CN116878819B - Wind tunnel test device and method for aerodynamic characteristics of aircraft - Google Patents
Wind tunnel test device and method for aerodynamic characteristics of aircraft Download PDFInfo
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- CN116878819B CN116878819B CN202311141917.9A CN202311141917A CN116878819B CN 116878819 B CN116878819 B CN 116878819B CN 202311141917 A CN202311141917 A CN 202311141917A CN 116878819 B CN116878819 B CN 116878819B
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- 238000002474 experimental method Methods 0.000 claims description 9
- 238000005259 measurement Methods 0.000 claims description 5
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- Transportation (AREA)
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides a wind tunnel testing device and method for aerodynamic characteristics of an aircraft, which can realize the dynamic aerodynamic characteristics of the aircraft and the aerodynamic characteristics test under the condition of high maneuvering and large attitude angle change. The invention is based on a triaxial rotation actuating mechanism, an aircraft in a fixed wind tunnel test is installed, steady-state aerodynamic characteristic test of the aircraft under a specified attitude working condition and dynamic aerodynamic characteristic test of the aircraft under a triaxial rotation specified transient working condition are realized through motion control of the actuating mechanism, and aerodynamic characteristic test of the aircraft with larger yaw angle, roll angle and pitch angle variation range is realized through the design of the triaxial mechanism.
Description
Technical Field
The invention relates to the technical field of aerodynamic performance testing of aircrafts, in particular to an aerodynamic performance wind tunnel testing device and method of an aircraft.
Background
The aerodynamic properties of an aircraft are key elements that need to be considered for its design development and motion control. Accurate computational simulation of aerodynamic properties of an aircraft has also been difficult to achieve. Therefore, wind tunnel experimental tests of the aircraft solid model are required to be carried out in the development stage of the aircraft to obtain aerodynamic characteristics of the aircraft solid model. The current wind tunnel experimental method for the aircraft is that a special fixture for the aircraft is installed and fixed in a wind tunnel, a pneumatic balance (six-component sensor) is arranged in an aircraft cabin, the pneumatic six-component force of the aircraft is measured by the pneumatic balance under the specified attitude (pitch angle, yaw angle, roll angle and the like) and steady-state conditions of the aircraft under the given wind speed, and therefore the steady-state pneumatic characteristic of the aircraft is obtained. The existing aircraft aerodynamic characteristic testing method has the following defects:
1) The aircraft is always in an unsteady dynamic pneumatic stress state in operation, and the dynamic pneumatic characteristics of the aircraft cannot be obtained by using the existing device and method;
2) The existing device is limited by the installation and fixation modes, the range of the attitude angle of the aircraft can be smaller, and the aerodynamic characteristic test of the aircraft under the condition of high maneuver under the condition of large attitude angle change can not be realized.
Disclosure of Invention
In view of the above, the invention provides a wind tunnel testing device and a wind tunnel testing method for aerodynamic characteristics of an aircraft, which can realize the dynamic aerodynamic characteristics of the aircraft and the aerodynamic characteristics test under the condition of large attitude angle change under the high maneuvering condition.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the wind tunnel testing device for the aerodynamic characteristics of the aircraft comprises a triaxial rotary actuating mechanism, a pneumatic balance and a base, wherein the triaxial rotary actuating mechanism comprises a yaw angle moving ring, a pitch angle moving ring, a roll angle moving shaft, a motor and an angle sensor; the roll angle moving shaft is connected and arranged at the inner side of the pitch angle moving ring through a motor, and can rotate around the rotating axis of the motor; an angle sensor is arranged in the motor and used for controlling the movement of the motor and measuring the angle of the transverse rolling angle movement shaft; the aircraft is rigidly connected with the roll angle movement shaft through the pneumatic balance, so that the pneumatic balance measures pneumatic six-component force applied to the aircraft in a wind tunnel experiment.
The invention also provides a wind tunnel test method for the aerodynamic characteristics of the aircraft, which adopts the device to test the steady-state aerodynamic characteristics of the aircraft and comprises the following steps:
the method comprises the steps of installing and fixing an aircraft in a wind tunnel, adjusting and setting the aircraft to a specified attitude angle through controlling the output angle of a motor under a given wind speed, braking to lock the attitude angle after the motor reaches a specified corner position, measuring pneumatic six component force of the aircraft through a pneumatic balance, changing the attitude angle, repeating the process, gradually obtaining the pneumatic six component force of the aircraft under various attitude angle combinations, and obtaining a steady-state pneumatic characteristic curve of the aircraft through curve fitting.
The pneumatic characteristic steady-state test is characterized in that a certain attitude angle is single-changed, or three attitude angles are combined in pairs or three attitude angles are combined integrally; in the experiment, the angles of all control surfaces of the aircraft are changed, pneumatic six-component force applied to the aircraft under corresponding working conditions is measured, and a corresponding pneumatic characteristic curve is obtained.
The invention relates to a wind tunnel test method for aerodynamic characteristics of an aircraft, which adopts the device to test the dynamic aerodynamic characteristics of the aircraft and comprises the following steps: the method comprises the following steps of installing and fixing an aircraft in a wind tunnel, and measuring dynamic aerodynamic characteristics on the basis of steady-state aerodynamic characteristic test, wherein the method comprises the following specific steps of:
the dynamic input of the attitude angle is realized by controlling the regulating motors of the three attitude angles, so that the aircraft can perform the motion of any waveform of step, sine, square wave, sweep frequency and random signal of the pitch angle, synchronously acquire and measure the pneumatic six component force born by the aircraft, and process the experimental data obtained by measurement to obtain the dynamic pneumatic characteristic parameters and characteristic curves of the aircraft;
and measuring dynamic aerodynamic characteristics of the roll angle and the yaw angle in the same way to obtain an aerodynamic characteristic curve and characteristic parameters of corresponding working conditions.
And testing dynamic aerodynamic characteristics of the combined working conditions of the three attitude angles or the combined working conditions of the three attitude angles.
Advantageous effects
1. The device is based on a triaxial rotation actuating mechanism, an aircraft in a fixed wind tunnel test is installed, steady-state aerodynamic characteristic test of the aircraft under a specified attitude working condition and dynamic aerodynamic characteristic test of the aircraft under a triaxial rotation specified transient working condition are realized through motion control of the actuating mechanism, and aerodynamic characteristic test of the aircraft with a larger yaw angle, roll angle and pitch angle change range is realized through the design of the triaxial mechanism. The motor actuation attitude angle setting based on the triaxial rotation actuating device can efficiently realize working condition switching and automatic rapid adjustment of the steady-state aerodynamic characteristic test of the aircraft, and improve experimental efficiency and test precision. The steady-state and dynamic aerodynamic characteristic test in the wind tunnel experiment of the aircraft is realized through the motion control of the attitude angle adjusting motor, the aerodynamic experimental data of the aircraft are obtained, experimental data support is provided for the determination of the relevant characteristic parameters of speed and acceleration in the aerodynamic torque coefficient expression, and the accurate expression of the aerodynamic characteristic of the aircraft under all working conditions is realized.
2. The method is based on a triaxial rotation actuating mechanism, an aircraft in a fixed wind tunnel test is installed, steady-state aerodynamic characteristic test of the aircraft under a specified attitude working condition and dynamic aerodynamic characteristic test of the aircraft under a triaxial rotation specified transient working condition are realized through motion control of the actuating mechanism, and aerodynamic characteristic test of the aircraft with a larger yaw angle, roll angle and pitch angle change range is realized through design of the triaxial mechanism.
3. According to the method, based on the motor actuation attitude angle setting of the triaxial rotary actuation device, the working condition switching and automatic rapid adjustment of the steady-state aerodynamic characteristic test of the aircraft can be efficiently realized, and the experimental efficiency and the testing precision are improved. The steady-state and dynamic aerodynamic characteristic test in the wind tunnel experiment of the aircraft is realized through the motion control of the attitude angle adjusting motor, the aerodynamic experimental data of the aircraft are obtained, experimental data support is provided for the determination of the relevant characteristic parameters of speed and acceleration in the aerodynamic torque coefficient expression, and the accurate expression of the aerodynamic characteristic of the aircraft under all working conditions is realized.
Drawings
FIG. 1 is a schematic diagram of an aircraft wind tunnel experimental device of the present invention;
FIG. 2 is a schematic view of an aircraft pneumatic balance mounting connection of the present invention;
FIG. 3 is a schematic diagram of an experimental view of aerodynamic characteristics of a pitch (angle of attack) attitude of an aircraft according to the present invention;
FIG. 4 is a schematic diagram of an experimental aerodynamic performance of a roll attitude of an aircraft according to the present invention;
FIG. 5 is a schematic illustration of an experimental schematic of aerodynamic characteristics of a yaw attitude of an aircraft according to the present invention;
FIG. 6 is a schematic diagram of an experimental schematic diagram of aerodynamic characteristics of a composite attitude of an aircraft according to the present invention;
fig. 7 is a schematic view of an aircraft attitude adjustment actuation motor of the present invention.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The aerodynamic performance wind tunnel test device for the aircraft is based on the triaxial rotation actuating mechanism, the aircraft in the fixed wind tunnel test is installed, steady-state aerodynamic performance test of the aircraft under the specified attitude working condition and dynamic aerodynamic performance test of the aircraft under the triaxial rotation specified transient working condition are realized through the motion control of the actuating mechanism, and aerodynamic performance test of the aircraft with larger yaw angle, roll angle and pitch angle change range is realized through the design of the triaxial mechanism.
The wind tunnel testing device for aerodynamic characteristics of the aircraft, as shown in fig. 1, comprises a triaxial rotary actuating mechanism, a pneumatic balance and a base 1, wherein the triaxial rotary actuating mechanism comprises a yaw angle moving ring 2, a pitch angle moving ring 5, a roll angle moving shaft 8 and a motor and an angle sensor which are connected with the yaw angle moving ring 2, the pitch angle moving ring 5 and the roll angle moving shaft.
The base 1 is arranged and fixed in an aerodynamic wind tunnel, and the outline of the frame is slightly larger than the outline of the section of the wind tunnel wind cylinder, so that the base is not affected by experimental wind pressure and does not interfere with an experimental wind field; the base 1 is rotationally hinged with the yaw angle moving ring 2 through a first motor 3 at the upper end and the lower end of the yaw angle moving ring 2, so that the upper rotating shaft and the lower rotating shaft are coaxial, the yaw angle moving ring 2 can rotationally move around a vertical shaft AB, and a first angle sensor 4 (shown in figure 7) is arranged in the first motor 3 and used for controlling the movement of the motor and measuring the angle of the yaw angle moving ring 2; and similarly, a pitch angle moving ring 5 is arranged on the inner side of the yaw angle moving ring 2, and the yaw angle moving ring 2 and the pitch angle moving ring 5 are rotatably hinged through two second motors 6 arranged on a CD axis perpendicular to the AB axis, so that the pitch angle moving ring 5 can rotate around the CD axis. The AB shaft is a rotating shaft which rotates around the yaw angle motion, and the shaft is a rotating shaft which rotates around a stator of the rotor of the first motor 3; the CD axis is the axis of rotation about which the pitch motion rotates, i.e. the axis of rotation about which the rotor of the second motor 6 rotates about its stator.
In order to reduce the influence of the pitching moving ring 5 on the experimental wind field, part of the pitching moving ring 5 is eliminated to form a non-complete ring, and a second angle sensor 7 ((as shown in fig. 7)) is also arranged in the second motor 6 for motor motion control and angle measurement of the pitching moving ring 5; further, a roll angle moving shaft 8 is installed at the inner side of the pitch angle moving ring 5, and the pitch angle moving ring 5 and the roll angle moving shaft 8 are connected through a third motor 9, so that the roll angle moving shaft 8 can rotate around a rotating axis EF of the third motor 9, and the EF is a rotating shaft around which the roll angle moving shaft rotates, and the shaft is a rotating shaft around which a rotor of the third motor 9 rotates around a stator of the third motor. A third angle sensor 10 (fig. 7) is likewise installed in the third motor 9 for motor movement control, as well as for angle measurement of the roll angular movement axis 8; the aircraft 11 is further rigidly connected with the roll angle motion shaft 8 through the pneumatic balance 12, so that the pneumatic balance 12 can measure pneumatic six-component force applied to the aircraft in a wind tunnel experiment.
Based on the testing device, the invention provides a wind tunnel testing method for aerodynamic characteristics of an aircraft, which comprises the following steps of testing steady-state aerodynamic characteristics of the aircraft and testing dynamic aerodynamic characteristics of the aircraft:
1. aircraft steady-state aerodynamic performance testing:
the aircraft is installed and fixed in a wind tunnel in the mode shown in figure 1, the aircraft is adjusted and set to a specified attitude angle by controlling the output angle of a motor under a given wind speed, the motor is braked to lock the attitude angle after reaching a specified corner position, further the pneumatic six-component force applied to the aircraft is measured by a pneumatic balance, the attitude angle is changed, the process is repeated, the pneumatic six-component force of the aircraft under various attitude angle combinations is gradually obtained, and a steady pneumatic characteristic curve of the aircraft can be obtained through curve fitting.
The aerodynamic steady-state test can be a single change of a certain attitude angle, such as a aerodynamic steady-state test under a pitch angle attitude change (fig. 3), a aerodynamic steady-state test under a roll angle attitude change (fig. 4), a aerodynamic steady-state test under a yaw angle attitude change (fig. 5), or a combination of two by two or an integral combination of three attitude angles (fig. 6). In the experiment, the angles of the control surfaces of the aircraft can be changed to measure pneumatic six-component force applied to the aircraft under the corresponding working condition, and a corresponding pneumatic characteristic curve is obtained.
2. Test of dynamic aerodynamic characteristics of an aircraft:
the aircraft is installed and fixed in the wind tunnel as shown in fig. 1, and the dynamic aerodynamic characteristics are measured on the basis of the steady-state aerodynamic characteristic test. The dynamic input of the attitude angle is realized by controlling the three attitude angle adjusting motors, for example, the dynamic input (angle, angular speed or angular acceleration) of the pitch angle of the aircraft is realized by driving the pitch angle moving ring by the motors, the aircraft can perform the motion of any waveform such as step, sine, square wave, sweep frequency, random signal and the like of the pitch angle, the pneumatic six component force applied to the aircraft is synchronously collected and measured, and the experimental data obtained by measurement are processed to obtain the dynamic pneumatic characteristic parameters and characteristic curves of the aircraft.
The method can be used for measuring the dynamic aerodynamic characteristics of the roll angle and the yaw angle in the same way, and obtaining the aerodynamic characteristic curves and characteristic parameters of corresponding working conditions. Further, the dynamic aerodynamic characteristics of the three attitude angles can be tested in a pairwise compound or three attitude angle integral compound working condition.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The wind tunnel testing device for the aerodynamic characteristics of the aircraft is characterized by comprising a triaxial rotary actuating mechanism, a pneumatic balance and a base, wherein the triaxial rotary actuating mechanism comprises a yaw angle moving ring, a pitch angle moving ring, a roll angle moving shaft, a motor and an angle sensor; the roll angle moving shaft is connected and arranged at the inner side of the pitch angle moving ring through a motor, and can rotate around the rotating axis of the motor; an angle sensor is arranged in the motor and used for controlling the movement of the motor and measuring the angle of the transverse rolling angle movement shaft; the aircraft is rigidly connected with the roll angle movement shaft through the pneumatic balance, so that the pneumatic balance measures pneumatic six-component force applied to the aircraft in a wind tunnel experiment.
2. A method for testing aerodynamic properties of an aircraft, wherein the steady-state aerodynamic properties of the aircraft are tested by the device of claim 1, comprising the steps of:
the method comprises the steps of installing and fixing an aircraft in a wind tunnel, adjusting and setting the aircraft to a specified attitude angle through controlling the output angle of a motor under a given wind speed, braking to lock the attitude angle after the motor reaches a specified corner position, measuring pneumatic six component force of the aircraft through a pneumatic balance, changing the attitude angle, repeating the process, gradually obtaining the pneumatic six component force of the aircraft under various attitude angle combinations, and obtaining a steady-state pneumatic characteristic curve of the aircraft through curve fitting;
the pneumatic characteristic steady-state test is characterized in that a certain attitude angle is single-changed, or three attitude angles are combined in pairs or three attitude angles are combined integrally; in the experiment, the angles of all control surfaces of the aircraft are changed, pneumatic six-component force applied to the aircraft under corresponding working conditions is measured, and a corresponding pneumatic characteristic curve is obtained.
3. A method for testing aerodynamic properties of an aircraft, wherein the method for testing aerodynamic properties of an aircraft comprises the steps of: the method comprises the following steps of installing and fixing an aircraft in a wind tunnel, and measuring dynamic aerodynamic characteristics on the basis of steady-state aerodynamic characteristic test, wherein the method comprises the following specific steps of:
the dynamic input of the attitude angle is realized by controlling the regulating motors of the three attitude angles, so that the aircraft can perform the motion of any waveform of step, sine, square wave, sweep frequency and random signal of the pitch angle, synchronously acquire and measure the pneumatic six component force born by the aircraft, and process the experimental data obtained by measurement to obtain the dynamic pneumatic characteristic parameters and characteristic curves of the aircraft;
measuring dynamic aerodynamic characteristics of the roll angle and the yaw angle in the same way to obtain an aerodynamic characteristic curve and characteristic parameters of corresponding working conditions;
and carrying out the dynamic aerodynamic characteristic test of the combined working conditions of the three attitude angles or the combined working conditions of the three attitude angles.
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