CN116929702B - Aerodynamics test balance device and test method for aircraft - Google Patents
Aerodynamics test balance device and test method for aircraft Download PDFInfo
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- CN116929702B CN116929702B CN202311190144.3A CN202311190144A CN116929702B CN 116929702 B CN116929702 B CN 116929702B CN 202311190144 A CN202311190144 A CN 202311190144A CN 116929702 B CN116929702 B CN 116929702B
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- 238000012360 testing method Methods 0.000 title claims abstract description 51
- 238000010998 test method Methods 0.000 title abstract description 4
- 238000005259 measurement Methods 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims description 4
- 230000009977 dual effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 7
- 238000005096 rolling process Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Classifications
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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
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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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
Abstract
The invention provides an aircraft pneumatic characteristic test balance device and a test method, wherein the integral six-component force measuring device is decomposed into a combination of a three-component force sensor and one or more single-component force sensors, or a combination of a three-component force sensor and a two-component force sensor, the structure is simple, and three component force and 1-3 component force can be measured by selecting corresponding three component force plus N single-component force sensors according to the requirements of the aircraft pneumatic test working condition. The design difficulty and cost of the pneumatic balance are reduced, and the calibration difficulty and workload of the sensor are also reduced.
Description
Technical Field
The invention relates to the technical field of aerodynamic performance testing of aircrafts, in particular to a machine testing method of an aerodynamic performance testing balance device of an aircraft.
Background
Aerodynamic characteristics are the key of aircraft design, and the aerodynamic characteristics of an aircraft cannot be accurately obtained through theoretical calculation at present. In the design and development of the aircraft, the scaling model is required to be applied to experimental test and verification of aerodynamic characteristics in the wind tunnel. The aerodynamic characteristic experiment needs to connect and fix a multiaxial force (moment) sensor for measuring aerodynamic six-component force on an aircraft physical model, and the aerodynamic balance is generally formed. In order to reduce the influence of the appearance of the sensor on aerodynamic stress, a pneumatic balance is generally installed and fixed in the cabin or the tail of an aircraft, and the shape of the pneumatic balance is generally columnar. The sensor for realizing six-component force sensing measurement in a narrow space is high in design difficulty, high in resolution (decoupling) difficulty of the six-component force and high in sensor calibration difficulty. Thus, current pneumatic balance products are expensive to manufacture. The existing pneumatic balance is high in cost and difficult to calibrate.
Disclosure of Invention
In view of the above, the invention provides an aircraft aerodynamic characteristic test balance device and a test method, which can reduce the design difficulty and cost of an aerodynamic balance and reduce the calibration difficulty and workload of a sensor.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the utility model provides an aircraft pneumatic characteristics test balance device, includes three minute force transducer, three minute force transducer connecting blocks, single component force or two minute force transducer and linking arm, and three minute force transducer bottom is connected by three minute force transducer connecting blocks and is fixed in the aircraft cabin, and the other end is with one side fixed connection of single component force or two minute force transducer, and single component force transducer or two minute force transducer other end and linking arm fixed connection, and the linking arm is connected with follow-up test base.
Wherein the single component force or the two component force sensor is a beam-shaped sensor.
The device comprises a three-component force sensor and a single-component force sensor, wherein the three-component force sensor and the single-component force sensor are mechanically fixedly connected, the mounting angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Z-axis direction of the three-component force sensor, a force couple formed by forces Fsz born by two ends of the single-component force sensor forms the pitching moment of the aircraft, and the force value obtained by measuring the single-component force sensor is multiplied by the pitching moment born by the corresponding pitching moment arm Dry in the aerodynamic test of the aircraft.
The device comprises a three-component force sensor and two single-component force sensors, wherein the three force sensors are mechanically and fixedly connected, the two single-component force sensors are symmetrically arranged on two sides by taking an X axis of the three-component force sensor as a center, the installation angle ensures that the stress direction of the two single-component force sensors is consistent with the Z axis direction of the three-component force sensor, and the force obtained by measurement of the two single-component force sensors is multiplied by a transverse rolling force arm Drx respectively and then added to be the transverse rolling moment of the aircraft in pneumatic test.
The force obtained by measurement of the two single-component force sensors is multiplied by the same pitch moment arm Dry and then added to obtain the pitch moment applied to the aerodynamic test of the aircraft.
The device comprises a three-component force sensor and a single-component force sensor, wherein the three-component force sensor and the single-component force sensor are mechanically fixedly connected, the mounting angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Y-axis direction of the three-component force sensor, a force couple formed by the forces born by the two ends of the single-component force sensor forms the yaw moment of the aircraft, and the force value obtained by measuring the single-component force sensor is multiplied by the yaw moment arm Drz to be the yaw moment born by the aircraft in the pneumatic test.
The single component force sensor is used for measuring and obtaining the force multiplied by the transverse rolling force arm Drx to obtain the transverse rolling moment applied to the aerodynamic test of the aircraft.
The device comprises a three-component force sensor and a two-component force sensor, wherein the three-component force sensor and the two-component force sensor are mechanically fixedly connected, the mounting angles of the two-component force sensor ensure that the stress direction of the two-component force sensor is consistent with the Y-axis direction and the Z-axis direction of the three-component force sensor, the force born by the outer side end part of the two-component force sensor takes moment to the center point of the three-component force sensor to form yaw moment, roll moment and pitching moment of an aircraft, the Y-direction force Fsy obtained by measurement of the two-component force sensor is multiplied by a yaw moment arm Drz to obtain the yaw moment, the Y-direction force Fsy is multiplied by a roll moment arm Drx to obtain the roll moment, and the Z-direction force Fsz is multiplied by a yaw moment arm Drz to obtain the yaw moment.
The invention also provides a method for testing aerodynamic characteristics of the aircraft, which adopts the device of the invention to measure and acquire various component forces, and obtains corresponding component forces or moments through mechanical calculation to realize measurement of aerodynamic six component forces.
Advantageous effects
1. When the device is used for measuring, the pneumatic six-component force of the aircraft is tested by using the combination of the simple three-component force, the simple two-component force and the simple single-component force sensor, so that the experimental cost is greatly reduced on the premise of ensuring the test precision, each sensor can be calibrated independently, and the calibration workload of the system is reduced.
2. The device provided by the invention decomposes the integral six-component force measuring device into a combination of a three-component force sensor and a plurality of single-component force sensors, has a simple structure, and can select corresponding three-component force plus N single-component force sensors to realize measurement of three-component force and 1-3 component force moment according to the aerodynamic test working condition requirement of the aircraft. The design difficulty and cost of the pneumatic balance are reduced, and the calibration difficulty and workload of the sensor are also reduced.
3. The measuring method of the invention adopts three-component force sensor and a plurality of single-component force sensor to realize the measurement of pneumatic six-component force of the aircraft, and is reliable and has small calibration quantity.
4. When the method is used for measuring, the combination of simple three-component force, two-component force and single-component force sensors is used for realizing the pneumatic six-component force test of the aircraft, the experimental cost is greatly reduced on the premise of ensuring the test precision, each sensor can be calibrated independently, and the calibration workload of the system is reduced.
Drawings
FIG. 1 is a schematic view of an aircraft aerodynamic property test balance device of the present invention.
Fig. 2 is a schematic diagram of a pneumatic three-component and pitching moment test in an embodiment of the present invention.
Fig. 3 is a schematic diagram of pneumatic three component and roll and pitch moment testing in an embodiment of the present invention.
Fig. 4 is a schematic diagram of a pneumatic three component and roll and yaw moment test in an embodiment of the present invention.
Fig. 5 is a schematic diagram of pneumatic three component and roll, yaw and pitch moment testing in an embodiment 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 pneumatic characteristic test balance device for the aircraft breaks down the integral six-component force measuring device into a combination of a three-component force sensor and one or more single-component force sensors, or a combination of the three-component force sensor and one two-component force sensor, and can select corresponding three-component force plus N single-component force sensors to realize measurement of three-component force and 1-3 component moment according to the pneumatic test working condition requirement of the aircraft. The invention not only reduces the design difficulty and cost of the pneumatic balance, but also reduces the calibration difficulty and workload of the sensor. In a non-orthogonal connection mode of each axis of the traditional multi-axis test balance, the non-decoupling of each axis is measured, and a large number of inter-axis coupling coefficients need to be measured and calibrated.
The invention relates to an aircraft pneumatic characteristic test balance device, which is shown in figure 1, and comprises an aircraft shell 1, a three-component force sensor connecting block 2, a three-component force sensor 3, a single-component force sensor or a two-component force sensor 4 (shown in figure 5) and a single-component force sensor or two-component force sensor connecting arm 5, wherein the bottom end of the three-component force sensor 3 is fixedly connected with an aircraft cabin through the three-component force sensor connecting block 2, the other end of the three-component force sensor is fixedly connected with one side of the single-component force sensor or the two-component force sensor 4, the other end of the single-component force sensor (or the two-component force sensor) is fixedly connected with the connecting arm 5, and the connecting arm 5 is connected with a subsequent test base. The three-component force sensor is mechanically fixedly connected with a plurality of single-component force (or two-component force) sensors, on the basis of three-component force measurement, the corresponding directional force is measured by the single-component force sensor, and the designated directional moment is obtained by mechanical calculation, so that the pneumatic six-component force (three-component force and three-component moment) measurement is realized. Wherein the single component force (or two component force) sensor is a beam-shaped sensor.
Example 1: in this embodiment, the pneumatic tri-component and pitching moment test is shown in fig. 2. In the integral six-component force measuring device, a three-component force sensor is mechanically fixedly connected with a single-component force sensor, the mounting angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Z-axis direction of the three-component force sensor, and a force couple formed by forces Fsz born by two ends of the single-component force sensor forms the pitching moment of the aircraft, namely, the force value obtained by measurement of the single-component force sensor is multiplied by the pitching moment born by the corresponding pitching moment arm Dry in the aerodynamic test of the aircraft.
Example 2: in the pneumatic three-component force and roll moment and pitching moment test in the embodiment, as shown in fig. 3, in the integral six-component force measuring device, one three-component force sensor is mechanically fixedly connected with two single-component force sensors, the two single-component force sensors are symmetrically arranged on two sides by taking the X axis of the three-component force sensor as a center, the mounting angle ensures that the stress direction of the two single-component force sensors is consistent with the Z axis direction of the three-component force sensor, and the forces obtained by measurement of the two single-component force sensors are multiplied by the roll moment arm Drx and added to obtain the roll moment of the aircraft in the pneumatic test. In addition, the force obtained by measurement of the two single-component force sensors is multiplied by the same pitch moment arm Dry and then added to obtain the pitch moment applied to the aerodynamic test of the aircraft.
Example 3: in the test of pneumatic three-component force, rolling moment and yaw moment in the embodiment, as shown in fig. 4, in the integral six-component force measuring device, one three-component force sensor is mechanically connected with one single-component force sensor, the installation angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Y-axis direction of the three-component force sensor, and a couple formed by the forces born by the two ends of the single-component force sensor forms the yaw moment of the aircraft, namely, the yaw moment born by the pneumatic test of the aircraft is obtained by multiplying the force value obtained by the measurement of the single-component force sensor by the yaw moment arm Drz.
In addition, the single component force sensor measures the acquired force and multiplies the roll force arm Drx to obtain the roll moment applied to the aerodynamic test of the aircraft.
Example 4: in the test of pneumatic three-component force and roll moment, yaw moment and pitch moment in the embodiment, as shown in fig. 5, in the integral six-component force measuring device, one three-component force sensor is mechanically connected with one two-component force sensor, the mounting angles of the two-component force sensors ensure that the stress directions of the two-component force sensors are consistent with the Y-axis and Z-axis directions of the three-component force sensor, and the forces born by the outer end parts of the two-component force sensors take moments towards the center points of the three-component force sensors to form yaw moment, roll moment and pitch moment of the aircraft, namely, the yaw moment is obtained by multiplying the Y-direction force Fsy obtained by measuring the two-component force sensor by the yaw moment arm Drz, the roll moment is obtained by multiplying the Y-direction force Fsy by the roll moment arm Drx, and the yaw moment is obtained by multiplying the Z-direction force Fsz by the yaw moment arm Drz.
Based on the testing device, the invention provides an aircraft aerodynamic characteristic testing method, which comprises the following specific embodiments:
according to the pneumatic characteristic test working condition requirement, the integral six-component force measuring device is decomposed into a combination of a three-component force sensor and one or more single-component force sensors, or a combination of a three-component force sensor and a two-component force sensor, the three-component force sensor is mechanically fixedly connected with a plurality of single-component force (or two-component force) sensors, on the basis of three-component force measurement, the corresponding directional force is measured by the single-component force sensor, and the designated directional moment is obtained by mechanical calculation, so that the pneumatic six-component force (three-component force and three-component moment) measurement is realized.
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 aerodynamics characteristic test balance device of the aircraft is characterized by comprising a three-component force sensor, a three-component force sensor connecting block, a single component force sensor or a two-component force sensor and a connecting arm, wherein the bottom end of the three-component force sensor is fixedly connected with an aircraft cabin through the three-component force sensor connecting block, the other end of the three-component force sensor is fixedly connected with one side of the single component force sensor or the two-component force sensor, the other end of the single component force sensor or the two-component force sensor is fixedly connected with the connecting arm, and the connecting arm is connected with a subsequent test base;
the device comprises a three-component force sensor and a single-component force sensor, wherein the three-component force sensor and the single-component force sensor are mechanically fixedly connected, the mounting angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Z-axis direction of the three-component force sensor, a force couple formed by the forces born by the two ends of the single-component force sensor forms the pitching moment of the aircraft, and the force value obtained by measurement of the single-component force sensor is multiplied by the corresponding pitching moment arm to be the pitching moment born by the aircraft in the pneumatic test;
the device comprises a three-component force sensor and two single-component force sensors, wherein the three force sensors are mechanically and fixedly connected, the two single-component force sensors are symmetrically arranged on two sides by taking an X axis of the three-component force sensor as a center, the installation angle ensures that the stress direction of the two single-component force sensors is consistent with the Z axis direction of the three-component force sensor, and the forces obtained by measurement of the two single-component force sensors are multiplied by a roll moment arm respectively and added to be roll moment of an aircraft in pneumatic test; the force obtained by measurement of the two single-component force sensors is multiplied by the same pitching moment arm and then added to obtain pitching moment received in aerodynamic test of the aircraft;
the device comprises a three-component force sensor and a single-component force sensor, wherein the three-component force sensor and the single-component force sensor are mechanically fixedly connected, the installation angle of the single-component force sensor ensures that the stress direction of the single-component force sensor is consistent with the Y-axis direction of the three-component force sensor, a force couple formed by the forces born by the two ends of the single-component force sensor forms the yaw moment of the aircraft, and the force value obtained by measuring the single-component force sensor is multiplied by the yaw moment arm to be the yaw moment born by the aircraft in the pneumatic test; the single component force sensor is used for measuring and obtaining force multiplied by a roll force arm to obtain roll moment received in pneumatic test of the aircraft;
the device comprises a three-component force sensor and a two-component force sensor, wherein the three-component force sensor and the two-component force sensor are mechanically fixedly connected, the mounting angles of the two-component force sensor ensure that the stress direction of the two-component force sensor is consistent with the directions of a Y axis and a Z axis of the three-component force sensor, the force born by the outer side end part of the two-component force sensor is taken to the center point of the three-component force sensor to form yaw moment, roll moment and pitching moment of the aircraft, the Y-directional force obtained by measurement of the two-component force sensor is multiplied by the yaw moment to obtain the yaw moment, the Y-directional force is multiplied by the roll moment to obtain the roll moment, and the Z-directional force is multiplied by the yaw moment to obtain the yaw moment.
2. The apparatus of claim 1, wherein the single or dual force sensor is a beam sensor.
3. A method for testing aerodynamic characteristics of an aircraft, characterized in that the device according to any one of claims 1-2 is used for measuring and obtaining component forces, and corresponding component forces or moments are obtained through mechanical resolution, so that measurement of aerodynamic six component forces is realized.
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