Thin wing type control surface load continuous measuring device and method based on SMA tube direct drive

Abstract

The invention discloses a thin airfoil control surface load continuous measurement device and method based on SMA tube direct drive, and belongs to the technical field of aviation power wind tunnel tests. The invention solves the problems that the deflection driving device of the existing control surface has higher requirements on the installation space and is not suitable for the thin wing type control surface with the compact space characteristic. A balance control surface integrated piece is hinged to a thin wing type main body, a rotary supporting piece is installed on the thin wing type main body, one end of an SMA pipe is connected with the thin wing type main body, the other end of the SMA pipe is connected with the thin wing type main body through the rotary supporting piece, a cavity is formed in the SMA pipe, and a heating core rod is arranged in the cavity of the SMA pipe. According to the thin airfoil control surface load continuous measurement device and method based on SMA tube direct drive, the SMA tube is adopted as a control surface deflection driving device, the driving device and the control surface rotating shaft are coaxially arranged in the same space, the space outside the control surface is not occupied, and the thin airfoil control surface load continuous measurement device and method are more suitable for a test model with a compact space.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation power wind tunnel test, and in particular relates to a thin airfoil control surface load continuous measurement device and method based on SMA tube direct drive. Background Art

[0002] Aircraft wind tunnel test is an important means to verify the aerodynamic performance of aircraft. Among various wind tunnel tests, the aircraft rudder load measurement test is used to obtain the aerodynamic load of the aircraft rudder components, which is an important test link before the detailed design of the aircraft. The traditional aircraft rudder component load measurement test device consists of an aircraft body, a rudder balance, a rudder and an angle block. In order to meet the requirements of the rudder load measurement envelope, it is often necessary to design and process a large number of angle blocks with stepped angles. At the same time, in the wind tunnel test, the wind tunnel test personnel need to constantly manually replace different angle blocks to achieve different angle deflection states of the rudder. On the one hand, this method reduces the test efficiency and increases the test cost. On the other hand, due to the discontinuity of the rudder angle, it also affects the accuracy of the test data curve.

[0003] In response to the above problems, the patent publication number CN 111623950 A discloses a hinge torque measurement device, system and measurement method for automatic deflection of the rudder surface, and the patent publication number CN 114001906 B discloses an automatic variable rudder deflection device and its use method for the hinge torque measurement test in a hypersonic wind tunnel. The above two patents are mainly applicable to the full-moving rudder surface of missile models, and the deflection drive device and measurement device of the rudder surface need to be installed inside the missile body. The patent publication number CN 115356072 B discloses an automatic variable angle aircraft wind tunnel model component load dynamic measurement device and method. This method is mainly applicable to the load measurement of the flaperon rudder surface of the half-mold model. The deflection drive device of the rudder surface needs to be arranged inside the half-mold fuselage, which has a large requirement for the installation space. For thin airfoil rudder surfaces with compact space characteristics, the above existing methods are not applicable, and a new measurement device and means need to be proposed to solve the demand for continuous measurement of the load of thin airfoil rudder surfaces in wind tunnels.

[0004] Therefore, the present application proposes a thin airfoil rudder load continuous measurement device and method based on SMA tube direct drive to solve the above problems. Summary of the invention

[0005] The purpose of the present invention is to solve the problem that the deflection drive device of the current rudder surface requires a large installation space and is not applicable to thin airfoil rudder surfaces with compact space characteristics. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0006] The technical solution of the present invention: Solution 1: A thin airfoil rudder load continuous measurement device based on SMA tube direct drive, including a thin airfoil body, a rotating support, a balance rudder integrated part, an SMA tube and a heating core rod, the balance rudder integrated part is hinged on the thin airfoil body, the rotating support is installed on the thin airfoil body, one end of the SMA tube is connected to the thin airfoil body, and the other end of the SMA tube is connected to the thin airfoil body through the rotating support, the SMA tube has a cavity, and a heating core rod is arranged in the cavity of the SMA tube.

[0007] Furthermore, the SMA tube is externally sheathed with a heat insulating sleeve.

[0008] Furthermore, the thin airfoil body is provided with a right rudder surface support shaft and a left rudder surface support shaft, and the balance rudder surface integrated part is connected to the thin airfoil body through the right rudder surface support shaft and the left rudder surface support shaft.

[0009] Furthermore, a rudder surface upper cover plate and a rudder surface lower cover plate are provided on the thin airfoil body. The rudder surface upper cover plate is installed on the upper end surface of the thin airfoil body, and the rudder surface lower cover plate is installed on the lower end surface of the thin airfoil body.

[0010] Solution 2: A method for continuously measuring the load of a thin airfoil rudder surface based on direct drive of an SMA tube. The method is implemented based on the device for continuously measuring the load of a thin airfoil rudder surface based on direct drive of an SMA tube as described in Solution 1, and includes the following steps: Step 1: Install the assembled thin airfoil body in the wind tunnel and collect the initial reading of the balance; Step 2: Start the wind tunnel and energize the heating core rod to make it heat up. The heated SMA tube itself begins to twist and deform, and drives the balance rudder integrated part to rotate around the right support shaft and the left support shaft of the rudder surface. When heating starts, the balance data is continuously collected synchronously, and the existing video measurement system of the wind tunnel is used to measure the change value of the rudder surface angle in real time; Step 3: When the SMA tube drives the balance rudder integrated component to complete the movement of the entire deflection range, stop the operation of the balance and video rudder angle measurement system, and close the wind tunnel; Step 4: Subtract the initial balance reading collected in step 1 from the balance data collected during the experiment, and convert it through the balance formula to obtain a continuous curve of the rudder surface load changing with the rudder surface deflection angle.

[0011] The present invention has the following beneficial effects: 1. The thin-airfoil rudder load continuous measurement device based on SMA tube direct drive of the present invention adopts a design scheme of integrating a balance and a rudder. The calibration center of the balance is close to the centroid of the rudder. The accuracy of the balance measurement result is better than that of the traditional balance arranged outside the rudder. The SMA tube is used as a driving device for the deflection of the rudder. The driving device is coaxially and spatially arranged with the rudder shaft, does not occupy space outside the rudder, and is more suitable for test models with compact space.

[0012] 2. The thin airfoil rudder load continuous measurement method based on SMA tube direct drive of the present invention can obtain the continuously changing load of the rudder in the entire deflection angle range in one test through continuous deflection of the rudder angle and continuous measurement of the balance. It is more accurate than the load data under traditional step angles and greatly improves the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the structure of a thin airfoil rudder load continuous measurement device based on SMA tube direct drive; Figure 2 It is a schematic diagram of the section AA perpendicular to the axis of rotation of the rudder surface; Figure 3 It is a schematic diagram of section BB which is parallel to and passes through the rudder surface rotation axis.

[0014] In the figure, 1 is a thin airfoil body, 2 is an upper cover plate of the rudder surface, 3 is a rotating support, 4 is a right support shaft of the rudder surface, 5 is an integrated part of the balance rudder surface, 6 is a lower cover plate of the rudder surface, 7 is a left support shaft of the rudder surface, 8 is an SMA tube, 9 is an insulation sleeve, and 10 is a heating core rod. DETAILED DESCRIPTION

[0015] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0016] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection (i.e., non-detachable connection) includes but is not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but is not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: welding connection is selected for fixed connection, and hinge connection is selected for detachable connection.

[0017] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral 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, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0018] Embodiment 1, combination Figure 1-Figure 3 The present embodiment is described. The present embodiment is a thin airfoil rudder load continuous measuring device based on SMA tube direct drive, comprising a thin airfoil body 1, a rotating support 3, a balance rudder surface integrated part 5, an SMA tube 8 and a heating core rod 10. The balance rudder surface integrated part 5 is hinged on the thin airfoil body 1, the rotating support 3 is installed on the thin airfoil body 1, one end of the SMA tube 8 is connected to the thin airfoil body 1, and the other end of the SMA tube 8 is connected to the thin airfoil body 1 through the rotating support 3. The SMA tube 8 has a cavity inside, and a heating core rod 10 is arranged in the cavity of the SMA tube 8.

[0019] The left side of the balance rudder surface integrated part 5 is connected to the thin airfoil body 1 through the left rudder surface support shaft 7, and the right side of the balance rudder surface integrated part 5 is connected to the thin airfoil body 1 through the right rudder surface support shaft 4. The SMA tube 8 is directly installed on the thin airfoil body 1, and the other end thereof is connected to the thin airfoil body 1 through the rotating support 3. The end of the SMA tube 8 connected to the rotating support 3 is connected to the balance rudder surface integrated part 5 through a rectangular block. The heating core rod 10 is installed in the cavity of the SMA tube 8 to heat the SMA tube 8 and make it rotate and parallel. The heat insulation sleeve 9 covers the outside of the SMA tube 8 to prevent the high temperature generated by the heating core rod 10 inside the SMA tube 8 from spreading to the balance rudder integrated part 5 and affecting the balance rudder integrated part 5.

[0020] The SMA tube 8 is a hollow tubular structure made of shape memory alloy material. Its characteristics are that when the temperature of the structure rises, both ends of the SMA tube 8 can produce relative angular displacement deformation along the tube axis and have a large driving torque.

[0021] Embodiment 2, combined Figure 1-Figure 3 This embodiment is described. The method for continuous measurement of thin airfoil rudder load based on SMA tube direct drive in this embodiment includes the following steps: Step 1: Install the assembled thin airfoil body 1 in a wind tunnel and collect the initial reading of the balance; Step 2: Start the wind tunnel, energize the heating core rod 10 to make it heat up, and the heated SMA tube 8 itself begins to twist and deform, and drives the balance rudder integrated part 5 to rotate around the right support shaft 4 and the left support shaft 7 of the rudder surface. When heating starts, the balance data is continuously collected synchronously, and the existing video measurement system of the wind tunnel is used to measure the change value of the rudder surface angle in real time; Step 3: After the SMA tube 8 drives the balance rudder surface integrated part 5 to complete the movement of the entire deflection range, the balance and the video rudder surface angle measurement system are stopped, and the wind tunnel is closed; Step 4: Subtract the initial balance reading collected in step 1 from the balance data collected during the experiment, and convert it through the balance formula to obtain a continuous curve of the rudder surface load changing with the rudder surface deflection angle.

[0022] This embodiment is only an exemplary description of the present invention and does not limit its protection scope. Those skilled in the art may also make partial changes thereto. As long as they do not exceed the spirit of the present invention, they are within the protection scope of the present invention.

Claims

1. A thin airfoil rudder load continuous measurement device based on SMA tube direct drive, characterized by: The invention comprises a thin airfoil body (1), a rotating support member (3), a balance rudder integrated member (5), an SMA tube (8) and a heating core rod (10), wherein the balance rudder integrated member (5) is hinged on the thin airfoil body (1), the rotating support member (3) is mounted on the thin airfoil body (1), one end of the SMA tube (8) is connected to the thin airfoil body (1), and the other end of the SMA tube (8) is connected to the thin airfoil body (1) via the rotating support member (3), the SMA tube (8) has a cavity therein, and the heating core rod (10) is arranged in the cavity of the SMA tube (8).

2. The thin airfoil control surface load continuous measurement device based on SMA tube direct drive according to claim 1 is characterized in that: The SMA tube (8) is sheathed with a heat insulation sleeve (9) on the outside.

3. The thin airfoil rudder load continuous measurement device based on SMA tube direct drive according to claim 2 is characterized in that: The thin airfoil body (1) is provided with a right rudder support shaft (4) and a left rudder support shaft (7), and the balance rudder integrated component (5) is connected to the thin airfoil body (1) via the right rudder support shaft (4) and the left rudder support shaft (7).

4. The thin airfoil rudder load continuous measurement device based on SMA tube direct drive according to claim 3 is characterized in that: The thin airfoil body (1) is provided with a rudder surface upper cover plate (2) and a rudder surface lower cover plate (6); the rudder surface upper cover plate (2) is mounted on the upper end surface of the thin airfoil body (1), and the rudder surface lower cover plate (6) is mounted on the lower end surface of the thin airfoil body (1).

5. A method for continuously measuring the load of a thin airfoil rudder surface based on direct drive of an SMA tube, the method being implemented based on the device for continuously measuring the load of a thin airfoil rudder surface based on direct drive of an SMA tube as claimed in claim 4, characterized in that: The following steps are involved: Step 1: Install the assembled thin airfoil body (1) in a wind tunnel and collect an initial reading on a balance; Step 2: Start the wind tunnel and energize the heating core rod (10) to heat it. The heated SMA tube (8) itself begins to twist and deform, and drives the balance rudder integrated part (5) to rotate around the right support shaft (4) and the left support shaft (7) of the rudder. When heating starts, the balance data is continuously collected synchronously, and the existing video measurement system of the wind tunnel is used to measure the change value of the rudder angle in real time; Step 3: After the SMA tube (8) drives the balance rudder surface integrated component (5) to complete the movement of the entire deflection range, the balance and the video rudder surface angle measurement system are stopped, and the wind tunnel is closed; Step 4: Subtract the initial balance reading collected in step 1 from the balance data collected during the experiment, and convert it through the balance formula to obtain a continuous curve of the rudder surface load changing with the rudder surface deflection angle.

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