| Sounding rocket is a launch vehicle with simple structure and without control system. Through changing the motor, it can get to different height, and it is far more economic than satellite and space station. Now it is widely used in near space environment detection, micro-gravity experiment, validation of new space technology and many other domain. In this paper, under the background of a type sounding rocket, the whole flight process is being modeled, the characteristics of both the separation and falling process of the parachute-sonde system are being discussed, the effect of error parameters on the flight’s height is being studied, considering wind’s effect on the whole process, a wind compensation method focused on the successfully separation is provided.First of all, the rocket models on the launching-rail and in the air are being established, and the basic characteristics of this process is analysed. Sinking angles’ effect of different launching elevation on the flight’s height is discussed.Secondly, the dynamic characteristic of parachute’s whole deploy process from separation to inflatable is being analysed. During this process, the distance between sonde and rocket’s body and possibility to collide is being studied.A multi-body model is built to study the relative motion of sonde and parachute in the wind.Then, chose the factors which may influence the height of the peak, carry out orthogonal test and do the simulation experiment. Through the analysis, the connection between factors and the peak height and the importance of each factor is discovered.What’s more, the separation condition of parachute-sonde system and rocket is studied. Based on the conclusion, through pattern search method, a wind conpensation method is introduced aiming at separation condition, and a simple interface is provided. Upon testing, the method is fast and have a high accuracy.This paper can provide references to design, analysis and research on relative problems on sounding rocket. |
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