Patent ID: 9643717
Date: 2017-05-09
CPC Classifications: B64C,F16H

Claim:
1. A control system for controlling pitching stabilizer means of an aircraft, the system being provided with at least one outlet shaft for turning the stabilizer means, the system having a first actuator and a second actuator, the first and second actuators being different, wherein the first actuator has a first driving portion that moves at a first speed, the second actuator has a second driving portion that moves at a second speed greater than the first speed, the control system comprising a control device connected to the first actuator and to the second actuator in order to cause the outlet shaft to be driven either by the first driving portion or by the second driving portion, or else by both the first driving portion and the second driving portion, the control system including a memory having a first relationship for electrically controlling the first actuator while limiting the authority of the first actuator for turning the outlet shaft over a first angular range, and a secondary relationship for electrically controlling the second actuator while giving the second actuator full authority for turning the outlet shaft over a second angular range, the first angular range being less than the second angular range, wherein the control system includes a differential device for connecting the first actuator and the second actuator to the outlet shaft, wherein the differential device comprises: