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Journal of Projectiles, Rockets, Missiles and Guidance >

2020 , Vol. 40 >Issue 3: 87 - 92

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2020.03.021

Effect of Carrier Initial Stance of Single Axis Rotating INS Error Propagation

  • XU Zhihao 1 ,
  • ZHOU Zhaofa 1 ,
  • GUO Qi 2 ,
  • XU Zihao 1 ,
  • CHANG Zhenjun 1
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  • 1 State Key Subject Laboratory of Weapon Launching Theory and Technology, Rocket Force University of Engineering, Xi’an 710025, China
  • 2 No. 96902 Unit, Beijing 100000, China

Received date: 2019-01-28

  Online published: 2025-02-12

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Abstract

The rotational modulation technology of INS is essentially a self-compensation technology for errors. In order to study the influence of initial attitude of carrier on error propagation characteristics of uniaxial rotating inertial navigation system, the error model of the rotary strapdown inertial navigation system was established, and the error propagation equation of strapdown inertial navigation system on stationary base was derived. The functional relationship between the equivalent constant error of inertial devices and the system error was obtained. The modulation form of constant drift of gyroscope and its influence on system error during uniaxial continuous rotation were analyzed, and the simulation experiment of any initial attitude was designed, and draws the conclusion: when the carrier is adjusted to the horizontal state, the effect of rotation modulation is the best.

Key words： single-axis rotation; SINS; error propagation character; gyro constant drift

Cite this article

XU Zhihao , ZHOU Zhaofa , GUO Qi , XU Zihao , CHANG Zhenjun . Effect of Carrier Initial Stance of Single Axis Rotating INS Error Propagation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2020 , 40(3) : 87 -92 . DOI: 10.15892/j.cnki.djzdxb.2020.03.021

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