Wing pitching and floating and sinking state measuring device and testing system

Abstract

The utility model discloses a device and a system for measuring pitching and floating and sinking states of a wing, and the device comprises a pedestal which is horizontally disposed on the ground; the supporting frame is vertically arranged on the base; the test wing is vertically arranged in the support frame; the top end sliding frame is horizontally and slidably connected to the upper end of the supporting frame; the fixed seat is arranged on the top end sliding frame and is connected with the upper end of the test wing; the bottom end sliding frame is horizontally and slidably connected to the lower end of the supporting frame; the rotating seat is arranged on the top end sliding frame and is connected with the lower end of the test wing; the driving mechanism is used for controlling the top end sliding frame and the bottom end sliding frame to slide synchronously. According to the utility model, the fixed seat and the rotary seat which can slide horizontally are arranged, so that the floating and sinking motion of the wing, namely the translational motion, can be tested, the pitching motion of the wing, namely the rotary motion, can also be tested, and the floating and sinking motion and the pitching motion of the wing can be tested at the same time, so that the practicability of the measuring device is improved; and the measurement precision is ensured.

Description

Technical Field

[0001] This utility model relates to the field of wind tunnel testing for airfoils, and in particular to a device and testing system for measuring and testing the pitch and buoyancy states of an airfoil. Background Technology

[0002] When a helicopter rotor is flying forward, it is in an unsteady flow state. Since the rotor is a nonlinear time-varying system that is coupled with an unsteady flow field, a highly flexible structure, and a control system, its aerodynamic flow field, dynamic characteristics, and the aeroelastic response characteristics of the coupling of the two are extremely complex, which seriously hinders the improvement of helicopter performance.

[0003] Chinese patent CN107525646B discloses a two-degree-of-freedom aeroelasticity experimental measurement device, comprising: a square frame, a top fixing mechanism, a wing torsion mechanism, and a wing lateral movement mechanism. The top fixing mechanism is located at the top of the square frame to fix one end of the wing. The wing torsion mechanism is located at the bottom of the square frame and is positioned opposite to the top fixing mechanism for axial torsion and fixing the other end of the wing. The wing torsion mechanism is located within the wing lateral movement mechanism that drives the wing to move linearly.

[0004] The measuring devices in the related technologies can only perform tests of floating and sinking motion (i.e., translational motion) and pitching motion (i.e., rotational motion) during operation. They cannot be tested independently, which reduces the practicality of the measuring devices and affects the measurement accuracy. Therefore, improvements are needed. Utility Model Content

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a wing pitch and buoyancy measurement device and testing system, which improves practicality and measurement accuracy.

[0006] A first aspect of this utility model provides a device for measuring the pitch and buoyancy of an airfoil, comprising:

[0007] The base is horizontally placed on the ground;

[0008] A support frame is vertically mounted on the base and forms a windward channel in the first direction;

[0009] The test wing is vertically mounted within the support frame;

[0010] The top sliding frame is horizontally slidably connected to the upper end of the support frame;

[0011] A fixed base is provided on the top sliding frame and connected to the upper end of the test wing;

[0012] The bottom sliding frame is horizontally slidably connected to the lower end of the support frame;

[0013] A rotating base is mounted on the top sliding frame and connected to the lower end of the test wing;

[0014] A drive mechanism is used to control the synchronous sliding of the top sliding frame and the bottom sliding frame.

[0015] In a preferred embodiment, the present invention can be further configured as follows: the driving mechanism includes a driving frame, a motor, a rotating wheel, and a guide rod. The driving frame is vertically arranged beside the support frame, and its upper and lower ends are respectively connected to the top sliding frame and the bottom sliding frame. The motor is arranged on the side wall of the support frame, the rotating wheel is arranged on the motor, the guide rod is horizontally arranged at the edge of the rotating wheel, and the driving frame is vertically provided with a strip-shaped guide hole for the guide rod to be inserted.

[0016] In a preferred embodiment, the present invention can be further configured such that: the fixed seat is horizontally slidably connected to the top sliding frame, the rotating seat is horizontally slidably connected to the bottom sliding frame, and both the top sliding frame and the bottom sliding frame are provided with elastic mechanisms distributed on both sides of the fixed seat and the rotating seat.

[0017] In a preferred embodiment, the present invention can be further configured such that: the elastic mechanism includes a seat plate, a plug rod, and a spring; the seat plate is fixed on the top sliding frame or the bottom sliding frame; the plug rod is horizontally disposed on the seat plate and slidably connected to the fixed seat or the rotating seat; and the spring is sleeved on the outer wall of the plug rod.

[0018] In a preferred embodiment, the present invention can be further configured such that: a sleeve surrounding the test wing is provided inside the support frame, and a through-flow windward channel is formed inside it.

[0019] In a preferred embodiment, the present invention can be further configured such that the support frame is detachably mounted on the upper end of the base.

[0020] In a preferred embodiment, the present invention can be further configured such that: the test wing includes a first connecting portion, a second connecting portion, located at both ends in its length direction, and a test portion located between the two, the test portion having a receiving cavity, and a sensor being disposed in the receiving cavity.

[0021] In a preferred embodiment, the present invention can be further configured such that the sleeve has a first panel, a second panel, a third panel, and a fourth panel arranged circumferentially along the inner surface of the support frame, wherein none of the first panel, the second panel, the third panel, and the fourth panel have a through structure.

[0022] A second aspect of this invention provides a testing system, comprising:

[0023] As described in the first aspect, the wing pitch and buoyancy measuring device;

[0024] A wind tunnel with a wind tunnel jet surface, which corresponds to the windward passage.

[0025] In a preferred embodiment, the present invention can be further configured such that the testing system also includes a moving track, and the base is disposed on the moving track for adjusting the relative position of the windward channel and the wind tunnel jet surface.

[0026] In summary, this utility model has the following beneficial effects: by setting up a fixed seat and a rotating seat that can slide horizontally, it can realize the testing of the wing's buoyancy movement, i.e., translational movement, as well as the testing of the wing's pitch movement, i.e., rotational movement. It can also work simultaneously to realize the simultaneous testing of the wing's buoyancy movement and pitch movement, thereby improving the practicality of the measuring device and ensuring the measurement accuracy. Attached Figure Description

[0027] Figure 1 This is a structural schematic diagram of an embodiment;

[0028] Figure 2 This is a schematic diagram of the bottom sliding frame in an embodiment.

[0029] Reference numerals: 1. Base; 2. Support frame; 21. Sleeve; 3. Test wing; 4. Top sliding frame; 5. Fixed seat; 6. Bottom sliding frame; 7. Rotating seat; 8. Drive mechanism; 81. Drive frame; 82. Motor; 83. Rotating wheel; 84. Guide rod; 85. Guide hole; 9. Elastic mechanism; 91. Seat plate; 92. Insert rod; 93. Spring. Detailed Implementation

[0030] The present invention will be further described in detail below with reference to the accompanying drawings.

[0031] like Figure 1 , Figure 2 As shown, a device for measuring the pitch and buoyancy of an airfoil includes a base 1, a support frame 2, a test airfoil 3, a top sliding frame 4, a fixed seat 5, a bottom sliding frame 6, a rotating seat 7, and a drive mechanism 8.

[0032] like Figure 1 , Figure 2 As shown, the base 1 is horizontally set on the ground, the support frame 2 is vertically set on the base 1, and the test wing 3 is vertically set inside the support frame 2. The support frame 2 is provided with a sleeve 21 surrounding the test wing 3, and a through windward channel is formed inside it to simulate a wind tunnel and ensure the accuracy of the test.

[0033] like Figure 1 , Figure 2As shown, the top sliding frame 4 is horizontally slidably connected to the upper end of the support frame 2, and the fixed seat 5 is set on the top sliding frame 4 and rotatably connected to the upper end of the test wing 3. The bottom sliding frame 6 is horizontally slidably connected to the lower end of the support frame 2, and the rotating seat 7 is set on the top sliding frame 4 and connected to the lower end of the test wing 3, and is used to control the torsion of the test wing 3.

[0034] like Figure 1 , Figure 2 As shown, the drive mechanism 8 is used to control the synchronous sliding of the top sliding frame 4 and the bottom sliding frame 6. The drive mechanism 8 includes a drive frame 81, a motor 82, a rotating wheel 83, and a guide rod 84.

[0035] like Figure 1 , Figure 2 As shown, the drive frame 81 is vertically mounted on the side of the support frame 2, and its upper and lower ends are connected to the top sliding frame 4 and the bottom sliding frame 6, respectively. The motor 82 is mounted on the side wall of the support frame 2, the rotating wheel 83 is mounted on the motor 82, the guide rod 84 is horizontally mounted on the edge of the rotating wheel 83, and the drive frame 81 has a vertically mounted strip-shaped guide hole 85 for the guide rod 84 to be inserted.

[0036] When testing the wing's entry and exit, the rotation seat 7 and the fixed seat 5 can be used to control the twist of the test wing 3, thereby measuring the pitch motion state.

[0037] The motor 82 can also be used to control the rotation of the wheel 83. The wheel 83 drives the guide rod 84 to rotate synchronously. At this time, with the cooperation of the guide hole 85 on the drive frame 81, the guide rod 84 pushes the drive rod to move horizontally back and forth. At this time, the drive frame 81 drives the top sliding frame 4 and the bottom sliding frame 6 to move synchronously, and controls the fixed seat 5 and the rotating seat 7 to slide synchronously, so as to realize the measurement of the floating and sinking motion state.

[0038] With the cooperation of the rotating seat 7 and the fixed seat 5, the pitch motion state can be measured at the same time, and the top sliding frame 4 and the bottom sliding frame 6 can be controlled to move synchronously by the drive mechanism 8, so as to measure the pitch motion and buoyancy motion at the same time, thereby improving the practicality of the measuring device and ensuring the measurement accuracy.

[0039] like Figure 1 , Figure 2 As shown, the fixed seat 5 is horizontally slidably connected to the top sliding frame 4, and the rotating seat 7 is horizontally slidably connected to the bottom sliding frame 6. Both the top sliding frame 4 and the bottom sliding frame 6 are provided with elastic mechanisms 9 distributed on both sides of the fixed seat 5 and the rotating seat 7.

[0040] like Figure 1 , Figure 2As shown, the elastic mechanism 9 includes a seat plate 91, a rod 92, and a spring 93. The seat plate 91 is fixed on the top sliding frame 4 or the bottom sliding frame 6. The rod 92 is horizontally arranged on the seat plate 91 and slidably connected to the fixed seat 5 or the rotating seat 7. The spring 93 is sleeved on the outer wall of the rod 92.

[0041] Therefore, during the operation of the fixed seat 5 and the rotating seat 7, the position of the fixed seat 5 and the rotating seat 7 is limited by the elastic action of the springs 93 on both sides. During the sliding and shaking process, the fixed seat 5 and the rotating seat 7 can shake freely under the guidance of the insertion rod 92 and the elastic action of the springs 93, thus avoiding restriction of the degree of freedom of the fixed seat 5 and the rotating seat 7, thereby ensuring that the operation of the test wing 3 conforms to the actual working state and improving the accuracy of the measurement process.

[0042] In some embodiments, the support frame 2 is detachably mounted on the upper end of the base 1.

[0043] In some embodiments, the test wing 3 includes a first connecting portion, a second connecting portion, and a test portion located at both ends in its length direction, and the test portion having a receiving cavity in which a sensor is disposed for measuring the experimental effect of the wing.

[0044] In some embodiments, the sleeve 21 has a first panel, a second panel, a third panel, and a fourth panel arranged circumferentially along the inner surface of the support frame 2, wherein the first panel, the second panel, the third panel, and the fourth panel do not have through structures to ensure the stability of the wind force.

[0045] In some embodiments, this application also provides a testing system, including,

[0046] The wing pitch and buoyancy measuring device as described above;

[0047] A wind tunnel with a wind tunnel jet surface, which corresponds to the windward passage.

[0048] The testing system also includes a moving track, on which the base 1 is mounted to adjust the relative position of the windward channel and the wind tunnel jet surface, thereby improving testing efficiency.

[0049] The specific embodiments are merely explanations of this utility model and are not intended to limit it. After reading this specification, those skilled in the art can make modifications to these embodiments without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this utility model.

Claims

1. A device for measuring the pitch and buoyancy of an airfoil, characterized in that: include: The base (1) is horizontally placed on the ground; The support frame (2) is vertically mounted on the base (1) and forms a windward passage in the first direction; The test wing (3) is vertically installed inside the support frame (2); The top sliding frame (4) is horizontally slidably connected to the upper end of the support frame (2); A fixed base (5) is provided on the top sliding frame (4) and connected to the upper end of the test wing (3); The bottom sliding frame (6) is horizontally slidably connected to the lower end of the support frame (2); A rotating seat (7) is mounted on the top sliding frame (4) and connected to the lower end of the test wing (3); A drive mechanism (8) is used to control the synchronous sliding of the top sliding frame (4) and the bottom sliding frame (6).

2. The device for measuring the pitch and buoyancy of an airfoil according to claim 1, characterized in that: The drive mechanism (8) includes a drive frame (81), a motor (82), a rotating wheel (83), and a guide rod (84). The drive frame (81) is vertically arranged on the side of the support frame (2), and its upper and lower ends are respectively connected to the top sliding frame (4) and the bottom sliding frame (6). The motor (82) is arranged on the side wall of the support frame (2), the rotating wheel (83) is arranged on the motor (82), and the guide rod (84) is horizontally arranged at the edge of the rotating wheel (83). The drive frame (81) has a vertically arranged strip-shaped guide hole (85) for the guide rod (84) to be inserted.

3. The device for measuring the pitch and buoyancy of an airfoil according to claim 1, characterized in that: The fixed seat (5) is horizontally slidably connected to the top sliding frame (4), and the rotating seat (7) is horizontally slidably connected to the bottom sliding frame (6). Both the top sliding frame (4) and the bottom sliding frame (6) are provided with elastic mechanisms (9) distributed on both sides of the fixed seat (5) and the rotating seat (7).

4. The device for measuring the pitch and buoyancy of an airfoil according to claim 3, characterized in that: The elastic mechanism (9) includes a seat plate (91), a plug rod (92), and a spring (93). The seat plate (91) is fixed on the top sliding frame (4) or the bottom sliding frame (6). The plug rod (92) is horizontally arranged on the seat plate (91) and slidably connected to the fixed seat (5) or the rotating seat (7). The spring (93) is sleeved on the outer wall of the plug rod (92).

5. The device for measuring the pitch and buoyancy of an airfoil according to claim 1, characterized in that: The support frame (2) is provided with a sleeve (21) surrounding the test wing (3) and a through-flow windward channel is formed inside it.

6. The device for measuring the pitch and buoyancy of an airfoil according to claim 1, characterized in that: The support frame (2) is detachably mounted on the upper end of the base (1).

7. The device for measuring the pitch and buoyancy of an airfoil according to claim 1, characterized in that: The test wing (3) includes a first connecting part, a second connecting part located at both ends in its length direction, and a test part located between the two. The test part has a receiving cavity, and a sensor is disposed in the receiving cavity.

8. The device for measuring the pitch and buoyancy of an airfoil according to claim 5, characterized in that: The sleeve (21) has a first panel, a second panel, a third panel, and a fourth panel arranged circumferentially along the inner surface of the support frame (2), wherein the first panel, the second panel, the third panel, and the fourth panel do not have a through structure.

9. A testing system, characterized in that: include, The wing pitch and buoyancy measuring device as described in any one of claims 1-8; A wind tunnel with a wind tunnel jet surface, which corresponds to the windward passage.

10. The testing system according to claim 9, characterized in that: It also includes a moving track, on which the base (1) is set to adjust the relative position of the windward channel and the wind tunnel jet surface.

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