Longitudinal Control 285Let: (Note q = x3) x A x5then:. SB = Kfiwhere: K = Afi + Bs,9. School Management Software With Source Code In Php here. 4.4 Additional Feedback TermsSometimes, to achieve required handling qualities, an additional feedback termbased upon the normal acceleration measured at the c.g. Is included in thefeedback control law used in pitch SAS thus:8~ = Kqq + Kazazcg (9.57)From the point of view of modern control theory, eq. (9.57) is no more thananother expression of a full state variable feedback control law.

From the point of StabilityAugmentation Systems Controller and-4 Y(4 actuator + 6 ~ ( s ) Aircraft dynamics [ (4azcg sRate gyroJ~F- I Accelerometer Figure 9.13 Pitch rate and acceleration feedback SAS.view of a flight control engineer, eq. (9.57) is the practical alternative, requiringonly pitch rate and normal acceleration to be measured. Both variables arerelatively straightforward to measure using rate gyros and accelerometers locatedat the aircraft's c.g. The block diagram of a SAS, using the control law of eq.(9.57), is represented in Figure 9.13, with its corresponding dynamic responseshown in Figure 9.14. This response should be compared with that of theuncontrolled aircraft which is shown in Figure 9.3(b). Close Up Toothpaste Telugu Ringtone Free Download.