Aglietti, GS and Gabriel, SB and Langley, RS and Rogers, E (1996) Initial modelling and controller design for active control of spacecraft microvibrations. In: UNSPECIFIED pp. 633-640..Full text not available from this repository.
Microvibrations, at frequencies between 1 and 1000 Hz, generated by on board equipment, propagate throughout a spacecraft structure affecting the performance of sensitive payloads. The purpose of this work is to investigate strategies to model and reduce these dynamic disturbances by active control. Initial studies were performed by considering a mass loaded panel where the disturbance excitation source consisted of point forces, the objective being to minimise the displacement at an arbitrary output location. Piezoelectric patches acting as sensors and actuators were used. The equations of motion are derived by using Lagrange's equation with modal shapes as Ritz functions. The number of sensors/actuators and their location is variable. The set of equations obtained is then transformed into state variables and some initial controller design studies have been undertaken. These are based on feedback control implemented using a full state feedback and an observer which reconstructs the state vector from the available sensor signal. Here, the basics behind the structural modelling and controller design will be described. This preliminary analysis will also be used to identify short to medium term further work.
|Item Type:||Conference or Workshop Item (UNSPECIFIED)|
|Divisions:||Div C > Applied Mechanics|
|Depositing User:||Cron Job|
|Date Deposited:||09 Dec 2016 18:20|
|Last Modified:||27 Mar 2017 08:56|