PRECISION ZEM/ZEV FEEDBACK GUIDANCE ALGORITHM UTILIZING VINTI'S ANALYTIC SOLUTION OF PERTURBED KEPLER PROBLEM

被引：0

作者：

Ahn, Jaemyung ^{[1
]}

Guo, Yanning ^{[2
]}

Wie, Bong ^{[3
]}

机构：

[1] Korea Adv Inst Sci & Technol, Dept Aerosp Engn, Seoul, South Korea

[2] Harbin Inst Technol, Dept Control Sci & Engn, Harbin, Peoples R China

[3] Iowa State Univ, Asteroid Deflect Res Ctr, Dept Aerosp Engn, 2271 Howe Hall, Ames, IA 50011 USA

来源：

SPACEFLIGHT MECHANICS 2016, PTS I-IV | 2016年 / 158卷

基金：

新加坡国家研究基金会;

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A new implementation of a zero-effort-miss/zero-effort-velocity (ZEM/ZEV) feedback guidance scheme, which utilizes the computational efficiency and accuracy of analytical orbit propagators, is proposed. Kepler's propagator and Vinti's algorithm for the solution of perturbed Kepler problem are used to predict the ZEM and ZEV state vectors and determine the acceleration command, which are often obtained by numerical integration of the equations of motion in the conventional approach. A procedure for optimal time-to-go estimation that can be used with the new guidance algorithm for intercept of moving target is introduced. The effectiveness of the proposed implementation is demonstrated by the performance comparison with the open-loop optimization approach through several case studies.

引用

页码：1855 / 1874

页数：20