multirotor aircraft: modelling, state estimation and...
TRANSCRIPT
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Multirotor Aircraft: Modelling,
State Estimation and Control
Robert MahonyCollege of Engineering and
Computer Science
Australian National University
Tutorial on International Conference on Robotics and
Automation
Friday, 20 May, 2016.23-May-16 1
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The quadrotor
Quadrotor aerial vehicle is the most
flexible and adaptable platforms for
undertaking aerial research.
• Small and safe.
• Operates well in indoor laboratory
environment.
• Many manufacturers but fairly
uniform functionality.
• Can carry sensor and computer
payload to function autonomously –
at least for short time.
• Capable of hover flight or forward
flight.
• Sensing and control problems are
ubiquitous for aerial robotics.
Small scale research quadrotors
and larger commercial vehicles
use identical control code.
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Part I: Modelling
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Quadrotors
Quadrotor control is achieved by
differential control of the thrust
generated by each rotor.
• Heave (total thrust) is the sum
of thrust generated by each
rotor.
• Pitch and roll are obtained by
differential thrust along the NS
axis or EW axis.
• Yaw control is obtained by
differential control of the NS
rotors compared to the EW
rotors such that the total thrust
is constant. A quadrotor consists of 4 individual rotors
attached to a rigid cross airframe.
A quadrotor is under-actuated and the remaining degrees of freedom, translational
velocity in the horizontal plane, must be controlled through the system dynamics.
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N - rotor vehicles
The conceptual idea of a quadrotor is
straightforward to extend to multirotor
vehicles.
The advantage of these configurations is
safety and and redundancy rather than
aerodynamic efficiency.
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Rigid body dynamics of quadrotor
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rotation
matrix
velocity
position
drag
gravity
inertia tensor
angular velocity
torque
thrust
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Rigid-body dynamics in generalized coord.
Rigid-body dynamics in
homogeneous coordinates
Rigid-body
dynamics in
local
generalised
coordinates.
RT R = I
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Primary aerodynamics of quadrotor
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Primary thrust relationship
The thrust cT coefficient for a
given rotor motor system is best
identified using static thrust tests.
ModelData
Lumped parameter model
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We will look at one or two of the
secondary aerodynamic effects
since they effect secondary stability.
But we will base the control design
on the primary model.
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Multirotor vehicle
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There are a number of secondary aerodynamic effects
associated with quadrotors.
Secondary Aerodynamic effects
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Horizontal forces
• Blade flapping
• Parasitic drag
• Aerodynamic drag
Vertical Forces
• Ground effect
• Inflow damping
• Translational lift
Other aerodynamic effects
• Vortex states
• Flow variation due to local environment
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Horizontal aerodynamic forces
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Aerodynamic drag
23-May-16HYCON2-EECI-M2: Aerial Robotic Vehicles 16
Aerodynamic drag has similar characteristics to blade flapping effects.
• Aerodynamic drag is quadratic in velocity: It is negligible at low speeds and
dominates at high speed.
• Blade flapping is linear with velocity: It is dominant at low speeds and
negligible at high speed.
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Ground effect
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Other aerodynamic effects
Inflow damping
Reduced thrust
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Other aerodynamic effects
Translational lift
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Vortex state
A vortex state in a full sized helicopter
occurs when the tip vortex grows to
create a closed air cell in which the
helicopter is trapped. The helicopter
will fall to the ground unless the pilot
takes action.
Vortex state is generally caused in
vehicles carrying heavy payloads and
descending slowly. For this reasons,
most helicopters do not directly
descend in hover, they will always fly
in at an angle.
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Part II: State Estimation
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Estimation from IMU and GPS
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Complementary filters
-
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Frequency response of complementary filter
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Basic attitude estimation
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Attitude observer on SO(3)
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Block diagram of SO(3) filter with bias est.
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Velocity aided attitude
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Velocity aided attitude
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Velocity Aided Attitude in bod-fixed frame
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Allibert, Mahony, Bangura, “Velocity Aided Attitude Estimation for Aerial Robotic
Vehicles Using Latent Rotation Scaling”, ICRA 2016 (TuCbT3.12)
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Results
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• Implementation on
several UAV systems are
all highly successful.
• Easily add estimation of gyro bias.
• When accelerometers are used for
attitude estimate this minimises drift
in yaw estimate.
Modelling, estimation and control of quads
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Monte-Carlo comparison of performance
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Monte-Carlo simulation averaged over 100 repeats of initial conditions drawn from
an initial distribution. Noise characteristics typical of UAV platform. (Zamani 2012)
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Part III: Control
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Control architecture
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Almost all control systems for small scale aerial robotics use a hierarchical
control architecture as shown above.
The key to high performance control is
• A trajectory planner that minimizes snap actuation requirements on the
motors.
• Integrated attitude trajectory planning with attitude control.
• High gain robust motor control
The key constraint in the control is the motor control response, including steady
state error, disturbance rejection, and limited bandwidth..
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Control architecture
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Almost all control systems for small scale aerial robotics use a hierarchical
control architecture as shown above.
The key to high performance control is
• A trajectory planner that minimizes snap actuation requirements on the
motors.
• Integrated attitude trajectory planning with attitude control.
• High gain robust motor control
The key constraint in the control is the motor control response, including steady
state error, disturbance rejection, and limited bandwidth..
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Control architecture
23-May-16Modelling, estimation and control of quads 36
Almost all control systems for small scale aerial robotics use a hierarchical
control architecture as shown above.
The key to high performance control is
• A trajectory planner that minimizes snap actuation requirements on the
motors.
• Integrated attitude trajectory planning with attitude control.
• High gain robust motor control
The key constraint in the control is the motor control response, including steady
state error, disturbance rejection, and limited bandwidth..
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Control architecture
23-May-16Modelling, estimation and control of quads 37
Almost all control systems for small scale aerial robotics use a hierarchical
control architecture as shown above.
The key to high performance control is
• A trajectory planner that minimizes snap actuation requirements on the
motors.
• Integrated attitude trajectory planning with attitude control.
• High gain robust motor control
The key constraint in the control is the motor control response, including steady
state error, disturbance rejection, and limited bandwidth..
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Control architecture
23-May-16Modelling, estimation and control of quads 38
Almost all control systems for small scale aerial robotics use a hierarchical
control architecture as shown above.
The key to high performance control is
• A trajectory planner that minimizes snap actuation requirements on the
motors.
• Integrated attitude trajectory planning with attitude control.
• High gain robust motor control
The key performance constraint is motor control response, including
steady state error, disturbance rejection, and limited bandwidth..
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Block diagram of system architecture
FastestFastNormalSlow
Typical value
10-20Hz
Typical value
50-200Hz
Typical value
500Hz-2kHz
Typical value
1-5Hz
Limitation is typically the motor control bus rate
AvionicsInertial Navigation System ESCElectronic
speed
controllers
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Motor-Rotor control
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Mom
entu
m
theory
Bla
de e
lem
ent
mo
mentu
m t
heory
BE
MT
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Control on Electronic Speed Controller (ESC)
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Identify the constants
in offline experiments.
Computes CT in real time on the
electronic speed controller
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Motor-Rotor control loop design on ESC
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• Inner loop current control: tuned to be nearly unstable to generate fast rise
time.
• Intermediate loop: regulates aerodynamic mechanical power
• The outer-level: standard PI regulator for thrust.
The resulting system has a rise time of 50ms (comparable to RPM controllers) and
gust disturbance rejection of 90% (compared to RPM control).
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Thrust Control Experiments
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Using this approach –
errors in thrust control for
individual rotors can be
improved by an order of
magnitude: 20% error
was reduced to <2%
error.
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Motor Control
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The key performance constraint for quadrotors is motor-rotor control
response, including steady state error, disturbance rejection, and limited
bandwidth.
Present systems typically have rise times around 50ms.
There isn’t time in this talk to discuss this topic in detail today but this is an
active research area.
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Attitude Control
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Canonical error for control
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Stability demonstration
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Control architecture
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The inner loop stability problem can be solved using estimates provided by
the attitude filter discussed earlier in the talk.
This control and estimator run on the embedded avionics system at rates of
50-200Hz.
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Trajectory stabilisation (position control)
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Attitude planning
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Needed for feedforward in
attitude control
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Control architecture
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The trajectory planner should take into account the system limitations – in
particular the rate limitations of the motor system.
Typically this is done by minimizing a suitable cost functional that penalizes the
snap (or 4th derivative the trajectory).
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Trajectory planning
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Optimal trajectories
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Control architecture
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Quadrotor
Fundamental questions in aerial
robotic systems.
• Attitude estimation – IMU,
• Velocity estimation – GPS, IMU,
VICON …
• Position estimation – Vision,
VICON, GPS, …
• Motor control – embedded control.
• Attitude control – robustness and performance.
• Integrated path planning and position/velocity control – performance,
replanning, feedback.
All of this has to implemented on embedded hardware weighing as little
as possible. Finally, you will want to do something with the quadrotor.
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Aerial Robotics
THANKS