| Popis: |
The application of gyroscopic systems on spacecraft has received considerable attention (e.g. [I]-[3]). It has been proposed that as a control strategy, a large number of momentum wheels and/or control gyros be employed in large flexible spacecraft for attitude control as well as shape control. Because of the nature of the origin of gyroscopic torques in large space structures (i.e., momentum wheels or control gyros), i t has been common for them to be considered as lumped elements in an analysis. A very convenient and useful means of modelling elastic structures which have a large number of small spinning rotors has been advanced by D'Eleuterio et al. [4]-[8] by way of the concept of a gyroelastic continuum. A gyroelastic continuum is a concept that imagines a body that has a continuous distribution of mass, stiffness and angular momentum. The angular momentum distribution is assumed to be independent of the motion of the body and it is further assumed that i t can be separately specified without dependence on the mass distribution or stiffness distribution. D'Eleuterio and Hughes [5] have termed the distributed angular momentum as stored angular momentum or gyricity, the latter term shall be used .here. D'Eleuterio et al. [4]-[8] have reported the dynamics of continuous elastic gyroscopic systems for the |
