for rotation in upper and lower bearing 172 174 an electric motor 180 has an output shaft coupled to drive the gear 162 which in turn produces rotation of both the bevel gear 170 and the pinion gear 144 thus driving both the aerofin 120 and the rack 140 this in turn drives the yoke plate 132 a feedback transducer 182 is connected to the aerofin bevel gear 170 by a shaft 184 thereby providing aerofin position data for the control system of the drive arrangement 100 the coupling between the motor 180 and the gear 162 is represented by the block 178 this preferably incorporates a speed reducing gear train to transform the motor 39 s relatively high speed and low torque into low speed and high torque such speed reducers are known in the art details are omitted from fig5 for simplicity a different integrated steering arrangement which uses a combination of aerofin in and jet reaction control jrc is represented schematically in fig6 8 fig6 shows an actuator assembly like that depicted in fig5 except that here the actuator assembly serves to control an associated auxiliary jet steering system rather than the thrust vector control system of the main nozzle as previously described the actuator assembly portion of fig6 to the left of the broken line a u2014 a is the same as that shown in fig5 and the same reference numerals are used to identify like elements it should be clear of course that there are four of the assemblies like the one depicted at the bottom of fig6 one for each of four fins 120 mounted at 90 degree angles about the missile 110 the jet reaction control portion of the arrangement of fig6 is shown comprising a jrc housing 200 mounted just.