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Consider the engine-propeller system in Monday's class notes (2018/10/22), which has the following governing equations of...
Build up a SIMULINK model of the engine-propeller system with the following governing equations o...
Build up a SIMULINK model of the engine-propeller system with the following governing equations of motion and system parameters Governing equations of motion J,9, + k.(9, _ θ.) + bé, sgn@p)-0 System parameters: Je1 Jp-2, kr-120, b-0.5, T-16 Required: Plot the rotation speeds θ, and ëp for 0 10
Build up a SIMULINK model of the engine-propeller system with the following governing equations of motion and system parameters Governing equations of motion J,9, + k.(9, _ θ.) + bé, sgn@p)-0...
omework 13: 1) Derive the equations of motion of the system shown in Fig. 1, where...
omework 13: 1) Derive the equations of motion of the system shown in Fig. 1, where vis the input to the and θ2 are the output. and, Ans: d i dt K,: motor torque constant 1262 kr(01-02)-cr62 Load u2 T u 2) Figure 2 is the circuit diagram of a spced-control system in which the de motor voltage is supplied by a generator driven by an engine. The motor voltage va is varied by changing the generator input
Consider the system given below. The output is y(displacement from equilibrium position) and the input is...
Consider the system given below. The output is y(displacement from equilibrium position) and the input is V. (source voltage). The motor has an electrical constant Ke, a torque constant K, an armature inductance Lg and a resistance R. The rotor, shaft and disk together have inertia J and a viscous friction coefficient B. The disk has a radius ofr. (For the motor, assume that the torque is T = Ki,, and the back EMF is emf = KO). a. Derive...
Problem 1 Consider a paper airplane that has a rubber band driven propeller. The equations of...
Problem 1 Consider a paper airplane that has a rubber band driven propeller. The equations of motion for it longitu dinal dynamics can be written as where its state vector is given by the velocity V and the flight path angle y, i.e., xV,E R2, and the control input is given by the thrust u. All of other variables, namely mass m, gravitational acceleration g, lift parameters I, and drag parameter d are fixed constants (a) Let V* > 0...
Consider the electromechanical dynamic system shown in Figure 1(a). It consists of a cart of mass...
This assignment is for my Engr dynamics systems class.
Consider the electromechanical dynamic system shown in Figure 1(a). It consists of a cart of mass m moving without slipping on a linear ground track. The cart is equipped with an armature-controlled DC motor, which is coupled to a rack and pinion mechanism to convert the rotational motion to translation and to create the driving force for the system. Figure 1(b) shows the simplified equivalent electric circuit and the mechanical model...
3.10 (Motor drive) Consider a system consisting of a motor driving two masses that are connected...
3.10 (Motor drive) Consider a system consisting of a motor driving two masses that are connected by a torsional spring, as shown in the diagram below. Motor This system can represent a motor with a flexible shaft that drives a load. Assuming that the motor delivers a torque that is proportional to the current I, the dynamics of the system can be described by the equations dt dt (3.43) dtdt where Ф1 and P2 are the angles of the two...
3.2 Pre-Lab Assignment When deriving the governing equations for an electromechanical system, it is often beneficial...
3.2 Pre-Lab Assignment When deriving the governing equations for an electromechanical system, it is often beneficial to examine the electrical and mechanical components independently. Looking at only the electrical components of the QUBE-Servo DC motor (as shown in Figure 3.2): R v00 C e, (00 Figure 3.2: Electrical curcuit of the QUBE-Servo DC motor Q1. Write the differential equation in the form of Kirchoff's voltage law) in the Laplace domain for the electrical circuit (do not use parameter values given...
Problem 3: (30 Consider a block diagram which represents the satellite control system with a cont...
Problem 3: (30 Consider a block diagram which represents the satellite control system with a controller Ge(s) (a) Assuming no initial conditions, find the output response y(t) when the impulse input is applied to the system, where Gc(s) is a proportional gain K. (10) (b) Design a lead-compensator Ge(s) for which the complex pole of the closed-loop system has 0.5 of damping ratio () and 2 rad/s of undamped natural frequency (on) (The zero of a lead-compensator is given as...
Consider the mass-spring-damper system depicted in the figure below, where the input of the system is...
Consider the mass-spring-damper system depicted in the figure below, where the input of the system is the applied force F(t) and the output of the system is xít) that is the displacement of the mass according to the coordinate system defined in that figure. Assume that force F(t) is applied for t> 0 and the system is in static equilibrium before t=0 and z(t) is measured from the static equilibrium. b m F Also, the mass of the block, the...
Problem 4 (25%) Consider the attitude control system of a rigid satellite shown in Figure 1.1....
Problem 4 (25%) Consider the attitude control system of a rigid satellite shown in Figure 1.1. Fig. 1.1 Satellite tracking control system In this problem we will only consider the control of the angle e (angle of elevation). The dynamic model of the rigid satellite, rotating about an axis perpendicular to the page, can be approximately written as: JÖ = tm - ty - bė where ) is the satellite's moment of inertia, b is the damping coefficient, tm is...
Build up a SIMULINK model of the engine-propeller system with the following governing equations of motion and system parameters Governing equations of motion J,9, + k.(9, _ θ.) + bé, sgn@p)-0 System parameters: Je1 Jp-2, kr-120, b-0.5, T-16 Required: Plot the rotation speeds θ, and ëp for 0 10
Build up a SIMULINK model of the engine-propeller system with the following governing equations of motion and system parameters Governing equations of motion J,9, + k.(9, _ θ.) + bé, sgn@p)-0...
omework 13: 1) Derive the equations of motion of the system shown in Fig. 1, where vis the input to the and θ2 are the output. and, Ans: d i dt K,: motor torque constant 1262 kr(01-02)-cr62 Load u2 T u 2) Figure 2 is the circuit diagram of a spced-control system in which the de motor voltage is supplied by a generator driven by an engine. The motor voltage va is varied by changing the generator input
Consider the system given below. The output is y(displacement from equilibrium position) and the input is V. (source voltage). The motor has an electrical constant Ke, a torque constant K, an armature inductance Lg and a resistance R. The rotor, shaft and disk together have inertia J and a viscous friction coefficient B. The disk has a radius ofr. (For the motor, assume that the torque is T = Ki,, and the back EMF is emf = KO). a. Derive...
Problem 1 Consider a paper airplane that has a rubber band driven propeller. The equations of motion for it longitu dinal dynamics can be written as where its state vector is given by the velocity V and the flight path angle y, i.e., xV,E R2, and the control input is given by the thrust u. All of other variables, namely mass m, gravitational acceleration g, lift parameters I, and drag parameter d are fixed constants (a) Let V* > 0...
This assignment is for my Engr dynamics systems class.
Consider the electromechanical dynamic system shown in Figure 1(a). It consists of a cart of mass m moving without slipping on a linear ground track. The cart is equipped with an armature-controlled DC motor, which is coupled to a rack and pinion mechanism to convert the rotational motion to translation and to create the driving force for the system. Figure 1(b) shows the simplified equivalent electric circuit and the mechanical model...
3.10 (Motor drive) Consider a system consisting of a motor driving two masses that are connected by a torsional spring, as shown in the diagram below. Motor This system can represent a motor with a flexible shaft that drives a load. Assuming that the motor delivers a torque that is proportional to the current I, the dynamics of the system can be described by the equations dt dt (3.43) dtdt where Ф1 and P2 are the angles of the two...
3.2 Pre-Lab Assignment When deriving the governing equations for an electromechanical system, it is often beneficial to examine the electrical and mechanical components independently. Looking at only the electrical components of the QUBE-Servo DC motor (as shown in Figure 3.2): R v00 C e, (00 Figure 3.2: Electrical curcuit of the QUBE-Servo DC motor Q1. Write the differential equation in the form of Kirchoff's voltage law) in the Laplace domain for the electrical circuit (do not use parameter values given...
Problem 3: (30 Consider a block diagram which represents the satellite control system with a controller Ge(s) (a) Assuming no initial conditions, find the output response y(t) when the impulse input is applied to the system, where Gc(s) is a proportional gain K. (10) (b) Design a lead-compensator Ge(s) for which the complex pole of the closed-loop system has 0.5 of damping ratio () and 2 rad/s of undamped natural frequency (on) (The zero of a lead-compensator is given as...
Consider the mass-spring-damper system depicted in the figure below, where the input of the system is the applied force F(t) and the output of the system is xít) that is the displacement of the mass according to the coordinate system defined in that figure. Assume that force F(t) is applied for t> 0 and the system is in static equilibrium before t=0 and z(t) is measured from the static equilibrium. b m F Also, the mass of the block, the...
Problem 4 (25%) Consider the attitude control system of a rigid satellite shown in Figure 1.1. Fig. 1.1 Satellite tracking control system In this problem we will only consider the control of the angle e (angle of elevation). The dynamic model of the rigid satellite, rotating about an axis perpendicular to the page, can be approximately written as: JÖ = tm - ty - bė where ) is the satellite's moment of inertia, b is the damping coefficient, tm is...
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