of the principle of controlling displacement of a high aspect ratio wing follower loading device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] An embodiment of the present invention provides a high aspect ratio wing follower loading device for a load calibration test of a high aspect ratio wing. The high aspect ratio wing follower loading device of the embodiment of the present invention comprises a force direction control component, a displacement control component, a position monitoring component and a servo control component.

[0024] like Figure 1 to Figure 4As shown, the force direction control assembly 2 is used to adjust the direction of the force applied to the load-loading section of the high aspect ratio wing 1. The force direction control assembly 2 is fixed to the load-loading section of the high aspect ratio wing 1, and includes a clamping plate 6, a tension pressure sensor 7, a connecting rod 8, and a ball joint 9.

[0025] The clamping card plate 6 is clamped and fixed on the load loading point of the high aspect ratio wing 1, and the clamping card plate 6 includes: an upper clamping card plate, which is arranged above the high aspect ratio wing 1; a lower clamping card plate, which is arranged below the high aspect ratio wing 1; a plurality of wooden blocks, which are arranged between the upper clamping card plate and the lower clamping card plate and the surface of the high aspect ratio wing 1, and each wooden block matches the surface of the high aspect ratio wing 1; a connecting rod, which is connected to the upper clamping card plate and the lower clamping card plate at the same time, and the upper clamping card plate and the lower clamping card plate are clamped to the high aspect ratio wing 1 through the wooden blocks through nuts.

[0026] The tension pressure sensor 7 is fixed on the clamping card plate 6, and is connected to the clamping lower card plate of the clamping card plate 6 through a nut. Through control, the direction of the force applied to the load loading section of the large aspect ratio wing 1 is consistent with the direction of the tension pressure sensor 7. The connecting rod 8 is fixed on the lower side of the tension pressure sensor 7, and is used to connect the tension pressure sensor 7 with the ball joint 9. The ball joint 9 is connected to the tension pressure sensor 7 through the connecting rod 8, and the component force of the tension of the ball joint 9 on the tension pressure sensor 7 along the direction of the tension pressure sensor 7 is the indication value of the tension pressure sensor 7.

[0027] As described above, the force direction control assembly 2 is fixed to the high aspect ratio wing 1 through the clamping plate 6, the clamping plate 6 is connected to the tension pressure sensor 7 through a nut, the tension pressure sensor 7 is threadedly connected to the ball joint 9 through the connecting rod 8. When loading, the direction of the force at the wing load loading point is consistent with the direction of the tension pressure sensor 7. Through the connecting rod 8, the direction of the force is consistent with the component force of the ball joint 9 in the direction of the connecting rod 8, and the force value displayed by the tension pressure sensor 7 is the calibrated force value.

[0028] The displacement control assembly 3 is used to control the displacement of the force direction control assembly 2. The displacement control assembly 3 includes a connecting ring 10, an electric servo cylinder 11, and a lead screw linear slide 12. The connecting ring 10 is fixed to the lower side of the ball joint 9, connected to the ball joint 9 through a flange, and used to connect the ball joint 9 and the electric servo cylinder 11. The electric servo cylinder 11 is fixed to the lower side of the connecting ring 10, connected to the connecting ring 10 through a thread, and used to bend the high aspect ratio wing 1 downward by contraction. The lead screw linear slide 12 is fixed to the ground, and fixedly connected to the electric servo cylinder 11 through screws, and used to control the movement of the electric servo cylinder 11 in the horizontal direction, thereby realizing the displacement of the force direction control assembly 2 in the wingspan direction parallel to the high aspect ratio wing 1.

[0029] The position monitoring assembly is used to monitor the position change of the wing load loading point, and includes a vertical displacement sensor 13 and a horizontal displacement sensor 14. The vertical displacement sensor 13 is used to detect the displacement in the vertical direction, and has a first end and a second end, the first end is connected to the base of the electric servo cylinder 11, and the second end is connected to the connecting ring 10. The horizontal displacement sensor 14 is arranged on the screw linear slide 12, and is used to detect the horizontal displacement of the electric servo cylinder 11 under the control of the screw linear slide 12.

[0030] The servo control component is used to control the displacement control component 3 to adjust the horizontal and vertical displacements of the force direction control component 2 according to the feedback of the position monitoring component, thereby realizing the follow-up loading of the large aspect ratio wing.

[0031] The working process of the high aspect ratio wing follow-up loading device of the embodiment of the present invention is as follows: when the calibration force value in the load calibration test is determined, the calibration force value is input into the servo control component, the servo control component gives a control instruction to the displacement control component, and performs servo control on the screw linear slide 12 in real time according to the feedback of the position monitoring component, until the loading device reaches stability and the force value of the tension pressure sensor 7 is the calibration force value, and the strain data under this calibration force value is recorded to realize the force value calibration of the high aspect ratio wing 1.

[0032] like Figure 4 As shown, the horizontal distance between the force direction control component 2 and the wing fixed point 15 (wing root) is X, and the vertical distance between the force direction control component 2 and the ball joint 9 is Y. By inputting the calibration force value, the lead screw linear slide 12 controls the electric servo cylinder 11 to move toward the wing fixed point 15, and the electric servo cylinder 11 pulls the high aspect ratio wing 1 downward, and controls the force value of the pull pressure sensor 7 to be the calibration force value. After the device remains stable, the horizontal displacement sensor 13 gives the horizontal displacement of the electric servo cylinder 11 as x, and the vertical displacement sensor 14 gives the vertical displacement as y. The angle between the high aspect ratio wing 1 and the horizontal plane is θ, and the vertical distance between the loading section and the original horizontal plane is Δy. The verticality (90°) between the high aspect ratio wing 1 and the force direction control component 2 at the loading point is achieved by clamping the card plate 6, so that the direction of the force at the wing loading point is consistent with the direction of the force of the pull pressure sensor 7. The force value displayed by the pull pressure sensor 7 can be regarded as the calibration force value, that is, the follow-up force loading of the high aspect ratio wing 1 is achieved. When the high aspect ratio wing 1 and the force direction control assembly 2 are perpendicular (90°) at the loading point by the clamping plate 6, the indications of the vertical displacement sensor 13 and the horizontal displacement sensor 14 should satisfy the following mathematical formula:

[0033]

[0034] The correlation between the displacement values ​​of the vertical displacement sensor 13 and the horizontal displacement sensor 14 is obtained as follows:

[0035] (xX) 2 +(yY) 2 =X 2 +Y 2 That is, when the force value of the tension pressure sensor 7 meets the calibration force value, the displacement values ​​of the vertical displacement sensor 13 and the horizontal displacement sensor 14 are controlled to maintain the above correlation, the large aspect ratio wing 1 and the force direction control component 2 are vertical at the loading section and the entire loading device remains in a stable state.

[0036] The high aspect ratio wing follower loading device of the embodiment of the present invention has the following beneficial effects:

[0037] 1. The present invention adopts a dual displacement sensor to measure the position change of the loading point, thereby realizing precise servo control. Compared with other follow-up loading methods, the present invention proposes a wing load calibration error correction method relying on dual displacement. The configuration of the dual displacement sensor also reduces the test cost. The device of the present invention is suitable for load loading and determination in a small laboratory, including other flexible devices such as wing models. The quantitative load follow-up loading of the device can be realized through the force sensor and the servo control system.

[0038] 2. The present invention adopts the combined control of a lead screw linear slide and an electric servo cylinder to realize follow-up loading. Compared with other follow-up loading methods, it reduces the requirements for laboratory space and the risks in the test process. It can realize quantitative load loading of flexible devices in a low-cost and small space, and can be applied to the preliminary load determination work of small laboratories in universities or companies, including load calibration.

[0039] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A high aspect ratio wing follower loading device, characterized in that: Including force direction control components, displacement control components, position monitoring components and servo control components, The force direction control component includes a clamping card plate, a tension pressure sensor, a connecting rod, and a ball joint. The clamping card plate is clamped and fixed on the load loading point of the large aspect ratio wing, including an upper clamping card plate arranged above the large aspect ratio wing and a lower clamping card plate arranged below the large aspect ratio wing. The tension pressure sensor is fixed on the lower clamping card plate. The connecting rod is fixed on the lower side of the tension pressure sensor and is used to connect the tension pressure sensor and the ball joint. The direction of the force at the load loading point is consistent with the direction of the tension pressure sensor, and the component force of the tension of the ball joint on the tension pressure sensor along the direction of the tension pressure sensor is the force value displayed by the tension pressure sensor. The displacement control assembly includes a connecting ring, an electric servo cylinder and a lead screw linear slide, wherein the connecting ring is fixed to the lower side of the ball joint and is used to connect the ball joint and the electric servo cylinder, the electric servo cylinder is fixed to the lower side of the connecting ring and is used to bend the large aspect ratio wing downward by contraction and pulling, and the lead screw linear slide is connected to the electric servo cylinder and is used to control the horizontal displacement of the electric servo cylinder; The position monitoring component includes a vertical displacement sensor and a horizontal displacement sensor, the vertical displacement sensor is used to detect the vertical displacement caused by the contraction of the electric servo cylinder, and the horizontal displacement sensor is used to detect the horizontal displacement of the electric servo cylinder controlled by the lead screw linear slide; The servo control component is used to control the movement of the lead screw linear slide according to the vertical displacement detected by the vertical displacement sensor and the horizontal displacement detected by the horizontal displacement sensor until the force value displayed by the tension and pressure sensor is the calibrated force value, thereby realizing the follow-up loading of the large aspect ratio wing.

2. The high aspect ratio wing follower loading device according to claim 1, characterized in that: The servo control component controls the movement of the lead screw linear slide, and the vertical displacement detected by the vertical displacement sensor and the horizontal displacement detected by the horizontal displacement sensor satisfy the following formula: (xX) 2 +(yY) 2 =X 2 +Y 2 , Among them, x is the horizontal displacement detected by the horizontal displacement sensor, y is the vertical displacement detected by the vertical displacement sensor, X is the distance between the load loading point of the high aspect ratio wing and the wing root, and Y is the distance between the high aspect ratio wing and the bottom of the ball joint.

3. The high aspect ratio wing follower loading device according to claim 1 or 2, characterized in that: The clamping card also includes: A plurality of wooden blocks are arranged between the upper clamping plate and the lower clamping plate and the surface of the high aspect ratio wing, and each wooden block matches the surface of the high aspect ratio wing; The connecting rod is connected with the upper clamping plate and the lower clamping plate, so that the upper clamping plate and the lower clamping plate clamp the large aspect ratio wing through the multiple wooden blocks.

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