A pneumatic test device for rudder surface model

Abstract

The invention discloses a rudder surface model aerodynamic test device, which comprises: a frame, in which a closed chamber is arranged; a motor, which is arranged at the bottom of the chamber; a wind tunnel balance, which is arranged above the motor and connected to the output end of the motor, and both ends of the wind tunnel balance are rotatably connected to the frame through a bearing respectively; a rotary encoder, which is arranged above the wind tunnel balance, the stator of the rotary encoder is connected to the frame, the rotor of the rotary encoder is connected to the upper end of the wind tunnel balance, the upper end of the wind tunnel balance is used to connect the rudder surface model, and the rudder surface model is exposed in the chamber; an accelerometer is attached to the rudder surface model; the device adopts the motor to drive the rudder surface model, can be used for carrying out unsteady aerodynamic tests of the rudder surface in supersonic and hypersonic wind tunnels, has a compact structure, is easy to be installed in the wind tunnel, can conveniently change the attack angle of the rudder surface model at any time, and overcomes the limitation that the exciter can only realize small attack angle vibration.

Description

Technical Field

[0001] The invention belongs to the technical field of aerodynamic testing of rudder surface models, and more specifically, relates to a pneumatic testing device for a rudder surface model. Background Art

[0002] During the aircraft design process, it is necessary to avoid flutter within its flight envelope. Wind tunnel testing is an indispensable research method for such problems. Through wind tunnel testing, the aerodynamic elastic characteristics such as aerodynamic shape and structural design can be evaluated, and the flutter boundaries of the aircraft and its components can be determined.

[0003] At present, domestic aeroelastic tests are mainly carried out in low-speed and subsonic wind tunnels. There are fewer aeroelastic test devices in supersonic wind tunnels, and even fewer aeroelastic tests in hypersonic wind tunnels. The vibration excitation of the rudder model in the currently known hypersonic wind tunnel aeroelastic test device is achieved by an exciter. Its test device has the following disadvantages: (1) It is difficult to change the rudder angle of attack. It is impossible to directly drive the rudder to change the angle of attack. The required rudder angle of attack can only be set through assembly relationships before the wind tunnel test, and the angle of attack is fixed and cannot be changed during the wind tunnel test; (2) Since the space of the wind tunnel test section is small, the test device needs to be compactly designed so that the installation and debugging of the test process can be easily carried out. However, the exciter is large in size and must be installed horizontally, which greatly occupies the space in the wind tunnel test section, making the installation and debugging of the wind tunnel test stage very difficult; (3) The vibration amplitude of the exciter is small, so it can only excite the rudder to vibrate with a small amplitude, and cannot achieve large-amplitude vibration of the rudder, which limits the state condition selection of unsteady aerodynamic wind tunnel tests. Summary of the invention

[0004] The purpose of the present invention is to provide a rudder model aerodynamic test device in view of the deficiencies in the prior art. The device adopts a motor to drive the rudder model and can be used to carry out unsteady aerodynamic tests of the rudder in supersonic and hypersonic wind tunnels. The device has a compact structure and is easy to install in the wind tunnel. The angle of attack of the rudder model can be changed conveniently at any time, and the limitation that the exciter can only achieve small angle vibration is overcome.

[0005] In order to achieve the above object, the present invention provides a control surface model aerodynamic test device, the device comprising:

[0006] A frame, wherein a closed chamber is arranged in the frame;

[0007] A motor is arranged at the bottom of the chamber;

[0008] A wind tunnel balance is arranged above the motor and connected to the output end of the motor, and both ends of the wind tunnel balance are rotatably connected to the frame through a bearing respectively;

[0009] A rotary encoder is arranged above the wind tunnel balance, wherein the stator of the rotary encoder is connected to the frame, the rotor of the rotary encoder is connected to the upper end of the wind tunnel balance, the upper end of the wind tunnel balance is used to connect a rudder surface model, and the rudder surface model is exposed outside the chamber;

[0010] The accelerometer is attached to the rudder surface model.

[0011] Optionally, the rack comprises:

[0012] Base;

[0013] Two vertical plates, the two vertical plates are arranged on the base at intervals;

[0014] A surrounding plate, surrounding the two vertical plates, forming the chamber between the two vertical plates;

[0015] A reflecting plate is connected to the top of the vertical plate and the enclosure plate, and the reflecting plate blocks the upper end of the chamber. The other end of the rotor of the rotary encoder passes through the through hole on the reflecting plate to connect to the rudder surface model.

[0016] Optionally, two L-shaped plates are symmetrically arranged on the base, one side of the L-shaped plate is connected to the base via bolts, and the other side of the L-shaped plate forms the vertical plate.

[0017] Optionally, a bottom platform is provided below the base, and the base is fixed to the bottom platform by bolts.

[0018] Optionally, the enclosure panel includes a front enclosure panel and a rear enclosure panel, the front end of the front enclosure panel is provided with a sharp corner that gradually expands from front to rear, and the rear end of the rear enclosure panel is provided with a sharp corner that gradually expands from rear to front.

[0019] Optionally, the motor is connected to the frame via a bearing motor seat, and the bearing at the lower end of the wind tunnel balance is installed in the bearing motor seat.

[0020] Optionally, the bearing at the upper end of the wind tunnel balance is mounted on the frame via a bearing seat.

[0021] Optionally, the lower end of the wind tunnel balance is connected to the output end of the motor through a coupling.

[0022] Optionally, a flange is connected to the upper end of the wind tunnel balance, a clamp is provided at the lower part of the rudder surface model, and the clamp is detachably connected to the flange.

[0023] Optionally, the rudder model includes a rudder frame, the two accelerometers are attached to the tip surface of the rudder frame, and the outside of the rudder frame is wrapped with a rudder foam layer.

[0024] The invention provides a rudder surface model aerodynamic test device, which has the beneficial effects of: the device adopts a motor to drive the rudder surface model, can be used for carrying out unsteady aerodynamic tests of the rudder surface in supersonic and hypersonic wind tunnels, has a single-axis mechanism formed by two bearings fixed at the upper and lower ends of a wind tunnel balance, the motor directly drives the single-axis mechanism, has a compact structure, is easy to install in the wind tunnel, can conveniently change the angle of attack of the rudder surface model at any time, and overcomes the limitation that an exciter can only realize small angle vibration, and can realize small angle vibration and large angle vibration of the rudder surface model at any angle of attack.

[0025] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0027] Figure 1 A schematic structural diagram of a control surface model aerodynamic test device according to an embodiment of the present invention is shown.

[0028] Figure 2 A partial cross-sectional structural schematic diagram of a control surface model aerodynamic test device according to an embodiment of the present invention is shown.

[0029] Figure 3 A schematic structural diagram of a frame of a control surface model aerodynamic test device according to an embodiment of the present invention is shown.

[0030] Figure 4 A schematic diagram of the internal structure of a control surface model aerodynamic test device according to an embodiment of the present invention is shown.

[0031] Figure 5 A schematic structural diagram of a rudder surface model of a rudder surface model pneumatic test device according to an embodiment of the present invention is shown.

[0032] Description of reference numerals:

[0033] 1. Frame; 2. Motor; 3. Wind tunnel balance; 4. Bearing; 5. Rotary encoder; 6. Rudder model; 7. Accelerometer; 8. Base; 9. Reflector; 10. L-shaped plate; 11. Bottom platform; 12. Front panel; 13. Rear panel; 14. Bearing motor seat; 15. Bearing seat; 16. Coupling; 17. Flange; 18. Clamp; 19. Rudder frame; 20. Rudder foam layer; 21. Encoder seat. DETAILED DESCRIPTION

[0034] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0035] The present invention provides a rudder model pneumatic test device, which comprises:

[0036] a frame, wherein a closed chamber is disposed in the frame;

[0037] A motor is disposed at the bottom of the chamber;

[0038] A wind tunnel balance is arranged above the motor and connected to the output end of the motor, and both ends of the wind tunnel balance are rotatably connected to the frame through a bearing respectively;

[0039] A rotary encoder is arranged above the wind tunnel balance, a stator of the rotary encoder is connected to the frame, a rotor of the rotary encoder is connected to the upper end of the wind tunnel balance, the upper end of the wind tunnel balance is used to connect the rudder surface model, and the rudder surface model is exposed in the chamber;

[0040] Accelerometer, attached to the rudder model.

[0041] Specifically, the motor, wind tunnel balance, and rotary encoder arranged from bottom to top are located in a closed chamber, forming a single-axis mechanism fixed by two bearings to avoid being affected by the wind field in the wind tunnel. Only the rudder surface model is exposed in the chamber and in the wind field. The device uses a motor to directly drive the rotating rudder surface model. This single-axis mechanism not only has a compact structure and occupies a small space, but also can easily change the angle of attack of the rudder surface through the motor during the wind tunnel test. The motor can also excite the rudder surface model to achieve large-amplitude vibration of the rudder surface. During the wind tunnel test, the rotary encoder measures the deflection angle of attack and vibration angle response of the rudder surface model, the accelerometer measures the vibration acceleration response of the rudder surface model, and the wind tunnel balance measures the elastic torque borne by the rudder surface model.

[0042] In this embodiment, the motor is a servo motor.

[0043] Optionally, the rack includes:

[0044] Base;

[0045] Two vertical plates, the two vertical plates are arranged on the base at intervals;

[0046] A surrounding plate surrounds the two vertical plates to form a chamber between the two vertical plates;

[0047] The reflecting plate is connected with the top of the vertical plate and the enclosure plate, and the reflecting plate blocks the upper end of the chamber. The other end of the rotor of the rotary encoder passes through the through hole on the reflecting plate to connect with the rudder surface model.

[0048] Specifically, two vertical plates and a surrounding plate form a closed chamber, and a motor, a wind tunnel balance, and a rotary encoder are located in the closed chamber. The front end of the reflector is a triangular tip, and the upper surface of the front end of the reflector is a plane, and the lower surface is an inclined surface whose thickness increases from front to back, which is beneficial to reducing wind resistance.

[0049] Optionally, two L-shaped plates are symmetrically arranged on the base, one side of the L-shaped plate is connected to the base by bolts, and the other side of the L-shaped plate forms a vertical plate.

[0050] Specifically, two L-shaped plates are used, which are detachably connected to the base and form two side walls of the chamber, so as to facilitate installation of components in the chamber and maintenance and replacement of components in the chamber.

[0051] Optionally, a bottom platform is provided below the base, and the base is fixed to the bottom platform by bolts.

[0052] Specifically, the bottom platform is used to fix the device in the wind tunnel.

[0053] In one example, a motor accommodating groove is provided on the upper side of the bottom platform to accommodate the bottom of the motor, and a motor hole is provided on the base. The motor is inserted into the motor hole and the bottom is located in the motor accommodating groove.

[0054] Optionally, the enclosure panel includes a front enclosure panel and a rear enclosure panel, the front end of the front enclosure panel is provided with a sharp corner that gradually expands from front to rear, and the rear end of the rear enclosure panel is provided with a sharp corner that gradually expands from rear to front.

[0055] Specifically, the structure of the front panel and the rear panel enables the panel to form a shape with sharp corners at the front and rear, which is beneficial to reducing wind resistance.

[0056] Optionally, the motor is connected to the frame via a bearing motor seat, and the bearing at the lower end of the wind tunnel balance is installed in the bearing motor seat.

[0057] Specifically, the bearing motor seat is fixed on the L-shaped plate by bolts.

[0058] Optionally, the bearing at the upper end of the wind tunnel balance is mounted on the frame via a bearing seat.

[0059] Specifically, the bearing seat is fixed on the L-shaped plate by bolts.

[0060] Optionally, the lower end of the wind tunnel balance is connected to the output end of the motor through a coupling.

[0061] Optionally, a flange is connected to the upper end of the wind tunnel balance, a clamp is provided at the lower part of the rudder surface model, and the clamp is detachably connected to the flange.

[0062] Specifically, a through hole is arranged in the middle of the reflector plate, and the flange is rotatably arranged in the through hole.

[0063] Optionally, the rudder model includes a rudder frame, two accelerometers are attached to the tip surface of the rudder frame, and the outside of the rudder frame is wrapped with a rudder foam layer.

[0064] Specifically, the rudder surface model can be replaced according to test needs.

[0065] Example

[0066] like Figures 1 to 5 As shown, the present invention provides a rudder model aerodynamic test device, the device comprising:

[0067] A frame 1, wherein a closed chamber is provided in the frame 1;

[0068] A motor 2 is arranged at the bottom of the chamber;

[0069] The wind tunnel balance 3 is arranged above the motor 2 and connected to the output end of the motor 2. Both ends of the wind tunnel balance 3 are rotatably connected to the frame 1 through a bearing 4 respectively.

[0070] The rotary encoder 5 is arranged above the wind tunnel balance 3, the stator of the rotary encoder 5 is connected to the frame 1, the rotor of the rotary encoder 5 is connected to the upper end of the wind tunnel balance 3, the upper end of the wind tunnel balance 3 is used to connect the rudder surface model 6, and the rudder surface model 6 is exposed in the chamber;

[0071] The accelerometer 7 is attached to the rudder surface model 6 .

[0072] In this embodiment, the rack 1 includes:

[0073] Base 8;

[0074] Two vertical plates, the two vertical plates are arranged on the base 8 at intervals;

[0075] A surrounding plate surrounds the two vertical plates to form a chamber between the two vertical plates;

[0076] The reflecting plate 9 is connected to the top of the vertical plate and the enclosure plate. The reflecting plate 9 blocks the upper end of the chamber. The other end of the rotor of the rotary encoder 5 passes through the through hole on the reflecting plate 9 to connect to the rudder surface model 6.

[0077] In this embodiment, two L-shaped plates 10 are symmetrically arranged on the base 8, one side of the L-shaped plate 10 is connected to the base 8 by bolts, and the other side of the L-shaped plate 10 forms a vertical plate.

[0078] In this embodiment, a bottom platform 11 is provided below the base 8 , and the base 8 is fixed to the bottom platform 11 by bolts.

[0079] In this embodiment, the enclosure includes a front enclosure 12 and a rear enclosure 13. The front end of the front enclosure 12 is provided with a sharp corner that gradually expands from front to rear, and the rear end of the rear enclosure 13 is provided with a sharp corner that gradually expands from rear to front.

[0080] In this embodiment, the motor 2 is connected to the frame 1 via a bearing motor seat 14 , and the bearing 4 at the lower end of the wind tunnel balance 3 is installed in the bearing motor seat 14 .

[0081] In this embodiment, the bearing 4 at the upper end of the wind tunnel balance 3 is installed on the frame 1 through the bearing seat 15.

[0082] In this embodiment, the lower end of the wind tunnel balance 3 is connected to the output end of the motor 2 through a coupling 16 .

[0083] In this embodiment, a flange 17 is connected to the upper end of the wind tunnel balance 3 , and a clamp 18 is provided at the lower part of the rudder surface model 6 . The clamp 18 is detachably connected to the flange 17 .

[0084] In this embodiment, the control surface model 6 includes a control surface frame 19 , two accelerometers 7 are attached to the tip surface of the control surface frame 19 , and the outside of the control surface frame 19 is wrapped with a control surface foam layer 20 .

[0085] In this embodiment, the rotary encoder 5 is fixed on the frame 1 via an encoder seat 21 .

[0086] In summary, when the rudder model aerodynamic test device provided by the present invention is used, the device can be conveniently installed in a wind tunnel through the bottom platform 11, and is used to carry out unsteady aerodynamic tests of rudder surfaces in supersonic and hypersonic wind tunnels. The device is directly driven by a motor 2 to rotate the rudder model 6, so that the angle of attack of the rudder surface can be conveniently and at any time changed during the wind tunnel test. The motor can also excite the rudder model 6 to achieve large-amplitude vibration of the rudder model 6. The measurement function of the device is jointly realized by the rotary encoder 5 at the root of the rudder model 6, the accelerometer 7 inside the rudder model 6, and the wind tunnel balance 3. During the wind tunnel test, the rotary encoder 5 measures the deflection angle of attack and the vibration angle response of the rudder model 6, the accelerometer 7 measures the vibration acceleration response of the rudder model 6, and the wind tunnel balance 3 measures the elastic torque borne by the rudder model 6. Then, the unsteady aerodynamic force borne by the rudder model 6 is separated from the dynamic equation of the rudder model 6, and finally the unsteady aerodynamic force of the rudder model 6 under different angles of attack, different Ma numbers, different dynamic pressures, and different amplitudes is obtained.

[0087] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A rudder model aerodynamic test device, characterized in that: The device includes: A frame, wherein a closed chamber is arranged in the frame; A motor is arranged at the bottom of the chamber; A wind tunnel balance is arranged above the motor and connected to the output end of the motor, and both ends of the wind tunnel balance are rotatably connected to the frame through a bearing respectively; A rotary encoder is arranged above the wind tunnel balance, wherein the stator of the rotary encoder is connected to the frame, the rotor of the rotary encoder is connected to the upper end of the wind tunnel balance, the upper end of the wind tunnel balance is used to connect a rudder surface model, and the rudder surface model is exposed outside the chamber; an accelerometer, attached to the rudder surface model; The motor, wind tunnel balance, and rotary encoder arranged from bottom to top are in a closed cavity, forming a single-axis mechanism fixed by two bearings; the motor directly drives the rudder surface model to rotate, so that the angle of attack of the rudder surface can be conveniently and at any time changed during the wind tunnel test, and the motor can also excite the rudder surface model to achieve the vibration of the rudder surface model; during the wind tunnel test, the rotary encoder measures the deflection angle of attack and vibration angle response of the rudder surface model, the accelerometer measures the vibration acceleration response of the rudder surface model, and the wind tunnel balance measures the elastic moment borne by the rudder surface model; The upper end of the wind tunnel balance is connected with a flange, and the lower part of the rudder surface model is provided with a clamp, and the clamp is detachably connected to the flange; The rudder surface model comprises a rudder surface frame, two accelerometers are attached to the tip surface of the rudder surface frame, and the outside of the rudder surface frame is wrapped with a rudder surface foam layer.

2. The control surface model aerodynamic test device according to claim 1, characterized in that: The frame comprises: Base; Two vertical plates, the two vertical plates are arranged on the base at intervals; A surrounding plate, surrounding the two vertical plates, forming the chamber between the two vertical plates; A reflecting plate is connected to the top of the vertical plate and the enclosure plate, and the reflecting plate blocks the upper end of the chamber. The other end of the rotor of the rotary encoder passes through the through hole on the reflecting plate to connect to the rudder surface model.

3. The control surface model aerodynamic test device according to claim 2, characterized in that: Two L-shaped plates are symmetrically arranged on the base, one side of the L-shaped plate is connected to the base through bolts, and the other side of the L-shaped plate forms the vertical plate.

4. The control surface model aerodynamic test device according to claim 2, characterized in that: A bottom platform is arranged below the base, and the base is fixed on the bottom platform by bolts.

5. The control surface model aerodynamic test device according to claim 2, characterized in that: The enclosure panel comprises a front enclosure panel and a rear enclosure panel, wherein the front end of the front enclosure panel is provided with a sharp corner which gradually expands from front to back, and the rear end of the rear enclosure panel is provided with a sharp corner which gradually expands from back to front.

6. The control surface model aerodynamic test device according to claim 1, characterized in that: The motor is connected to the frame through a bearing motor seat, and the bearing at the lower end of the wind tunnel balance is installed in the bearing motor seat.

7. The control surface model aerodynamic test device according to claim 1, characterized in that: The bearing at the upper end of the wind tunnel balance is mounted on the frame via a bearing seat.

8. The control surface model aerodynamic test device according to claim 1, characterized in that: The lower end of the wind tunnel balance is connected to the output end of the motor through a coupling.

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