航天器轨道

提出了利用GPS导航数据片段和SGP4模型进行航天器轨道自主预报的方法。

The autonomous prediction of spacecraft orbit based on GPS navigation data segment and Simplified General Perturbations Version 4 model is put forward .

本文结合XXX追踪与反追踪技术课题，利用遗传算法对航天器轨道机动问题进行了研究。

Based on " Space maneuver platform technology " issues and using genetic algorithms on spacecraft orbit maneuver , this paper conducted a study .

本文导出了基于对象CARMA模型的多变量广义预测自适应控制器，并将这种新的控制方法应用于航天器轨道控制中。

It is presented in this paper a multivariable generalized predictive adaptive controller based on CARMA model and its application in the orbit control of spacecraft .

为了在航天器轨道机动过程中减小滤波器的估计误差，设计了用于航天器自主导航的自适应鲁棒扩展卡尔曼滤波（AREKF）算法。

In order to decrease the estimation error of the filter during orbit maneuvers of the spacecraft , an adaptive robust extended Kalman filter ( AREKF ) is designed for spacecraft autonomous navigation .

有限推力作用下航天器轨道优化设计方法研究

Study on Optimal Orbit Design for Spacecraft with Finite Thrust

航天器轨道和姿态参数对光学成像的影响分析

The Effect Analysis of Spacecraft Orbit and Attitude Parameters on Optical Imaging

航天器轨道向导式设计器的设计与实现

Design and Realization of Wizard Designer for Spacecraft Orbit

还讨论了比动能方程在上述两航天器轨道相遇和轨道交会问题中的应用。

The applications of ESKE to orbit meet and orbit rendezvous are discussed .

航天器轨道设计系统的小型化实现

Realization of A Small System of Spacecraft Orbit Design

航天器轨道机动过程中的自主导航方法

An Autonomous Navigation Method for Spacecrafts during Orbit Maneuver

航天器轨道设计因卫星应用目的和总体设计方案的不同而灵活多样。

Orbit design of Spacecraft is agility due to different application and overall solution .

先进航天器轨道快速优化

Fast Trajectory Optimization for Advanced Space Vehicle

载人航天器轨道运行段的救生问题

RESCUE FROM ORBITING MANNED SPACECRAFT manned spaceflight

航天器轨道转移与交会最优控制研究

Optimum Orbit Transfer and Rendezvous of Spacecraft

航天器轨道交会的一般策略

General Strategies for Orbital Rendezvous

在航天器轨道和碎片云中心轨道都确定情况下，研究了碰撞概率的一般算法；

General methods for calculating impact probability are introduced in the case that orbit errors are not considered .

根据航天器轨道动力学方程，建立航天器自主导航系统状态方程。

Based on the precise orbit dynamics model , the state function of spacecraft autonomous navigation systerm is established .

适应航天技术发展需求，建设多层次航天器轨道理论与应用系列课程

The Establishment of Series Courses of Spacecraft Orbit Theory and Application According to the Requirements of the Development of Space Technology

航天器轨道的确定是对航天器进行制导和控制的前提，是一项关键的技术。

One of the key techniques of spacecraft is to determine orbit , it is also the preconditions of control and guidance .

针对天文导航系统所采用的状态方程和量测方程对系统的性能和定位精度的影响，介绍了天文导航中常用的两种状态方程，航天器轨道动力学方程和牛顿受摄运动方程。

Different celestial navigation systems , which uses different kinds of motion equations and measurement equations have different navigation performance and precision .

遗传算法在解决多目标优化问题中有其独特的优势，而航天器轨道机动是典型的多目标优化问题。

Genetic algorithms to solve the multi-objective optimization problems have their unique advantages , and the spacecraft orbit maneuver was a typical multi-objective optimization problem .

由此，论文主要研究内容如下：首先，建立了天体及航天器轨道动力学模型。

Thus , the main contents of this thesis are organized as follows : First of all , the orbit dynamic model about celestial bodies and the spacecraft is established .

简要介绍了所开发的航天器轨道设计系统的功能，详细描述了这种小型轨道设计系统的实现策略、模块划分和总体结构。

This paper introduces the functions of the spacecraft orbit design system briefly , then describes the realization scheme , the modules and the structure of the small system detailedly .

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 .

利用GPS接收机的导航信息精确确定接收机载体航天器的轨道根数。

This paper proposes an accurate orbit determination technique to accurately determine orbit elements of a spacecraft equipped with a GPS receiver according to navigation messages from the receiver .

这也正是为什么美国国家航空航天局（NASA）早期研究太阳的航天器的轨道时建议先去木星——这样就更容易减速并到达太阳。[qh]

And that 's precisely why early mission trajectories for NASA 's spacecraft to study the sun proposed going out to Jupiter first - to make it easier to slow down and get to the sun . [ qh ]

从绝对运动与相对运动两方面推导了维持追踪航天器圆轨道运行的组合机动的运动规律，给出了V-bar接近段与逼近段的制导律。

The absolute and relative motions of the chaser in combined maneuvers were investigated when it maintains its initial circular orbit . Then the guidance rules of space rendezvous V-bar approach and final translation were derived respectively .

低地球轨道航天器的轨道碎片环境

Orbital debris environment for spacecraft designed to operate in low earth orbit

编队飞行航天器平均轨道根数非线性控制研究

A Nonlinear Control of Formation Flying Based on Mean Elements

哥伦布航天器对轨道碎片撞击危害的设计考虑

Design Considerations of COLUMBUS Space Vehicle Against Impact Hazard of Orbital Debris