采用相对轨道要素设计了理想的基准伴随轨道。
The periodic relative orbit was designed based on the relative orbit elements and the mission requirements.
而这种情况，无法用地球轨道要素、太阳辐射和火山喷发等解释。
Such a significant phenomenon cannot be explained by variations in Earth's orbit, solar radiation or volcanic eruption.
根据相对轨道要素的变轨机动控制，进行编队飞行卫星群构型的初始化。
The configuration initialization of satellite formations is carried out based on orbit maneuver control...
基于经典轨道要素偏差法分析了相对运动特性和大气阻力对相对运动的影响。
By using the classical orbit element differences method, the periodic characteristics of relative motion and the influence of atmospheric drag on relative motion were analyzed.
它的实质是以轨道要素的平均变化率为基础的微分方程，而方程的右端包含定积分。
The essence of this method is a group of differential equations based on the average change rate of orbit elements, and the right sides of these equations contain definite integrals.
在解析轨道理论基础上，给出了平均轨道要素偏差到瞬时轨道要素偏差的状态转移矩阵。
On the basis of analytical orbit theory, the state transition matrix from mean to transient orbit errors was put forward.
阐述了临界倾角太阳同步回归轨道这种特殊椭圆轨道的设计方法，总结了其轨道要素的计算步骤。
The method of designing special elliptic orbit which was critical inclined, sun synchronous and repeating ground trace was expounded, and the calculation process of this method was summarized.
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.
并且根据卫星群偏心率与倾角综合的分离思想，讨论了两种策略，使得卫星群的构形可通过每个成员的轨道要素简单表出。
The satellites follow a combined eccentricity and inclination vector separation strategy, so that the group geometry can be expressed simply by the orbital elements of each member.
并且根据卫星群偏心率与倾角综合的分离思想，讨论了两种策略，使得卫星群的构形可通过每个成员的轨道要素简单表出。
The satellites follow a combined eccentricity and inclination vector separation strategy, so that the group geometry can be expressed simply by the orbital elements of each member.
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