该模型模拟的太阳风暴比2003年的Holloween超级太阳风暴还要强烈，并研究出结果中的电子助焊剂对低轨道地球卫星产生的影响。
The model simulated a solar storm stronger than the so-called Halloween solar superstorms of 2003 and investigated what effect the resulting flux of electrons would have on LEO satellites.
分析了卫星总体设计中轨道设计、卫星设计和发射选择间的耦合关系与协同效应，建立了MDO的简化模型。
The coupling relationship and associated effect among orbit design, satellite design and launch determination in the satellite system design were analyzed, and the simplified MDO module was founded.
研究了通过遗传算法模型优化设计侦察卫星轨道高度、轨道倾角、右升交点角及平近点角等轨道参数的方法。
Through the GA model, the orbital elements of each satellite such as altitude, inclination, RAAN and mean anomaly are optimized.
摘要 ：使用距离多普勒模型进行SAR影象几何校正时，卫星轨道误差、系统成像参数误差和DEM高程的误差会影响几何校正精度。
Abstract : When using the Range-Doppler model for SAR image geometric correction, the error of satellite orbit, imaging parameter and DEM elevation will affect the geometric correction accuracy.
求出位系数模型和大气阻力引起的重力梯度卫星的轨道误差；
The orbital errors due to the potential coefficient model and atmospheric drag for the gradiometry satellite are obtained;
对可见的卫星轨道部分先进行粗略定位，然后加入摄动模型进行精确求解。
For the visible parts, their rough location are done advanced, and then the perturbation model into the rough results is added in.
低轨重力卫星轨道的精确确定是获得精密地球重力场模型的前提，而精密重力场模型又是获得高精度定轨结果的保证。
On the other hand, the precision gravity model is important guarantees for obtaining high precision orbiting results using the dynamic or reduced-dynamic orbit determination method.
其次，针对编队飞行卫星队形保持控制，以对地等张角绕飞编队为背景设计相对轨道模型预测控制算法。
Secondly, a model predictive control method is designed for the satellite formation keeping and formation of invariant angular to the ground as the background.
建立了小卫星相对轨道和姿态的误差动力学模型，根据作业任务和姿态指向要求确定了小卫星相对轨道和姿态的期望运动；
Positional and attitude error dynamics model of small satellite relative to a target satellite was derived, then the desired relative orbit and desired attitude of small satellite were designed.
还建立了卫星姿态运动、轨道运动、地球自转、地球曲率、高斯投影等影响下的星载线阵c CD成像模型。
The satellite CCD photograph model under the effects of orbit motion, earth rotation, earth shape and the Gauss map, etc. is also presented.
并将其应用于高度为800公里ERS-1 卫星的轨道计算，结果表明：修订后的J77模型比其它大气模型在测轨精度上有明显改善。
The new version of J77 is found to be obviously advantageous to the precision orbit determination of ERS-1, which is at the height of 800km, compared with other atmospheric models.
第三章，建立了卫星轨道动力学模型，设计了GPS和运动方程组合的卡尔曼滤波器，并针对不同轨道高度的微小卫星进行了定位仿真。
In chapter 3, the orbit dynamics models are established, the Kalman Filter of the GPS and kinematics equation combined are designed, and simulations of different orbit Micro-satellite are done.
第三章，建立了卫星轨道动力学模型，设计了GPS和运动方程组合的卡尔曼滤波器，并针对不同轨道高度的微小卫星进行了定位仿真。
In chapter 3, the orbit dynamics models are established, the Kalman Filter of the GPS and kinematics equation combined are designed, and simulations of different orbit Micro-satellite are done.
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