Integral frame three-section airfoil wind tunnel dynamic force test model

Abstract

The present invention discloses a three-section airfoil wind tunnel dynamic force measurement test model with an integral frame. The three-section airfoil wind tunnel dynamic force measurement test model with an integral frame includes a frame, an aerodynamic balance, a left section skin, a right section skin and a middle section skin. The left section skin, the middle section skin and the right section skin are fixed on the frame in sequence and wrap the frame. The two ends of the frame are respectively provided with a left rotating shaft and a right rotating shaft; the frame includes a main body, a main pipe beam, a front pipe beam, a rear pipe beam and two end plates. The main pipe beam, the front pipe beam and the rear pipe beam are arranged side by side on the main body. The two ends of the pipe beam, the front pipe beam and the rear pipe beam are fixed by end plates. A short shaft is provided on the main body. The aerodynamic balance is fixed on the short shaft, and the aerodynamic balance is also fixed on the middle section skin. The three-section airfoil wind tunnel dynamic force measurement test model with an integral frame of the present invention is light in weight and high in strength.

Description

Technical Field

[0001] The invention relates to the technical field of dynamic force measurement test of airfoil wind tunnels, and in particular to an integral frame three-section airfoil wind tunnel dynamic force measurement test model. Background Art

[0002] In order to obtain the dynamic aerodynamic performance of the airfoil, it is necessary to conduct a dynamic force measurement test on the airfoil. The existing airfoil test models are all fully filled and solid, with only one pipe beam. The aerodynamic balance is installed on the pipe beam. In order to facilitate the installation of the aerodynamic balance, the pipe beam needs to be disconnected and then assembled. The use of the existing airfoil test model for dynamic force measurement tests leads to two problems: (1) Due to the influence of the side wall interference of the airfoil wind tunnel test, the dynamic aerodynamic performance error obtained by measuring the force of the airfoil dynamic test model over the full wingspan is also large, so the force is usually measured in the middle section of the model in the span direction, which causes insufficient strength and stiffness of the model; (2) The mass and moment of inertia of the force measurement model and the middle section of the force measurement model are often large, and the measurement results of the aerodynamic balance contain large inertial forces and moments of inertia, which are difficult to eliminate and correct; at the same time, the load of the test drive mechanism is increased, limiting the amplitude and test frequency that can be achieved in the experiment. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide an integral frame three-section airfoil wind tunnel dynamic force measurement test model which increases strength while reducing mass.

[0004] In order to solve the above problems, the present invention provides an integral frame three-section airfoil wind tunnel dynamic force measurement test model, the integral frame three-section airfoil wind tunnel dynamic force measurement test model comprises a frame, an aerodynamic balance, a left section skin, a right section skin and a middle section skin, the left section skin, the middle section skin and the right section skin are fixed on the frame in sequence and wrap the frame, and a left rotating shaft and a right rotating shaft are respectively provided at two ends of the frame; the frame comprises a main body, a main pipe beam, a front pipe beam, a rear pipe beam and two end plates, the main pipe beam, the front pipe beam and the rear pipe beam are arranged side by side on the main body, the two ends of the pipe beam, the front pipe beam and the rear pipe beam are fixed by end plates, a short shaft is provided on the main body, the aerodynamic balance is fixed on the short shaft, and the aerodynamic balance is also fixed on the middle section skin.

[0005] Furthermore, the middle skin includes an upper skin and a lower skin, and the upper skin and the lower skin are fixed to form a receiving cavity.

[0006] Furthermore, a fixed plane is provided at the front end of the upper skin, the middle part of the upper skin is bent upward, a plurality of avoidance notches are provided on the side wall of the middle part of the upper skin, a balance mounting plate is also provided in the middle part of the upper skin, and a fixed step is provided at the rear end of the upper skin.

[0007] Furthermore, a fixed plane is provided at the front end of the lower skin, the middle part of the lower skin is bent downward, a plurality of avoidance notches are provided on the side wall of the middle part of the lower skin, and a fixed plane is provided at the rear end of the lower skin.

[0008] Furthermore, ribs are provided on both the upper skin and the lower skin.

[0009] Furthermore, a keyway is provided on the short shaft.

[0010] Furthermore, the frame also includes a support plate, and the support plate is fixed on the main pipe beam, the front pipe beam and the rear pipe beam.

[0011] Furthermore, the middle section skin is made of aluminum alloy or carbon fiber.

[0012] Furthermore, the left section skin and the right section skin are made of wood, fiberglass or carbon fiber.

[0013] The frame of the three-section airfoil wind tunnel dynamic force measurement test model of the integral frame of the present invention is provided with left, middle and right skins installed on the frame to form a whole. Meanwhile, the frame is formed by welding a main body, a main pipe beam, a front pipe beam, a rear pipe beam and two end plates, so that the interior of the model is hollow and has strong support, thereby making the entire model as a whole light in weight and high in strength. The test using the model can achieve a higher oscillation amplitude and frequency, reduce the inertia force and inertia moment during the test, and reduce the test error and the load of the test drive mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of a preferred implementation of the integral frame three-section airfoil wind tunnel dynamic force measurement test model of the present invention.

[0015] Figure 2 It is a cross-sectional view of AA.

[0016] Figure 3 It is a cross-sectional view of BB.

[0017] Figure 4 It is a structural diagram of the framework.

[0018] Figure 5 It is a schematic diagram of the structure of the upper skin.

[0019] Figure 6 This is a bottom view of the upper skin.

[0020] Figure 7 It is a schematic diagram of the structure of the lower skin.

[0021] Figure 8 This is a bottom view of the lower skin. DETAILED DESCRIPTION

[0022] The present invention will be further described below in conjunction with the accompanying drawings.

[0023] like Figures 1 to 3 As shown, the integral frame three-section airfoil wind tunnel dynamic force measurement test model of the present invention is suitable for a 1.6m×3m rectangular cross-section airfoil wind tunnel test section, and the model is set to have a full span of 1.6m and a chord length of 0.7m. The preferred embodiment of the integral frame three-section airfoil wind tunnel dynamic force measurement test model of the present invention comprises a frame 1, an aerodynamic balance 5, a left section skin 2, a right section skin 3 and a middle section skin 4, wherein the left section skin 2, the middle section skin 4 and the right section skin 3 are sequentially fixed on the frame 1 and wrap the frame 1, the aerodynamic balance 5 is fixed on the frame 1 and the middle section skin 4, and the aerodynamic balance 5 is only connected to the frame 1 and the middle section skin 4, effectively ensuring the accurate measurement of the aerodynamic balance 5, and the aerodynamic balance 5 realizes measurement while transmitting force. The two ends of the frame 1 are respectively provided with a left rotating shaft 6 and a right rotating shaft 7. The left section skin 2 and the right section skin 3 are made of wood, fiberglass or carbon fiber to reduce their weight.

[0024] Combination Figure 4 For reference, the frame 1 includes a main body 11, a main pipe beam 12, a front pipe beam 13, a rear pipe beam 14, a support plate 15 and two end plates 16. The main pipe beam 12, the front pipe beam 13 and the rear pipe beam 14 are arranged side by side on the main body 11, and the two ends of the pipe beam, the front pipe beam 13 and the rear pipe beam 14 are fixed by the end plates 16. The support plate 15 is fixed on the main pipe beam 12, the front pipe beam 13 and the rear pipe beam 14 to increase the rigidity and strength of the frame 1. The main body 11 is provided with a short shaft 17, and the aerodynamic balance 5 is connected to the short shaft 17. The short shaft 17 is provided with a keyway, and a key 171 is inserted in the keyway to fix the connection between the aerodynamic balance 5 and the short shaft 17.

[0025] like Figures 5 to 8As shown, the middle skin 4 includes an upper skin 41 and a lower skin 42, and the upper skin 41 and the lower skin 42 are fixed to form a receiving cavity, which divides the middle skin 4 into two parts, so as to facilitate the installation of the aerodynamic balance 5. The upper skin 41 and the lower skin 42 are both provided with ribs 43 to increase the strength and rigidity of the middle skin 4. A fixing plane 411 is provided at the front end of the upper skin 41, and the middle part of the upper skin 41 is bent upward to form a receiving space; a plurality of avoidance notches 412 are provided on the side wall in the middle of the upper skin 41, and a balance mounting plate 413 is also provided in the middle of the upper skin 41, and a fixing step 414 is provided at the rear end of the upper skin 41. A fixing plane 421 is provided at the front end of the lower skin 42, and the middle part of the lower skin 42 is bent downward to form a receiving space; a plurality of avoidance notches 422 are provided on the side wall in the middle of the lower skin 42, and a fixing plane 423 is provided at the rear end of the lower skin 42. The avoidance notch 412 of the upper skin 41 and the avoidance notch 422 of the lower skin 42 cooperate to form a plurality of holes, and the main pipe beam 12, the front pipe beam 13, the rear pipe beam 14 and the short shaft 17 are inserted into the corresponding holes. The fixing plane 411 at the front end of the upper skin 41 is fitted and fixed with the fixing plane 421 at the front end of the lower skin 42, and the step surface of the fixing step 414 at the rear end of the upper skin 41 is fitted and fixed with the fixing plane 423 at the rear end of the lower skin 42.

[0026] The frame 1 of the three-section airfoil wind tunnel dynamic force measurement test model of the present invention is equipped with left, middle and right skins 2, 4 and 3 to form a whole. At the same time, the frame 1 is welded by a main body 11, a main pipe beam 12, a front pipe beam 13, a rear pipe beam 14 and two end plates 16, so that the interior of the model is hollow and has strong support, so that the entire model has the characteristics of light weight, high strength and small moment of inertia. The test using the model can achieve a higher oscillation amplitude and frequency, reduce the inertia force and inertia moment and inertia moment during the test, and reduce the test error and the load of the test drive mechanism.

[0027] The above are only implementation modes of the present invention, and are not intended to limit the patent scope of the present invention. Any equivalent structure made using the contents of the present invention's specification and drawings, directly or indirectly used in other related technical fields, are also within the patent protection scope of the present invention.

Claims

1. An integral frame three-section airfoil wind tunnel dynamic force test model, characterized in that: The invention comprises a frame, an aerodynamic balance, a left skin section, a right skin section and a middle skin section, wherein the left skin section, the middle skin section and the right skin section are fixed on the frame in sequence and wrap the frame, and the two ends of the frame are respectively provided with a left rotating shaft and a right rotating shaft; the frame comprises a main body, a main pipe beam, a front pipe beam, a rear pipe beam and two end plates, the main pipe beam, the front pipe beam and the rear pipe beam are arranged side by side on the main body, the two ends of the pipe beam, the front pipe beam and the rear pipe beam are fixed by the end plates, a short shaft is provided on the main body, the aerodynamic balance is fixed on the short shaft, and the aerodynamic balance is also fixed On the middle section of the skin; the middle section of the skin includes an upper skin and a lower skin, the upper skin and the lower skin are fixed to form a accommodating cavity, the front end of the upper skin is provided with a fixed plane, the middle part of the upper skin is bent upward, the side wall of the middle part of the upper skin is provided with a plurality of avoidance notches, the middle part of the upper skin is also provided with a balance mounting plate, the rear end of the upper skin is provided with a fixed step, the front end of the lower skin is provided with a fixed plane, the middle part of the lower skin is bent downward, the side wall of the middle part of the lower skin is provided with a plurality of avoidance notches, and the rear end of the lower skin is provided with a fixed plane.

2. The integral frame three-section airfoil wind tunnel dynamic force test model according to claim 1, characterized in that: Ribs are provided on both the upper skin and the lower skin.

3. The integral frame three-section airfoil wind tunnel dynamic force test model according to claim 1, characterized in that: A keyway is arranged on the short shaft.

4. The integral frame three-section airfoil wind tunnel dynamic force test model according to claim 1, characterized in that: The frame further comprises a support plate, and the support plate is fixed on the main pipe beam, the front pipe beam and the rear pipe beam.

5. The integral frame three-section airfoil wind tunnel dynamic force test model according to claim 1, characterized in that: The middle section skin is made of aluminum alloy or carbon fiber.

6. The integral frame three-section airfoil wind tunnel dynamic force test model according to claim 1, characterized in that: The left section skin and the right section skin are made of wood, glass fiber reinforced plastic or carbon fiber.

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