An actuator system composed primarily of a ball screw and a permanent-magnet DC electric motor is...
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An actuator system composed primarily of a ball screw and a permanent-magnet DC electric motor is used to position a flight control surface as indicated in Figure 1. The armature voltage of the motor is controlled. The motor turns the ball screw shaft, displacing the nut in accordance with the relationship In = NsOm- (1) The nut is coupled to the flight control surface with a linkage that has non-zero compliance and damping. A system model is provided in Figure 2 to clarify the damping and other elements as well. Though not indicated, the motor model for the permanent-magnet DC machine that has been derived in class should be employed for this assignment. The electrical and mechanical system parameters are provided in Table 1. Pay careful attention to units. The load on the control surface is largely produced by wind drag. It is assumed that the force is dependent on aircraft speed V and surface displacement 0s. Without any development, you may use the expression Fw = BwV20, (2) which has been linearized for small deviations in control surface deflection and acts on the center of the control surface. The units of the force are N if the velocity units are km/h and the angular displacement units are radians. Tasks 1. Develop a state model for the system where the aircraft speed and armature voltage are the inputs. Wind Flight Control Surface Om, wm 85, w s Nut Ball Screw Motor Figure 1: Flight control surface actuator system. Te M₂ Kn m Br Вт xvn Fw Js Figure 2: Flight control surface system diagram. An actuator system composed primarily of a ball screw and a permanent-magnet DC electric motor is used to position a flight control surface as indicated in Figure 1. The armature voltage of the motor is controlled. The motor turns the ball screw shaft, displacing the nut in accordance with the relationship In = NsOm- (1) The nut is coupled to the flight control surface with a linkage that has non-zero compliance and damping. A system model is provided in Figure 2 to clarify the damping and other elements as well. Though not indicated, the motor model for the permanent-magnet DC machine that has been derived in class should be employed for this assignment. The electrical and mechanical system parameters are provided in Table 1. Pay careful attention to units. The load on the control surface is largely produced by wind drag. It is assumed that the force is dependent on aircraft speed V and surface displacement 0s. Without any development, you may use the expression Fw = BwV20, (2) which has been linearized for small deviations in control surface deflection and acts on the center of the control surface. The units of the force are N if the velocity units are km/h and the angular displacement units are radians. Tasks 1. Develop a state model for the system where the aircraft speed and armature voltage are the inputs. Wind Flight Control Surface Om, wm 85, w s Nut Ball Screw Motor Figure 1: Flight control surface actuator system. Te M₂ Kn m Br Вт xvn Fw Js Figure 2: Flight control surface system diagram.
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Related Book For
Managing Supply Chain and Operations An Integrative Approach
ISBN: 978-0132832403
1st edition
Authors: Thomas Foster, Scott E. Sampson, Cynthia Wallin, Scott W Webb
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