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Analysis of gyro noise in non-linear attitude estimation using a single vector measurement
, Article IET Control Theory and Applications ; Volume 6, Issue 14 , 2012 , Pages 2226-2234 ; 17518644 (ISSN) ; Namvar, M ; Sharif University of Technology
IET
2012
Abstract
This study investigates the effect of noisy measurements of the angular rate in a non-linear attitude estimator for satellites. The attitude estimator uses measurement of a single attitude sensor such as Sun, Earth-horizon, star tracker or magnetometer together with a rate gyro, and guarantees exponential convergence of the attitude estimation error to zero under a no-noise condition. In view of a realistic situation where the presence of noise in gyro measurement is not negligible, this study presents stochastic and deterministic upper bounds for the attitude estimation error resulting from noisy angular rate measurement. A realistic simulation is presented to illustrate the results
Noise analysis in satellite attitude estimation using angular rate and a single vector measurement
, Article Proceedings of the IEEE Conference on Decision and Control, 12 December 2011 through 15 December 2011 ; December , 2011 , Pages 7476-7481 ; 01912216 (ISSN) ; 9781612848006 (ISBN) ; Namvar, M ; Sharif University of Technology
Abstract
This paper investigates the effect of noisy measurements of the angular rate in a nonlinear attitude estimator for satellites. The attitude estimator uses measurement of a single attitude sensor such as sun, earth horizon, star tracker or magnetometer together with a rate gyro, and guarantees exponential convergence of the attitude estimation error to zero under no noise condition. This paper presents stochastic and deterministic upper bounds for the attitude estimation error affected by the noise in gyro. A realistic simulation is presented to illustrate the results
Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle
, Article Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ; Volume 226, Issue 6 , 2012 , Pages 631-645 ; 09544100 (ISSN) ; Mohammadkarimi, H ; Sharif University of Technology
2012
Abstract
In this study, the guidance and control problem of a single-channel spinning missile is investigated. The missile utilizes a single ON-OFF actuator to drive a pair of control surfaces (e.g. elevators) and consequently to perform all required lateral maneouvers. An approximated linear response of the so-called non-rotating frame to ON-OFF input, applied to the rotating frame, is derived using the multiple-input describing function technique. It is shown that there is a relationship between the response of the non-rotating frame and that of the equivalent non-rotating body. It is also shown that the two-channel flight controller, designed for the equivalent non-rotating body, can be reduced to...