P10.1 The design of a lunar excursion module is an inter

esting control problem. The attitude control system for the lunar vehicle is shown in Figure P10.1. The vehicle damping is negligible, and the attitude is controlled by gas jets. The torque, as a first approximation, will be considered to be proportional to the signal V(s) so that T s( ) = K V2 ( )s . The loop gain may be selected by the designer in order to provide a suitable damping.

A damping ratio of ζ = 0.6 with a settling time (with a 2% criterion) of less than 2.5 seconds is required. 

Using a lead network compensation, select the nec

essary compensator G s c( ) by using

(a) frequency re

sponse techniques and

(b) root locus methods.

Compensation Actuator Vehicle V(s) T(s) Reference Ge(s) K Attitude FIGURE P10.1 Attitude control system for a lunar excursion module. K