Strain Gauge Utilization for Aerial Vehicle Dynamic Load Measurement
Abstract
The strain gauge is a commonly used tool for dynamic load and strain measurement of a system. The work presented in this thesis describes the development and evaluation of strain gauges applied to both an aerodynamic decelerator system and an unmanned
aerial vehicle. This thesis has three main objectives: (1)develop and evaluate test a circular parachute strain gauge-based load distribution measurement system, (2) develop and
evaluate a strain gauge thrust estimation system for a quadrotor unmanned aircraft, and
(3)compare the developed strain gauge-based thrust estimation technique with an indirect
real time parameter estimation technique for motor fault detection.
In pursuit of the first thesis objective, a load distribution measurement system for
the suspension lines of circular parachutes was developed. The motivation to create a
load distribution measurement system stems from parachute system design traditionally
requiring an extensive flight testing regimen. Numerical solution-based design is difficult
due to the highly nonlinear deformation behavior of the parachute canopy. Traditionally,
circular parachutes are assumed to have symmetric canopy loading upon inflation and
during terminal descent. Asymmetric canopy loading can have a significant impact on
circular parachute suspension line loads, but is typically neglected. The developed strain
gauge-based load distribution measurement system for circular parachutes has wireless
capabilities and can be readily applied to a wide variety of aerodynamic declarator systems. The developed system can be used to observe asymmetric behaviors in order to
help determine the significance of asymmetric canopy loading. Custom strain gauge load
cells with mounted custom circuitry to calibrate, amplify, and transmit the load data were
fixed to canopy suspension lines. Parachute drop testing was performed to evaluate the effectiveness to identify any significant asymmetric canopy loading behavior. Drop testing
was performed with a 1.2m (4.0ft) quarter-spherical cross based canopy with a payload
of 2.0kg (4.4lbs). A 12m (39ft) guide-line based drop rig was implemented to prevent
canopy rotational movement that could hinder testing repeatability. Load distribution data
was first verified via both static calibration and in-flight total canopy load measurements.
Drop testing was then conducted to identify loading asymmetry during both inflation and
terminal descent. Results demonstrated the use of the strain gauge-based load distribution
measurement system for measuring significant asymmetric canopy loading patterns.
In pursuit of the second thesis objective, strain gauges were used to aid in the
development of a thrust estimation system for individual motors/propellers of a small
quadrotor unmanned aerial vehicle (UAV). Small UAVs have become increasingly utilized for a wide range of applications; however, such aircraft typically do not undergo
the same rigorous safety protocols as their larger human-piloted counterparts. A thrust
estimation technique for a quadrotor unmanned aircraft was developed and evaluated that
could potentially improve flight control design by increasing sensory feedback information. Strain gauges were integrated into the quadrotor frame to provide total force measurements on each arm of the aircraft. A dynamic model coupled with state information
from motion capture and on-board measurement data was implemented to compensate for
inertial forces caused by rotational and translational acceleration. Testing was conducted
to evaluate the accuracy of the individual load cells, inertial compensation,and free-flight
motor thrust estimates. Results demonstrate inertial force compensation during high frequency aircraft motion, which could potentially be useful for detecting an in-flight failure.
The measurement system therefore has the potential to quickly detect an in-flight failure.
The focus of the third thesis objective is to expand on the development of the
thrust estimation system by performing an evaluation of the fault detection capabilities.
A comparative study was conducted of the thrust estimation system along with a real
time parameter estimation in the frequency domain during two motor failure scenarios
of a small quadrotor UAV. Detecting and mitigating disturbances caused by in-flight mo
tor/propeller failures is an important aspect of a robust flight controller for multirotor
aircraft. The comparative study was performed in an attempt to determine whether direct
thrust estimation (strain gauge-based) or indirect thrust estimation (parameter estimation
using on-board measurement) more accurately and quickly capture an in-flight failure.
Flight test results were post-processed to mimic real-time parameter estimation and strain
gauged-based fault detection. Results show the strain gauge-based parameter estimation
exhibits noisy estimates, but does have faster response to the failure. The parameter estimation using onboard data does not respond to failures as quickly as the strain-gauge
based technique, but does produce better parameter estimate stability. Although both estimation techniques display strengths and weaknesses, neither technique is optimal for
real time failure detection individually. A combination of the real-time parameter estimation in the frequency domain and the strain gauge-based thrust estimation techniques may
yield a fast yet stable fault detection system. The evaluation of the fault detection capabilities of the thrust estimation system did not prove unsuccessful, however it has warranted
further investigation into the overall effectiveness of the system for fault detection.
Table of Contents
Introduction -- Literature review -- Validation and flight testing of a wireless load distribution measurement system -- Feasibility of in-flight quadrotor individual motor thrust measurements -- Conclusion
Degree
M.S.