Robust Generalized Dynamic Inversion Quadrotor Control
نویسندگان
چکیده
منابع مشابه
Robust Control of a Quadrotor
In this paper, a robust tracking control method for automatic take-off and trajectory tracking of a quadrotor helicopter is presented. The designed controller includes two parts: a position controller and an attitude controller. The attitude controller is designed by using the sliding mode control (SMC) method to track the desired pitch and roll angles, which are the output of position controll...
متن کاملDynamic inversion with zero-dynamics stabilisation for quadrotor control
Abstract: For a quadrotor, one can identify the two well-known inherent rotorcraft characteristics: underactuation and strong coupling in pitch-yaw-roll. To confront these problems and design a station-keeping and tracking controller, dynamic inversion is used. Typical applications of dynamic inversion require the selection of the output control variables to render the internal dynamics stable....
متن کاملSliding Mode Approach to Control Quadrotor Using Dynamic Inversion
Nowadays unmanned rotorcraft are designed to operate with greater agility, rapid maneuvering, and are capable of work in degraded environments such as wind gusts etc. The control of this rotorcraft is a subject of research especially in applications such as rescue, surveillance, inspection, mapping etc. For these applications, the ability of the rotorcraft to maneuver sharply and hover precisel...
متن کاملrobust control of a quadrotor
in this paper, a robust tracking control method for automatic take-off and trajectory tracking of a quadrotor helicopter is presented. the designed controller includes two parts: a position controller and an attitude controller. the attitude controller is designed by using the sliding mode control (smc) method to track the desired pitch and roll angles, which are the output of position controll...
متن کاملInertia-Independent Generalized Dynamic Inversion Spacecraft Control
The generalized dynamic inversion control methodology is applied to the spacecraft attitude trajectory tracking problem. It is shown that the structure of the skew symmetric cross product matrix alleviates the need to include the inertia matrix in the control law. Accordingly, the proposed control law depends solely on attitude and angular velocity measurements, and it neither requires knowledg...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: IFAC-PapersOnLine
سال: 2017
ISSN: 2405-8963
DOI: 10.1016/j.ifacol.2017.08.1266