CN105631179B - Vehicle transient response predicting method based on satellite and the rocket load coupling analysis result - Google Patents
Vehicle transient response predicting method based on satellite and the rocket load coupling analysis result Download PDFInfo
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- CN105631179B CN105631179B CN201410601583.3A CN201410601583A CN105631179B CN 105631179 B CN105631179 B CN 105631179B CN 201410601583 A CN201410601583 A CN 201410601583A CN 105631179 B CN105631179 B CN 105631179B
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Abstract
The invention discloses a kind of vehicle transient response predicting methods based on satellite and the rocket load coupling analysis result, include the following steps：It will obtain on vehicle/rocket docking point that the vehicle/rocket interface time domain acceleration information obtained during satellite and the rocket load coupling analysis is loaded into vehicle and the assembly physical model of payload within certain development stage as the agreement boundary between vehicle and rocket in a manner of degree of being accelerated up, then instantaneous response analysis carried out to assembly physical model described in this, required vehicle/payload interface and carrier interior node response data is calculated.The vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention avoids frequency response analysis method and carries out the existing boundary impedance of response indication and the larger problem of practical flight operating mode difference, and calculation times are not limited by whole rocket load coupling analysis number, are indicated and are evaluated so as to the part change effect to carrier structure.
Description
Technical field
The present invention relates to vehicle design fields, more particularly to a kind of vehicle/rocket interface coupling that is based on to analyze
Time domain acceleration information, by transient response method to vehicle/payload interface and carrier interior node acceleration
Response carries out the vehicle transient response predicting method of indication calculating.
Background technology
In the development process of vehicle, need in advance to vehicle during practical flight/payload interface and
The response of carrier interior node acceleration carries out indication calculating, to carry out single machine dynamic environmental test according to indication result of calculation
The work such as the formulation of condition.Currently, the indication of vehicle/payload interface and the response of carrier interior node acceleration etc.
It calculates and is mainly carried out by satellite and the rocket load coupling analysis process, vehicle/effectively is contained in satellite and the rocket load coupling analysis result
Load interface data and carrier interior node acceleration responsive data etc..Alternatively, it is also possible to use frequency response method pair
Vehicle/payload interface and the response of carrier interior node acceleration carry out indication calculating, but both methods is equal
It is not well positioned to meet the needs of vehicle development process, the reason is as follows that：
According in the vehicle/payload interface and vehicle obtained during satellite and the rocket load coupling analytical method
The dynamic environmental test condition that portion node acceleration response data is formulated can be good at reacting flight features, but due to
Following reason, which there are problems that cannot be satisfied, to be needed repeatedly to carry out indication calculating in vehicle development process：Since carrier rocket is sent out
Motivation starts low frequency transient vibration environment caused by shutdown and occupies important proportion in vehicle mechanical environment, carries out dynamic and carries
Lotus coupling analysis needs carrier rocket and vehicle combining progress, that is, as shown in Figure 1, satellite and the rocket load coupling analysis
Model need to integrate payload, vehicle, rocket tripartite's Dynamic Characteristics model, since payload, vehicle and rocket are each
Square development progress and dynamic dynamics model real-time are difficult to matching and coordination so that there are iterative repetition work for the work of load coupling analysis
The difficulties such as amount is big, the period is long, interface is unstable so that by satellite and the rocket load coupling analysis entire vehicle development rank
Limited number can only be carried out in section, and on the other hand, it can propose that repeatedly part changes to vehicle in vehicle development process
It is dynamic, for example, increasing new single machine at some positions, or change the installation site of single machine, improves being required for being indicated every time
It calculates, to which the part change effect to carrier structure indicates, therefore, using satellite and the rocket load coupling analytical method to fortune
Device transient response is carried to carry out indicating that the method for calculating is difficult to meet the demand in the development process of vehicle；
Vehicle/payload interface and carrier interior node response computation are carried out using frequency response method, deposited
Impedance and the larger problem of practical flight operating mode difference on boundary, it is higher to show as frequency response peak computational result, leads to evidence
This single machine low-frequency vibration formulated experiment (one kind of single machine dynamic environmental test) condition is more harsh, this will make single machine be to meet
Environmental suitability weightening is more, to influence the carrying capacity of vehicle, if formulating single machine experimental condition using this data can lead
It causes single machine to examine sternly, or even occurs cannot be satisfied the possibility of mechanical environment adaptability requirement.
Invention content
Present invention solves the technical problem that being existing vehicle/payload interface and the response of carrier interior node
Indication computational methods, which do not adapt to either need to carry out in vehicle development process repeatedly to indicate, calculates requirement or according to calculating
As a result the dynamic environmental test condition formulated cannot react the problem of flight operating mode well, and then offer one kind can either facilitate
Ground carries out repeatedly indication and calculates and the dynamic environmental test condition formulated according to result of calculation can be made to react flight operating mode well
The vehicle transient response predicting method based on satellite and the rocket load coupling analysis result.
In order to solve the above-mentioned technical problem, the technical solution adopted by the present invention is as follows：
The vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention, including following step
Suddenly：
S01：Vehicle/rocket interface time domain the acceleration information obtained during satellite and the rocket load coupling analysis is obtained,
As the agreement boundary between vehicle and rocket in certain development stage；
S02：By the vehicle physical model after being adjusted according to development progress or needs and payload physics or mathematical modulo
Type docks to form assembly physical model, and the payload physics or mathematical model are coupled using satellite and the rocket load in step S01
The payload physics or mathematical model used in analysis；
S03：By the vehicle obtained in step S01/rocket interface time domain acceleration information in a manner of degree of being accelerated up
It is loaded on the vehicle in the assembly physical model/rocket docking point；
S04：The assembly physical model to loading vehicle/rocket interface acceleration time history carries out transient state sound
It should analyze and required vehicle/payload interface and carrier interior node response data is calculated；
S05：After vehicle model adjusts again, then returns and repeat step S02 to S04.
Preferably, instantaneous response analysis is carried out using modal method in step S04, is carried out the equation of motion using structural eigenvector
Simplify and decouple, each modal response is superimposed to obtain transient response result.
Preferably, further include the steps that carrying out satellite and the rocket load coupling analysis before step S01.
Preferably, the vehicle obtained in step S01/rocket interface time domain acceleration information is vehicle/rocket interface
Six-freedom degree time domain acceleration information.
Preferably, the vehicle/payload interface and carrier interior node response data include in vehicle
Interfacial force between line/angular acceleration of each designated position in portion, speed, displacement and two groups of units and interface torque.
Preferably, further include changing result in time domain being transformed into frequency spectrum by response spectra between step S04 and step S05
The step of distribution.
Beneficial effects of the present invention are as follows：
The vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention, the number based on rocket
Model, forcing function comparative maturity are learned, payload model kinetic characteristics are constrained by Interface Control File, certain in vehicle
Vehicle/the rocket that will not be varied widely, therefore can will be obtained from a satellite and the rocket load coupling analysis in development stage
Interface typical condition time domain acceleration information, provisioning interface of the solidification as both sides within certain development stage, not only avoids frequency
Rate response analysis method carries out the existing boundary impedance of response indication and the larger problem of practical flight operating mode difference, and makes
The method calculation times of the present invention are not limited by whole rocket load coupling analysis number, are changed so as to the part to carrier structure
Dynamic effect is indicated and is evaluated, and lead time and management cost are saved, and effectively instructs the indication of vehicle mechanical environment and power
It learns environmental condition and formulates work.
Description of the drawings
Fig. 1 is satellite and the rocket load coupling analytical method flow diagram in the prior art；
Fig. 2 is the flow of the vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention
Figure；
Fig. 3 is the comparison for the payload interface data that method using the present invention and satellite and the rocket load coupling analysis obtain.
Specific implementation mode
Technical scheme of the present invention and advantageous effect are further illustrated in the following with reference to the drawings and specific embodiments.
Referring to attached drawing 2, the vehicle transient response predicting method of the invention based on satellite and the rocket load coupling analysis result, packet
Include following steps：
S01：Vehicle/rocket interface time domain the acceleration information obtained during satellite and the rocket load coupling analysis is obtained, i.e.,
Acceleration time history, as the agreement boundary between vehicle and rocket within certain development stage；
S02：By the vehicle physical model after being adjusted according to development progress or needs and payload physics or mathematical modulo
Type docks to form assembly physical model, and the payload physics or mathematical model are coupled using satellite and the rocket load in step S01
The payload physics or mathematical model used in analysis；
S03：By the vehicle obtained in step S01/rocket interface time domain acceleration information in a manner of degree of being accelerated up
It is loaded on the vehicle in the assembly physical model/rocket docking point；
S04：The assembly physical model to loading vehicle/rocket interface acceleration time history carries out transient state sound
It should analyze and required vehicle/payload interface and carrier interior node response data is calculated；
S05：After vehicle model adjusts again, then returns and repeat step S02 to S04.
Wherein, may be used in step S04 modal method carry out instantaneous response analysis, using structural eigenvector by the equation of motion into
Row simplifies and decoupling, and each modal response is superimposed to obtain transient response result.This method reduces problem using structural eigenvector
The size of solution room, decoupling motion equation keep numerical solution highly efficient.
In the present invention, the vehicle/rocket interface time domain acceleration information obtained in step S01 is vehicle/rocket circle
Face six-freedom degree time domain acceleration information, avoids the phenomenon that boundary impedance is inconsistent in frequency response analysis.
The present invention uses satellite and the rocket load coupling analysis data in step S01 should be from completed satellite and the rocket load coupling analysis
As a result it is obtained in, when necessary before step S01 the step of setting progress satellite and the rocket load coupling analysis.
The vehicle/payload interface and carrier interior node response data include that carrier interior is each specified
Interfacial force between line/angular acceleration of position, speed, displacement and two groups of units and interface torque.By in step S04 and step
The step of result in time domain is transformed into spectrum distribution by setting by response spectra variation between S05 obtains shock response spectral curve, uses
In instruct vehicle system grade interface, equipment, the design of the mechanical environment condition at payload interface on arrow.
Vehicle/payload interface indication data that the predicting method of the present invention is calculated are coupled with whole rocket load
Vehicle/payload interface data is compared it is found that since transient response calculating considers and rocket battery in analysis result
Junction six-freedom degree time domain data, does not deposit the phenomenon that boundary impedance is inconsistent in frequency response analysis, as shown in figure 3, delivery
Device/payload interface time domain indication data are coincide preferable with coupling analysis calculated value.
The predicting method of the present invention can be applied in carrier interior node Environment Design：
Carrier interior node result of calculation, which is generally at three directional acceleration response spectras of each node and key node, to be added
Velocity Time course, interfacial force etc. are vehicle instrument and equipment mechanical environments as the indication of flight operating mode lower structure dynamic response
The important evidence that condition is formulated.Due to transient response calculating consider with rocket joint face six-freedom degree time domain data, do not deposit
The inconsistent phenomenon of boundary impedance in Frequency Response Analysis, mechanical environment condition formulation can reflect flight features.
The predicting method of the present invention applies also for reducing vehicle/payload interface shock response spectrum, delivery general ability
The work such as portion's structure optimization effect analysis：
Payload interface shock response spectrum is analyzed beyond environmental condition in working for satellite and the rocket load coupling analysis
Work, adjustment carrier structure parameter are calculated, and are obtained payload interface time domain data and are processed into shock response spectrum, lead to
The scheme of adjustment Different structural parameters is crossed, such as adjustment adapter skin thickness, instrument room skin thickness, payload branch erect
Column thickness etc. is compared calculating, finds to reducing vehicle/most effective structural adjustment of payload interface shock response spectrum
Mode；Using same principle, vehicle partial structurtes Optimization Work is carried out, according to the method for the present invention analysis optimization effect, such as
This achievees the effect that optimize vehicle partial structurtes repeatedly.
Claims (6)
1. the vehicle transient response predicting method based on satellite and the rocket load coupling analysis result, which is characterized in that including following step
Suddenly：
S01：The vehicle obtained during satellite and the rocket load coupling analysis and rocket interface time domain acceleration information are obtained, certain
As the agreement boundary between vehicle and rocket in development stage；
S02：By the vehicle physical model after being adjusted according to development progress or needs and payload physics or mathematical model pair
It connects to form assembly physical model, the payload physics or mathematical model are using satellite and the rocket load coupling analysis in step S01
The middle payload physics used or mathematical model；
S03：The vehicle obtained in step S01 and rocket interface time domain acceleration information are loaded in a manner of degree of being accelerated up
To in the assembly physical model vehicle or rocket docking point on；
S04：Transient response is carried out to the assembly physical model of load vehicle or rocket interface acceleration time history
Required vehicle and payload interface and carrier interior node response data is calculated in analysis；
S05：After vehicle model adjusts again, then step S02 to S04 is repeated.
2. the vehicle transient response predicting method as described in claim 1 based on satellite and the rocket load coupling analysis result, feature
It is：Instantaneous response analysis is carried out using modal method in step S04, the equation of motion is simplified and solved using structural eigenvector
Each modal response is superimposed to obtain transient response result by coupling.
3. the vehicle transient response predicting method as claimed in claim 2 based on satellite and the rocket load coupling analysis result, feature
It is：Further include the steps that carrying out satellite and the rocket load coupling analysis before step S01.
4. the vehicle transient response predicting method as claimed in claim 3 based on satellite and the rocket load coupling analysis result, feature
It is：The vehicle or rocket interface time domain acceleration information obtained in step S01 is vehicle or six, rocket interface freedom
Spend time domain acceleration information.
5. the vehicle transient response predicting method as claimed in claim 4 based on satellite and the rocket load coupling analysis result, feature
It is：The vehicle or payload interface and carrier interior node response data include each specific bit of carrier interior
Interfacial force between line or angular acceleration, speed, displacement and the two groups of units set and interface torque.
6. the vehicle transient response indication based on satellite and the rocket load coupling analysis result as described in any one of claim 1 to 5
Method, it is characterised in that：Further include that result in time domain is transformed by frequency by response spectra variation between step S04 and step S05
The step of Spectral structure.
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| FR3064089B1 (en) * | 2017-03-14 | 2019-04-19 | Centre National D'etudes Spatiales | METHOD FOR ANALYZING A VEHICLE / PASSENGER TORQUE SYSTEM |
| CN108446457B (en) * | 2018-02-28 | 2022-03-04 | 北京空间飞行器总体设计部 | Method and system for analyzing dynamic response of satellite star frame system |
| CN109858189B (en) * | 2019-01-09 | 2023-03-31 | 蓝箭航天空间科技股份有限公司 | Carrier rocket load analysis method |
| CN113821869B (en) * | 2021-08-25 | 2024-03-19 | 浙江大学 | Aircraft force load online prediction method based on multi-source data fusion |
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