An aircraft landing gear control system 100 has at least one position sensor 131,132,133 and a controller 140. The controller receives a signal from the sensor of the position of a part of either a landing bay door 111, or a landing gear 121, during their movement between stowed and deployed positions, and controls movement of the other part on the basis of the signal. The positions of both parts may be sensed, and parts relative position used by the controller to control the movement. The sensors may sense angular position, linear position and/or curvilinear position, and may continuously or repeatedly sense the position along a path, the controller determining the speed of movement of the sensed part. The controller may be used to initiate movement of the controlled part; rate-controllable actuators 114,124 used to move the controlled part with the controller varying the speed of movement on the basis of the position or speed of the sensed part; alternatively, on the basis of additional signals such as: bogie pitch, another landing gear status, engine status, component failure or defect, and/or crab angle.
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