Design and simulation study of ema

International Journal of Scientific and Research Publications, Volume 10, Issue 7, July 2020 225
ISSN 2250-3153
This publication is licensed under Creative Commons Attribution CC BY.
http://dx.doi.org/10.29322/IJSRP.10.07.2020.p10327 www.ijsrp.org
Design and Simulation study of Electro-Mechanical
Actuator for Missile Maneuvering
*Mantri Siddharth Ram, ** Kukutam Sumanth, B. Jawaharlal
*
Department of ECE, Vasavi College of Engineering.
**
Department of ECE, Vasavi College of Engineering.
Scientist, DRDO-RCI, Hyderabad
DOI: 10.29322/IJSRP.10.07.2020.p10327
http://dx.doi.org/10.29322/IJSRP.10.07.2020.p10327
Abstract- Electro-Mechanical Actuator (EMA) is the key
component in the guidance systems of missiles to convert
electrical power into mechanical power. EMAs have shown
significant improvement in response times and are more reliable
compared to other actuators. This paper proposes a Simulink
model for linear electromechanical actuator which is very efficient
and can withstand noise and disturbances. Electromechanical
actuators are mechanical actuators where the control handle has
been supplanted by an electric motor. This model is subjected to
sudden loads and disturbances and the precise actuation is
obtained within the specified settling time. The model is also
subjected to nonlinearities and the results were found out to be
competent.
Index Terms- Electromechanical Actuator, BLDC motor, Electric
motor, Simulink, Non-Linearities.
I. INTRODUCTION
A typical aerospace application involves a device or object which
is able to change its direction and follow a desired path. The object
is able to dynamically change its trajectory and moves from point
A to point B. The object can change its direction with the help of
fins, or flaps. These flaps/fins generate a torque due to
aerodynamic friction present in the atmosphere and this torque
rotates the object flying in the atmosphere. These fins are raised
and lowered depending on the direction our object has to follow.
The movement of flaps is done with the help of actuators.
In aerospace applications, precision and accuracy play a very
important role. But there are many aerodynamic forces that affect
the missile during its motion to the interception of the target. A
slight error can cause adverse effects to the object. So, the
integration of guidance system to a missile is to provide the
required force for its propulsion, intelligence to evade targets and
effective maneuvering which are the main features of the guided
missile systems. In recent years, the requirements for the quality
of automatic control increased significantly due to increased
complexity of design of aerospace applications.
In the real time scenario, there are many factors that affect the
precision and accuracy of the missile. When describing the action
of forces, one must account for both the magnitude and the
direction. In flight, a missile is subjected to four forces; weight,
thrust, and the aerodynamic loading, lift and drag [1]. These forces
account for deviation of the missile from its trajectory which can
ruin the performance of the whole system as the missile fails to
terminate the target. In order to avoid this, missiles are equipped
with fins which helps us to steer the missile in such a way that the
missile gets back into trajectory. So, the efficiency of the system
depends on the efficiency of the fin actuators. In our project, we
have developed a linear electromechanical actuator which is very
efficient and this control system can withstand noise and
disturbances. So, this paper emphasizes on the modelling of
PMBLDC motor and controlling its position using PID Controller
to suit all the aerospace application requirements which can
withstand the effects of disturbances and non-linearities.
II. ELECTRO-MECHANICAL ACTUATOR
The mechanical actuators where the control handle has been
supplanted by an electric motor is Electro-Mechanical Actuator.
The rotary motion of the BLDC motor is converted to linear
motion. In the greater part of the electromechanical actuators, the
principal activity depends on the inclined plane concept.
In order to achieve higher mechanical efficiency, speed operation,
and increment load capacity, the variations of Electro-mechanical
Actuators are devised.[2]
The main advantage of EMAs is that engineers have unlimited
oversight over the motion profile. These are provided with
encoders that can accurately control velocity and position. The
ability to monitor and regulate torque is also provided by them
resulting the amount of force applied. Electromechanical actuation
systems can be programmed and reconfigured without shutting
them down, which means the force and motion profile can be
altered by the software while the device is still running.
Electromechanical actuators also offer critical cost savings since
they possibly devour power when they are performing work. To
maintain a position, the system stays in place while idle which
makes it very efficient.
The operating costs are drastically reduced making them suitable
to use in hazardous areas because of their high efficiencies, low
maintenance, and increased up time.
Electromechanical actuators can disentangle the design procedure
since they are simpler to indicate and design.

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Figure 1. Electro-Mechanical Actuator
An EMA generally consists of a PID controller, a BLDC motor,
a speed reduction gearbox, a lead or ball screw as shown in
figure 1. All these blocks work in congruence and give an
accurate actuation motion.
A. PID Controller
PID control represents a proportional–integral–derivative control.
PID control is a feedback mechanism utilized in a control system.
By ascertaining and controlling three boundaries – the
proportional, integral, and derivative of how much a procedure
variable veers off from the ideal set-point esteem – we can
accomplish diverse control actions for specific work. The error
between the actuator position and the input signal is given to the
PID controller. The PID controller used in this simulation uses the
compensator formula as shown in equation (1). The block output
is a weighted sum of the input signal, the integral of the input
signal, and the derivative of the input signal [3].
The PID position controller has the following parameters:
𝑆 = 𝑃 + 𝐼
1
𝑠
+ 𝐷
𝑁
1 + 𝑁
1
𝑠
(1)
Where,
S: Speed at an instant
P: Proportional gain
I: Integral gain
D: Derivative gain
N: Filter co-efficient.
B. BLDC Motor
EMA typically employs a BLDC motor because of its high
efficiency, high reliability, increased lifespan, better speed-torque
characteristics, and low electromagnetic interference. The stator
windings should be energized in a sequence to rotate the BLDC
motor. It is essential to realize the rotor position to comprehend
energized winding following the energizing sequence.
Figure 2. Switching Sequence
Rotor position is sensed using Hall Effect sensors embedded into
the stator. Most BLDC motors have three Hall sensors embedded
into the stator on the non-driving end of the motor [4]. Whenever
the rotor magnetic poles pass near the Hall sensors, they give a
high or low signal, indicating the N or S pole is passing near the
sensors. Based on the combination of these three Hall sensor
signals, the exact sequence of commutation can be determined. A
commutation logic specifies correct phases to be excited to the 3-
phase inverter. This block represents how a motor would spin (at
a constant speed) depending upon the position of the rotor. There
are totally six switches from S1 to S6 on the 3-phase inverter which
forms the commutation circuit. Process of switching ON and
switching OFF the switches in the inverter arms is based on the
predefined pattern or sequence depending on hall sensor values as
shown in the fig.2.
Figure 3. Decoder Implementation
The decoder logic for the above switching sequence is
implemented in Simulink as shown in figure 3.
The output of this implementation is given as gate pulse inputs to
the 3-phase inverter. A gearbox is used to reduce the shaft speed
of the motor while increasing the output torque. It also helps in
reducing the size of the motor there by reducing the form factor of
EMA. Backlash affects almost each mechanical system and
ignoring its presence during control design causes a severe

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deterioration of system performance which can even lead to
instability [5]. This nonlinearity increases with wear of the
systems. When backlash is traversed, there is no torque
transmitted through the shaft and when sudden contact is
established, the resulted impact can destroy the gear and it causes
a high frequency noise.
C. Lead Screw
A lead screw converts rotational motion of the motor into linear
motion which is the most essential part of a linear actuator. The
ratio of linear to rotational motion is called the lead of the screw.
The pitch of the screw determines the amount of distance the
actuator advances per one rotation of the screw.
As we have considered a missile as our aerospace application, the
EMA is connected to the fins of the missile. The linear motion of
the lead screw results in the angular rotation of the fin which
changes the direction of the missile.
III. DESIGN IMPLEMENTATION IN SIMULINK
The designed model in SIMULINK software is shown in figure 4.
The voltage demanded by this design is limited to 180V as most
of the missile electrical systems work within this limit. This
voltage is supplied to a 3-Phase inverter which controls the speed
of the BLDC motor which is driven by the commutation sequence
provided by the decoder. Now the rotational motion of the BLDC
motor is converted into linear motion by the lead screw. The
mathematical representation of the lead screw is given by eq-2.
𝑇𝐹 =
𝑃
2 ∗ 𝜋 ∗ 𝑠
(2)
Where,
TF: Transfer function of the Lead screw
P: Pitch of the Screw
As the lead screw is attached to the fin of the missile, the linear
motion is converted to angular motion of the fin. The pitch of the
screw determines the distance travelled by the screw for one
rotation. The pitch of the screw used in our design is taken as 3
millimeters. We have designed the model considering that our fin
shifts by 40
in position for every 5-millimeter displacement in the
lead screw. So, if the desired fin movement is 500
, the actuator
should give a linear displacement of 62.5-millimeters.
In a control system, generally there are many unwanted inputs
which will affect the output of control system resulting in the
increase of system error [6]. These unwanted signals are
disturbance signals. So, in order to eliminate these disturbances
from the system, we use the system feedback to enable the control
system to monitor and process them to minimize these
disturbances to reach a state of stability. The model is designed to
resist these unwanted signals dynamically. Also, the control
systems are susceptible to the non- linearities (static or dynamic).
A motor that does not react to very low input voltages due to
frictional forces shows a nonlinearity called dead zone. Gears that
do not fit perfectly exhibit a nonlinearity called backlash [7]. This
model is designed in such a way to withstand them to certain
acceptable range.
IV. RESULTS AND DISCUSSION
The system requirements and system parameters used in this
design are shown tables 1 and 2. The input signal and the actuator
response are shown in the figure 5,6. The error signal which is the
difference between input signal and feedback decreases with time
as shown in figure 12. The demanded speed S by the BLDC motor
is shown in figure 7. This assumes that the motor initially demands
high speed and once the desired actuation output is achieved, the
motor stops spinning. Also, it is observed that when a sudden load
is acted on the motor (at 0.5 sec), the motor tries to counteract the
load and the desired actuation is achieved with some delay as
shown in figure 8. The demanded voltage by the EMA is shown in
figure 9. It is observed that initially 180V is demanded by the
actuator and the demand correspondingly reduces as the fin
approaches the desired position. Stator currents and Hall sensor
outputs are shown in figures 10, 11. The PID controller is tuned in
such a way that if a backlash nonlinearity with a dead band value
of 60 is applied, the system is still able to achieve the desired
actuation within specified time of 2 seconds as shown in figure 13.
The model is also tuned to withstand a dead zone nonlinearity with
a band value ranging from -30 to +30 as shown in the figure 14.
Table 1. System Requirements
Parameter Value
Settling time 2 seconds
Peak overshoot <10%
Maximum input voltage 180 volts
Table 2. System Parameters
Parameter Value
Power Supply 180V DC
Number of phases 3
Back EMF waveform Trapezoidal
Mechanical Input Torque
Stator phase resistance Rs (ohm) 0.2
Stator phase inductance Ls (H) 8.5e-3
Flux linkage 0.175
Motor Current 15A
Inertia (J(kg.m2
)) 0.6e-3
Viscous damping (F(N.m.s)) 1e-3
Screw (displacement per
revolution)
3 mm
Table 3. Various PID values
Sl. No Kp Ki Kd
1 10 0.0001 0.005
2 25 0.02 0.000001
3 50 10 0.5
4 70 20 0
5 90 1 1

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6 90 0.1 40
The fin response to various PID values as in table 3 are shown in
figure 15.
V. CONCLUSION
The design and simulation study of Electro-Mechanical Actuator
using MATLAB Simulink software has been executed and is
validated. The model is developed towards high reliability and
high-power efficiency. The effects of parameters variations on
system’s stability and performance were also analyzed. The model
can handle the disturbances and non-linearities to a great extent.
This model can also thwart the effect of sudden load on the motor
and can achieve desired actuation within a very short settling time.
The maximum tolerable range for nonlinearities has been found
out. The model stands out to be very reliable even when acted upon
with disturbances and high amounts of non-linearities the
outcomes acquired from this simulation study are satisfactory and
experimental validations are presented.
VI. REFERENCES
1. https://www.grc.nasa.gov/WWW/K-
12/rocket/rktfor.html#:~:text=In%20flight%2C%20a%2
0rocket%20is,the%20parts%20of%20the%20rocket.
2. https://www.machinedesign.com/mechanical-motion-
systems/article/21836654/engineering-refresher-the-
basics-and-benefits-of-electromechanical-actuators
3. MathWorks Help :
https://in.mathworks.com/help/simulink/slref/pidcontrol
ler.html
4. https://shodhganga.inflibnet.ac.in/bitstream/10603/1415
33/10/10_chapter%202.pdf
5. M. L. Corradini, G. Orlando, G. Parlangeli: Robust
control of nonlinear uncertain systems with sandwiched
backlash, 44th IEEE Conference on Decision and
Control, 2006.
6. Ashraf Abd Almageed Ahmad, Dr.Eltahar Mohammed
Hussein: Effect of Disturbance on Closed-Loop Control
System, ISSN: 2319-8753, Vol. 3, Issue 8, August 2014.
7. Norman.Nise - “Control.Systems.Engineering”-
6th.Edition.
Figure.4. Electromechanical Actuator Subsystem

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Figure 5. Model input-output
Figure 6. Fin response
Figure 7. Demanded Speed by the motor

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Figure 8. Motor response for sudden load at 0.5 sec

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Figure.9 Demanded Voltage Figure 12. Error Signal
Figure.10. Stator Currents Figure.13 Introduction of Backlash nonlinearity
Figure 11. Hall Sensors Figure.14 Introduction of Deadzone nonlinearity

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Figure 15. Fin response for different PID values

Design and simulation study of ema

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