Earticle

초록

영어

The position and velocity errors are divergent of traditional navigation algorithms used in ballistic missile for it cannot estimate the bias of accelerometer precisely. To solve this problem, a novel SINS/CNS integrated navigation algorithm is proposed in this paper, which adds high angle error, azimuth angle error and height error on the basis of the traditional navigation method. As these three values are related to the position of missile, the proposed method can constrain the divergence of navigation errors. Meanwhile, a system model for ballistic missile is deduced. To verify the navigation precision of the proposed algorithm, the observable analysis and simulation experiments are performed. And the results show that the system state of proposed method is observable completely, and the divergence of navigation error can be restrained thoroughly.

목차

Abstract
 1. Introduction
 2. The Definition of Reference Frames
 3. Operating Principle of System
 4. System Model
  4.1. State Equation
  4.2. Measurement Equation
 5. Simulations and Analysis
  5.1. Simulation Conditions
  5.2. Simulation Results and Analysis
 6. Conclusions
 References

키워드

저자

• Lihua Yang [ School of Economics and Management, Hubei University of Automotive Technology, Shiyan, 442002, China ]
• Baolin Li [ School of Economics and Management, Hubei University of Automotive Technology, Shiyan, 442002, China ]
• Lei Ge [ Institute 706, Second Academy of China Aerospace Science and Industry Corporation, Beijing, 100854, China ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  International Journal of Security and Its Applications

• 간기

  격월간

• pISSN

  1738-9976

• 수록기간

  2008~2016

• 등재여부

  SCOPUS

• 십진분류

  KDC 505 DDC 605