In addition, a simulated orbit equation for saltation was derived.
特别对跃移运动还给出模拟轨迹方程。
The paper researches into the orbit equation of the projectile motion and the projectile crosswise deviation when the earth rotates.
本文通过研究地球自转时抛体运动的轨道方程和抛体的横向偏离等，揭示了地球自转对抛体运动的影响。
Based on the orbit equation of particle motion in central force field, the stable property and close property of orbit were discussed.
在中心势场中粒子运动轨道方程的基础上，进一步讨论粒子轨道的闭合性、稳定性。
The motion of charged particle acted upon by Lorentz force and other external force are analyzed, calculating formulae of orbit equation and curvature radius are derived.
分析了带电粒子受到洛伦兹力和其他恒定外力作用下的运动情况，导出了轨道方程和曲率半径的计算公式。
Use static elements or relative static elements in the changing graph to get the main moving point and its relations with other known conditions to correctly calculate the orbit equation.
利用变动图形吕的静止或相对静止因素，抓住主要动点及其与已知条件的联系，正确求出轨迹方程。
Also that velocity, v, in that equation number five will also change with time because it's an elliptical orbit.
同样的，第五个方程序，中的速度同样，会随时间改变，因为这是椭圆形轨道。
This algorithm avoids soling differential equation frequently as well as redundant orbit, and it is easy to control the accuracy and to get the picture of manifold.
该算法避免了频繁求解微分方程问题，没有求解多余的轨道，且求解的精度也容易控制，得到的流形图直观。
Considering constraints of energy, time and line-of-sight angle, a near-range autonomous rendezvous glidescope orbit design method is studied based on the differential equation method.
考虑能量、时间、视线等约束条件，基于微分方程法研究了近程自主交会滑移轨道设计方法。
In this paper , the undermined function method has been used to study the analytic solution of nonlinear orbit differential equation. In a case four kinds analytic solution are given.
利用待定函数法研究了非线性轨道微分方程的解析解，求出了一类情形下的四类解析解。
Near-field autonomous rendezvous orbit design problem is discussed by adopting CW equation in the paper.
采用线性化CW方程研究了空间飞行器近程自主交会轨道设计问题。
A quantized elliptical orbit of electron in hydrogen_like atom is concisely derived from Binet equation with the aid of Bohr_Sommerfeld s quantized condition.
从比耐公式出发，结合玻尔———索末菲量子化条件，对类氢原子电子的量子化椭圆轨道，给出了一个简化的推导，并在此基础上，对轨道的稳定性进行进一步的讨论。
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。
The variation equation of the satellite orbit elements under both J2 and drag perturbations was derived based on the Gauss perturbation equation.
基于高斯摄动方程，推导了卫星在同时考虑J2和大气摄动情况下的轨道根数变化方程。
A new algorithm was developed throw the tailor equation based on the imaging analysis. The new algorithm can supply the high precise attitude data even in the low orbit.
依据成像几何分析通过泰勒展开公式推导并提出了新的姿态角运算方法，保证了低轨道姿态运算精度；
The combined radiation and conduction heat transfer in multilayer perforated insulation material MLPIM in orbit were investigated. The energy equation of the reflective screen was established.
分析了空间多层打孔隔热材料中导热和辐射换热的复合传热问题，建立了关于反射屏的能量方程。
The precision of hanging dynamic model based on CW equation was analyzed in detail, and a low earth orbit satellite octahedron configuration was simulated for validation.
对基于C-W方程的悬停动力学模型进行了精度分析，最后以低轨道航天器的八面体编队构型为例进行了数学仿真验证。
The precision of hanging dynamic model based on CW equation was analyzed in detail, and a low earth orbit satellite octahedron configuration was simulated for validation.
对基于C-W方程的悬停动力学模型进行了精度分析，最后以低轨道航天器的八面体编队构型为例进行了数学仿真验证。
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