Optimal Energy Utilization for a Solar-Powered Aircraft using Sliding Mode-Based Attitude Control

Aerodynamic structural design and control for a new miniature coaxial dual-rotor unmanned aerial vehicle

“…In order to verify the rationality and effectiveness of the CDRUAV's structural design and aerodynamic layout, CFD simulation is introduced. [23][24][25] The CFD numerical calculation method is to use the 3D non-normal Euler equation or Navier-Stokes equation and its deformation and to solve the induced velocity at each point of the discrete propeller solution, which can accurately describe the characteristics of the rotor flow field, and at the same time, the calculation accuracy is high. 17 CFD method can simulate the aerodynamic process, which provides convenience for obtaining parameters of mathematical dynamics model without the problems of high cost and a long period of actual wind tunnel experiments.…”

“…The aerodynamic characteristics of the CDRUAV are analyzed by computational fluid dynamics (CFD) to verify the rationality of the selected structure parameters. [23][24][25] Moreover, the dynamics model of the CDRUAV is derived according to Newton's second law and rigid body rotation theory. Then, a cascade proportional-integral-derivative (PID) controller is designed to track the desired position and attitude.…”

A Novel Multiport DC-DC Converter for Enhancing the Design and Performance of Battery–Supercapacitor Hybrid Energy Storage Systems for Unmanned Aerial Vehicles

“…The reference battery power (P b-R ) is obtained by applying an asymmetric limiter to the low-frequency power component to control the charge/discharge power of the battery based on specified limits to preserve its lifetime. Given that the battery power is defined by the battery stage inductor current (I b ) multiplied by the average voltage seen at point A (shown in Figure 6), which is estimated using (7), the reference value for the battery stage inductor current I b-R that is required to deliver this battery power is determined and passed to the battery current control loop that generates the PWM for the switches S3 and S4 accordingly. On the other hand, the SC's reference power (P SC _ R ) is obtained by subtracting the reference battery power P b-R (subject to specific battery limitations) from the total energy storage power requirement (P t ).…”

“…Alternative propulsion based on environmentally friendly energy sources is rapidly growing to minimize carbon dioxide emissions. Accordingly, the applications of electric UAVs powered by electric power sources are expected to have more expansions, especially for the photovoltaic (PV)-powered UAVs that became widely popular due to their increased flight endurance [5][6][7]. Advanced applications of electric UAVs in advanced remote sensing techniques using synthetic aperture radar (SAR) as a payload [8,9] introduce more challenges for the design of UAVs power system, which is required to supply the high-power pulses consumed by these payloads whilst being restricted by the weight/volume limits imposed on UAVs' subsystems.…”

Study and Implementation of a High-Quality True Sine Wave DC-to-AC Inverter for Solar Power Generation Systems

“…Most of these MPPT algorithms cannot strictly analyze the convergence and stability, or cannot quickly track the maximum power point, resulting in the reduction of output power. Sliding mode reaching law (SMRL) is simple and easy to design, and is robust to parameter changes and external disturbances in smooth motion [ 10 , 11 ]; many related SMRL applications have been published in the control of solar power generation systems [ 12 , 13 , 14 , 15 , 16 , 17 , 18 , 19 , 20 , 21 , 22 , 23 , 24 , 25 , 26 ]. However, in practice, the solar system controlled by the SMRL is affected by uncertainty, the system state convergence time is not limited, and steady-state errors will occur, which will affect the stability, convergence, and performance of the system.…”