Trajectory planning algorithm of exo-atmosphere aircraft under the influence of the J2 perturbation

被引：0

作者：

Wei Q. ^{[1
]}

Cai Y.-L. ^{[1
]}

机构：

[1] School of Electronic and Information Engineering, Xi'an Jiaotong University, Xi'an, 710049, Shaanxi

来源：

Cai, Yuan-Li (ylicai@mail.xjtu.edu.cn) | 1600年 / South China University of Technology卷 / 33期

基金：

中国国家自然科学基金;

关键词：

Elliptical trajectory parameters; J[!sub]2[!/sub] perturbations; Lambert's problem; Prediction model; Trajectory deviation;

D O I：

10.7641/CTA.2016.50959

中图分类号：

学科分类号：

摘要：

A modified Lambert algorithm considering the earth's J2 perturbation gravitational is put forward for the trajectory planning problem of exo-atmosphere aircraft limited by two constraint conditions-the aircraft's initial/terminal points and flight time. According to the classic Lambert guidance theory, the normal trajectory within the assumed condition of central gravitational force is determined to meet the constraint conditions. Then, comparing with the actual trajectory within earth's oblateness perturbation, an analytic solution of trajectory deviation based on trajectory parameters is derived. By constructing a prediction model about the virtual terminal point in view of the J2 perturbation gravitational to correct the deviation of perturbation, the trajectory planning problem is covered to the discussion of Lambert problem within twobody theory. Comparing with the existing perturbation correction method, the modified algorithm of prediction model with 6 independent variables has a complete response to the influence between trajectory deviation and the parameters. At the same time, the prediction model has strong robustness, high accuracy and fast computation speed. © 2016, Editorial Department of Control Theory & Applications South China University of Technology. All right reserved.

引用

页码：1245 / 1251

页数：6

共 14 条

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