说明：  以CZ 系列运载火箭为对象,提出了一种基于MATLABPSimulink 的运载火箭6 自由度运动仿真的方 法。采用模块化的建模思想,建立决定箭体运动相关部分的数学模型,包括空气动力模型、发动机推力模型、六自 由度运动学模型,然后对各个子模块分别采用Simulink 建立单元仿真模型。通过对单元仿真模型的集成得到了火 箭6 自由度运动的仿真模型,基于该仿真模型进行了单元仿真。对比实测数据,证明提出的方法可行,模型建立正 确。
(Distributed satellites (DS) moving in low earth orbit is suffered from the influence of atmospheric perturbation , and the orbit configuration of the DS is destroyed soon. The center of the relative orbit of the circling satellite is drifting continuously. This study was conducted to establish a compensatory approach to reduce the influence of atmospheric perturbation on the orbit configuration of the DS. Thus , the orbit configuration can be maintained naturally better. In the study , based on the atmospheric density model considering the effect of altitude change and diurnal variation of solar radiation , the semi- major axis perturbation equation of circling satellite with different initial phase in the DS is deduced. A semi- major axis modified method is presented to compensate the influence of atmospheric perturbation. It is shown from the simulation that the influence of the atmospheric perturbation can be decreased greatly in a given time period using this modified method)