CN105631179A - Carrier transient response indication method based on star satellite load couple analysis result - Google Patents
Carrier transient response indication method based on star satellite load couple analysis result Download PDFInfo
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- CN105631179A CN105631179A CN201410601583.3A CN201410601583A CN105631179A CN 105631179 A CN105631179 A CN 105631179A CN 201410601583 A CN201410601583 A CN 201410601583A CN 105631179 A CN105631179 A CN 105631179A
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Abstract
The present invention discloses a carrier transient response indication method based on a star satellite load couple analysis result. The method comprises the following steps of taking carrier or satellite interface time domain acceleration data obtained in the star satellite load couple analysis process as an agreed boundary between the carrier and the satellite in a certain research stage and loading the data to a carrier or satellite docking point in a combined body physical model of the carrier and effective load in a forced acceleration manner, and performing transient response analysis and calculation on the combined body physical model so as to obtain desired carrier or an effective load interface and response data of internal nodes of the carrier. According to the carrier transient response indication method based on the star satellite load couple analysis result, the large difference between boundary impedance and actual flying condition of the frequency response analysis method in response indication is prevented, and calculation number of times are not limited by whole satellite load couple analysis number of times, so that the local improvement effect of the carrier structure can be indicated and evaluated.
Description
Technical field
The present invention relates to vehicle design field, particularly relate to a kind of based on vehicle/rocket interface coupling analysis time domain acceleration information, by transient response method, vehicle/payload interface and carrier interior node acceleration responsive are carried out the vehicle transient response predicting method of indication calculating.
Background technology
In the development process of vehicle, need in advance vehicle in practical flight process/payload interface and carrier interior node acceleration to be responded to carry out indication calculating, in order to according to indicating that result of calculation carries out the work such as the formulation of unit dynamic environmental test condition. At present, the indication of vehicle/payload interface and carrier interior node acceleration response etc. calculates and carries out mainly through satellite and the rocket load coupling analysis process, contains vehicle/payload interface data and carrier interior node acceleration responsive data etc. in satellite and the rocket load coupling analysis result. Alternatively, it is also possible to adopt frequency response method that vehicle/payload interface and carrier interior node acceleration are responded carry out indication calculating, but both approaches is not all well positioned to meet the needs of vehicle development process, and reason is as follows:
Reaction flight features is can be good at according to the dynamic environmental test condition that the vehicle/payload interface obtained in satellite and the rocket load coupling analytical method process and carrier interior node acceleration response data are formulated, but it is due to the fact that to exist and cannot meet the problem that in vehicle development process, needs repeatedly carry out indication calculating: in vehicle mechanical environment, occupy important proportion owing to Launch Vehicle Engine starts the produced low frequency transient vibration environment of shutdown, carry out dynamic load coupling analysis to need to combine carrier rocket and vehicle to carry out, namely, as shown in Figure 1, satellite and the rocket load model of coupling needs integrated payload, vehicle, rocket tripartite's Dynamic Characteristics model, due to payload, vehicle and rocket each side Development Schedule and dynamic dynamics model real-time are difficult to matching and coordination, the work of load coupling analysis is made to there is iterative repetition workload big, cycle is long, the difficulties such as interface is unstable, and then make to carry out limited number of times within the development stage of whole vehicle by satellite and the rocket load coupling analysis, and on the other hand, vehicle can be proposed repeatedly local by vehicle development process change, such as, new unit is increased at some positions, or change the installation site of unit, improve every time and be required for carrying out indication calculating, thus the local change effect of carrier structure is indicated, therefore, the method that vehicle transient response is carried out indication calculating by satellite and the rocket load coupling analytical method is adopted to be difficult to meet the demand in the development process of vehicle,
Frequency response method is adopted to carry out vehicle/payload interface and carrier interior node RESPONSE CALCULATION, there is the problem that border impedance is bigger with practical flight operating mode difference, show as frequency response peak computational result higher, cause that unit low-frequency vibration test (one of the unit dynamic environmental test) condition formulated accordingly is comparatively harsh, this will make unit more for meeting environmental suitability weightening finish, thus affecting the carrying capacity of vehicle, if it is tight to utilize these data formulation unit experimental condition can cause that unit was examined, even there is meeting the possibility of mechanical environment adaptability requirement.
Summary of the invention
Present invention solves the technical problem that and be existing vehicle/payload interface and carrier interior node response indication computational methods do not adapt to need in vehicle development process to carry out repeatedly indication calculation requirement or the dynamic environmental test condition formulated according to result of calculation can not well react the problem of flight operating mode, and then provide a kind of and can either be conveniently carried out repeatedly indication and calculate the dynamic environmental test condition that can make again to formulate according to result of calculation and well react the vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of flight operating mode.
In order to solve above-mentioned technical problem, the technical solution used in 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, comprises the following steps:
S01: obtain the vehicle/rocket interface time domain acceleration information obtained in satellite and the rocket load coupling analysis process, it can be used as the agreement border between vehicle and rocket within certain development stage;
S02: adopt the payload physics or mathematical model that use in satellite and the rocket load coupling analysis in step S01 by docking formation assembly physical model, described payload physics or mathematical model according to the vehicle physical model after development progress or needs adjustment with payload physics or mathematical model;
S03: by the vehicle obtained in step S01/rocket interface time domain acceleration information to be loaded on the vehicle in described assembly physical model/rocket docking point in the way of degree of being accelerated up;
S04: the described assembly physical model loading vehicle/rocket interface acceleration time history is carried out instantaneous response analysis calculating and obtains required vehicle/payload interface and carrier interior node response data;
S05: after vehicle model adjusts again, then return and repeat step S02 to S04.
Preferably, step S04 adopts modal method carry out instantaneous response analysis, utilize structural eigenvector to be undertaken simplifying and decoupling by the equation of motion, each modal response superposition is obtained transient response result.
Preferably, before step S01, also include the step carrying out satellite and the rocket load coupling analysis.
Preferably, the vehicle/rocket interface time domain acceleration information obtained in step S01 is vehicle/rocket interface six-freedom degree time domain acceleration information.
Preferably, described vehicle/payload interface and carrier interior node response data include carrier interior and respectively specify interfacial force between the line/angular acceleration of position, speed, displacement and two groups of unit and interface moment.
Preferably, between step S04 and step S05, also include the step that by response spectra change, result in time domain is transformed into spectrum distribution.
Beneficial effects of 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, mathematical model based on rocket, forcing function comparative maturity, payload model dynamics is retrained by ICD, large change will not be there is within vehicle certain development stage, therefore vehicle/rocket interface typical condition time domain the acceleration information that can will obtain from a satellite and the rocket load coupling analysis, the provisioning interface as both sides is solidified within certain development stage, frequency response analysis method is not only avoided to respond the indication border impedance of problems and the bigger problem of practical flight operating mode difference, and the method calculation times of the present invention is not limited by whole rocket load coupling analysis number of times, such that it is able to the local change effect of carrier structure is indicated and evaluates, save lead time and management cost, effectively instruct the indication of vehicle mechanical environment and mechanical environment condition formulation work.
Accompanying drawing explanation
Fig. 1 is satellite and the rocket load coupling analytical method schematic flow sheet of the prior art;
Fig. 2 is the flow chart of the vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention;
Fig. 3 is the comparison of the payload interface data adopting the method for the present invention and satellite and the rocket load coupling analysis to obtain.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, technical scheme and beneficial effect are further illustrated.
Referring to accompanying drawing 2, the vehicle transient response predicting method based on satellite and the rocket load coupling analysis result of the present invention, comprise the following steps:
S01: obtain the vehicle/rocket interface time domain acceleration information obtained in satellite and the rocket load coupling analysis process, i.e. acceleration time history, it can be used as the agreement border between vehicle and rocket within certain development stage;
S02: adopt the payload physics or mathematical model that use in satellite and the rocket load coupling analysis in step S01 by docking formation assembly physical model, described payload physics or mathematical model according to the vehicle physical model after development progress or needs adjustment with payload physics or mathematical model;
S03: by the vehicle obtained in step S01/rocket interface time domain acceleration information to be loaded on the vehicle in described assembly physical model/rocket docking point in the way of degree of being accelerated up;
S04: the described assembly physical model loading vehicle/rocket interface acceleration time history is carried out instantaneous response analysis calculating and obtains required vehicle/payload interface and carrier interior node response data;
S05: after vehicle model adjusts again, then return and repeat step S02 to S04.
Wherein, step S04 can adopt modal method carry out instantaneous response analysis, utilize structural eigenvector to be undertaken simplifying and decoupling by the equation of motion, each modal response superposition is obtained transient response result. This method utilizes the size in structural eigenvector reduction problem solving space, decoupling motion equation, makes numerical solution highly efficient.
In the present invention, the vehicle/rocket interface time domain acceleration information obtained in step S01 is vehicle/rocket interface six-freedom degree time domain acceleration information, it is to avoid the phenomenon that in frequency response analysis, border impedance is inconsistent.
The present invention uses satellite and the rocket load coupling analysis data in step S01 and should obtain from completed satellite and the rocket load coupling analysis result, arranges the step carrying out satellite and the rocket load coupling analysis if desired before step S01.
Described vehicle/payload interface and carrier interior node response data include carrier interior and respectively specify the interfacial force between the line/angular acceleration of position, speed, displacement and two groups of unit and interface moment. By response spectra change, result in time domain is transformed into the step of spectrum distribution obtains shock response spectral curve by arranging between step S04 and step S05, for instructing the mechanical environment condition design at equipment, payload interface on vehicle system level interface, arrow.
Calculated for the predicting method of present invention vehicle/payload interface indication data are compared known with vehicle/payload interface data in whole rocket load coupling analysis result, consider and rocket battery's junction six-freedom degree time domain data owing to transient response calculates, do not deposit the phenomenon that in frequency response analysis, border impedance is inconsistent, as it is shown on figure 3, vehicle/payload interface time domain indication data are coincide better with coupling analysis value of calculation.
The predicting method of the present invention may apply in carrier interior node Environment Design:
Carrier interior node result of calculation is generally three directional acceleration response spectras of each node and key node place acceleration time history, interfacial force etc., as the indication of structure dynamic response under flight operating mode, it it is the important evidence of vehicle instrument and equipment mechanical environment condition formulation. Considering and rocket battery's junction six-freedom degree time domain data owing to transient response calculates, the phenomenon that to be absent from Frequency Response Analysis border impedance inconsistent, mechanical environment condition is formulated can reflect flight features.
The predicting method of the present invention applies also for the work such as reduction vehicle/payload interface shock response spectrum, vehicle partial structurtes effect of optimization analysis:
In working for satellite and the rocket load coupling analysis, payload interface shock response spectrum is analyzed work beyond environmental condition, adjust carrier structure parameter to be calculated, obtain payload interface time domain data and be processed into shock response spectrum, by adjusting the scheme of Different structural parameters, such as adjust adapter skin thickness, instrument room skin thickness, payload bracket upright post thickness etc., compare calculating, find reducing vehicle/maximally effective structural adjustment mode of payload interface shock response spectrum; Utilize same principle, carry out vehicle partial structurtes Optimization Work, the method according to the invention analysis optimization effect, so repeatedly, reach the effect that vehicle partial structurtes are optimized.
Claims (6)
1. based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result, it is characterised in that comprise the following steps:
S01: obtain the vehicle/rocket interface time domain acceleration information obtained in satellite and the rocket load coupling analysis process, it can be used as the agreement border between vehicle and rocket within certain development stage;
S02: adopt the payload physics or mathematical model that use in satellite and the rocket load coupling analysis in step S01 by docking formation assembly physical model, described payload physics or mathematical model according to the vehicle physical model after development progress or needs adjustment with payload physics or mathematical model;
S03: by the vehicle obtained in step S01/rocket interface time domain acceleration information to be loaded on the vehicle in described assembly physical model/rocket docking point in the way of degree of being accelerated up;
S04: the described assembly physical model loading vehicle/rocket interface acceleration time history is carried out instantaneous response analysis calculating and obtains required vehicle/payload interface and carrier interior node response data;
S05: after vehicle model adjusts again, then repeat step S02 to S04.
2. as claimed in claim 1 based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result, it is characterized in that: step S04 adopts modal method carry out instantaneous response analysis, utilize structural eigenvector to be undertaken simplifying and decoupling by the equation of motion, each modal response superposition is obtained transient response result.
3. as claimed in claim 2 based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result, it is characterised in that: before step S01, also include the step carrying out satellite and the rocket load coupling analysis.
4. as claimed in claim 3 based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result, it is characterised in that: the vehicle/rocket interface time domain acceleration information obtained in step S01 is vehicle/rocket interface six-freedom degree time domain acceleration information.
5. as claimed in claim 4 based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result, it is characterised in that: described vehicle/payload interface and carrier interior node response data include carrier interior and respectively specify the interfacial force between the line/angular acceleration of position, speed, displacement and two groups of unit and interface moment.
6. based on the vehicle transient response predicting method of satellite and the rocket load coupling analysis result as according to any one of claim 1 to 5, it is characterised in that: between step S04 and step S05, also include the step that by response spectra change, result in time domain is transformed into spectrum distribution.
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| CN108446457A (en) * | 2018-02-28 | 2018-08-24 | 北京空间飞行器总体设计部 | A kind of satellite carrier system dynamics response analysis method and system |
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| CN110431552A (en) * | 2017-03-14 | 2019-11-08 | 国家空间研究中心 | The method for combining system for analyzing delivery vehicle/passenger |
| CN113821869A (en) * | 2021-08-25 | 2021-12-21 | 浙江大学 | Multi-source data fusion-based aircraft force load online prediction method |
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