CN107727340B - The elastic vibration mode testing method of rotary missile - Google Patents
The elastic vibration mode testing method of rotary missile Download PDFInfo
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- CN107727340B CN107727340B CN201710714401.7A CN201710714401A CN107727340B CN 107727340 B CN107727340 B CN 107727340B CN 201710714401 A CN201710714401 A CN 201710714401A CN 107727340 B CN107727340 B CN 107727340B
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- guided missile
- rolling
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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
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0066—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by exciting or detecting vibration or acceleration
Abstract
The present invention provides a kind of elastic vibration mode testing methods of rotary missile comprising following steps: step 1, is horizontally suspended guided missile by two elastic strings, is connected between guided missile and elastic string using rolling bearing, makes guided missile around the free rolling of the longitudinal axis；Guided missile one end is connect by fixture with a Flexible Rotating, and a rolling driving device drives guided missile rolling by Flexible Rotating, and enabling body to generate laterally free displacement, revolving speed is controllable simultaneously, and elimination rolling drives the boundary constraint to body tail end；Step 2, the rolling driving device being made of motor, deceleration device, Flexible Rotating and drive control device can drive guided missile to reach and maintain specified revolving speed rolling, and revolving speed is continuously adjusted within the scope of 0~20 revolutions per second.Present invention obtains the elastic response characteristics under guided missile rotation status, can be applied to mould measurement of the guided missile under rotation status.
Description
Technical field
The present invention relates to guided missile elastic vibration and mould measurement fields, and in particular, to a kind of elastic vibrating of rotary missile
Dynamic mode testing method.
Background technique
Rotary missile due at low cost, response quickly, be conducive to the features such as miniaturization and suitable dress property are good, in guided weapon field
With huge development potentiality and application prospect.For the rapidity of raising, reduce flight resistance, rotary missile be commonly designed compared with
Big slenderness ratio, therefore the rigidity of structure is lower；Simultaneously with the raising of maneuverability requirement, missile flight overload is increasing.?
Under the conditions of the big angle of attack, body can generate serious flexible deformation.By taking nurse guided missile is drawn in the U.S. as an example, slenderness ratio is more than 20, maximum
Flight overload 45g or more, body longitudinal side are significant to elastic vibration.
Longitudinal side is that high mobile missile master-plan and Control System Design must be taken into consideration to elastic vibration, especially for
Rotary missile, body elastic vibration characteristics of mode under rotation status will change, while suffered aerodynamic loading is also with revolving speed
Cyclically-varying causes elastic movement and rotary motion to generate serious cross-coupling and acts on.One side cross-coupling reduces bullet
The dynamic stability of body may cause appearance dynamic instability due to caused by flexible deformation in missile flight；On the other hand, coupling
The measurement output that dynamic response seriously affects control feedback transducer is closed, the control system designed according to non-rotating situation is caused
It controls in practical flight and does not restrain, flight is caused to fail.
It influences to solve rotary missile elastic vibration to master-plan and guidance control system design bring, accurately obtains
It is highly important for obtaining the elastic vibration characteristics of guided missile in rotating condition.Guided missile elastic modal parameters are obtained using research technique
It is the basis of missile dynamics modeling and Control System Design with the changing rule of revolving speed.For the springform of non-rotating guided missile
State test method has developed into ripe, but this method can not be applied to mould measurement of the guided missile under rotation status.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of elastic vibration mould measurements of rotary missile
Method, which give the elastic response characteristics under guided missile rotation status, can be applied to mode of the guided missile under rotation status and survey
Examination.
According to an aspect of the present invention, a kind of elastic vibration mode testing method of rotary missile is provided, feature exists
In, the rotary missile elastic vibration mode testing method the following steps are included:
Step 1 is horizontally suspended guided missile by two elastic strings, is connected between guided missile and elastic string using rolling bearing,
Make guided missile around the free rolling of the longitudinal axis；Guided missile one end is connect by fixture with a Flexible Rotating, and a rolling driving device passes through
Flexible Rotating drives guided missile rolling, and enabling body to generate laterally free displacement, revolving speed is controllable simultaneously, eliminates rolling driving pair
The boundary constraint of body tail end；
Step 2, the rolling driving device being made of motor, deceleration device, Flexible Rotating and drive control device, can drive
Dynamic guided missile reaches and maintains specified revolving speed rolling, and revolving speed is continuously adjusted within the scope of 0~20 revolutions per second；
Guided missile is divided into N number of website along axial direction by step 3, and N is natural number and N >=10, and each website installs acceleration
Sensor, one copybook of sensor are mounted in body surface, and acceleration transducer response output is sent out in real time by wireless data transmission device
It is sent to ground base station, and by the first data logger recording responses signal；
Step 4 motivates rolling bearing using power hammer vertically upward, and pumping signal is output to the second number through charge amplifier
It is input to spectrum analyzer according to recorder, and together with the sensor response signal of the first data logger, using orthogonal multinomial
Formula method identifies modal parameter of the guided missile under given rotating speed.
Preferably, the rigidity, the rigidity of fixture of the rolling bearing, which are both greater than, is tested the 1.5 of guided missile maximum test frequency
Times；The frequency of elastic string is less than the 10% of subject guided missile fundamental frequency；The body initial level limits of error of elastic string are not
More than 5 ‰, the extensibility of elastic string should be between 40%~60%；The gross mass of rolling bearing and fixture is no more than full bullet quality
2%.
Preferably, the rolling bearing is made of internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle,
Internal layer anchor ear is capable of fixing on body surface, and outer layer anchor ear is connect with elastic string.
Preferably, the Flexible Rotating is steel rod structure, and corner frequency is less than subject guided missile fundamental frequency
10%, under the constraint condition subject guided missile first-order modal frequency and Free Modal frequency compared to deviation less than 1%, second order
Modal frequency deviation is less than 3%, three rank modal frequency deviation less than 5%.
Preferably, the acceleration transducer grouping is connect with multiple wireless data transmission devices.
Preferably, the elastic vibration mode testing method of the rotary missile uses mounting bracket, elastic string, wobble shaft
Hold, rolling driving device, wireless sensor measuring system, power hammer excitation system and spectrum analyzer, rolling driving device by
Fixture, Flexible Rotating, motor, deceleration device and drive control device composition, wireless sensor measuring system by acceleration transducer,
Wireless data transmission device, ground base station and the first data logger composition, power hammer excitation system by power hammer into shape, charge amplifier and
Second data logger composition.
Preferably, the Flexible Rotating and guided missile are in alignment, and in same level plane.
Preferably, mode ginseng of the spectrum analyzer using orthogonal polynomial method identification guided missile under given rotating speed
Number, orthogonal polynomial method are to carry out Laplace transformation to system differential equation using the rational fraction of frequency response function as mathematical model,
Equationof structure group, finds out the eigen vector of system, finally identifies each modal parameter.
Compared with prior art, the present invention is with following the utility model has the advantages that the present invention is outstanding using being made of rolling bearing
Extension system, body can rotate freely during test, while by rolling driving device, body revolving speed is controllable and linearly may be used
It adjusts.Using the rolling drive system being made of Flexible Rotating, Flexible Rotating is steel rod structure, can transmit motor generation
Rolling driving moment, simultaneously because its structural modal frequency is much smaller than the longitudinal side of guided missile to structural modal frequency, to test result
Influence can be ignored.Using the wireless sensor measuring system being made of high-sensitivity accelerometer, solves acceleration sensing
Device caused conducting wire during guided missile rolling winds problem.Present invention obtains the elastic response under guided missile rotation status is special
Property, it can be used for instructing rotary missile master-plan and Control System Design.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the working principle diagram of the elastic vibration mode testing method of rotary missile of the invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As shown in Figure 1, the elastic vibration mode testing method of rotary missile of the present invention the following steps are included:
Step 1 is horizontally suspended guided missile by two elastic strings, is connected between guided missile and elastic string using rolling bearing,
Allow guided missile around the free rolling of its longitudinal axis；Guided missile one end (generally selecting tail end) is connect by fixture with a Flexible Rotating,
One rolling driving device drives guided missile rolling by Flexible Rotating, and body is enabled to generate laterally free displacement revolving speed simultaneously
Controllably, boundary constraint of the rolling driving to body tail end is eliminated；
Step 2, the rolling driving device being made of motor, deceleration device, Flexible Rotating and drive control device, can drive
Dynamic guided missile reaches and maintains specified revolving speed rolling, and revolving speed is continuously adjusted within the scope of 0~20 revolutions per second；
Guided missile is divided into N number of website along axial direction by step 3, and N is natural number and N >=10, and each website installs acceleration
Sensor, one copybook of sensor are mounted in body surface, and acceleration transducer response output is sent out in real time by wireless data transmission device
It is sent to ground base station, and by the first data logger A recording responses signal；
Step 4 motivates rolling bearing using power hammer vertically upward, and pumping signal is output to the second number through charge amplifier
It is input to spectrum analyzer according to recorder B, and together with the sensor response signal of the first data logger A, using orthogonal more
Modal parameter of the item formula method identification guided missile under given rotating speed.
Rigidity, the rigidity of fixture of rolling bearing are both greater than 1.5 times of subject guided missile maximum test frequency；The frequency of elastic string
Rate is less than the 10% of subject guided missile fundamental frequency；The body initial level limits of error of elastic string are no more than 5 ‰, elastic string
Extensibility should be between 40%~60%；The gross mass of rolling bearing and fixture is no more than the 2% of full bullet quality, improves accurate
Degree.
Rolling bearing is made of internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle, and internal layer anchor ear can
It is fixed on body surface, outer layer anchor ear is connect with elastic string, in this way raising intensity.
Flexible Rotating is steel rod structure, and corner frequency is less than the 10% of subject guided missile fundamental frequency, in the constraint
Under the conditions of subject guided missile first-order modal frequency and Free Modal frequency compared to deviation less than 1%, second-order modal frequency departure
Less than 3%, three rank modal frequency deviation less than 5%, accuracy is improved.
In test, guided missile, which is driven by motor, reaches and maintains specified revolving speed, hammers pulsed excitation wobble shaft into shape using power
Acceleration transducer output on bullet is transmitted to ground base station by wireless data transmission device and recorded by the outer wall held.According to
The excitation and response signal of data logger acquisition, using spectrum analyzer using orthogonal polynomial method identification guided missile given
Modal parameter under revolving speed.This method obtains the elastic response characteristics under guided missile rotation status, can be used for instructing rotary missile
Master-plan and Control System Design.
Acceleration transducer grouping is connect with multiple wireless data transmission devices, so that body rolling is not connected conducting wire and does
It disturbs.
The elastic vibration mode testing method of rotary missile of the present invention is using mounting bracket 1, elastic string, rolling bearing, rolling
Rotary driving device, wireless sensor measuring system, power hammer excitation system and spectrum analyzer, rolling driving device by fixture,
Flexible Rotating, motor, deceleration device and drive control device composition, wireless sensor measuring system is by acceleration transducer, wireless
Data transmission device, ground base station and the first data logger composition, power hammer excitation system is by power hammer, charge amplifier and second
Data logger composition, easy to use in this way, structure is simple, at low cost.Flexible Rotating and guided missile are in alignment, and same
In horizontal plane, stability is improved in this way.
Storing data (such as response signal) is output to spectrum analysis by the first data logger and the second data logger
Instrument, modal parameter of the spectrum analyzer using orthogonal polynomial method identification guided missile under given rotating speed, orthogonal polynomial method
It is Laplace transformation to be carried out to system differential equation, equationof structure group finds out and is using the rational fraction of frequency response function as mathematical model
The eigen vector of system finally identifies each modal parameter, in this way raising accuracy.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (1)
1. a kind of elastic vibration mode testing method of rotary missile, which is characterized in that the elastic vibrating dynamic model of the rotary missile
State test method the following steps are included:
Step 1 is horizontally suspended guided missile by two elastic strings, is connected between guided missile and elastic string using rolling bearing, is made to lead
Bullet is around the free rolling of the longitudinal axis；Guided missile one end is connect by fixture with a Flexible Rotating, and a rolling driving device passes through flexibility
Shaft drives guided missile rolling, and enabling body to generate laterally free displacement, revolving speed is controllable simultaneously, eliminates rolling driving to body
The boundary constraint of tail end；
Step 2, the rolling driving device being made of motor, deceleration device, Flexible Rotating and drive control device, can drive and lead
Bullet reaches and maintains specified revolving speed rolling, and revolving speed is continuously adjusted within the scope of 0~20 revolutions per second；
Guided missile is divided into N number of website along axial direction by step 3, and N is natural number and N >=10, and each website installs acceleration sensing
Device, one copybook of sensor are mounted in body surface, and acceleration transducer response output is sent in real time by wireless data transmission device
Ground base station, and by the first data logger recording responses signal；
Step 4 motivates rolling bearing using power hammer vertically upward, and pumping signal is output to the second data through charge amplifier and remembers
Instrument is recorded, and is input to spectrum analyzer together with the sensor response signal of the first data logger, using orthogonal polynomial side
Method identifies modal parameter of the guided missile under given rotating speed；
Rigidity, the rigidity of fixture of the rolling bearing are both greater than 1.5 times of subject guided missile maximum test frequency；The frequency of elastic string
Rate is less than the 10% of subject guided missile fundamental frequency；The body initial level limits of error of elastic string are no more than 5 ‰, elastic string
Extensibility should be between 40%~60%；The gross mass of rolling bearing and fixture is no more than the 2% of full bullet quality；
The rolling bearing is made of internal layer anchor ear, single-groove grooved ball bearing, outer layer anchor ear and axial baffle, and internal layer anchor ear can
It is fixed on body surface, outer layer anchor ear is connect with elastic string；
The Flexible Rotating is steel rod structure, and corner frequency is less than the 10% of subject guided missile fundamental frequency, in the constraint
Under the conditions of subject guided missile first-order modal frequency and Free Modal frequency compared to deviation less than 1%, second-order modal frequency departure
Less than 3%, three rank modal frequency deviation less than 5%；
The acceleration transducer grouping is connect with multiple wireless data transmission devices；
The elastic vibration mode testing method of the rotary missile is using mounting bracket, elastic string, rolling bearing, rolling driving dress
Set, wireless sensor measuring system, power hammer excitation system and spectrum analyzer, rolling driving device by fixture, Flexible Rotating,
Motor, deceleration device and drive control device composition, wireless sensor measuring system are filled by acceleration transducer, wireless data transmission
It sets, ground base station and the first data logger composition, power hammer excitation system is by power hammer, charge amplifier and the second data logger
Composition；
The Flexible Rotating and guided missile are in alignment, and in same level plane；
Modal parameter of the spectrum analyzer using orthogonal polynomial method identification guided missile under given rotating speed, orthogonal polynomial
Method is to carry out Laplace transformation to system differential equation, equationof structure group is asked using the rational fraction of frequency response function as mathematical model
The eigen vector of system out finally identifies each modal parameter.
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| CN108845553B (en) * | 2018-06-15 | 2021-03-09 | 上海航天控制技术研究所 | Servo elastic vibration suppression comprehensive inspection method for slender aircraft |
| CN109323831B (en) * | 2018-09-05 | 2020-07-28 | 哈尔滨工程大学 | Elongated rotating shaft modal test device based on preload sudden release excitation method |
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