Photovoltaic power generation is mainly connected to the grid by grid-connected inverter. Compared with the traditional synchronous generator, it has the advantages of flexible control and quick response, but there is...
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ISBN:
(纸本)9781538685495
Photovoltaic power generation is mainly connected to the grid by grid-connected inverter. Compared with the traditional synchronous generator, it has the advantages of flexible control and quick response, but there is also lack of inertia and damping. With the increasing of the permeability of the photovoltaic power supply, the rotating spare capacity and the moment of inertia in the power system are relatively reduced, which poses a severe challenge to the safe and stable operation of the power grid. The introduction of photovoltaic virtual synchronous generator makes the grid connected inverter have similar operation characteristics of synchronous generator and improve the stability of power system. In this paper, a hardware in loop simulation test scheme based on RT-LAB is proposed for PV virtual synchronous generator, and a simulation test platform is set up to study the testing method of the performance of the PV virtual synchronous generator. Based on this platform, the characteristics of the PV virtual synchronous generator, such as the inertia and the primary frequency modulation, are carried out. The test results show that the simulation platform is correct.
With the development of control algorithms and structural features in the control system, the hardware-in-loopsimulation technology has been widely used after unremitting research and exploration on the basis of off-...
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The aircraft arrester gear system is required to perform arrestment of various types of aircrafts in case of emergency landing and reject takeoff. The design of a single arresting gear system to accommodate a wide ran...
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ISBN:
(纸本)9781509036462
The aircraft arrester gear system is required to perform arrestment of various types of aircrafts in case of emergency landing and reject takeoff. The design of a single arresting gear system to accommodate a wide range of aircraft weights and speeds is a complex task and requires an electronic control system with sensors which sense the incoming aircraft type, its speed and adjusts the braking force accordingly. The main subsystems of the arrester gear are: 1) a tape and net assembly to arrest the aircraft on the runway, 2) control system and 3) an energy absorber system consisting of two energy absorbers, one on either side. The control system is required to perform controlled braking within the specified deceleration values so as to bring the aircraft to halt within the specified runout distance. During the system design it was required to verify the controller gain values which have been derived from the modelling and simulation of the arrester gear system. hardware in loop simulation is a very effective technique for testing the control algorithm, embedded electronics & sensors and other available hardware in the absence of the actual system. For this purpose a hardware in loop simulation setup was developed where the control system and hydraulic system performance was evaluated using a model of the aircraft arrester gear to simulate the weights and velocities of the aircraft.
simulation tools have been extensively used for the design and improvement of electrical systems for decades. The evolution of simulation tools has progressed dramatically in recent years with the advancement in compu...
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ISBN:
(纸本)9781509025978
simulation tools have been extensively used for the design and improvement of electrical systems for decades. The evolution of simulation tools has progressed dramatically in recent years with the advancement in computing technologies. The present trend in simulation is Real Time simulation where the computer model runs at the same rate as the actual physical time. The only reason to conduct Real-Time simulation is to connect real hardware to the simulated model. This is where the importance of hardware in the loopsimulation emerges where the virtual plant model is controlled using a real controller. Synchronization of external PWM signals with the simulation time step of the virtual plant model is the main concern while conducting HIL simulation of Power Electronic systems. In this work a time compensation algorithm is developed to deduce the accurate switching instant of the control signals. Time compensation hardware is implemented using FPGA and accurate switching, instant is incorporated into the simulation process with the help of time compensated libraries for switching elements. The algorithm is tested by giving PWM signals from external controllers to a virtual buck converter model simulated inside Full Spectrum Simulator (FSS). Results obtained by enabling and disabling the algorithm are analyzed thoroughly and is finding that time compensation greatly helps to obtain maximum accuracy while conducting HIL simulation.
The aircraft arrester gear system is required to perform arrestment of various types of aircrafts in case of emergency landing and reject takeoff. The design of a single arresting gear system to accommodate a wide ran...
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ISBN:
(纸本)9781509036479
The aircraft arrester gear system is required to perform arrestment of various types of aircrafts in case of emergency landing and reject takeoff. The design of a single arresting gear system to accommodate a wide range of aircraft weights and speeds is a complex task and requires an electronic control system with sensors which sense the incoming aircraft type, its speed and adjusts the braking force accordingly. The main subsystems of the arrester gear are: 1) a tape and net assembly to arrest the aircraft on the runway, 2) control system and 3) an energy absorber system consisting of two energy absorbers, one on either side. The control system is required to perform controlled braking within the specified deceleration values so as to bring the aircraft to halt within the specified runout distance. During the system design it was required to verify the controller gain values which have been derived from the modelling and simulation of the arrester gear system. hardware in loop simulation is a very effective technique for testing the control algorithm, embedded electronics & sensors and other available hardware in the absence of the actual system. For this purpose a hardware in loop simulation setup was developed where the control system and hydraulic system performance was evaluated using a model of the aircraft arrester gear to simulate the weights and velocities of the aircraft.
In this paper, an adaptive backstepping-based control scheme is proposed to perform autonomous lateral maneuvers under significant lateral offset in the center of gravity (c.g.) position in a UAV. It is first shown th...
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In this paper, an adaptive backstepping-based control scheme is proposed to perform autonomous lateral maneuvers under significant lateral offset in the center of gravity (c.g.) position in a UAV. It is first shown that the coupled equations of motion arising from lateral c.g. shift can be simplified and cast in block strict feedback form making it amenable to a two-step backstepping control design. Useful nonlinear terms in the equations of motion are identified and retained in the backstepping design to ensure a less conservative control. Adaptation law is incorporated to dynamically adjust to changes in the c.g. position by adding an adaptive term to each step of the backstepping control. Lyapunov's direct method and LaSalle's invariance principle are applied to establish asymptotic stability of both tracking errors and errors in the c.g. estimate. To validate the effectiveness of the proposed control strategy, simulation results for horizontal turn maneuver are presented for the fixed wing Aerosonde UAV and maneuver performance is observed to remain highly insensitive to a wide range of lateral c.g. positions on either side of the fuselage centerline. Furthermore, a comparative control performance analysis is carried out against an ad-hoc model-based adaptive backstepping control scheme available in the literature and the results show significant performance enhancement in the proposed scheme. Along with the c.g. variations, the effects of steady crosswind are also investigated and the control formulation is modified to mitigate these effects too. Real-time control hardware in loop simulations are also provided in support of the real time viability of the proposed control.
The greenhouse is a complex nonlinear system, which provides a suitable growing environment for plants. Realizing a comprehensive control for such systems is more challenging in the premise of the presence of model pa...
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hardware in loop simulation HILS-based waypoint simulation for fixed wing unmanned aerial vehicles is proposed in this paper. It uses an open-source arducopter as a flight controller, mission planner, and X-plane simu...
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hardware in loop simulation HILS-based waypoint simulation for fixed wing unmanned aerial vehicles is proposed in this paper. It uses an open-source arducopter as a flight controller, mission planner, and X-plane simulator. Waypoint simulation is carried out in the flight controller and executed in an X-plane simulator through a mission planner. A fixed wing unmanned aerial vehicle with an inverted T tail configuration has been chosen to study and validate waypoint flight control algorithms. The data transmission between mission planner and flight controller is done by serial protocol, whereas data exchange between X-plane and mission planner is done by User Datagram Protocol (UDP). APM mission planner is used as a machine interface to exchange data between the flight controller and the user. User inputs and flight gain parameters, both inner loop and outer loop, can be modified with the help of a mission planner. In addition to that, the mission planner provides a visual output representation of flight data and navigation algorithm.
hardware-In-loopsimulation (HILS) is the only platform where the dynamics of the subsystem is tested and on-board software is validated in real time environment before the flight trial. The flight systems consist of ...
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ISBN:
(纸本)9780769550138
hardware-In-loopsimulation (HILS) is the only platform where the dynamics of the subsystem is tested and on-board software is validated in real time environment before the flight trial. The flight systems consist of navigation, guidance and control. The Inertial Navigation system (INS) which is embedded system is sending the required navigation information for the guidance and control algorithm which resides in on-board computer-OBC (embedded system). The plant model is used to create environment near flight condition and to validate guidance and control as well as navigation. The newly developed navigation package based on MIL-STD 1553 communication protocol introduced in HILS for total trajectory dynamics validation in different phases. Firstly the navigation algorithm resided in INS is validated and the sensors i.e. gyros are excited in next step to test for delays, and non linearity. The total methodology adopted for the testing of the navigation package-INS is presented in this paper.
The ever-increasing load demand motivates the adoption of the six-phase transmission system as a viable alternative to the conventional three-phase double-circuit line because of its enhanced power transfer capability...
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The ever-increasing load demand motivates the adoption of the six-phase transmission system as a viable alternative to the conventional three-phase double-circuit line because of its enhanced power transfer capability. However, the acceptance of six-phase transmission is highly dependent on its protection scheme, which is a challenging task due to the large number of possible faults. In this regard, this paper describes a novel concept based on the hybridization of wavelet transform, adaptive particle swarm optimization (APSO) and ANN for fault classification and location in the six-phase transmission line. The proposed scheme overcomes the difficulties associated with existing ANN-based protection schemes related to the selection of architecture and convergence to the non-global optimal set of weight vectors and biases post-training. From the features/attributes extracted using wavelet transform, the hybrid algorithm utilizes the strong exploration and mapping capability of APSO and ANN, respectively, for input-output mapping. It significantly increases the probability of global convergence for ANN training, thereby improving the performance of the protection scheme in terms of fault detection, classification and location estimation accuracy. The proposed scheme has been extensively tested for wide variation in different fault attributes. In addition to the offline simulations, the effectiveness of the proposed scheme has been validated in real-time environment by carrying out hardware in loop simulations using OPAL-RT digital simulator.
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