CN106596014B - One kind going straight up to vibration environmental simulation experiment method in cabin - Google Patents
One kind going straight up to vibration environmental simulation experiment method in cabin Download PDFInfo
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- CN106596014B CN106596014B CN201611068514.6A CN201611068514A CN106596014B CN 106596014 B CN106596014 B CN 106596014B CN 201611068514 A CN201611068514 A CN 201611068514A CN 106596014 B CN106596014 B CN 106596014B
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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Abstract
The invention discloses one kind to go straight up to vibration environmental simulation experiment method in cabin.It is described to go straight up to vibration environmental simulation experiment method in cabin and include the following steps: step 1: to obtain helicopter to be tested vertical vibration data in the cabin under actual flight state；Step 2: narrowband pass filter being carried out to vertical vibration data in cabin, to obtain airborne vibration data；Step 3: generating sinusoidal reference signal according to main paddle fundamental frequency in cabin is gone straight up to；Step 4: vibration excitor output signal is calculated by recurrence least square adaptive algorithm；Step 5: being that the helicopter to be tested or helicopter model to be tested carry out going straight up to vibration environmental simulation test in cabin by vibration excitor output signal.The vibration environmental simulation experiment method in cabin of going straight up to of the application can be used for the vibration environmentals in cabin of going straight up to of current all configurations and simulate, and provide vibration environmental for helicopter vibration active control system ground experiment.
Description
Technical field
The present invention relates to helicopter vibration analogue technique fields, go straight up to vibration environmental in cabin more particularly to one kind
Simulation experiment method.
Background technique
Helicopter vibration active control system ground experiment is mainly to vibration active control system to going straight up to position in cabin
The effectiveness in vibration suppression test set, the test of vibration damping robustness and compatibility test and the scientific research and testing of development stage.Realize helicopter
Position vibration environmental is identical as live flying vibration environment in cabin, interviews with being related to helicopter vibration active control system
The key tested.
In helicopter simulating cabin when position vibration environmental problem, the prior art generallys use spectral method, carries out
Level of vibration is simulated under predominant oscillatory frequencies.It goes straight up to vibration environmental simulation in position in cabin and is mainly passing through people at this stage
Work is simulated various flight operating condition methods and is realized.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
Vibration environmental simulation experiment method is gone straight up in cabin the purpose of the present invention is to provide one kind to overcome or extremely
Mitigate at least one drawbacks described above of the prior art less.
To achieve the above object, the present invention provides one kind to go straight up to vibration environmental simulation experiment method in cabin, institute
It states and goes straight up to vibration environmental simulation experiment method in cabin and include the following steps:
Step 1: obtaining helicopter to be tested vertical vibration data in the cabin under actual flight state；
Step 2: being center frequency to vertical vibration in the step 1 cabin obtained to go straight up to main paddle fundamental frequency in cabin
Dynamic data carry out narrowband pass filter, to obtain filtered airborne vibration data；
Step 3: going straight up to main paddle fundamental frequency generation sinusoidal reference signal in cabin according to described；
Step 4: according to the sinusoidal reference signal in the airborne vibration data and the step 3 in the step 2, and leading to
It crosses recurrence least square adaptive algorithm and calculates vibration excitor output signal；
Step 5: being that the helicopter to be tested or helicopter model to be tested are gone straight up to by vibration excitor output signal
Vibration environmental simulation test in cabin.
Preferably, the step 1 specifically: according to position in cabin is gone straight up to, vibrating sensor is arranged on helicopter, is surveyed
Measure the vertical vibration data d of the helicopter position under various flight operating conditions0。
Preferably, the step 2 specifically: go straight up to position in cabin under the various flight operating conditions measured according to step 1
Vertical vibration data d0, it is concerned about that (main paddle fundamental frequency) frequency carries out narrow bandpass as center frequency f to go straight up to position in cabin
Filtering, obtained filtered airborne vibration data d.
Preferably, the step 3 is specially sinusoidal using the generation of following formula according to position care frequency f in cabin is gone straight up to
Reference signal u；
U=sin (ft)；Wherein, t is the time；F is center frequency；U is sinusoidal reference signal.
Preferably, the step 4 specifically: filtered airborne vibration data d and step 3 are obtained according to the step 2
Obtained sinusoidal reference signal u calculates vibration excitor output signal using recurrence least square adaptive algorithm.
Preferably, the recurrence least square adaptive algorithm in the step 4 calculates vibration excitor output signal specifically:
The first step carries out algorithm initialization
P (0)=δ-1I
Second step is to each moment, and n=1,2 ... calculate
π (n)=P (n-1) u (n)
And
P (n)=λ-1P(n-1)-λ-1k(n)uH(n)P(n-1)
Third step, output vibration excitor control signal
Wherein,
I: unit diagonal matrix；K (n): the n-th moment, time-varying gain vector；D (n): second step obtains filtered flight vibration
The nth data of dynamic data d；P (n): the n-th moment, estimationCovariance matrix about noise variance δ2Normalization；N-th moment, tap weights vector estimation；ξ (n): the n-th moment, prior estimate error；π (n): the n-th moment, intermediate quantity；
N: iterative calculation moment；[]H: Matrix Conjugate transposition；λ: step parameter；Y (n): the n-th moment, vibration excitor control signal；
Initial time, tap weights vector estimation；P (0): initial time, estimationCovariance matrix about noise variance δ2Return
One changes；λ-1: step parameter；P (n-1): the (n-1)th moment, estimationCovariance matrix about noise variance δ2Normalizing
Change；U (n) are as follows: the sinusoidal reference signal input quantity of nth iteration；*: estimator.
The vibration environmental simulation experiment method in cabin of going straight up to of the application can be used for going straight up to for current all configurations
Vibration environmental is simulated in cabin, vibration environmental is provided for helicopter vibration active control system ground experiment, to straight
Rise machine vibration active control system design guidance direction.
Detailed description of the invention
Fig. 1 is the process signal according to an embodiment of the invention for going straight up to vibration environmental simulation experiment method in cabin
Figure.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
Fig. 1 is the process signal according to an embodiment of the invention for going straight up to vibration environmental simulation experiment method in cabin
Figure.
Vibration environmental simulation experiment method in cabin of going straight up to as shown in Figure 1 includes the following steps:
Step 1: obtaining helicopter to be tested vertical vibration data in the cabin under actual flight state；
Step 2: being center frequency to vertical vibration in the step 1 cabin obtained to go straight up to main paddle fundamental frequency in cabin
Dynamic data carry out narrowband pass filter, to obtain filtered airborne vibration data；
Step 3: generating sinusoidal reference signal according to main paddle fundamental frequency in cabin is gone straight up to；
Step 4: according to the sinusoidal reference signal in the airborne vibration data and the step 3 in step 2, and by passing
Least square adaptive algorithm is returned to calculate vibration excitor output signal；
Step 5: being that the helicopter to be tested or helicopter model to be tested are gone straight up to by vibration excitor output signal
Vibration environmental simulation test in cabin.
In the present embodiment, step 1 specifically: according to position in cabin is gone straight up to, vibrating sensor is arranged on helicopter,
Measure the vertical vibration data d of the helicopter position under various flight operating conditions0。
In the present embodiment, step 2 specifically: go straight up to position in cabin under the various flight operating conditions measured according to step 1
The vertical vibration data d set0, narrowband pass filter is carried out as center frequency f to go straight up to the main paddle fundamental frequency in position in cabin, is obtained
The filtered airborne vibration data d arrived.
In the present embodiment, the step 3 is specially that basis goes straight up to the main paddle fundamental frequency f in position in cabin using following public
Formula generates sinusoidal reference signal u；
U=sin (ft)；
Wherein, t is the time；F is center frequency；U is sinusoidal reference signal.
In the present embodiment, step 4 specifically: filtered airborne vibration data d is obtained according to step 2 and step 3 obtains
The sinusoidal reference signal u arrived calculates vibration excitor output signal using recurrence least square adaptive algorithm.
In the present embodiment, the recurrence least square adaptive algorithm in step 4 calculates vibration excitor output signal specifically:
The first step carries out algorithm initialization
P (0)=δ-1I
Second step is to each moment, and n=1,2 ... calculate
π (n)=P (n-1) u (n)
And
P (n)=λ-1P(n-1)-λ-1k(n)uH(n)P(n-1)
Third step, output vibration excitor control signal
Wherein,
I: unit diagonal matrix；K (n): the n-th moment, time-varying gain vector；D (n): second step obtains filtered flight vibration
The nth data of dynamic data d；P (n): the n-th moment, estimationCovariance matrix about noise variance δ2Normalization；N-th moment, tap weights vector estimation；ξ (n): the n-th moment, prior estimate error；π (n): the n-th moment, intermediate quantity；
N: iterative calculation moment；[]H: Matrix Conjugate transposition；λ: step parameter；Y (n): the n-th moment, vibration excitor control signal；
Initial time, tap weights vector estimation；P (0): initial time, estimationCovariance matrix about noise variance δ2Return
One changes；λ-1: step parameter；P (n-1): the (n-1)th moment, estimationCovariance matrix about noise variance δ2Normalizing
Change；U (n) are as follows: the sinusoidal reference signal input quantity of nth iteration；*: estimator.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (5)
1. one kind goes straight up to vibration environmental simulation experiment method in cabin, which is characterized in that described to go straight up to flight vibration in cabin
Dynamic environment simulation test method includes the following steps:
Step 1: obtaining helicopter to be tested vertical vibration data in the cabin under actual flight state；
Step 2: being center frequency to vertical vibration number in the step 1 cabin obtained to go straight up to main paddle fundamental frequency in cabin
According to narrowband pass filter is carried out, to obtain filtered airborne vibration data；
Step 3: going straight up to main paddle fundamental frequency generation sinusoidal reference signal in cabin according to described；
Step 4: according to the sinusoidal reference signal in the airborne vibration data and the step 3 in the step 2, and by passing
Least square adaptive algorithm is returned to calculate vibration excitor output signal；
Step 5: being that the helicopter to be tested or helicopter model to be tested carry out going straight up to cabin by vibration excitor output signal
Interior vibration environmental simulation test.
2. going straight up to vibration environmental simulation experiment method in cabin as described in claim 1, which is characterized in that the step
1 specifically: according to position in cabin is gone straight up to, vibrating sensor is arranged on helicopter, measures going straight up under various flight operating conditions
The vertical vibration data d that seat in the plane is set0。
3. going straight up to vibration environmental simulation experiment method in cabin as claimed in claim 2, which is characterized in that the step
2 specifically: the vertical vibration data d for going straight up to position in cabin under the various flight operating conditions measured according to step 10, to go straight up to
The main paddle fundamental frequency in position is that frequency f in center carries out narrowband pass filter, obtained filtered airborne vibration data d in cabin.
4. going straight up to vibration environmental simulation experiment method in cabin as claimed in claim 3, which is characterized in that the step
3 be specially that basis goes straight up to the main paddle fundamental frequency f in position in cabin using following formula generation sinusoidal reference signal u；
U=sin (ft)；
Wherein, t is the time；F is center frequency；U is sinusoidal reference signal.
5. going straight up to vibration environmental simulation experiment method in cabin as claimed in claim 4, which is characterized in that the step
Recurrence least square adaptive algorithm in 4 calculates vibration excitor output signal specifically:
The first step carries out algorithm initialization
P (0)=δ-1I
Second step is to each moment, and n=1,2 ... calculate
π (n)=P (n-1) u (n)
And
P (n)=λ-1P(n-1)-λ-1k(n)uH(n)P(n-1)
Third step, output vibration excitor control signal
Wherein,
I: unit diagonal matrix；K (n): the n-th moment, time-varying gain vector；D (n): second step obtains filtered airborne vibration number
According to the nth data of d；P (n): the n-th moment, estimationCovariance matrix about noise variance δ2Normalization；
N-th moment, tap weights vector estimation；ξ (n): the n-th moment, prior estimate error；π (n): the n-th moment, intermediate quantity；N: iteration meter
Calculate the moment；[]H: Matrix Conjugate transposition；λ: step parameter；Y (n): the n-th moment, vibration excitor control signal；When initial
It carves, tap weights vector estimation；P (0): initial time, estimationCovariance matrix about noise variance δ2Normalization；
λ-1: step parameter；P (n-1): the (n-1)th moment, estimationCovariance matrix about noise variance δ2Normalization；u
(n) are as follows: the sinusoidal reference signal input quantity of nth iteration；*: estimator.
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107818711B (en) * | 2017-12-03 | 2020-02-21 | 中国直升机设计研究所 | Single-degree-of-freedom vibration system for simulating helicopter vibration |
| CN110895184B (en) * | 2019-12-04 | 2021-09-21 | 中国直升机设计研究所 | Ground test system for unidirectional vibration reduction efficiency of helicopter vibration active control system |
| CN114115190B (en) * | 2021-11-19 | 2024-04-02 | 中国直升机设计研究所 | Simulation test bed for complex vibration environment of helicopter |
| CN114878121B (en) * | 2022-07-11 | 2022-09-23 | 中国飞机强度研究所 | Aerospace plane structure vibration environment simulation test method |
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| US5309766A (en) * | 1991-06-24 | 1994-05-10 | Aerospatiale Societe Nationale Industrielle | Helicopter shaft vibration simulator |
| US5390543A (en) * | 1992-06-03 | 1995-02-21 | Westland Helicopters Limited | Method and apparatus for in-flight shake testing of an aircraft fuselage |
| CN201364232Y (en) * | 2009-01-15 | 2009-12-16 | 江西昌河航空工业有限公司 | Test-state-based vibration exciter of helicopter blade |
| CN105092191A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material propeller fatigue test system and method |
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2016
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5309766A (en) * | 1991-06-24 | 1994-05-10 | Aerospatiale Societe Nationale Industrielle | Helicopter shaft vibration simulator |
| US5390543A (en) * | 1992-06-03 | 1995-02-21 | Westland Helicopters Limited | Method and apparatus for in-flight shake testing of an aircraft fuselage |
| CN201364232Y (en) * | 2009-01-15 | 2009-12-16 | 江西昌河航空工业有限公司 | Test-state-based vibration exciter of helicopter blade |
| CN105092191A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material propeller fatigue test system and method |
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