地球扁率

在地球扁率摄动下的卫星编队飞行控制

Control of Satellites Formation Flying in Earth Oblateness Perturbation Environment

卫星编队飞行的地球扁率摄动分析

Analysis of the Earth oblateness perturbation on formation flying satellites

首先，在CW方程的基础上，分别求解了地球扁率的整体摄动和相对摄动，分析了摄动规律。

First , bulk and relative perturbation of J2 term are solved and analyzed based on the CW equations .

本文研究了地球扁率J2项摄动对卫星编队飞行的影响。

The J 2 effect on satellite formation flying is investigated .

针对地球扁率（J2）的影响，给出了一种修正方法，提高了本方法的计算精确度。

A modified method is presented to improve calculating accuracy of this method aimed at the effect of earth eccentricity ( J_2 ) .

给出了卫星悬停的轨道动力学模型，不考虑地球扁率J2摄动影响，通过在一段时间内对轨道实施连续有限推力控制，使得卫星运行在新的轨道上，实现对目标卫星的悬停。

Dynamics analysis of hovering orbit was presented , not considering J2 perpetual . By implementing a continuous pulse thrust control , the satellite was kept in a period of time on a new hovering orbit other than Kepler orbit .

地球扁率引起红外地平仪姿态量测误差的数学模型

Mathematical model of attitude correction of scanning horizon sensor for earth oblateness

考虑地球扁率的大椭圆轨道编队飞行优化设计

J_2 Optimization Design of Formation Satellites in Highly Elliptic Orbits

考虑地球扁率影响的任意椭圆轨道小推力最优交会控制

Optimum Low-Thrust Power Rendezvous between Neighboring Elliptic Orbits Considering the Oblateness of Earth

详细计算分析了地球扁率对最优轨道的影响。

The changes of optimal trajectory caused by Earth 's oblateness are computed .

一种考虑地球扁率的卫星自主导航方法研究

Autonomous Navigation with Earth Oblateness Compensation for Satellite

基于地球扁率红外地平仪测量值修正算法研究

The correction algorithms of measurement of the scanning horizon sensor based on earth oblateness

考虑地球扁率效应的两圆轨道之间的双共切最优转移

Optimal Dual-Tangential Transfer Between Two Circular Orbits in Consideration of the Earth 's Flattening Effect

第一节研究主惯性矩和地球扁率的计算公式；

Section 1 formulates the Earth 's principal moments of inertia and the Earth 's flattening ;

而采用相应方法对地球扁率影响进行改正后，温度廓线的误差明显减弱，从而证明了改正方法的正确性。

The correction method is tested useful because the temperature errors decreased obviously with this method .

建立了考虑地球扁率的远程弹道导弹动力学与运动学方程组。

The dynamics equations and kinematic equations of ballistic missile are established , in which Earth oblateness is considered .

针对地球扁率，基于方位角的确定，分别给出了滚动角和俯仰角的测量误差模型。

In allusion to Earth 's oblateness , roll / pitch models of attitude correction based on the azimuths are given .

从动力学出发在考虑大气阻力和地球扁率的情况下推导出详细的航天器相对运动方程表达式。

The effects of air drag and oblateness of the earth on relative orbit were derived by simulations under different conditions .

分析得出地球扁率和红外辐射是扫描式红外地平仪测量误差的主要原因。

The reason of attitude correction of scanning infrared horizon sensor is presented by reason of Earth 's oblateness and infrared radiation .

接着考虑安全性和编队飞行相对距离的限制，研究了绕飞轨道的相对轨道要素取值范围，详细推导了大气阻力摄动与地球扁率摄动的相对摄动表达式。

Then , considering safety and limit of relative distance of formation flying , the select area of relative orbit elements are studied .

本文求得了空间飞行器在地球扁率摄动作用下简单形式的一阶解。

A Simple form unretarted orbit of space vehicles under the first order perturbation of the oblateness of the earth is obtained in this paper .

在考虑地球扁率以及再入段空气阻力的情况下对落点偏差进行补偿，得到虚拟目标。

The landing error , considering the Earth oblateness and the air friction in the reentry phase , is compensated and the virtual target is hit .

求解需要速度时，实时地考虑了地球扁率的影响，并给出了利用中间轨道法求解需要速度的过程。

When solving required velocity , It real-timely thinks about influence of oblateness of the earth and gives the process of solving required velocity by midcourse trajectory method .

讨论地球扁率对人造地球卫星轨道平面的影响，介绍卫星的太阳同步轨道设计原理。

The effect of the flat rate of the earth on the orbit planes of satellites is discussed and the design principle of sun-synchronous orbit of satellites is introduced .

采用运动学变量建立的最优控制方程可以得到空间转移轨道的解析解，且在考虑地球扁率摄动时也能得到解析解。

The optimal control equations based on kinematic variables can get its analytic solution of space orbit transfer and can get the analytic solution when considering the Earth 's oblateness .

分析了引起地平仪测量误差的主要误差源&地球扁率和大气红外辐射不均匀性。

The first part is to analyze the two error sources of the earth horizon sensor : one is earth oblateness and the other is non-uniformly distributed atmospheric infrared radiation .

摄动因素对卫星编队飞行的影响以及如何尽量减小摄动影响是应用中非常关心的问题，本文考虑地球扁率和大气阻力两种摄动因素，对此进行了研究。

Much attention is paid to the effect of perturbations on satellite formation flying and how to decrease the effect , which are studied with the Earth oblateness and atmospheric drag considered .

本文采用模拟的方法，分析其中地球扁率及电离层对反演结果的影响，并讨论局部圆弧修正及电离层修正的效果。

In this paper , we discuss the effect of the Earth 's oblateness and ionosphere on the retrieval , and analyze the result of the local curvature correction and the ionosphere calibration .

基于拉格朗日轨道动力学方程，本文分析了地球扁率摄动、大气阻力摄动以及太阳引力对卫星动力学影响，通过适当简化，建立简化卫星轨道动力学模型。

Based on the Lagrange orbit dynamic formulas , the effect of earth oblateness perturbation , atmospheric drag and solar gravitation was analyzed . Through proper simplifying , simple orbit dynamic model of satellite were set up .

应用最新的海洋模式数据，研究了海水质量再分布对地球动力学扁率变化（δJ2）的影响。

Based on the most recently global numerical ocean models , the effect of oceanic mass redistribution on the Earth 's oblateness variation is examined .