Earticle

초록

영어

In missile guidance systems, classical proportional navigation law has been used most widely. But with the increasing of the maneuverability of the targets, the classical proportional navigation guidance law has been unable to meet the requirements of people on the ballistic parameters. So this paper will further study the algorithm error of guidance law. Based on the previous theoretical results and the working principle of aircraft in the homing guidance system, this paper studies a guidance trajectory guidance principle which based on the ratio, and has carried on the analysis and the simulation theory. And simulation accuracy analysis has been carried on with practical examples. The results show that the method is put forward to effectively reduce the guided ballistic calculation method of error.

목차

Abstract
 1. Introduction
 2. Guiding Principle of Aircraft
 3. Proportional Guidance Equation
 4. Guidance Ballistic Based On Guidance of Principle
 5. Trajectory Simulation
 6. Conclusions
 References

키워드

저자

• Wang Xin [ Shenyang Ligong University, Shenyang, 110159, China ]
• Guo Xin [ Shenyang Ligong University, Shenyang, 110159, China ]
• Yao Jun [ Shenyang Ligong University, Shenyang, 110159, China ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  International Journal of Hybrid Information Technology

• 간기

  격월간

• pISSN

  1738-9968

• 수록기간

  2008~2016

• 십진분류

  KDC 505 DDC 605