PWM Modeling for Attitude Control of a Launcher During Ballistic Phase and Comparative Stability Analysis - CentraleSupélec
Conference Papers Year : 2012

PWM Modeling for Attitude Control of a Launcher During Ballistic Phase and Comparative Stability Analysis

Abstract

The present paper exposes a novel description of the effect of a pulse generator on a double integrator representing one axis of rotation for a space vehicle. By considering the difference between the angular velocity obtained with zero-order-hold (ZOH) actuator and the one with a PWM actuator, a perturbation operator expressing the influence of the PWM on the angular speed is defined. Using this configuration in a linear fractional representation (LFR), a stability analysis allows comparing LMI-based and IQC-based stability results for a one degree of freedom rotating body with uncertain PWM and saturation and permits dwelling on improvements to make for further analyses.

Domains

Automatic
No file

Dates and versions

hal-00738191 , version 1 (03-10-2012)

Identifiers

Cite

Julien Chaudenson, Dominique Beauvois, S. Bennani, M. Ganet, Guillaume Sandou, et al.. PWM Modeling for Attitude Control of a Launcher During Ballistic Phase and Comparative Stability Analysis. ROCOND'12, Jun 2012, Aalborg, Denmark. pp.CD-Rom, ⟨10.3182/20120620-3-DK-2025.00109⟩. ⟨hal-00738191⟩
60 View
0 Download

Altmetric

Share

More