CN105912772A - Model correction method integrated with frequency, vibration modes and frequency response functions - Google Patents
Model correction method integrated with frequency, vibration modes and frequency response functions Download PDFInfo
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Abstract
The present invention discloses a model correction method integrated with frequency, vibration modes and frequency response functions. A multi-satellite distributor has complex space configuration characteristics of multiple branches, high center of mass and low frequency, and model correction integrated with frequency, vibration modes and frequency response functions is performed on a established space finite element model. The method specifically comprises the steps of performing preliminary modal analysis on the preliminarily established space finite element model, performing modal and frequency response analysis on the model after primary screening, performing comparison with test results of modal tests and sine sweep tests, performing further correction according to the comparison results, setting the model to be in a flight state, and obtaining a flight state space finite element model. The model can be used for performing dynamic response analysis, or be used for performing full-scale dynamic characteristic and full-scale dynamics response calculation on basic rockets.
Description
Technical field
The present invention relates to spacecraft dynamics analysis technical field, particularly to one collection frequency, the vibration shape and frequency
Ring the model modification method that function is integrated, for multi-branch complex space structure FEM (finite element) model is repaiied
Just.
Background technology
Upper Stage is between rocket and satellite, and for adapting to many stars launch mission, Upper Stage allotter often sets
The Complicated Spatial Structure that Ji Cheng branch is many, barycenter is high, frequency is low, some branch mode effective mass is relatively simultaneously
Greatly, add structural vibration response level and the risk of dynamic interference under state of flight to a certain extent, because of
This is necessary that setting up fine finite element indicates flight dynamic response, to formulate rational experimental condition
Or vibration suppression measure.Simultaneously in assembly Ground Vibration Test, for avoiding overtesting need to formulate different frequency
Interface acceleration under rate/interfacial force band paddy control condition, also proposes high requirement to finite element modeling precision.
Upper Stage Modifying model can not simply indiscriminately imitate carrier rocket or satellite mode, and carrier rocket slenderness ratio is relatively big,
Typically do not carry out whole arrow low-frequency vibration test, but Main Basis free boundary modal test is to frequency or the vibration shape
Being modified, but the low frequency capability for correcting of this modification method is limited, the general frequency correction upper limit is not more than
35Hz.Design of spacecraft structure is the compactest, does not the most carry out modal test, but the whole star of Main Basis is low
Frequency and frequency response function are modified by frequency vibration test, but this modification method is mainly used in checking entirety
The horizontal and vertical frequency of single order.
Upper Stage branched structure is many and branch mode effective mass is bigger so that a combination thereof body dynamics characteristic
More horn of plenty compared with conventional aerospace device, the upper frequency limit that need to verify is the highest (sometimes up to 40Hz even more
High), therefore need to explore the multi-branch complex space structure Finite Element Model Updating meeting requirement of engineering.
Summary of the invention
It is an object of the invention to overcome the deficiencies in the prior art, propose one collection frequency, the vibration shape and frequency response letter
The model modification method that number is integrated, the method is many for the branch of complex space configuration, barycenter is high, frequency
Low feature, carries out preliminary model analysis to the preliminary spatial finite element model set up, the most again to primary dcreening operation after
Model carry out mode and Frequency Response Analysis, and compare with the result of the test of modal test and sine sweep test
Right, according to comparison result, model is revised further, determine the model of state of flight, the party the most again
Method can realize frequency, the vibration shape and frequency response correction, and revised model is more accurate.
The above-mentioned purpose of the present invention is achieved through the following technical solutions:
A kind of model modification method integrating frequency, the vibration shape and frequency response function, comprises the steps:
(1), set trystate under, according to spacecraft each section structure, repropellenting quality,
Test boundary condition, sets up the spatial finite element model of spacecraft, and carries out each section inspection and combined physical examination
Look into: if checking that result meets setting demand, enter step (2)；If checking that result is unsatisfactory for setting to need
Ask, then return step (1) and described spatial finite element model is adjusted；
(2), spatial finite element model is carried out free state model analysis and clamped state model analysis；Point
Analysis result meets setting index, then enter step (3)；Otherwise return step (1) to Space finite element mould
Type is adjusted；
(3), to spatial finite element model carrying out model analysis and Frequency Response Analysis, concrete analysis process is as follows:
(3a), carry out clamped state model analysis, obtain the clamped model frequency of assembly and clamped vibration shape value；
Carry out free state model analysis, obtain assembly Free Modal frequency and free vibration shape value；
(3b) carry out frequency response analysis, obtain setting position acceleration frequence responses curve, described
Search the top n peak value after descending sequence on curve, record frequency values corresponding to described N number of peak value and
Accekeration；N is positive integer；
(4) model frequency, by outside modal test obtained and vibration shape value, with step (3a) model analysis
Obtain model frequency and vibration shape value contrasts, determine whether to carry out spatial finite element model according to comparing result
Revise；
(5) result of the test, by outside sine sweep test obtained, with step (3b) frequency response analysis
The frequency response results obtained contrasts, and determines whether that carrying out spatial finite element model repaiies according to comparing result
Just；
(6), spatial finite element model is set as state of flight, is used for carrying out dynamic response analysis, or uses
Dynamic Character and whole rocket dynamic response budget is carried out in base level rocket.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, in step (1)
In, when setting up the spatial finite element model of spacecraft, preferential use shell unit to be modeled, for can not
The parts being modeled with shell unit, use beam element, lumped mass dot element or solid element to be modeled.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, in step (2)
In, spatial finite element model is carried out free state model analysis and clamped state model analysis, concrete analysis
Process and outcome evaluation method are as follows:
Spatial finite element model is carried out free state model analysis, obtain each section, assembly each rank from
By model frequency, if the first six rank is zero-frequency and other each rank are non-zero-frequency, then judge that free state mode is divided
Analysis result meets setting index；
Spatial finite element model is carried out clamped state model analysis: obtain the first horizontal intrinsic Integral modes in rank
Frequency and the first rank longitudinally intrinsic Integral modes frequency, if two model frequency values are satisfied by the rocket set
Fundamental frequency index, then judge that clamped state modal analysis result meets and set index.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, it is judged that free module
Whether state frequency is that the concrete grammar of zero-frequency is as follows: each rank Free Modal free state model analysis obtained
Frequency compares with the zero-frequency thresholding of setting, if Free Modal frequency is less than or equal to zero-frequency thresholding, then
Judge that described Free Modal frequency is zero-frequency.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, it is judged that free module
Whether state frequency is that the concrete grammar of zero-frequency is as follows: Free Modal frequency and the first horizontal intrinsic Integral modes in rank
Frequency or the first rank longitudinally intrinsic Integral modes frequency ratio less than setting thresholding, then judges described Free Modal
Frequency is zero-frequency.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, in step (4)
In, the model frequency that outside modal test is obtained and vibration shape value, obtain mould with step (3a) model analysis
State frequency and vibration shape value compare, and determine whether to carry out spatial finite element model correction according to comparing result,
Implement process as follows:
(4a) model frequency, by modal test obtained obtains model frequency with model analysis and compares,
Obtain clamped frequency deviation fgWith free frequency deviation delta fz, whereinfgA
And fzAIt is respectively model analysis and obtains clamped model frequency and Free Modal frequency, fgBAnd fzBIt is respectively mode
Test the clamped model frequency and Free Modal frequency obtained；
(4b) clamped vibration shape value that vibration shape value and the model analysis, obtained by modal test obtains and freely shaking
Offset is compared and is obtained clamped vibration shape coincident indicator value MACgWith free vibration shape coincident indicator value MACz；
If (4c) Δ fg≤Δfth、Δfz≤Δfth、MACg≤MACthOr MACz≤MACth, then step is returned
(1), spatial finite element model is modified, wherein Δ fthAnd MACthIt is respectively the first frequency set inclined
Difference thresholding and vibration shape concordance thresholding.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, in step (5)
In, the result of the test that outside sine sweep test is obtained, obtain with step (3b) frequency response analysis
Frequency response results contrasts, and determines whether to carry out spatial finite element model correction according to comparing result, tool
It is as follows that body realizes process:
(5a) the N number of peak value respective frequencies value, by step (3b) recorded and accekeration, with outside just
Frequency values that N number of peak value in the acceleration frequence responses curve that string scan test obtains is corresponding and accekeration
Contrast, obtain corresponding relative frequency deviation and absolute acceleration deviation；
If (5b) relative frequency deviation is more than the second frequency deviation threshold set, then return step (1)
Carry out spatial finite element model adjustment；If absolute acceleration deviation is less than 0, then adjust modal damping value also
Return step (3b) and re-start frequency response analysis；Wherein, the initial value design of described modal damping value is
1%.
Above-mentioned a kind of model modification method integrating frequency, the vibration shape and frequency response function, in step (6)
In, after spatial finite element model is set as state of flight, first spatial finite element model is carried out free shape
State model analysis and clamped state model analysis, concrete analysis content is as follows:
Spatial finite element model is carried out free state model analysis, obtain each section, assembly each rank from
By model frequency；If the first six rank is zero-frequency and other each rank are non-zero-frequency, then judge the sky under state of flight
Between FEM (finite element) model normal；Otherwise it is judged as occurring extremely, then adjusting flight status parameter or Free Modal being divided
The boundary condition of analysis；
Spatial finite element model is carried out clamped state model analysis, checks the horizontal intrinsic Integral modes of assembly
Whether frequency and longitudinally intrinsic Integral modes frequency meet the fundamental frequency index of the base level rocket set.
Present invention advantage compared with prior art is:
(1), the present invention on the basis of traditional modal frequency and mode shape correction, screened by frequency response theory analysis
Go out crest frequency and the peak value of response in three orthogonal test directions, and carry out with ground sine sweep test result
Join, be effectively increased efficiency and the precision of kinetic model correction.
(2) present invention is by the assessment to modal damping value, can draw the power of traditional 1% modal damping value
Learn response theory value of calculation and can cover flight environment of vehicle value, if conservative conclusion.
Accompanying drawing explanation
Fig. 1 is the process stream of the model modification method integrating frequency, the vibration shape and frequency response function of the present invention
Cheng Tu；
Fig. 2 is that the acceleration responsive curve that medium frequency response analysis of the present invention obtains obtains with sine sweep test
The comparison diagram of acceleration scanning curve.
Detailed description of the invention
The present invention will be further described in detail with specific embodiment below in conjunction with the accompanying drawings:
The present invention is directed to the complex space configuration feature that Upper Stage allotter branch is many, barycenter is high, frequency is low,
Proposing a kind of model modification method integrating frequency, the vibration shape and frequency response function, the method is set up preliminary
Spatial finite element model carry out preliminary model analysis, the most again the model after primary dcreening operation is carried out mode and frequency response
Analyze, and compare, according to comparison result to mould with the result of the test of modal test and sine sweep test
Type is revised further, determines the model of state of flight the most again.Method flow diagram as shown in Figure 1,
The present invention integrates the model modification method of frequency, the vibration shape and frequency response function, implements step as follows:
The first step: finite element modeling and model trial inspection
Under the trystate set, according to spacecraft each section structure, repropellenting quality, test limit
Boundary's condition, sets up the spatial finite element model of spacecraft.Wherein, test boundary condition is freely to suspend operating mode in midair
Or fix support operating mode.When setting up this model, preferential use shell unit is modeled, for not using shell
The parts that unit is modeled, use beam element, lumped mass dot element or solid element to be modeled.
Then the preliminary spatial finite element model set up being carried out trial inspection, particular exam project includes: will
The quality of spatial finite element model check point, barycenter and rotary inertia value compare with setting value or test value
Relatively, if comparing whether the deviation value obtained meets requirement: if meeting, entering next step, otherwise returning
Spatial finite element model is adjusted by the first step.
During spatial finite element model is set up, need model unified to international single by non SI units system
Place value, needs to check for model modification situation not in place.
Second step, preliminary model analysis and correction
In this step spatial finite element model is carried out free state model analysis and clamped state model analysis
Concrete analysis process and outcome evaluation method are as follows:
Spatial finite element model is carried out free state model analysis, obtain each section, assembly each rank from
By model frequency, if the first six rank is zero-frequency and other each rank are non-zero-frequency, then judge that free state mode is divided
Analysis result meets setting index.And spatial finite element model is carried out clamped state model analysis, obtain first
The horizontal intrinsic Integral modes frequency in rank and the first rank longitudinally intrinsic Integral modes frequency, if two model frequencies
Value is satisfied by the rocket fundamental frequency index set, then judge that clamped state modal analysis result meets and set index.
If above analysis result is satisfied by setting index, then entering next step, otherwise returning the first step has space
Limit meta-model is adjusted.
In above free state model analysis, it is judged that whether Free Modal frequency is that the method for zero-frequency has two kinds:
1st kind: each rank Free Modal frequency that free state model analysis is obtained and the zero-frequency thresholding of setting
Compare, if Free Modal frequency is less than or equal to zero-frequency thresholding, then judge described Free Modal frequency
For zero-frequency.Zero-frequency thresholding can be set in the present embodiment as 10-5Hz。
2nd kind: Free Modal frequency is the most intrinsic with the first horizontal intrinsic Integral modes frequency in rank or the first rank
Integral modes frequency ratio less than setting thresholding, then judges that described Free Modal frequency is zero-frequency.In this enforcement
This threshold sets can be 0.1% by example.
3rd step: model analysis and Frequency Response Analysis
In this step, need spatial finite element model is carried out model analysis and Frequency Response Analysis, concrete analysis
Process is as follows:
(3a), carry out clamped state model analysis, obtain the clamped model frequency of assembly and clamped vibration shape value；
Carry out free state model analysis, obtain assembly Free Modal frequency and free vibration shape value；
(3b) carry out frequency response analysis, obtain setting position acceleration frequence responses curve, described
Search the top n peak value after descending sequence on curve, record frequency values corresponding to described N number of peak value and
Accekeration；N is positive integer.Carry out main reason is that of above operation: the peak value in Frequency Response Analysis is frequently
Model frequency in rate and clamped mode has certain corresponding relation, and the overall second order of multiple branching construction or three rank
Laterally frequency is relatively big on the impact of assembly acceleration responsive, therefore before modal test and Modifying model, and Ying Tong
Cross frequency response Analysis and Screening and go out all directions major peaks frequency and upper range thereof, carry out emphasis identification and correction.
In the present embodiment, when carrying out frequency response analysis, set input acceleration excitation frequency range as
5-100Hz, magnitude is 0.05g, and sets each rank modal damping as 1%.Obtain under this imposes a condition
Acceleration responsive curve is as in figure 2 it is shown, the theoretical value that also obtained by frequency response analysis in figure and sine sweep
Test value in test is contrasted.
4th step: modal analysis result compares with two modal testing results
In this step, the model frequency that outside modal test is obtained and vibration shape value, divide with the 3rd step mode
Analysis obtains model frequency and vibration shape value contrasts, and determines whether to carry out Space finite element mould according to comparing result
Type correction, implements process as follows:
(4a) model frequency, by modal test obtained obtains model frequency with model analysis and compares,
Obtain clamped frequency deviation fgWith free frequency deviation delta fz, whereinfgA
And fzAIt is respectively model analysis and obtains clamped model frequency and Free Modal frequency, fgBAnd fzBIt is respectively mode
Test the clamped model frequency and Free Modal frequency obtained；
(4b) clamped vibration shape value that vibration shape value and the model analysis, obtained by modal test obtains and freely shaking
Offset is compared and is obtained clamped vibration shape coincident indicator value MACgWith free vibration shape coincident indicator value MACz.
Wherein specific formula for calculation is:
{φtesti_gIt it is i-th clamped Modal Test vibration shape vector；
{φj_gIt it is jth clamped Analysis Mode vibration shape vector.
{φtesti_gIt it is i-th Free Test Mode Shape vector；
{φj_gIt it is jth free Analysis Mode vibration shape vector.
If (4c) Δ fg≤Δfth、Δfz≤Δfth、MACg≤MACthOr MACz≤MACth, then step is returned
(1), spatial finite element model is modified, wherein Δ fthAnd MACthIt is respectively the first frequency set inclined
Difference thresholding and vibration shape concordance thresholding.
5th step: frequency response analysis result compares with sine sweep test result
In this step, the result of the test obtained by outside sine sweep test, with the frequency response of the 3rd step
Analyze the frequency response results obtained to contrast, determine whether to carry out Space finite element mould according to comparing result
Type correction, implements process as follows:
(5a), by N number of peak value respective frequencies value of the 3rd step record and accekeration, sweep with outside sine
Retouch frequency values corresponding to the N number of peak value in the acceleration frequence responses curve that test obtains and accekeration is carried out
Contrast, obtains corresponding relative frequency deviation and absolute acceleration deviation.Wherein, the meter of relative frequency deviation
Calculation method is: first by poor to the frequency values of frequency response analysis record and the frequency values of sine sweep test, then
By this difference divided by test frequency value, obtain relative frequency deviation.Absolute acceleration deviation is equal to frequency response
The accekeration analyzing record deducts the accekeration of sine sweep test.
If (5b) relative frequency deviation is more than the second frequency deviation threshold set, then return step (1)
Carry out spatial finite element model adjustment；If absolute acceleration deviation is less than 0, then adjust modal damping value also
Return step the three step and re-start frequency response analysis.Wherein, in the frequency response analysis of the 3rd step,
Setting the initial value of modal damping value as 1%, this initial value is the most commonly used modal damping value,
The present invention can adjust this modal damping value according to absolute acceleration deviation, thus obtains having the most accurately
Limit meta-model.
6th step: determine state of flight model
In this step, spatial finite element model is set as state of flight, will relevant parameter in model
Value is all set as flight status parameter, thus obtains the spatial finite element model of state of flight, and this model can be used
In carrying out dynamic response analysis, or carry out Dynamic Character and whole rocket dynamic response is pre-for base level rocket
Calculate.
In this step, in order to determine that state of flight model state is normal, can be first to this Space finite element
Model carries out free state model analysis, obtains each rank Free Modal frequency of each section, assembly；If
The first six rank is zero-frequency and other each rank are non-zero-frequency, then judge that the spatial finite element model under state of flight is normal；
Otherwise it is judged as occurring extremely, then adjusts flight status parameter or the boundary condition of Free Modal Analysis.
Then this spatial finite element model is carried out clamped state model analysis, checks that assembly is horizontal intrinsic whole
Whether body model frequency and longitudinally intrinsic Integral modes frequency meet the fundamental frequency index of the base level rocket set.
Utilize the model parameter that the model modification method of the present invention obtains as shown in table 1, including test value,
Comparative result before Modifying model and after Modifying model, comparing result from table is it can be seen that relative frequency
Deviation is less than 10%, MAC value > 0.6, Modifying model effectiveness comparison is good.
Table 1 modal calculation value contrasts table with test value
The above, only one detailed description of the invention of the present invention, but protection scope of the present invention is not limited to
In this, any those familiar with the art, in the technical scope that the invention discloses, can think easily
The change arrived or replacement, all should contain within protection scope of the present invention.
The content not being described in detail in description of the invention belongs to the known skill of professional and technical personnel in the field
Art.
Claims (8)
1. the model modification method integrating frequency, the vibration shape and frequency response function, it is characterised in that: comprise the steps:
(1), under the trystate set, according to spacecraft each section structure, repropellenting quality, test boundary condition, setting up the spatial finite element model of spacecraft, and carry out each section inspection and assembly inspection: if checking that result meets setting demand, entering step (2)；If checking that result is unsatisfactory for setting demand, then return step (1) and described spatial finite element model is adjusted；
(2), spatial finite element model is carried out free state model analysis and clamped state model analysis；Analysis result meets setting index, then enter step (3)；Otherwise return step (1) spatial finite element model is adjusted；
(3), to spatial finite element model carrying out model analysis and Frequency Response Analysis, concrete analysis process is as follows:
(3a), carry out clamped state model analysis, obtain the clamped model frequency of assembly and clamped vibration shape value；Carry out free state model analysis, obtain assembly Free Modal frequency and free vibration shape value；
(3b) carry out frequency response analysis, obtain setting position acceleration frequence responses curve, described curve is searched the top n peak value after descending sequence, records frequency values corresponding to described N number of peak value and accekeration；N is positive integer；
(4) model frequency, by outside modal test obtained and vibration shape value, obtain model frequency with step (3a) model analysis and vibration shape value contrast, determine whether to carry out spatial finite element model correction according to comparing result；
(5) result of the test, by outside sine sweep test obtained, the frequency response results obtained with step (3b) frequency response analysis contrasts, and determines whether to carry out spatial finite element model correction according to comparing result；
(6), spatial finite element model is set as state of flight, is used for carrying out dynamic response analysis, or carries out Dynamic Character and whole rocket dynamic response budget for base level rocket.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 1, it is characterized in that: in step (1), when setting up the spatial finite element model of spacecraft, preferential use shell unit is modeled, for the parts can not being modeled with shell unit, beam element, lumped mass dot element or solid element is used to be modeled.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 1, it is characterized in that: in step (2), spatial finite element model carries out free state model analysis and clamped state model analysis, and concrete analysis process and outcome evaluation method are as follows:
Spatial finite element model is carried out free state model analysis, obtains each rank Free Modal frequency of each section, assembly, if the first six rank is zero-frequency and other each rank are non-zero-frequency, then judges that free state modal analysis result meets and set index；
Spatial finite element model is carried out clamped state model analysis: obtain the first horizontal intrinsic Integral modes frequency in rank and the first rank longitudinally intrinsic Integral modes frequency, if two model frequency values are satisfied by the rocket fundamental frequency index set, then judge that clamped state modal analysis result meets and set index.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 3, it is characterized in that: judge that whether Free Modal frequency is that the concrete grammar of zero-frequency is as follows: each rank Free Modal frequency free state model analysis obtained compares with the zero-frequency thresholding of setting, if Free Modal frequency is less than or equal to zero-frequency thresholding, then judge that described Free Modal frequency is zero-frequency.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 3, it is characterized in that: judge that whether Free Modal frequency is that the concrete grammar of zero-frequency is as follows: Free Modal frequency less than setting thresholding, then judges that described Free Modal frequency is zero-frequency with the first horizontal intrinsic Integral modes frequency in rank or the first rank longitudinally intrinsic Integral modes frequency ratio.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 1, it is characterized in that: in step (4), the model frequency that outside modal test is obtained and vibration shape value, obtain model frequency with step (3a) model analysis and vibration shape value compares, determine whether to carry out spatial finite element model correction according to comparing result, implement process as follows:
(4a) model frequency, by modal test obtained obtains model frequency with model analysis and compares, and obtains clamped frequency deviation fgWith free frequency deviation delta fz, whereinfgAAnd fzAIt is respectively model analysis and obtains clamped model frequency and Free Modal frequency, fgBAnd fzBIt is respectively clamped model frequency and Free Modal frequency that modal test obtains；
(4b) vibration shape value, obtained by modal test obtains clamped vibration shape coincident indicator value MAC compared with the clamped vibration shape value that model analysis obtains and free vibration shape valuegWith free vibration shape coincident indicator value MACz；
If (4c) Δ fg≤Δfth、Δfz≤Δfth、MACg≤MACthOr MACz≤MACth, then return step (1), spatial finite element model be modified, wherein Δ fthAnd MACthIt is respectively the first frequency deviation threshold and vibration shape concordance thresholding set.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 1, it is characterized in that: in step (5), the result of the test that outside sine sweep test is obtained, the frequency response results obtained with step (3b) frequency response analysis contrasts, determine whether to carry out spatial finite element model correction according to comparing result, implement process as follows:
(5a) the N number of peak value respective frequencies value, step (3b) recorded and accekeration, the frequency values corresponding with the N number of peak value in the acceleration frequence responses curve that outside sine sweep test obtains and accekeration contrast, and obtain corresponding relative frequency deviation and absolute acceleration deviation；
If (5b) relative frequency deviation is more than the second frequency deviation threshold set, then returns step (1) and carry out spatial finite element model adjustment；If absolute acceleration deviation is less than 0, then adjusts modal damping value and return step (3b) and re-start frequency response analysis；Wherein, the initial value design of described modal damping value is 1%.
A kind of model modification method integrating frequency, the vibration shape and frequency response function the most according to claim 1, it is characterized in that: in step (6), after spatial finite element model is set as state of flight, first spatial finite element model carries out free state model analysis and clamped state model analysis, and concrete analysis content is as follows:
Spatial finite element model is carried out free state model analysis, obtains each rank Free Modal frequency of each section, assembly；If the first six rank is zero-frequency and other each rank are non-zero-frequency, then judge that the spatial finite element model under state of flight is normal；Otherwise it is judged as occurring extremely, then adjusts flight status parameter or the boundary condition of Free Modal Analysis；
Spatial finite element model is carried out clamped state model analysis, checks whether the horizontal intrinsic Integral modes frequency of assembly and longitudinal intrinsic Integral modes frequency meet the fundamental frequency index of the base level rocket set.
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| CN107685878A (en) * | 2017-08-29 | 2018-02-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft dynamics monitoring method based on Frequency Response Analysis |
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| CN107144388A (en) * | 2017-05-17 | 2017-09-08 | 苏交科集团股份有限公司 | A kind of universe of flexible rope vibration frequency searches peak method |
| CN107685878B (en) * | 2017-08-29 | 2020-06-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft dynamics monitoring method based on frequency response analysis |
| CN107685878A (en) * | 2017-08-29 | 2018-02-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft dynamics monitoring method based on Frequency Response Analysis |
| CN107991080A (en) * | 2017-12-05 | 2018-05-04 | 中国人民解放军总参谋部第六十研究所 | A kind of high frequency Modal Analysis on Blade method based on non-contact vibration measuring and simulation calculation |
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| CN109506696A (en) * | 2018-12-17 | 2019-03-22 | 湖北工业大学 | A kind of frequency response function calibration method based on sensor mass identification |
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| CN110083946B (en) * | 2019-04-29 | 2023-06-06 | 北京工业大学 | Multi-state model correction method based on unconstrained optimization model |
| CN110956001A (en) * | 2019-12-05 | 2020-04-03 | 哈尔滨工业大学 | Step-by-step model correction method for solidus boundary conditions |
| CN114166443A (en) * | 2021-11-01 | 2022-03-11 | 中国运载火箭技术研究院 | Dynamic envelope interference test and improvement method for instrument mounting structure assembly |
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