README.md

Quadrotor Formation using Model Predictive Control

Install Acados

To build Acados from source, see instructions here or as follows:

Clone acados and its submodules by running:

$ git clone https://github.com/acados/acados.git
$ cd acados
$ git submodule update --recursive --init

Install acados as follows:

$ mkdir -p build
$ cd build
$ cmake -DACADOS_WITH_QPOASES=ON ..
$ make install -j4

Install acados_template Python package:

$ cd acados
$ pip install -e interfaces/acados_template

Note: The <acados_root> is the full path from /home/.

Add two paths below to ~/.bashrc in order to add the compiled shared libraries libacados.so, libblasfeo.so, libhpipm.so to LD_LIBRARY_PATH (default path is <acados_root/lib>):

export LD_LIBRARY_PATH=$LD_LIBRARY_PATH:"<acados_root>/lib"
export ACADOS_SOURCE_DIR="<acados_root>"

Quadrotor Dynamics

The full explanation of the quadrotor dynamics is presented in here.

The quadrotor state space is described between the inertial frame $I$ and body frame $B$, as $\xi = \left[\begin{array}{cccc}p_{IB} & q_{IB} & v_{IB} & \omega_{B}\end{array}\right]^T$ corresponding to position $p_{IB} ∈ \mathbb{R}^3$, unit quaternion rotation on the rotation group $q_{IB} \in \mathbb{SO}(3)$ given $\left\Vert q_{IB}\right\Vert = 1$, velocity $v_{IB} \in \mathbb{R}^3$, and bodyrate $\omega_B \in \mathbb{R}^3$. The input modality is on the level of collective thrust $T_B = \left[\begin{array}{ccc}0 & 0 & T_{Bz} \end{array}\right]^T$ and body torque $\tau_B$ . From here on we drop the frame indices since they are consistent throughout the description. The dynamic equations are follows:

$$\dot{p}=v \\\ \dot{q}= \dfrac{1}{2}\Lambda(q)\left[\begin{array}{l}0\\\omega\end{array}\right] \\\ \dot{v}=g+\dfrac{1}{m}R(q)T\\\ \dot{\omega}=J^{-1}(\tau-\omega\times J\omega)$$

where $\Lambda$ represents a quaternion multiplication, $R(q)$ the quaternion rotation, $m$ the quadrotor’s mass, and $J$ its inertia.

The input space given by $T$ and $\tau$ is further decomposed into the single rotor thrusts $u =\left[T_1, T_2, T_3, T_4\right]^T$, where $T_i$ is the thrust at rotor $i \in \{1, 2, 3, 4\}$

$$T=\left[\begin{array}{c}0\\0\\\sum{T_i}\end{array}\right]$$

For $\times$ configuration quadrotor model

$$\tau=\left[\begin{array}{c}l/\sqrt{2}(T_1-T_2-T_3+T_4)\\\ l/\sqrt{2}(-T_1-T_2+T_3+T_4)\\\ c_\tau(-T_1+T_2-T_3+T_4)\end{array}\right]$$

For $+$ configuration quadrotor model

$$\tau=\left[\begin{array}{c}l(T_1-T_3)\\\ l(T_2-T_4)\\\ c_\tau(-T_1+T_2-T_3+T_4)\end{array}\right]$$

with the quadrotor’s arm length $l$ and the rotor’s torque constant $c_\tau$. The quadrotor’s actuators limit the applicable thrust for each rotor, effectively constraining $T_i$ as:

$$0\leq T_{min} \leq T_i \leq T_{max}$$

Results

Control performance

Moving to goal	Trajectory tracking

CPU time

ave estimation time is 0.00075
max estimation time is 0.00104
min estimation time is 0.00070