You will now have a new set of improved orbital elements.
你现在有了新的经过改进的轨道参数。
Based on a point source model, new spectroscopic orbital elements are determined.
依据点源模型获得了一组新的分光轨道解。
The perturbation effect of the earths magnetic field on the orbital elements of a charged satellite is further studied.
研究了地球磁场对带电的非赤道卫星的轨道根数的摄动影响。
Through the GA model, the orbital elements of each satellite such as altitude, inclination, RAAN and mean anomaly are optimized.
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。
All classic orbital elements and usual angular motion parameters can be calculated with the new set of generalized coordinates and their rates.
经典的质心轨道根数，以及系绳在质心轨道面内与轨道面外的摆动角，均可由上述六个广义坐标及其广义速度确定。
The influence of the variation of solar mass on the orbital elements of Asteroids is studied by using the method of Celestial Mechanics with variable mass.
利用变质量天体力学方法研究了太阳质量变化对小行星轨道根数的影响。
Based on the C-W equation, equations with both rectangular coordinates and orbital elements for the impulse maneuvers in long-distance guidance are derived.
基于C - W方程，推导了用直角坐标和轨道根数描述的远程导引段多冲量变轨段策略的方程，同时给出了求解方程组的迭代算法。
Simulation of the relative trajectories with various orbital elements and a qualitative theoretical analysis illustrate the advantages of the orbital elements method.
仿真了各种不同轨道根数下的相对运动轨迹，与定性的理论分析进行比较，说明了轨道根数描述方法的优越性。
The influences of the electronic induction drag on the variation of the orbital elements of a charged satellite moving in a magnetic-field-free ionosphere are studied.
研究了在高空电离层中运动的带电荷的卫星受电感应阻力后对轨道根数产生的摄动影响。
The secular influence of solar mass-loss on the orbital elements of meteor steams is examined by using the method of celestial mechanics of variable mass in this paper.
将作者在变质量天体力学所得理论结果应用于太阳质量损失对流星群轨道根数变化的长期效应上。
Finally, the orbital elements are introduced as state variables and the accelerations are produced by equation as control variables, the space interception model is established.
最后，采用轨道根数作为状态变量，以航天器发动机产生的推力加速度作为控制变量建立空间拦截模型。
This paper presents a method by using of which the orbital elements of two spacecrafts can be determined by an adjoint orbit. Also, this method can be used to the condition of multi-spacecraft.
文中给出一种从伴随轨道确定两个航天器轨道要素的方法，这一方法也可推广应用于多个航天器的情况。
This paper presents a method by using of which the orbital elements of two spacecrafts can be determined by an adjoint orbit. Also, this method can be used to the condition of multi-spacecraft.
文中给出一种从伴随轨道确定两个航天器轨道要素的方法，这一方法也可推广应用于多个航天器的情况。
应用推荐