Carrier transient response indication method based on star satellite load couple analysis result

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 [0001] The present invention relates to the technical field of vehicle design, in particular to a method for predicting and calculating the acceleration response of the vehicle / payload interface and internal nodes of the vehicle through the transient response method based on the vehicle / rocket interface coupling analysis time-domain acceleration data Vehicle Transient Response Prediction Method. Background technique [0002] In the development process of the vehicle, it is necessary to predict the acceleration response of the vehicle / payload interface and the internal nodes of the vehicle during the actual flight process in advance, so as to formulate the single machine mechanical environment test conditions according to the predicted calculation results. At present, the predictive calculation of the vehicle / payload interface and the acceleration response of the internal nodes of the vehicle is mainly carried out through the satellite-rocket load coupling ana...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is that the existing vehicle / payload interface and vehicle internal node response prediction calculation method can not meet the requirements of multiple prediction calculations in the development process of the vehicle or the mechanical environment test conditions formulated according to the calculation results The problem of not being able to respond to flight conditions well, and then provide a coupling analysis based on star-rocket loads that can not only conveniently perform multiple prediction calculations but also make the mechanical environment test conditions formulated according to the calculation results well respond to flight conditions Results of the Vehicle Transient Response Prediction Method

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