An angle speed and thrust relationship of the rotor system in the quadcopter aircraft

Abstract

Utilizing Quadcopter were still many obstacles such as; plane easy to fall; the battery is not durable; vulnerable to weather conditions and others. The research and development has grown to improve aircraft facilities and capabilities. Many parameters related to aircraft lift capability factors; fly long; flying high; type of motor; the type of propeller: including the sensors and control systems used. This study was to find the relationship between changes in the BLDC motor voltage source to the rotor angle velocity <em>(ω)</em>; rotor speed to rotor lift <em>(Ft)</em>; wind speed to rotor lift; push the following rotor <em>(Ct)</em>. Empirical testing was conducted in the laboratory to find the relationship of these parameters. The results data show that; the lift power generated with rotational speed was not proportional, non linearity occurs when the rotor was released from the self and starts pulling the strain gauge when the rotation speed reaches around 65 <em>rps</em>. Once the rotation speed of the rotor is able to reach up to 1.5 Newton lift then the thrust rising trend sharply<strong> </strong>increasing <strong>to</strong>increasing <strong>of </strong>the rotor speed. A motor hade 1200 <em>KV</em> and blade with a radius of 0.12 <em>m</em>, then obtained thrust <em>(Ct)</em> of 1.732.

Geometric control of quadrotor UAVs using integral backstepping

“…We observed the suggested control robustness. Figure (5) shows the trajectory of the quadrotor in 3D for two cases before and after changing the mass and the inertia by applying an external force . Thus, simulations have validated the different prescribed trajectories tracked by actual trajectories very well with this paper's proposed method.…”

“…Because of the intensive research in the filed [1,2]. Recently, a growing interest in the multirotor UAVs for the systems high capabilities (i.e., vertical take-off, and landing, navigation in narrow spaces and maneuvering capacity) [3][4][5]. However, the advantages of multi-rotor UAVs comes with highly coupled dynamic models which makes designing a decoupled control law that stabilizes the systems a changing task [6,7].…”

The influence of iron losses on selecting the minimum excitation capacitance for self-excited induction generator (SEIG) with wind turbine

“…This system is feeding a 1.5 KW induction oil pump load as in Figure 1. The used SEIG's parameters was exactly measured by testing the induction generator when using it as a motor [17][18][19].…”

Dynamic analysis and qft-based robust control design of a coaxial micro-helicopter

“…-The drag force The aerodynamic drag force of the vehicle F a caused by the friction of the air on the fuselage can be expressed as: [13] F a = 1 Ω 2…”