CN114813002B - Ground vibration mode testing method for large airplane - Google Patents
Ground vibration mode testing method for large airplane Download PDFInfo
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- CN114813002B CN114813002B CN202210732923.0A CN202210732923A CN114813002B CN 114813002 B CN114813002 B CN 114813002B CN 202210732923 A CN202210732923 A CN 202210732923A CN 114813002 B CN114813002 B CN 114813002B
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- 238000012360 testing method Methods 0.000 title claims abstract description 225
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- 230000005284 excitation Effects 0.000 claims description 113
- 238000005452 bending Methods 0.000 claims description 63
- 230000001133 acceleration Effects 0.000 claims description 36
- 230000004044 response Effects 0.000 claims description 31
- 238000000034 method Methods 0.000 claims description 8
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
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- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a ground vibration mode testing method for a large airplane, which comprises the following steps: 1. mounting a sensor on the test airplane; 2. simulating the air suspension state of the airplane; 3. arranging and installing a vibration exciter on the test airplane; 4. debugging a system; 5. testing the main body mode of the test airplane; 6. each control surface mode of the test aircraft was tested. The invention has strong applicability, can be effectively applied to the full-size ground resonance test of the large-scale airplane, can coordinate and excite vibration at each part of the airplane body through the number and the combination mode of a plurality of different vibration exciters, improves the test efficiency of modal parameters of the large-scale airplane, can effectively solve the problems of the full-size ground vibration test of the large-scale airplane, such as large wing deformation, intensive low-frequency modal, nonlinear structure and the like, and further improves the precision of the test result by optimizing the position and the size of the exciting force.
Description
Technical Field
The invention belongs to the technical field of airplane vibration testing, and particularly relates to a ground vibration mode testing method for a large airplane.
Background
With the rapid development of the aviation field, the carrying requirements of each field are increasing day by day, and new requirements such as large load, long endurance and the like are provided for the airplane. The large-scale airplane greatly improves the carrying capacity in the military and civil fields, adopts brand-new design in the aspects of overall size, aerodynamic appearance, body structure and the like, and has the characteristics of large size, large weight, large aspect ratio wings and the like. Large aircraft generally refers to transport aircraft with total takeoff weight over 100 tons, including large military and civil transport aircraft, and also including military aircraft with a flight distance of 3000 km.
The full-size ground vibration test is an important verification test in the process of aircraft development, is developed before the first flight of the aircraft, and tests the dynamic parameters of the aircraft, such as resonance frequency, vibration mode, damping ratio, generalized mass and the like, by means of the onboard ground test, thereby providing key data support for aircraft dynamic model modification, flight control system design and aircraft flutter test flight and providing important technical support for the successful first flight of the aircraft.
The traditional modal test mainly aims at small and medium-sized airplanes, adopts simple exciting force configuration, arranges an exciting force on each part, and can obtain relevant modal parameters of an airplane body through frequency modulation and force adjustment. The large-scale airplane is large in scale, large in size and complex in structural form, great difficulty and challenge are brought to a full-size ground vibration test, and the traditional excitation force configuration method cannot meet the test requirements of the large-scale airplane. When the exciting forces are arranged, the problems of large deformation of wings, dense low-frequency modes, structural nonlinearity and the like need to be considered, and the combination and phase relation of different exciting forces among all parts also need to be coordinated, so that a reasonable exciting force configuration needs to be provided for carrying out modal testing on the airplane.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a ground vibration mode testing method for a large airplane, which has strong applicability, can be effectively applied to a full-size ground resonance test of the large airplane, can coordinate vibration excitation at each part of a machine body through the number and combination mode of a plurality of different vibration exciters, improves the testing efficiency of modal parameters of the large airplane, and can effectively solve the problems of the full-size ground vibration test of the large airplane, such as large wing deformation, dense low-frequency modes, nonlinear structure and the like, by optimizing the position and the size of an excitation force, thereby improving the precision of the test result.
In order to solve the technical problems, the invention adopts the technical scheme that: a ground vibration mode testing method for a large airplane is characterized by comprising the following steps:
step one, installing a sensor on a test airplane: installing a plurality of acceleration sensors at each test part of a test airplane body, and connecting the acceleration sensors, a data acquisition unit and a test computer in sequence to form a test system;
wherein, each test part of the body of the test airplane comprises a wing, a fuselage, a horizontal tail, a vertical tail, an engine, an inner flap, an outer flap, an aileron, an elevator and a rudder, and acceleration sensors are arranged on the wing, the fuselage, the horizontal tail, the vertical tail, the engine, the inner flap, the outer flap, the aileron, the elevator and the rudder;
simulating the air suspension state of the airplane;
step three, arranging and installing vibration exciters on the test airplane: the method comprises the following steps that vibration exciters are installed on all testing parts of a test airplane body, each vibration exciter is connected with a power amplifier, a plurality of power amplifiers are connected with a force vector controller, the force vector controller is connected with a testing computer to form a vibration excitation system, and the testing system and the vibration excitation system form a testing and testing system;
step four, system debugging: adjusting the excitation phases and the excitation forces of the vibration exciters arranged at the tips of the two wings of the test airplane through a force vector controller to perform an excitation test, collecting the vibration response of the test airplane body through an acceleration sensor, and debugging the test testing system according to the measured vibration response until the whole test testing system works normally;
step five, testing the main body modes of the test airplane: sequentially adjusting the excitation phases and the excitation forces of the wings, the fuselage, the horizontal tail, the vertical tail of the test aircraft and the vibration exciters arranged on the engine through a force vector controller, carrying out excitation tests on the wings, the fuselage, the horizontal tail, the vertical tail and the bearing positions of the engine of the test aircraft, and acquiring the vibration response of the fuselage of the test aircraft through an acceleration sensor to obtain the main modes of each order of the fuselage of the test aircraft;
step six, testing the mode of each control surface of the test airplane: and sequentially adjusting the excitation phases and the excitation forces of the vibration exciters arranged on the inner flap, the outer flap, the ailerons, the elevator and the rudder of the test airplane through a force vector controller, exciting the bearing positions on the outer side of each control surface of the test airplane, and acquiring the vibration response of the test airplane body through an acceleration sensor to obtain the rotating modes of each operation surface of the test airplane body.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: in the third step, the machine head of the machine body is provided with two vibration exciters, two wings are provided with three vibration exciters, two horizontal tails are provided with three vibration exciters, the vertical tail is provided with two vibration exciters, two engines are provided with two vibration exciters, two inner wing flaps and two outer wing flaps are provided with one vibration exciter respectively, two ailerons are provided with one vibration exciter respectively, two elevators are provided with one vibration exciter respectively, and a rudder is provided with one vibration exciter;
the excitation directions of the plurality of vibration exciters are perpendicular to the surface of the airplane structure at the installation position.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: the two vibration exciters on the fuselage are respectively installed at one side of the nose and the bottom of the nose, the tip front edge, the tip top surface and the middle part of the wing are respectively installed to the three vibration exciters on the wing, the tip front edge, the tip top surface and the root of the horizontal tail are respectively installed to the three vibration exciters on the horizontal tail, the tip one side and the tip front edge of the vertical tail are respectively installed to the two vibration exciters on the vertical tail, and the bottom and one side of the engine are respectively installed to the two vibration exciters on the engine.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: and in the third step, the vibration exciter is connected with the body of the test airplane through a connecting rod and a vacuum sucker, and the vacuum sucker is connected with a vacuum negative pressure station through a rubber hose.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: in the fourth step, the vibration exciters arranged at the tips of the two wings of the test airplane have the same vibration exciting phase and simultaneously perform vibration excitation.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: in the fifth step, the tip parts of the two wings and the front positions of the middle bearing rib plates of the test airplane are simultaneously excited by changing the phase difference of the vibration exciters arranged in the middle of the two wings, so that symmetrical vertical bending and torsion modes of each step of the wings and anti-symmetrical vertical bending and torsion modes of each step of the wings are obtained;
exciting the front positions of two horizontal tail tip bearing rib plates of the test airplane simultaneously by changing the phase difference of vibration exciters arranged on the top surfaces of the two horizontal tail tip parts to obtain symmetrical vertical bending and torsion modes of each step of the horizontal tail and anti-symmetrical vertical bending and torsion modes of each step of the horizontal tail;
exciting the front position of a force bearing rib plate at the tip part of the vertical tail of the test airplane by a vibration exciter arranged at one side of the tip part of the vertical tail to obtain lateral bending and torsion modes of each step of the vertical tail;
exciting a bearing frame at the head position of the airplane body of the test airplane through two vibration exciters arranged on the airplane body respectively to obtain a vertical bending mode of each step of the airplane body and a lateral bending mode of each step of the airplane body;
and exciting the positions, close to the front, of the bearing rib plates of the two horizontal tail roots of the test airplane simultaneously by using the vibration exciters arranged on the two horizontal tail roots to obtain each-step torsional mode of the airplane body.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: in the fifth step, vibration exciters arranged at the bottoms of the two engines simultaneously excite the force bearing positions at the front parts of the two engines of the test airplane to obtain an engine symmetric pitching mode and an engine antisymmetric pitching mode;
and simultaneously exciting the force bearing positions at the front parts of the two engines of the test airplane by using the vibration exciters arranged at one side of the two engines to obtain an engine symmetrical side parallel navigation and yaw mode and an engine antisymmetric side parallel navigation and yaw mode.
The ground vibration mode testing method for the large airplane is characterized by comprising the following steps: step five, exciting the positions of the force bearing rib plates of the front edges of the two wing tip parts of the test airplane simultaneously through vibration exciters arranged on the front edges of the two wing tip parts to obtain the bending mode in each symmetrical plane of the wing and the bending mode in each anti-symmetrical plane of the wing;
exciting the positions of the force-bearing rib plates of the front edges of the two horizontal tail tip portions of the test airplane simultaneously by using vibration exciters arranged on the front edges of the two horizontal tail tip portions to obtain a bending mode in each symmetrical plane of the horizontal tail and a bending mode in each anti-symmetrical plane of the horizontal tail;
and exciting the position of the force bearing rib plate at the front edge of the tip part of the vertical tail of the test airplane by a vibration exciter arranged at the front edge of the tip part of the vertical tail to obtain the bending mode in each step surface of the vertical tail.
The invention has the advantages of strong applicability, effective application to the full-size ground resonance test of the large-scale airplane, coordinated excitation of all parts of the airplane body through the quantity and combination mode of various different exciters, improvement of the test efficiency of modal parameters of the large-scale airplane, effective solution of the full-size ground vibration test problems of the large-scale airplane, such as large wing deformation, dense low-frequency modal, nonlinear structure and the like, through optimization of the position and the size of the exciting force, and further improvement of the test result precision.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a block flow diagram of the method of the present invention.
Fig. 2 is a schematic layout of the vibration exciter of the test airplane.
Fig. 3 is a left side view of fig. 2.
Fig. 4 is a control block diagram of the present invention.
Fig. 5 is a schematic view of a connection structure of the vibration exciter and the wing.
Description of reference numerals:
1-an airfoil; 2-a fuselage; 3, flattening the tail;
4, hanging the tail; 5, an engine; 6-inner flaps;
7-outer flaps; 8-ailerons; 9-elevator;
10-rudder; 11-data collector; 12-testing computer;
13-a vibration exciter; 14-a power amplifier; 15-force vector controller;
16-an acceleration sensor; 17-a connecting rod; 18-a rubber hose;
19-vacuum chuck.
Detailed Description
1-4, a ground vibration mode testing method for a large aircraft, the method comprising the steps of:
step one, installing a sensor on a test airplane: a plurality of acceleration sensors 16 are arranged at each testing part of the body of the test airplane, and the acceleration sensors 16, the data acquisition unit 11 and the testing computer 12 are connected in sequence to form a testing system;
wherein, each test part of the body of the test airplane comprises a wing 1, a fuselage 2, a horizontal tail 3, a vertical tail 4, an engine 5, an inner flap 6, an outer flap 7, an aileron 8, an elevator 9 and a rudder 10, and acceleration sensors 16 are arranged on the wing 1, the fuselage 2, the horizontal tail 3, the vertical tail 4, the engine, the inner flap 6, the outer flap 7, the aileron 8, the elevator 9 and the rudder 10;
the acceleration sensor 16 is attached by means of bonding.
Step two, simulating the air suspension state of the airplane: a support system is adopted to support the test airplane, so that the test airplane simulates the flying state in the air;
in practical use, the supporting system is an air spring system and comprises an air bag structure for bearing the test airplane, the air bag structure is inflated, pressure generated by closed gas in the air bag structure is utilized for bearing, the air spring system is used as a soft supporting system and can generate a suspension supporting effect, and the air spring system is placed under the airplane for supporting, so that the airplane can simulate the free state of flying in the air.
Step three, arranging and installing vibration exciters on the test airplane: the method comprises the following steps that vibration exciters 13 are installed on each testing part of a test airplane body, each vibration exciter 13 is connected with a power amplifier 14, the power amplifiers 14 are connected with a force vector controller 15, the force vector controller 15 is connected with a testing computer 12 to form a vibration excitation system, and the testing system and the vibration excitation system form a testing system;
in actual use, the two vibration exciters 13 on the machine body 2 are respectively a vibration exciter F1 No. 1 mounted at the bottom of the machine head and a vibration exciter F2 No. 2 mounted at one side of the machine head, as shown in fig. 2 and 3, wherein marked F1 and F2 are the directions of the vibration exciting forces of the vibration exciters No. 1 and 2 respectively; the vibration exciters 13 on the top surfaces of the tips of the two wings 1 are respectively a No. 3 vibration exciter F3 and a No. 4 vibration exciter F4, the vibration exciters 13 in the middle of the two wings 1 are respectively a No. 5 vibration exciter F5 and a No. 6 vibration exciter F6, and the vibration exciters 13 on the front edges of the tips of the two wings 1 are respectively a No. 17 vibration exciter F17 and a No. 18 vibration exciter F18; the vibration exciters 13 on the top surfaces of the tips of the two horizontal tails 3 are respectively No. 11 vibration exciters F11 and No. 12 vibration exciters F12, the vibration exciters 13 at the roots of the two horizontal tails 3 are respectively No. 13 vibration exciters F13 and No. 14 vibration exciters F14, and the vibration exciters 13 on the front edges of the tips of the two horizontal tails 3 are respectively No. 19 vibration exciters F19 and No. 20 vibration exciters F20; the two vibration exciters 13 on the vertical tail 4 are respectively a No. 15 vibration exciter F15 arranged on one side of the tip part and a No. 16 vibration exciter F16 arranged on the front edge of the tip part; the bottom and one side of the engine 5 are respectively provided with a vibration exciter 13, the vibration exciters 13 at the bottom of the two engines 5 are respectively a No. 7 vibration exciter F7 and a No. 8 vibration exciter F8 at the front edge of the tip part, and the vibration exciters 13 at one side of the two engines 5 are respectively a No. 9 vibration exciter F9 and a No. 10 vibration exciter F10 at the front edge of the tip part; the exciters 13 on the two inner flaps 6 are 25 # exciters F25 and 26 # exciters F26, the exciters 13 on the two outer flaps 7 are 23 # exciters F23 and 24 # exciters F24, the exciters 13 on the two ailerons 8 are 21 # exciters F21 and 22 # exciters F22, the exciters 13 on the two elevators 9 are 27 # exciters F27 and 28 # exciters F28, and the exciters 13 on the rudder 10 are 29 # exciters F29.
It should be noted that the vibration exciters 13 on the two wings 1 are symmetrically arranged, the vibration exciters 13 on the two horizontal tails 3 are symmetrically arranged, the vibration exciters 13 on the two engines 5 are symmetrically arranged, the vibration exciters 13 on the two inner flaps 6 are symmetrically arranged, the vibration exciters 13 on the two outer flaps 7 are symmetrically arranged, the vibration exciters 13 on the two ailerons 8 are symmetrically arranged, and the vibration exciters 13 on the two elevators 9 are symmetrically arranged.
In specific implementation, the power amplifier 14 corresponding to the vibration exciter F1 No. 1 is the power amplifier No. 1, the power amplifier 14 corresponding to the vibration exciter F2 No. 2 is the power amplifier No. 2, … …, and so on, and the power amplifier 14 corresponding to the vibration exciter F29 No. 29 is the power amplifier No. 29.
In specific implementation, the control cable on the vibration exciter 13 is connected with the corresponding power amplifier 14.
In this embodiment, the force vector controller 15 may send an excitation force control signal for driving and controlling the vibration exciters 13 to move, and the force vector controller 15 may simultaneously control the magnitudes and phases of the excitation forces of the plurality of vibration exciters 13.
Step four, system debugging: adjusting excitation phases and excitation force of vibration exciters 13 arranged at the tips of two wings 1 of the test airplane through a force vector controller 15 to perform an excitation test, acquiring vibration response of the test airplane body through an acceleration sensor 16, and debugging the test testing system according to the measured vibration response until the whole test testing system works normally;
when the test aircraft is actually used, the power amplifier No. 3 and the power amplifier No. 4 are started, the excitation phases of the vibration exciter No. 3 and the vibration exciter No. 4 are consistent, the excitation force of the vibration exciter No. 3 and the vibration exciter No. 4 is adjusted through the force vector controller 15, the front positions of the force bearing rib plates at the tip parts of the two wings 1 are simultaneously excited, the excitation frequency is adjusted, the test aircraft vibrates under the symmetrical one-bend frequency of the wings, the vibration response of the aircraft body is collected through the acceleration sensor 16, the working conditions of each system are checked according to the measured vibration response, the problems are checked until the whole system works normally, and after the debugging is finished, the power amplifier No. 3 and the power amplifier No. 4 are closed; the vibration response refers to information such as the phase and amplitude of the acceleration response.
In specific implementation, according to HB5861-1984 airplane ground vibration test standard and other related standard requirements, the maximum supporting frequency of the air spring supporting system is less than 1/3 of the lowest-order elastic frequency of an airplane. Therefore, the lowest-order elastic modal frequency of the airplane needs to be tested before the test, and is compared with the frequency of the supporting system of the air spring system, so that the rationality of the supporting system used in the test is verified. For most airplanes, the lowest order elastic frequency is the symmetric vertical first order bending frequency of the wing, so that the vibration exciter 13 at the wing 1 is selected for exciting during debugging.
It should be noted that, during the debugging process, each system is in a working state, 2 vibration exciters are connected to the airplane, the neutral position of the vibration exciters is ensured, the vibration exciters vibrate at a bending frequency symmetrical to the wing, so that the airplane generates vibration, and the working conditions of each system are respectively checked:
supporting the working conditions of the system, including whether the motion of the air spring is normal or not, whether the plane is in a horizontal state or not and the like;
the working conditions of the vibration excitation system comprise the working conditions of the vacuum chuck, whether the vibration excitation signal is good or not and the like;
measuring the working condition of the system, including whether the sensor signal of each measuring point is normal or not;
each test application is run and a set of vibration response data is printed to check if the entire system meets the test requirements.
The debugging is repeatedly carried out, and the faults are eliminated until the whole system is completely normal.
In the debugging pre-test, the supporting frequency of a supporting system is measured, and meanwhile, the lowest order elastic modal frequency of the airplane is measured, so that whether the supporting frequency meets one third of the lowest order elastic modal frequency of the airplane or not is checked.
Step five, testing the main body mode of the test airplane: sequentially adjusting the excitation phases and the excitation forces of vibration exciters 13 arranged on the wing 1, the fuselage 2, the horizontal tail 3, the vertical tail 4 and the engine 5 of the test airplane through a force vector controller 15, carrying out excitation tests on the wing 1, the fuselage 2, the horizontal tail 3, the vertical tail 4 and the engine 5 of the test airplane at various bearing positions, and acquiring the vibration response of the test airplane body through an acceleration sensor 16 to obtain various stages of main modes of the test airplane body;
in practical use, each order of main modes of the test airplane body means that selective testing can be performed according to test requirements, and then a corresponding first order body main mode or a corresponding multi-order body main mode is obtained.
Step six, testing the mode of each control surface of the test airplane: the excitation phase and the excitation force of the vibration exciter 13 arranged on the inner flap 6, the outer flap 7, the aileron 8, the elevator 9 and the rudder 10 of the test airplane are sequentially adjusted through the force vector controller 15, the bearing positions outside the control surfaces of the inner flap 6, the outer flap 7, the aileron 8, the elevator 9 and the rudder 10 of the test airplane are excited, the vibration response of the test airplane body is collected through the acceleration sensor 16, and the rotation mode of each operation surface of the test airplane body is obtained.
During actual use, the plurality of vibration exciters 13 are arranged on each part of the test airplane body, the starting number, the space combination mode, the exciting force and the phase relation of the vibration exciters 13 are adjusted, full-size ground vibration mode excitation of the large airplane is achieved, ground vibration test efficiency of the large airplane is effectively improved, and test result precision is improved.
In this embodiment, a power amplifier No. 21, a power amplifier No. 22, a power amplifier No. 23, a power amplifier No. 24, a power amplifier No. 25, a power amplifier No. 26, a power amplifier No. 27, a power amplifier No. 28, and a power amplifier No. 29 are sequentially turned on, excitation phases of the inner flap 6, the outer flap 7, the aileron 8, the elevator 9, and the exciter 13 on the rudder 10 are adjusted by the force vector controller 15 so that the excitation phases are all 0 degrees, the magnitude of the excitation force is adjusted by the force vector controller 15, the bearing positions outside the control surfaces of the inner flap 6, the outer flap 7, the aileron 8, the elevator 9, and the rudder 10 are sequentially excited, the excitation frequency is adjusted so that the control surfaces vibrate at a rotational mode frequency, and vibration responses are collected by the acceleration sensor 16, so that rotational modes of the control surfaces are obtained. After the test is finished, the power amplifier No. 21, the power amplifier No. 22, the power amplifier No. 23, the power amplifier No. 24, the power amplifier No. 25, the power amplifier No. 26, the power amplifier No. 27, the power amplifier No. 28 and the power amplifier No. 29 are turned off in sequence.
In the third step, two vibration exciters 13 are arranged at the nose of the fuselage 2, three vibration exciters 13 are arranged on the two wings 1, three vibration exciters 13 are arranged on the two horizontal tails 3, two vibration exciters 13 are arranged on the vertical tail 4, two vibration exciters 13 are arranged on the two engines 5, one vibration exciter 13 is arranged on each of the two inner wing flaps 6 and the two outer wing flaps 7, one vibration exciter 13 is arranged on each of the two ailerons 8, one vibration exciter 13 is arranged on each of the two elevators 9, and one vibration exciter 13 is arranged on each of the rudders 10;
the excitation directions of the plurality of exciters 13 are all perpendicular to the surface of the airplane structure at the installation position.
During the concrete implementation, two vibration exciters 13 on the fuselage 2 are installed respectively in the bottom of one side of aircraft nose and aircraft nose, three vibration exciters 13 on the wing 1 are installed respectively at the pointed portion front edge, the pointed portion top surface and the middle part of wing 1, three vibration exciters 13 on the horizontal tail 3 are installed respectively at the pointed portion front edge, the pointed portion top surface and the root of horizontal tail 3, two vibration exciters 13 on the vertical tail 4 are installed respectively at pointed portion one side and the pointed portion front edge of vertical tail 4, the bottom and one side at engine 5 are installed respectively to two vibration exciters 13 on the engine 5.
When the vibration exciter is actually used, the vibration exciter at the lower part of the machine head is installed by adopting a bracket, and the rest parts are installed in a manner of hanging by adopting a rubber rope; the bracket is a liftable mounting frame, the lower part of the bracket is a fixed triangular frame and is used for supporting the weight of the vibration exciter 13 and avoiding the bracket from shaking during vibration excitation, and the upper part of the bracket is a liftable platform, so that the vibration exciter 13 is fixed on the liftable platform, and the mounting height can be adjusted. When in use, the bracket is placed on the ground and is usually used for the part with lower excitation height; the rubber rope suspension installation mode is that the vibration exciter 13 is suspended in the air by a special rubber rope, the height and the direction of the vibration exciter can be freely adjusted, and the rubber rope suspension installation mode is usually used for parts with higher vibration exciting height.
In the third step, as shown in fig. 5, the vibration exciter 13 is connected to the body of the test airplane through a connecting rod 17 and a vacuum chuck 19, and the vacuum chuck 19 is connected to the vacuum negative pressure station through a rubber hose 18.
When the vacuum suction cup 19 is used in practice, the vacuum suction cup 19 is closely attached to the body of the test airplane, and when the vacuum suction cup 19 is vacuumized through the vacuum negative pressure station, the vacuum suction cup 19 is tightly attached to the surface of the body of the test airplane, so that the vibration exciter 13 is fixed.
In the fourth step, the vibration exciters 13 mounted at the tips of the two wings 1 of the test airplane are in consistent vibration excitation phase and simultaneously vibrate.
In the fifth step, the tip parts of the two wings 1 and the front positions of the middle bearing rib plates of the test airplane are simultaneously excited by changing the phase difference of the vibration exciters 13 arranged in the middle of the two wings 1, so that symmetrical vertical bending and torsion modes of each step of the wings and anti-symmetrical vertical bending and torsion modes of each step of the wings are obtained;
exciting the front positions of the force bearing rib plates at the tip parts of the two horizontal tails 3 of the test airplane simultaneously by changing the phase difference of the vibration exciters 13 arranged on the top surfaces of the tip parts of the two horizontal tails 3 to obtain symmetrical vertical bending and torsion modes of each step of the horizontal tail and anti-symmetrical vertical bending and torsion modes of each step of the horizontal tail;
exciting the front position of a bearing rib plate at the tip part of the vertical tail 4 of the test airplane by a vibration exciter 13 arranged at one side of the tip part of the vertical tail 4 to obtain lateral bending and torsion modes of each step of the vertical tail;
exciting a bearing frame at the head position of the body 2 of the test airplane through two vibration exciters 13 arranged on the body 2 respectively to obtain a vertical bending mode of each step of the body and a lateral bending mode of each step of the body;
and exciting the positions, close to the front, of the bearing rib plates at the roots of the two horizontal tails 3 of the test airplane simultaneously by using the vibration exciters 13 arranged at the roots of the two horizontal tails 3 to obtain each-step torsional mode of the airplane body.
It should be noted that the main modes of each stage of the test aircraft body include symmetrical vertical bending and torsion modes of each stage of the wing, antisymmetric vertical bending and torsion modes of each stage of the wing, symmetrical vertical bending and torsion modes of each stage of the horizontal tail, antisymmetric vertical bending and torsion modes of each stage of the horizontal tail, side bending and torsion modes of each step of the vertical tail, vertical bending modes of each stage of the fuselage, side bending modes of each stage of the fuselage, torsion modes of each stage of the fuselage, in-plane bending modes of each stage of the wing, antisymmetric in-plane bending modes of each stage of the wing, in-plane bending modes of each stage of the horizontal tail, antisymmetric in-plane bending modes of each stage of the horizontal tail, in-plane bending modes of each stage of the vertical tail, symmetrical engine pitching modes and antisymmetric engine pitching modes, symmetrical engine side plane navigation and yaw modes of the engine, and antisymmetric side plane bending modes of the engine and yaw modes of the engine.
When the test aircraft is actually used, the power amplifier No. 1, the power amplifier No. 2, the power amplifier No. 3, the power amplifier No. 4, the power amplifier No. 5, the power amplifier No. 6, the power amplifier No. 11, the power amplifier No. 12, the power amplifier No. 13, the power amplifier No. 14 and the power amplifier No. 15 are started, the excitation phases of the vibration exciter No. 3 and the vibration exciter No. 4 are adjusted through the force vector controller 15, the excitation phases of the vibration exciter No. 3 and the vibration exciter No. 4 are consistent, the excitation phases of the vibration exciter No. 5 and the vibration exciter No. 6 are consistent, the excitation phases of the vibration exciter No. 3 and the vibration exciter No. 5 can be adjusted to be the same or 180-degree difference according to requirements, the excitation force is adjusted through the force vector controller 15, the vibration excitation is simultaneously performed on the front positions of the tip parts and the middle bearing rib plates of the two airfoils 1, the vibration frequency is adjusted, the test aircraft vibrates under the vertical frequency of each modal of the airfoils 1, and the vibration response of the aircraft is acquired through the acceleration sensor 16, so that the symmetric bending and the torsional modes of each modal of the airfoils are obtained; adjusting the excitation phases of a No. 3 vibration exciter and a No. 4 vibration exciter through a force vector controller 15 to ensure that the excitation phases of the No. 3 vibration exciter and the No. 4 vibration exciter are 180 degrees different, adjusting the excitation phases of a No. 5 vibration exciter and a No. 6 vibration exciter simultaneously to ensure that the excitation phases of the No. 5 vibration exciter and the No. 6 vibration exciter are 180 degrees different, and adjusting the excitation phases of the No. 3 vibration exciter and the No. 5 vibration exciter to be the same or 180 degrees different according to requirements, adjusting the excitation force through a force vector controller 15, exciting the front positions of the tip parts and the middle bearing rib plates of the two wings 1 simultaneously, adjusting the excitation frequency, vibrating the test airplane under the vertical modal frequency of each step of the wings, and acquiring the vibration response of the airplane body through an acceleration sensor 16 to obtain the anti-symmetric vertical bending and torsion modes of each step of the wings; the excitation phases of the No. 11 vibration exciter and the No. 12 vibration exciter are adjusted through the force vector controller 15, so that the excitation phases of the No. 11 vibration exciter and the No. 12 vibration exciter are consistent, the excitation force is adjusted through the force vector controller 15, the positions, close to the front, of the force bearing rib plates at the tip parts of the two horizontal tails 3 are excited simultaneously, the excitation frequency is adjusted, so that the test airplane vibrates under the vertical modal frequency of each step of the horizontal tail, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the symmetrical vertical bending and torsion modes of each step of the horizontal tail are obtained; the excitation phases of the No. 11 vibration exciter and the No. 12 vibration exciter are adjusted through the force vector controller 15, so that the excitation phases of the No. 11 vibration exciter and the No. 12 vibration exciter are 180 degrees apart, the excitation force is adjusted through the force vector controller 15, the front positions of the force bearing rib plates at the tip parts of the two horizontal tails 3 are simultaneously excited, the excitation frequency is adjusted, so that the test airplane vibrates under the vertical modal frequency of each step of the horizontal tail, the vibration response of the airplane body is collected through the acceleration sensor 16, and thus the anti-symmetric vertical bending and torsion modes of each step of the horizontal tail are obtained; the excitation phase of the No. 15 vibration exciter is adjusted through the force vector controller 15, the excitation phase of the No. 15 vibration exciter is made to be 0 degree, the excitation force is adjusted through the force vector controller 15, the front position of the force bearing rib plate at the tip of the vertical tail 4 is excited, the excitation frequency is adjusted, the test airplane vibrates under the lateral modal frequency of each step of the vertical tail, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the lateral bending and torsion modes of each step of the vertical tail are obtained; the excitation phase of the No. 1 vibration exciter is adjusted through the force vector controller 15, the excitation phase of the No. 1 vibration exciter is 0 degree, the magnitude of the excitation force is adjusted through the force vector controller 15, the bearing frame at the head position of the airplane body 2 is excited, the excitation frequency is adjusted, the airplane to be tested vibrates under the frequency of each order of vertical modes of the airplane body 2, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore each order of vertical bending modes of the airplane body is obtained; the excitation phase of the No. 2 vibration exciter is adjusted through the force vector controller 15, the excitation phase of the No. 2 vibration exciter is 0 degree, the magnitude of the excitation force is adjusted through the force vector controller 15, the bearing frame at the head position of the airplane body 2 is excited, the excitation frequency is adjusted, the test airplane vibrates under the lateral modal frequency of each order of the airplane body, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the lateral bending mode of each order of the airplane body is obtained; the excitation phases of the No. 13 vibration exciter and the No. 14 vibration exciter are adjusted through the force vector controller 15, so that the excitation phases of the No. 13 vibration exciter and the No. 14 vibration exciter are consistent, the excitation force is adjusted through the force vector controller 15, the positions, close to the front, of the bearing rib plates at the roots of the two horizontal tails 3 are simultaneously excited, the excitation frequency is adjusted, the test airplane vibrates under the torsional mode frequency of each step of the airplane body, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the torsional mode of each step of the airplane body is obtained. After the test is finished, the power amplifier No. 1, the power amplifier No. 2, the power amplifier No. 3, the power amplifier No. 4, the power amplifier No. 5, the power amplifier No. 6, the power amplifier No. 11, the power amplifier No. 12, the power amplifier No. 13, the power amplifier No. 14 and the power amplifier No. 15 are turned off.
In the fifth step, vibration exciters 13 mounted at the bottoms of the two engines 5 simultaneously excite the force bearing positions at the front parts of the two engines 5 of the test airplane to obtain an engine symmetric pitch mode and an engine antisymmetric pitch mode;
and exciting the force bearing positions at the front parts of the two engines 5 of the test airplane simultaneously by using vibration exciters 13 arranged at one sides of the two engines 5 to obtain an engine symmetrical side horizontal navigation and yaw mode and an engine antisymmetric side horizontal navigation and yaw mode.
During actual use, the No. 7 power amplifier, the No. 8 power amplifier, the No. 9 power amplifier and the No. 10 power amplifier are started, the excitation phases of the No. 7 vibration exciter and the No. 8 vibration exciter are adjusted through the force vector controller 15, the excitation phases of the No. 7 vibration exciter and the No. 8 vibration exciter are consistent, the magnitude of the excitation force is adjusted through the force vector controller 15, the force bearing positions at the front parts of the two engines 5 are simultaneously excited, the excitation frequency is adjusted, the test airplane vibrates under the pitch modal frequency, the vibration response of the airplane body is collected through the acceleration sensor 16, the engine symmetric pitch modal is obtained, and when the excitation phases of the No. 7 vibration exciter and the No. 8 vibration exciter are 180 degrees different, the anti-symmetric pitch modal of the engines is obtained; the excitation phases of the No. 9 vibration exciter and the No. 10 vibration exciter are adjusted through the force vector controller 15, so that the excitation phases of the No. 9 vibration exciter and the No. 10 vibration exciter are consistent, the excitation force is adjusted through the force vector controller 15, the force bearing positions in the front parts of the two engines 5 are simultaneously excited, the excitation frequency is adjusted, so that the test airplane vibrates under the lateral modal frequency, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the anti-symmetric lateral-flat and yaw modes of the engine are obtained, and when the excitation phases of the No. 9 vibration exciter and the No. 10 vibration exciter are 180 degrees different, the anti-symmetric lateral-flat and yaw modes of the engine are obtained. After the test is completed, the power amplifier No. 7, the power amplifier No. 8, the power amplifier No. 9 and the power amplifier No. 10 are turned off.
In the fifth step, vibration exciters 13 mounted on the front edges of the tips of the two wings 1 are used for exciting the positions of the bearing rib plates of the front edges of the tips of the two wings 1 of the test airplane at the same time, so that the bending mode in each symmetrical plane of each step of the wing and the bending mode in each anti-symmetrical plane of each step of the wing are obtained;
exciting the positions of the force-bearing rib plates of the front edges of the tip parts of the two horizontal tails 3 of the test airplane simultaneously by using vibration exciters 13 arranged on the front edges of the tip parts of the two horizontal tails 3 to obtain a bending mode in each symmetrical plane of the horizontal tail and a bending mode in each anti-symmetrical plane of the horizontal tail;
and exciting the position of the bearing rib plate at the front edge of the tip part of the vertical tail 4 of the test airplane by a vibration exciter 13 arranged at the front edge of the tip part of the vertical tail 4 to obtain the bending mode in each step surface of the vertical tail.
When the test aircraft is actually used, a No. 17 power amplifier, a No. 18 power amplifier, a No. 19 power amplifier and a No. 20 power amplifier are started, the excitation phases of a No. 17 vibration exciter and a No. 18 vibration exciter are adjusted through a force vector controller 15, the excitation phases of the No. 17 vibration exciter and the No. 18 vibration exciter are consistent, the magnitude of the excitation force is adjusted through the force vector controller 15, the positions of bearing rib plates at the front edges of the tips of two airfoils 1 are simultaneously excited, the excitation frequency is adjusted, the test aircraft vibrates under the mode frequency of each stage of the airfoil, the vibration response of the aircraft body is collected through an acceleration sensor 16, so that the bending mode in each stage of the airfoil is obtained, and when the excitation phases of the No. 17 vibration exciter and the No. 18 vibration exciter are 180 degrees different, the bending mode in each stage of the airfoil is obtained; adjusting the excitation phases of a No. 19 vibration exciter and a No. 20 vibration exciter through a force vector controller 15 to enable the excitation phases of the No. 19 vibration exciter and the No. 20 vibration exciter to be consistent, adjusting the magnitude of the excitation force through the force vector controller 15, simultaneously exciting the positions of bearing rib plates at the front edges of two horizontal tail tip parts, adjusting the excitation frequency to enable the test airplane to vibrate under the mode frequency in each step surface of the horizontal tail 3, collecting the vibration response of the airplane body through an acceleration sensor 16 to obtain the bending mode in each step symmetrical surface of the horizontal tail, and obtaining the bending mode in each step anti-symmetrical surface of the horizontal tail when the excitation phases of the No. 19 vibration exciter and the No. 20 vibration exciter are 180 degrees different; the excitation phase of the No. 16 vibration exciter is adjusted through the force vector controller 15, the excitation phase of the No. 16 vibration exciter is 0 degree, the excitation force is adjusted through the force vector controller 15, the bearing rib plate position of the front edge of the tip portion of the vertical tail 4 is simultaneously excited, the excitation frequency is adjusted, the test airplane vibrates under the mode frequency in each step surface of the vertical tail, the vibration response of the airplane body is collected through the acceleration sensor 16, and therefore the bending mode in each step surface of the vertical tail is obtained. After the test is completed, the power amplifier No. 17, the power amplifier No. 18, the power amplifier No. 19 and the power amplifier No. 20 are turned off.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (3)
1. A ground vibration mode testing method for a large airplane is characterized by comprising the following steps:
step one, installing a sensor on a test airplane: a plurality of acceleration sensors (16) are arranged at each test part of the body of the test airplane, and the acceleration sensors (16), the data acquisition unit (11) and the test computer (12) are sequentially connected to form a test system;
wherein each test part of the body of the test airplane comprises a wing (1), a fuselage (2), a horizontal tail (3), a vertical tail (4), an engine (5), an inner flap (6), an outer flap (7), an aileron (8), an elevator (9) and a rudder (10), and acceleration sensors (16) are arranged on the wings;
simulating the air suspension state of the airplane;
step three, arranging and installing vibration exciters on the test airplane: the method comprises the following steps that vibration exciters (13) are installed on each testing part of a test airplane body, each vibration exciter (13) is connected with a power amplifier (14), the power amplifiers (14) are connected with a force vector controller (15), the force vector controller (15) is connected with a testing computer (12) to form a vibration exciting system, and the testing system and the vibration exciting system form a testing and testing system;
the aircraft nose of the aircraft body (2) is provided with two vibration exciters (13), the two wings (1) are respectively provided with three vibration exciters (13), the two horizontal tails (3) are respectively provided with three vibration exciters (13), the vertical tail (4) is provided with two vibration exciters (13), the two engines (5) are respectively provided with two vibration exciters (13), the two inner wing flaps (6) and the two outer wing flaps (7) are respectively provided with one vibration exciter (13), the two ailerons (8) are respectively provided with one vibration exciter (13), the two elevators (9) are respectively provided with one vibration exciter (13), and the rudder (10) is provided with one vibration exciter (13);
the excitation directions of the plurality of exciters (13) are all perpendicular to the surface of the airplane structure at the installation position;
the two vibration exciters (13) on the machine body (2) are respectively installed at one side of the machine head and the bottom of the machine head, the three vibration exciters (13) on the wing (1) are respectively installed at the front edge of the tip part, the top surface of the tip part and the middle part of the wing (1), the three vibration exciters (13) on the horizontal tail (3) are respectively installed at the front edge of the tip part, the top surface of the tip part and the root part of the horizontal tail (3), the two vibration exciters (13) on the vertical tail (4) are respectively installed at one side of the tip part and the front edge of the tip part of the vertical tail (4), and the two vibration exciters (13) on the engine (5) are respectively installed at the bottom and one side of the engine (5);
step four, debugging the system: adjusting the excitation phases and the excitation force of vibration exciters (13) arranged at the tips of two wings (1) of the test airplane through a force vector controller (15) to perform an excitation test, acquiring the vibration response of the test airplane body through an acceleration sensor (16), and debugging the test system according to the measured vibration response until the whole test system works normally;
step five, testing the main body mode of the test airplane: sequentially adjusting the excitation phase and the excitation force of vibration exciters (13) arranged on the wing (1), the fuselage (2), the horizontal tail (3), the vertical tail (4) and the engine (5) of the test airplane through a force vector controller (15), carrying out excitation tests on the wing (1), the fuselage (2), the horizontal tail (3), the vertical tail (4) and the engine (5) of the test airplane, and acquiring the vibration response of the test airplane body through an acceleration sensor (16) to obtain each-order main mode of the test airplane body;
exciting the tip parts of the two wings (1) of the test airplane and the front positions of the middle bearing rib plates by changing the phase difference of vibration exciters (13) arranged in the middle parts of the two wings (1) simultaneously to obtain symmetrical vertical bending and torsion modes of each step of the wings and anti-symmetrical vertical bending and torsion modes of each step of the wings;
exciting the positions, close to the front, of the force bearing rib plates at the tip parts of the two horizontal tails (3) of the test airplane simultaneously by changing the phase difference of vibration exciters (13) arranged on the top surfaces of the tip parts of the two horizontal tails (3) to obtain symmetrical vertical bending and torsion modes of each step of the horizontal tail and anti-symmetrical vertical bending and torsion modes of each step of the horizontal tail;
exciting the front position of a force bearing rib plate at the tip part of the vertical tail (4) of the test airplane by a vibration exciter (13) arranged at one side of the tip part of the vertical tail (4) to obtain lateral bending and torsion modes of each step of the vertical tail;
exciting a bearing frame at the head position of the body (2) of the test airplane through two vibration exciters (13) arranged on the body (2) respectively to obtain a vertical bending mode of each step of the body and a lateral bending mode of each step of the body;
exciting the positions close to the front of the bearing rib plates at the roots of the two horizontal tails (3) of the test airplane simultaneously by using vibration exciters (13) arranged at the roots of the two horizontal tails (3) to obtain torsional modes of each step of the airplane body;
exciting the force bearing positions at the front parts of the two engines (5) of the test airplane simultaneously by using vibration exciters (13) arranged at the bottoms of the two engines (5) to obtain an engine symmetric pitching mode and an engine antisymmetric pitching mode;
exciting force bearing positions at the front parts of the two engines (5) of the test airplane simultaneously through vibration exciters (13) arranged on one sides of the two engines (5) to obtain an engine symmetrical side parallel navigation and yaw mode and an engine antisymmetric side parallel navigation and yaw mode;
exciting the positions of bearing rib plates of the front edges of the tip parts of the two wings (1) of the test airplane simultaneously by using vibration exciters (13) arranged on the front edges of the tip parts of the two wings (1) to obtain bending modes in symmetrical planes of each step of the wings and bending modes in anti-symmetrical planes of each step of the wings;
exciting the positions of force bearing rib plates of the front edges of the tip parts of the two horizontal tails (3) of the test airplane simultaneously by using vibration exciters (13) arranged on the front edges of the tip parts of the two horizontal tails (3) to obtain a bending mode in each symmetrical plane of the horizontal tail and a bending mode in each anti-symmetrical plane of the horizontal tail;
exciting the position of a bearing rib plate at the front edge of the tip part of the vertical tail (4) of the test airplane by a vibration exciter (13) arranged at the front edge of the tip part of the vertical tail (4) to obtain bending modes in each step surface of the vertical tail;
step six, testing the mode of each control surface of the test airplane: sequentially adjusting the excitation phase and the excitation force of vibration exciters (13) arranged on an inner flap (6), an outer flap (7), an aileron (8), an elevator (9) and a rudder (10) of the test airplane through a force vector controller (15), exciting the bearing positions on the outer sides of all control surfaces of the test airplane, and acquiring the vibration response of the test airplane body through an acceleration sensor (16) to obtain the rotating mode of all the control surfaces of the test airplane body;
the vibration test device can be effectively applied to the full-size ground resonance test of the large-size airplane, and can coordinate vibration excitation at all parts of the airplane body through the number and combination mode of various different vibration exciters, so that the test efficiency of modal parameters of the large-size airplane is improved, and the full-size ground vibration test problems of the large-size airplane, such as large wing deformation, dense low-frequency modal, nonlinear structure and the like, can be effectively solved through optimizing the position and the size of the exciting force, so that the test result precision is improved.
2. The ground vibration mode testing method for the large aircraft according to claim 1, wherein: in the third step, the vibration exciter (13) is connected with the body of the test airplane through a connecting rod (17) and a vacuum sucker (19), and the vacuum sucker (19) is connected with a vacuum negative pressure station through a rubber hose (18).
3. The ground vibration mode testing method for the large aircraft according to claim 1, wherein the ground vibration mode testing method comprises the following steps: in the fourth step, the vibration exciters (13) arranged at the tips of the two wings (1) of the test airplane are consistent in vibration exciting phase and are excited simultaneously.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6375127B1 (en) * | 2000-07-07 | 2002-04-23 | Kari Appa | Active control surface modal system for aircraft buffet and gust load alleviation and flutter suppression |
| CN102384833A (en) * | 2011-10-28 | 2012-03-21 | 北京航空航天大学 | Device and method for testing combination control of multiple excitation sources |
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
| CN208860567U (en) * | 2018-09-30 | 2019-05-14 | 华南理工大学 | Low-frequency vibration detection device for UAV based on digital speckle |
| CN110949689A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Method for measuring full-motion horizontal tail rotation mode of airplane |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6915989B2 (en) * | 2002-05-01 | 2005-07-12 | The Boeing Company | Aircraft multi-axis modal suppression system |
| DE102007019402B4 (en) * | 2007-04-23 | 2011-08-25 | Airbus Operations GmbH, 21129 | Method for performing a soil vibration test on aircraft |
-
2022
- 2022-06-27 CN CN202210732923.0A patent/CN114813002B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6375127B1 (en) * | 2000-07-07 | 2002-04-23 | Kari Appa | Active control surface modal system for aircraft buffet and gust load alleviation and flutter suppression |
| CN102384833A (en) * | 2011-10-28 | 2012-03-21 | 北京航空航天大学 | Device and method for testing combination control of multiple excitation sources |
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
| CN208860567U (en) * | 2018-09-30 | 2019-05-14 | 华南理工大学 | Low-frequency vibration detection device for UAV based on digital speckle |
| CN110949689A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Method for measuring full-motion horizontal tail rotation mode of airplane |
Non-Patent Citations (1)
| Title |
|---|
| 某大展弦比飞机全机地面模态试验研究;李智劳等;《通讯世界》;20170630(第11期);正文第284-285页 * |
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