CRASH AVOIDANCE SYSTEM FOR DRONES

International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056
Volume: 09 Issue: 11 | Nov 2022 www.irjet.net p-ISSN: 2395-0072
© 2022, IRJET | Impact Factor value: 7.529 | ISO 9001:2008 Certified Journal | Page 364
CRASH AVOIDANCE SYSTEM FOR DRONES
R.Snehith1, Vaibhavi Karanth2, Shikha Rai A3
1,2 Students, Department of Electronics & Communication Engineering, Sahyadri College of Engineering &
Management, Mangalore, India
3Asst Professor, Department of Electronics & Communication Engineering, Sahyadri College of Engineering and
Management, Mangalore, India
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Abstract - Several factors must be considered to ensure a
safe flight while a drone is in the air, there are times when
one of the drone's motor does not respond or does not work
at all. In this instance, the drone loses its stability and
crashes into the ground at a high velocity, potentially
causing harm to both the drone and its surroundings.
Drones are high-priced pieces of equipment used in a variety
of sectors for a variety of purposes, and losing drones on a
frequent basis can be expensive. The presented methodology
tackles this issue by focusing on both software and
hardware perspective, in contrast to the existing strategy,
which is primarily focused on software. We're aiming to
convert a quadcopter to a tri-copter by developing a system
that responds to this situation by altering the drone’s
configuration via manual signal sent by the pilot and
backed by an externally linked circuit to the flight
controller. This technique provides the pilot control over the
drone during the fail safe mechanism which switches the
configuration to tri-copter, unlike the conventional fail safe
systems, which ceases the control from pilots in many
occasions. This solution ensures that the drone will do no
harm to the surroundings or to itself by landing on the
desired coordinates.
Key Words: Robotics, UAV, Pixhawk
1. INTRODUCTION
A multi-rotor is a system that controls its aerial mobility
by using thrust force produced by many fixed pitch
propellers. Because the thrusters on the multirotor are all
oriented vertically, the horizontal steering system of the
platform requires fuselage attitude management, which
would be the process of supplying a fraction of the thrust
horizontally. The common hardware configurations, a
quadrotor arrangement with four propellers is the
minimum standards for a steady flight, and sustaining a
smooth ride is exceedingly difficult if one or even more
quadcopter thrusters fail. The ability to control the speed
and rotation of the motor is critical in the construction of a
drone. An electronic speed control (ESC) manages these
tasks, which includes a power distribution stage, a
current-sensing circuitry, a microprocessor, and a
communication link with the flight control system. The
crash avoidance system for drones is implemented where
additional logic is combined externally with Pixhawk and
the configuration is being made to change from
quadcopter to tricopter when the motor breaks down. The
dedicated switch in the transmitter is signaled for
changing the configuration. Once the Pixhawk gets this
signal, the drone seamlessly transitions to tri-mode. At this
stage, the drone is working on a tricopter configuration
state where it will consider only 3 inputs for the motors.
Once the drone is in this state the only goal is to land the
drone in a secure and sound manner, the pilot will have
control over the drone and the drone will respond in a
very subtle manner which will help the drone to be stable
and take the inputs from the pilot at the same time. Lately,
we can see the applications of drones in many fields,
varying from medical, agriculture to the military and
losing one would be the greater loss.
2. LITERATURE SURVEY
Lee, Seung Jae et.al [1] explains a quadcopter failsafe flying
system that can fly with the four controlled DOF as a
typical quadcopter even if a failure occurs in one of the
arms. The new method makes use of the T 3 -Multirotor, a
novel multirotor platform that applies a unique strategy of
actively manipulating the center of gravity to recover
controlled degrees of freedom. A specific control structure
is introduced, as well as a thorough examination of the
platform properties as they alter during emergency flights.
The practicality of the suggested method is validated using
experimental data.
B. Wang et.al [2] presents addressing simultaneous
actuator defects, a unique adaptive sliding-mode based
control allocation system. The suggested control method
consists of two independent control modules, one for
virtual control and the other for control allocation. The
control allotment system is being used as a basic control
module in fault-free as well as defective situations to
allocate virtual command signal among the available
motors. When several actuators fail at the same time, the
control allocation and reallocation module may not be able

to meet the needed virtual control signal, compromising
overall system stability. To reduce the influence of the
virtual control error and preserve the closed-loop
system's stability, the suggested online adaptive technique
may smoothly modify the control gains for the high-level
sliding mode control module and reorganize the
distribution of control signals. Furthermore, using the
boundary layer to build the adaptation law prevents
overestimation of control benefits, and adaptation stops
once the sliding variable is within the boundary layer. The
stability of the closed-loop system is assured in the
presence of simultaneous motor defects, which is an
important element of this research. Experimental findings
using a modified unmanned multirotor helicopter under
single and simultaneous actuator failures are compared to
a standard sliding mode controller and a linear quadratic
regulator system to illustrate the efficacy of the suggested
control strategy.
Wang, Rijun et.al [3] states Identifying and rebuilding
actuator failures in an aircraft flight system is critical for
minimizing negative effects on the drone, as well as its
surroundings. And a fault classification-based motor
defect detection and reconstruction technique for the hex-
rotor drone is proposed. The error of the actuator is first
examined and categorized, and then a motor failure model
based on multiple failure classification is created.
Second, for the hex-rotor unmanned aerial vehicle, a flaw
detection and reconstruction technique is provided.
Extended Kalman filter is used for fault identification and
separation in the proposed approach, and the multi-sensor
navigation unit provides the flight state input required.
The output is then used to suggest an actuator fault
reconstruction algorithm. For testing, the planned system
is fitted to a hex-rotor drone. The simulation results
demonstrate that the suggested design is capable of fault
detection and actuator fault reconstruction, and the actual
flight confirms the efficacy of the proposed approaches.
Giribet, Juan et.al [4] A multirotor with six degrees of
freedom (6DOF) has been the subject of several studies.
However, the capacity to maintain total control in case of a
complete loss of one of the rotors has yet to be
investigated. In this paper, it is demonstrated that eight
rotors are required to provide 6 degree of freedom control
of a multirotor in the event of a total loss of one of them.
Also presented and investigated through numerical
simulations is an Octo-rotor configuration with 6 degrees
of freedom control capabilities in a fault condition,
comparing flying performance in a normal and failure
mode.
Pose, Claudio et.al [5] examines fault tolerance in
multirotor vehicles, with a focus on hexarotors, where
fault tolerance is attained by changing the centroid in the
event of a failure.It will be demonstrated that for a
hexarotor vehicle, there is an ideal fixed location for the
center of mass for each of the potential motor failures
towards maintain independent control of four degrees of
freedom and gain the greatest mobility. In the event of a
motor failure, the performance of this approach will be
weighed up against a proceeding design based on rotor
reconfiguration.
3. METHODOLOGY
When the drone's motor fails, the operator will flip a
switch to transform the drone into a tricopter. The signal
for altering the configuration is first sent through the
specialized switch on the transmitter. The receiver then
sends the signal to the Pixhawk. Pixhawk sends the PWM
signal to the Arduino UNO through aux pins which are
preprogrammed in Qgroundcontrol.Fig.1 represents the
schema of a proposed solution when one of the motor
breaks down and the implementation flowchart is shown
in Fig.2.
Fig -1: Schema of proposed solution
Fig -2: Flowchart for Implementation of proposed solution

3.1 DESIGN
The Arduino boards are a good alternative since they
make it simple to integrate a variety of devices with a
microcontroller. Relays are a type of device that may be
interfaced with Arduino to operate a number of other
devices that are connected to the microcontroller. We
connected a four-channel relay module to an Arduino Uno.
First, we wired the common pin of each relay module to
the Electronic Speed Controller (ESC). Each relay module's
normally open pin has been linked to the 5, 6, 7, and 8 pins
of the pixhawk which are mapped to the tricopter
firmware. Each relay module's normally closed pin has
been linked to the 1, 2, 3, and 4 pins of the Pixhawk, which
are mapped to the quadcopter firmware. Arduino Relay
circuit is depicted in Fig.3.
Fig - 3 : Arduino Relay circuit
3.2 Implementation
Input signal for relay is first set to high to keep the relay
normally closed since the relay is an active low device,
which is done through digital Write function in Arduino
code, where it changes the state to high and low. Pulse In
function blocks the program and waits for a signal to
change it to a certain range, where it measures the
duration of the pulse. While the signal falls under PWM
range of 1800 to 2200, the input for relay is set to low
which triggers it and ESC is then connected to tricopter
pins and drone acts as a tricopter. We use the Serial.
printIn() function to check the output through the serial
monitor where it continuously checks for the PWM signal.
The firmware manipulation in pixhawk is done in such a
way that both quadcopter and tricopter works
simultaneously and one of the aux pins is programmed to
provide signal for Arduino.
Fig - 4 : Serial monitor before receiving signal from
transmitter
Fig - 5 : Serial monitor after receiving signal from
transmitter
By downloading the source code from Github and
changing INSTALL_SIM as false to exclude the simulation
software as shown in fig.6. For building the source code
CMake plays an important role. After building a custom
firmware with a .px4 extension, which is finally uploaded
to pixhawk through Qgroundcontrol. The custom firmware
runs both the firmware side by side computing data for
quad configuration and tri configuration as shown in fig.7.
Fig - 6 : Cloning of source code with Github

Fig-7 : Custom Firmware
After relay switches from normally closed to normally
open ESC starts getting a PWM signal for tricopter
configuration, which means it will only examine three
motor inputs. Once the drone is in this state, the only
purpose is to land it safely and securely. The pilot will
have very little control over the drone, and the drone will
respond in a subtle manner, allowing the drone to remain
steady.
Because of the servo system employed in the tail motor,
tricopters are more maneuverable than conventional
rotary wing aircraft. Tricopter’s fixed body which include,
ease of control, endurance, ease of to-downstream
maintains the air vibrations constant and, like many other
features, steady flight.
4. RESULTS
The implementation is successfully carried out by
firmware modification along with the supporting system
which is designed to change configuration. Pixhawk open
source code is modified to custom firmware so that the
processor runs both the firmware side by side computing
data for quad configuration and tri configuration. The
system was designed in order to support the firmware
modifications so that it could seamlessly transit from
quadcopter to tricopter as a fail-safe.
Fig.8 shows the proposed system with additional logic
changing configuration from quad to tri when one of the
motors breaks down.
Fig-8: Drone with the switching circuit
5. CONCLUSION
Drones are an emerging field with niche applications, the
use of this in developing projects is growing exponentially.
As the use of UAV technology is expanding to a wide range
of sectors, it has to adapt to new operational challenges
and risks. Here, together with the effective circuitry to
support it and with custom firmware, switching from a
quad configuration to a tri configuration when one of the
motors fails is successfully implemented.
REFERENCES
[1] Lee, Seung Jae, Inkyu Jang, and H. Jin Kim. "Fail-
Safe Flight of a Fully-Actuated Quadrotor in a Single Motor
Failure." IEEE Robotics and Automation Letters 5, no. 4
(2020): 6403-6410.
[2] B. Wang and Y. Zhang, "An Adaptive Fault-
Tolerant Sliding Mode Control Allocation Scheme for
Multirotor Helicopter Subject to Simultaneous Actuator
Faults," in IEEE Transactions on Industrial Electronics, vol.
65, no. 5, pp. 4227-4236, May 2018, doi:
10.1109/TIE.2017.2772153.
[3] Wang, Rijun, Changjun Zhao, Yue Bai, Wenhua Du,
and Junyuan Wang. "An actuator fault detection and
reconstruction scheme for hex-rotor unmanned aerial
vehicle." IEEE Access 7 (2019): 93937-93951.
[4] Giribet, Juan, Claudio Pose, and Ignacio Mas.
"Fault tolerance analysis of a multirotor with 6DOF." In
2019 4th Conference on Control and Fault Tolerant Systems
(SysTol), pp. 32-37. IEEE, 2019.
[5] Pose, Claudio, and Juan Giribet. "Multirotor fault
tolerance based on center-of-mass shifting in case of rotor
failure." In 2021 International Conference on Unmanned
Aircraft Systems (ICUAS), pp. 38-46. IEEE, 2021.

CRASH AVOIDANCE SYSTEM FOR DRONES

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CRASH AVOIDANCE SYSTEM FOR DRONES