What is the measure: effective control or overall control? As a general principle, the conduct of private persons or entities is not attributable to the State under international law. Circumstances may arise, however, where such conduct is attributable to the State because there exists a specific factual relationship between the persons or entities engaging in the conduct and the State.More complex issues arise in determining whether conduct was carried out under the control of the State or not. Such a conduct would be attributable to the State only if it controlled the specific operation. The degree of control which must be exercised by the State on the conduct to be attributable is an important and key issue. The question is whether this degree is effective control or overall control. This question consequently discusses fragmentation in a part of international law. The main question in this article is what degree of control must be exercised on attributing the conduct of group to the State. On the one hand the (ICJ), try to determine it, especially in cases of Nicaragua and Bosnia (2007).

A common method for controlling a group of parallel converters in decentralized control strategy structure in an island microgrid, the use is the droop-down characteristics of frequency ω-P and voltage E-Q. However, the problem with using this method is that the reactive power is not properly distributed (in proportion to the capacity of the micronutrients) between the micronutrients, which may lead to overload in the converters. Microgrids may also suffer from dynamic stability problems such as power fluctuations, which can be increased by switching between active and reactive power control. To avoid this problem, the X / R ratio of transmission lines is an important parameter that should be carefully considered in the design of micronutrient controllers. By linearizing and simplifying conditions, the control system conversion function model becomes a single input-single output system, which is efficient enough to show the relationship between control parameters such as slope of droop characteristics and derivative sentences, virtual impedance, and voltage controllers. Using this model, stability conditions for different parameters are analyzed. Also, to improve power distribution stability, common droop strategies are modified by adjusting the slope as well as adding nonlinear sentence sections. This approach reduces the coupling between active and reactive power control and reduces the dependence of power distribution on grid parameters such as the X / R ratio. To evaluate the reliability of the proposed model, the simulation results in a sample island microgrid in MATLAB software are presented.

The body freedom flutter phenomenon is one of the aeroelastic instabilities that occurs due to the coupling of the aeroelastic bending mode of the wing with the short-period mode in the flight dynamics of the aircraft. By using the aeroservoelastic model and applying closed loop control, this phenomenon can be suppressed in the operating conditions of the aircraft and the velocity of this event can be increased. The simplest model aircraft capable of displaying this instability includes the flexible wing and the planar flight dynamics model. For this purpose, the wing structure is modeled using the Euler-Bernoulli beam and, the theory of minimum variable State is used to model unstable aerodynamics to make the conditions suitable for modeling the system in State space. In the control section, the elevator is used as the control surface and LQR theory with Kalman filter is used to body freedom flutter suppression. Finally, the effect of adding a closed loop control to increase the body freedom flutter velocity and the limitations of this work are studied.

The dynamic voltage restorer (DVR) is the most advanced mitigation device that has been proposed to protect sensitive loads from the effects of voltage sags. The performance of DVR depends on the ability of PWM scheme to produce the required voltage and the control method. To improve transient and steady State response of DVR, in this paper a new closed 100p control based on the State feedback is proposed. Since the inverter switching using space vector modulation gives some advantages and the control algorithm based on DC signals are much more feasible than those based on sinusoidal signals, we presents a new State space description of DVR in terms of dq quantities that is used to derive a new control scheme, including State feedback and feed-forward path, to eliminate the source disturbance effects and the steady State error. Furthermore, the proposed State space feedback control is completed by integral control to eliminate the steady State error under variable load conditions. To compare the performance of this new control approach with that of some other control methods, some balanced and unbalanced voltage sags have been simulated on a test system in the PSCAD/EMTDC.

Performance and improvement of flight efficiency at various velocities for flight systems, in particular, rotorcrafts, with specific complexities in motion and its nonlinear equations are always of particular interest to researchers in the aerial and control domains. In this research, a new control algorithm is addressed based on the complete nonlinear Unmanned Rotorcraft (UR) model and its four main inputs. Exploiting State feedback and Polytopic Linear Parameter Varying (PLPV) modeling and using Linear Matrix Inequality (LMI), the velocity control problem is investigated. The trim points of the system are produced under different velocity control conditions. State feedback control gain matrix which plays a main role in producing the ultimate control signal, is computed by solving a set of LMIs under various conditions. Finally, instead of using a Nonlinear model, a Polytopic model is used for controller synthesis. With this goal, different scenarios for the proposed flight velocity control (in different dynamic ranges, minimum velocity to maximum velocity) are implemented. The simulation results demonstrate a very good performance of the proposed controller in the basis of PLPV modelling. It can be concluded that the proposed manner is useful to overcome the disruptions imposed on the flight system due to the changes in the equilibrium points and the uncertainties of the parameters and/or possible errors due to the unwanted possibilities in the system.