轨道要素

用两体相对运动的线性Hill方程进行了小卫星编队飞行队形的初步设计，并给出编队飞行中各绕飞小卫星轨道要素的确定过程。

The preliminary design of small satellites formation flying and the solving process of orbital elements of each circling satellite are presented by using the linear Hill equations for the relative motion .

利用参照轨道要素设计卫星编队轨道

Orbit design for satellites in formation flight using reference orbital elements

从平近点角决定目视双星轨道要素T和P的一种方法

The orbit determination of visual binary star with mean anomaly

该文利用相对轨道要素法推导了包含J2项摄动和大气阻力摄动参考轨道为椭圆的卫星编队相对运动较精确的状态转移方程。

The state transition equation for the relative motion that includes the effects caused by the drag and J_2 is developed using the geometry method .

平均轨道要素及其在卫星星座设计中的应用

The Mean Orbit Elements and Its Application in the Satellite Constellation Design

小卫星编队飞行队形设计与轨道要素确定

Design of Small Satellites Formation Flying and the Determination of Orbital Elements

人造卫星轨道要素的计算

The calculation of the orbit of an artificial satellite

利用参照轨道要素研究卫星星座/编队的几何特征

Study of geometrical characteristics of satellites constellation / formation using reference orbital elements

用加速度计的积分遥测量计算弹道参数及轨道要素

Using integral telemetric data of accelerometer to calculate trajectory parameters and orbital elements

基于平均轨道要素的轨道修正方法

Orbit Modulation Method Based on Mean Orbit Elements

地球轨道要素的变化及其对气候长期变化的影响

The variation of earth 's orbital elements and its effect on earth 's climate system

太阳多方模型对行星轨道要素变化的长期摄动影响

The Secular Perturbation Effect of the Solar Polytropic Model on the Variation of Planetary Orbital Elements

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 of relative elements .

作为星下点分布的一维量度，星间角距可由参照轨道要素解析地表达。

The mean angular separation can be formulated by reference orbital elements as a one-dimensioned measure of subpoints distribution .

导出了基于相对轨道要素的编队飞行卫星群轨道相对运动控制的轨道机动方程；

This paper deduces the orbit maneuver equations for relative motion control of satellite formations based on the relative orbit elements .

提出了合适的控制策略，通过对瞬时轨道要素偏差进行控制，实现平均轨道要素偏差的调整目的。

A proper control strategy controlling the transient orbit element errors to realize the modulation of mean orbit element errors was given .

定义了一组参数来描述卫星编队飞行的相对运动，称为相对轨道要素。

A set of parameters called relative orbital elements were defined to describe the relative motion of the satellites in the formation flying .

分析了航天器近距离相对运动动力学模型，推导了采用基于相对轨道要素的相对运动描述模型；

Based upon analyzing the relative motion dynamics model of the closing spacecrafts , the relative motion model using relative orbit elements is presented .

双星多方模型的形状及其对同步子星轨道要素的摄动影响

Configuration of the Polytropic Model of Binary Star and Its Perturbation Influence on the Orbital Elements of the Synchronous Components in Close Binary System

首先将相对运动参数与轨道要素直接联系起来，详细推导了利用相对轨道要素来描述的相对运动方程，据此可直接得出环绕卫星的轨道根数；

Firstly , the equation of relative motion based on kinematics is presented in detail , so relative motion parameters may relate directly with orbit elements .

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 .

在星间链路空间几何特性分析的基础上，建立空间传输损耗和多普勒频移的仿真模型，仿真分析其随卫星轨道要素变化的规律。

The simulation modules of space transmission lose and Doppler frequency shift are presented based on the result of geometric characteristics analysis . Simulate the regular pattern .

本文利用摄动方法研究引力辐射阻尼对双星轨道要素产生的影响。

In this paper the effect of gravitational radiation damping on the variation of the orbital elements of binary system is studied using the method of perturbation .

适当调整每颗卫星的轨道要素可以保持卫星群的构形在空间不变，或者对地（近赤道观测站）不变。

The group geometry in space ( or reference to ground station ) can be keeped unchanged with a simple modification of the orbital elements of each member .

利用参照轨道要素方法能较方便地找到可能存在的理想编队轨道和队形，并解出相应的轨道要素；

The reference orbital elements approach is convenient for designing ideal formation orbits and configurations and can select the satellites ' initial states according to the formation features .

利用相对轨道要素的概念，在前面测量结果的基础上，通过卡尔曼滤波进一步提高了定轨精度。

On the base of measurement results from previous three projects , using the concept of relative orbit elements , precision of orbit determination is improved by Kalman filter .

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 .

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 .

利用球面几何方法，引入参照轨道要素概念，给出其定义，并推导了用其描述的从星相对运动方程的精确形式。

The concept and the definition of the reference orbital elements are introduced using spherical geometry . In terms of the reference orbital elements , governing equations for relative motion are formulated .

本文在对四冲量远程交会制导方法建模和分析的基础上，利用混合遗传算法对基于轨道要素的轨道设计进行了优化和仿真分析。

Based on the model and analysis of the four-impulse guidance method of the long-range of rendezvous , this paper uses hybrid genetic algorithms to optimize and simulate the orbit elements of orbit design .