Abstract
Unmanned Aerial Vehicles (UAVs) continue to penetrate diverse sectors, including agriculture, disaster management, communication, transportation, and defense. The robustness and reliability of their
operation have become paramount due to the increasing ubiquity of these systems across numerous sectors. UAVs can undergo faults in their sensors, actuators (motors), and even structure - all of these have
different levels of severity and effects on the system. Motor faults can be of three main types, namely,
Motor Locking, Loss of Efficiency (LoE), and Loss of Actuation (LoA). Motor locking is a case where
the actuator keeps spinning at a given RPM and cannot be changed, whereas LoE is a case where the
actuator degrades over time and is not able to generate enough torque due to lower RPM. In this thesis, however, we focus on LoA, where an actuator stops working completely (gets stuck at zero RPM)
and can result in catastrophic failure in the UAV. This work delves into the dynamics of UAVs under
actuator fault conditions, examines the resulting instability issues, and explores potential methods for
identification and control reconfiguration for safe operation.
Once an actuator failure occurs, the Fault Detection & Isolation (FDI) module should be able to
locate the fault and pinpoint it with high accuracy and in a very short time, to allow the UAV to stabilize
the fault. Various approaches can be used for the FDI system, namely, rule-based, model-based, and
data-driven. Implementation of these methods can be relying on RPM sensors, battery monitors, and
software-only solutions. We propose a data-driven software module for this purpose, since it is UAV
frame agnostic, does not require any additional hardware (software-only), and can be run with minimal
setup. The proposed Rotation Forest based classifier can detect, classify, and report the fault within
120-250 milliseconds of occurrence of the fault. This is an acceptable delay, since we have observed
that the vehicle cannot handle delays upwards of 500 milliseconds in simulations.
Once a fault is reported by the FDI module, the Fault Tolerant Control (FTC) module reconfigures
the control system to stabilize the vehicle and continue the mission, or prevent a crash by peforming a
safe landing. This thesis focuses on cases of complete actuator failure in Hexacopter UAVs, specifically,
for single motor failure scenarios. The proposed FTC module performs UAV stabilization using control
reconfiguration, after fault occurrence.
We perform a thorough analysis for the FDI and FTC modules separately, extensively in simulation,
and demonstrate the same in real flight tests. We also combine the two modules and analyze the response
in the simulation. In real flights, the classifier (FDI module) responds to the fault in 2-5 sensor data
samples (at a 60ms rate per sample) and has a high true positive rate of 92.6%. Also, in real flights, the performance of the FTC module is measured in terms of tracking error, percentage overshoot, and
settling time.
Integration of the FDI and FTC modules is performed and simulation results are presented showing
satisfactory operation of each of these modules with guaranteed stable flight.