-31] 



POSSIBLE SYSTEM CONFIGURATIONS 



453 



and these signals are used to move the antenna in a direction opposite to 

 undesired space motions. Of course, the correction signals are not exact; 

 the gyros sense space velocity only, not the space position actually desired. 

 However, a control loop with sufficient accuracy and speed of response can 

 reduce antenna space motion to magnitudes much lower than those of the 

 interceptor, and the residual space position errors are further reduced by 

 the track loop which uses the target sight line as a reference. Details of 

 designing these stabilization loops are discussed in the subsequent para- 

 graphs. 



8-31 POSSIBLE SYSTEM CONFIGURATIONS 



Several physical configurations are used to mechanize the stabilization 

 loops. Some of them are shown in Fig. 8-37.^^ Theoretically, all of them 



Rate Command w + p 



(Volts) 

 From Radar 



Rate 



Command 



^ Aircraft Space Angle 

 \ An 



Aft 



(Volts) 



^ Rate 

 Signals 



Tracking Line Angle 



Gj Amplifier, Actuator, 

 Antenna 



G3 Rate Gyro 



(a) 

 Gyro Components 



(Current) 

 From 

 Radar 



Torque Y- 



Rate 

 Signals 



(b) 



G4Gyro Gimbal and Detector 

 G 5 Gyro Wheel 

 G 6 Torque Motor 



Three Channels /Two Channels 



Ga Aircraft 



GgAircraft Gyros j^ ^^^ ^i^^ 



Q Coordinate ^ 



" Converter 

 GrTachometer 



— *Gc 



1^ 



Rate 

 Signals 



•K> 



(c) 



Two Channels 



Fig. 8-37 Three Stabilization Loop Configurations, (a) Rate Gyro, (b) Inte- 

 grating Gyro, (c) Aircraft Gyro. 



33Another form is not illustrated. It consists of a gimbaled antenna dish which is rotated at 

 high speeds to become an effective gyroscope. It is used in some missile tracking systems 

 to provide stabilization. 



