![]() focused on the design and implementation of a roll-channel fractional order proportional integral (PI λ) flight controller for a small fixed-wing UAV. 13 Luo developed a fractional order (PI) λ controller to improve the flight control performance and robustness of a small fixed-wing UAV the inner closed-loop system of the roll-channel is approximately identified as a first-order plus time delay model using flight test data. 12 He also proposed designing heading and air speed control commands to accomplish the constrained nonlinear tracking control for small fixed-wing UAVs. 11 Ren considered the problem of constrained non-linear trajectory tracking control to reduce the twelve-state UAV model to a six-state model with altitude, heading, and velocity command inputs. implemented lateral path-following based on the proportional-integral-derivative (PID) feedback method in simulation. 5–14 According to the criterion of minimum energy and minimum manoeuvring, Zhu et al. Flight tests and survey missions were carried out with our self-developed delta fixed-wing UAV and MEMS-based autopilot to confirm the effectiveness and practicality of the proposed navigation method.Ī number of trajectory planning and control techniques have been extensively studied for UAVs. The non-linear controller can automatically adapt to ground velocity change, which is usually caused by gust disturbance, thus the UAV has good wind resistance characteristics. The longitudinal control employs traditional linear PID feedback to achieve the desired altitude of the UAV, while the lateral control uses a non-linear control method to complete the desired trajectory. ![]() ![]() The three-dimensional (3D) trajectory tracking control of a UAV could be approximately divided into lateral control and longitudinal control. The proportional-integral-derivative (PID) control was adopted for stabilization and attitude control. The trajectory tracking navigation loop is the outer loop of the attitude loop, while the attitude control loop is the outer loop of the stabilization loop. The system is designed under the inner loop and outer loop strategy. This paper presents a flight control and navigation system for a fixed-wing unmanned aerial vehicle (UAV) with low-cost micro-electro-mechanical system (MEMS) sensors. ![]()
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