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The purpose of this paper is to present the generic conception of the aircraft control system with the voice command interpretation interface. The paper's intention is also to present the first steps of work under control system for general aviation aircraft, which assists pilots using speech interpretation module.

The paper defines the main rules governing projecting and operating such systems, and defines and discusses the main functionality levels. The use of voice commands for the direct controlling of the flight of the plane is also presented and analyzed in detail.

The paper presents general rules, which could be applied for work under control systems with speech interpretation modules intended for general aviation aircraft.

The analyses and opinions included in this paper can be generic basis for future projects, which will try to use pilot's voice command to control the general aviation airplane.

This paper presets some conception of the control system with the speech recognition interface. There are main rules generally defining both the structure and the functionality the of such aircraft control system, included in this paper.

To develop general forms of multiscalar models of the induction motor and to present properties of the sensorless control systems based on such models.

Previously presented multiscalar model of the induction motor based on a stator current and rotor flux vector is generalized as a model of type 1. New model of type 2 is defined for stator current and the vector which is directly controlled by a voltage vector. The above models are applied in a sensorless control system with speed observer. Dynamical properties of the sensorless control systems are investigated by simulations and experiments.

Application of the multiscalar model of type 2 results in higher exactness of sensorless control system than application of the multiscalar model of type 1. Controlled variables are more smooth in transients.

This is not an analytical proof of stability of the control systems.

Provides very useful information for development of sensorless control systems for the induction motor.

This paper extends the known method of nonlinear control of the induction motor to the general form. It is possible to choose the sensorless control system of better properties than those used so far.

The aim of this paper is to undertake analysis and comparison of the closed‐loop and sensorless control systems sensitivity to the broken rotor for diagnostic purposes. For the same vector control system induction motor drive analysis concerning operation with the asymmetric motor, broken rotor fault handling and operation were investigated. Reliability, range of stable operation, fault symptoms and application of diagnosis methods based on control system variables utilization was analyzed.

Induction motor drive vector control system synthesis was applied using the multiscalar variables of the machine model with nonlinear feedback linearization applied to use classical cascaded PI controllers for the speed‐torque and flux decoupled control. Speed observer was applied for the rotor flux and rotor speed estimation for the sensorless control system synthesis.

Relative sensitivity of the state and control system variables to broken rotor fault based on experimental results for the closed‐loop and sensorless control systems is presented and compared. Drawbacks of using the MCSA analysis for the rotor fault diagnosis in the closed‐loop and sensorless control systems are pointed. Advantages and drawbacks of the state space estimators filtering characteristics in the sensorless control system are described.

Asymmetric IM motor drive handling and diagnosis. Broken rotor range diagnosis inconsistency using the popular MCSA method should be considered in the closed‐loop and sensorless control system of the induction motor drive. Depending on the IM motor drive application and the operation requirements the results can be used for asymmetric machine proper handling, choosing proper control system structure and control system variables for rotor fault early diagnosis.

Sensitivity of the state and control system variables to broken rotor fault based on experimental results for the closed‐loop and sensorless control systems is presented, which implies motor handling procedures and fault diagnosis.

The article describes a new approach to the cost/benefit aspect of management control systems which will help managers decide which control system is worthwhile improving and how. The new concept is based on two ideas: defining the purpose of a control system as: “Triggering corrective action that will prevent losses which came out of deviation from planned path”; and breaking up the control cycle into five steps and relating separately to each step for improving the present system and its cost/benefit performance.

Intelligent lighting control system can control lights to go off when people leave, which has been widely concerned by researchers.

In this study, an intelligent lighting control system based on wireless sensor network was designed. First, the hardware and software designs of the system were described briefly. Then, the lighting control algorithm was analyzed emphatically. Considering the illumination and uniformity of light, an intelligent lighting control algorithm based on gradient descent was designed.

In the system test, it was found that the system had a good through-wall communication function, and the communication distance could fully meet the system requirements and run normally. In the test of the lighting control algorithm, it was found that the user’s satisfaction on uniformity in different scenarios was close to 1, and the satisfaction on illumination could also meet the user’s needs, which verified the reliability of the lighting control algorithm.

This study provides some theoretical supports for the better application of wireless sensor network in intelligent light control system, which is conducive to the further development of light control system.

The guided missile system is considered as SISO plant with parameter perturbations. The structure of the missile system is not suitable for the use of classical linear controllers. On the other hand, the missile system should be capable of good performances, such as zero steady state error, less settling time etc. Standard VSC control laws fail to control the steady state error due to the structure of the system matrices. For this reason we have proposed two new robust output integral sliding mode controllers and design procedures. An integrator is included in the sliding function, which results in the reduction and removal of the output error. The total control consists of two parts: equivalent control which compensates the nominal regime of the missile system; and VSC which compensates the parameter perturbations (changes in Mach number, altitude and mass of the vehicle, etc.) of the missile system. We have derived new constructive sliding and stability conditions for both cases by using Lyapunov’s direct method. Computer simulations indicate that this approach yields a satisfactory control performance.

Weblabs are an additional resource in the execution of experiments in control engineering education, making learning process more flexible both in time, by allowing extra class laboratory activities, and space, bringing the learning experience to remote locations where experimentation facilities would not be available. The purpose of this paper is to investigate and report on a weblab project where the speed of a DC motor is controlled in closed loop, being the control system parameters set by the remote user (student).

The engine control experiments are run and on‐line transmitted by videoconference over the internet, from a didactical plant physically located at the Systems and Automation Laboratory of the Control and Automation Engineering department of the Pontifical Catholic University of Parana. The system response (transient motor speed) to the user's choice of parameters is evaluated through performance indices (IAE, ITAE), which are used to qualify the ability of the student to tune PID and RTS control algorithms. There is an option to run experiments in open loop, so the student can perform preliminary analysis to identify the system dynamic model and then apply mathematical models and computational methods, learned in theoretical classes, to define best performance control parameters. A simulation function was implemented, to further help the student in the problem solution. Virtual instrumentation resources were used to implement the Weblab, using the DC motor of a laboratory didactical plant. A local server runs a LabVIEWTM application, which can be remotely accessed in the client side through a web browser, where the system front panel is reproduced. This remote interface is directly originated at the LabVIEWTM application, through an embedded web server. At the user request, the control of the remote system is granted. The user interface is cognitive, with motor speed, control signal, set point and all the pertinent information displayed in evolving charts and indicators. Microsoft™ Skype is used to establish a videoconference with the laboratory where the plant is located. Results of the user experiments are stored in local files, which can be e‐mailed to the user at his command by the end of the session.

Used as a platform in weblab projects, LabVIEW combined with Skype provides a suitable solution for the necessary software/hardware integration for communications with data acquisition systems and advanced connectivity resources. In virtual instrumentation Skype has proved to be efficient in establishing the right environment without the need for developing complex software for teaching practical control engineering concepts.

The level of performance (speed of acquisition, accuracy and number of parameters that could be evaluated) of the current system would need to be evaluated compared to some existing systems. The implication is the changes brought to the adopted approach to the development of, access to and the overall cost of producing virtual laboratory systems used for science, engineering and technology education.

With further effort, the current and similar systems could be further upgraded with user login control and server, so that results can be submitted to the tutor, thus acting as a learning evaluation instrument.

The originality of this research lies in the innovative integration of technology in education, which involves the implementation of a carefully designed, cost‐effective virtual laboratory for teaching and learning of concepts in control engineering.

The purpose of this study is to test the performance of the designed automatic control system based on the Linear Quadratic Regulator (LQR) and Linear Quadratic Gaussian (LQG) algorithms during landing of the helicopter on the ship deck. This paper is a further development of the series based on Topczewski et al. (2020).

The system consists of two automatic control algorithms based on LQR and the LQG. It is integrated with the ship motion prediction system based on autoregressive algorithm with parameters calculated using Burg’s method. It is assumed that the source of necessary navigation data is integrated Inertial Navigation System with Global Positioning System. Landing of the helicopter on the ship deck is performed in automatic way, based on the preselected procedure. Performance of the control system is analyzed when all necessary navigation data is available for the system and in case when one of the parameters is unavailable during performing the procedure.

In this paper, description of the designed control system developed for performing the approach and landing of the helicopter using selected procedure is presented. Helicopter dynamic model is validated using the manufacturer data and by test pilots, overview is presented. Necessary information about ship motion model is also included. Tests showing mission performance while using LQR and LQG algorithms applied to the control system are presented and analyzed, taking into account both situations when full navigation data is available/unavailable for the control system.

Results of the system performance analyses can be used for selection of the proper control methodology for prospective helicopters autopilots. Furthermore, the system can be used to analyze the mission safety when information about one of the navigation parameters is identified by the navigation system as unavailable or incorrect and therefore unavailable during landing on the ship deck.

In this paper, control system dedicated for the automatic landing of the helicopter on the ship deck, based on two different control algorithms is presented. Influence of lack of information about one of the navigation parameters on the mission performance is analyzed.

The motivation to perform research on feedback control system for unmanned aerial vehicles, a fact that each quadrocopter is unstable.

For this reason, it is necessary to design a control system which is capable of making unmanned aerial vehicle vertical take-off and landing (UAV VTOL) stable and controllable. For this purpose, it was decided to use a feedback control system with cascaded PID controller. The main reason for using it was that PID controllers are simple to implement and do not use much hardware resources. Moreover, cascaded control systems allow to control object response using more parameters than in a standard PID control. STM32 microcontrollers were used to make a real control system. The rapid prototyping using Embedded Coder Toolbox, FreeRTOS and STM32 CubeMX was conducted to design the algorithm of the feedback control system with cascaded PID controller for unmanned aerial vehicle vertical take-off and landings (UAV VTOLs).

During research, an algorithm of UAV VTOL control using the feedback control system with cascaded PID controller was designed. Tests were performed for the designed algorithm in the model simulation in Matlab/Simulink and in the real conditions.

It has been proved that an additional control loop must have a full PID controller. Moreover, a new library is presented for STM32 microcontrollers made using the Embedded Coder Toolbox just for the research. This library enabled to use rapid prototyping while developing the control algorithms.

In this paper, results of the flight‐testing of an unmanned aerial vehicle (UAV) flight control system are presented. APC‐4 “SkyGuide” autonomous navigation and control system, designed and developed by the research team of the Department of Avionics and Control at Rzeszów University of Technology, has been tested. Properties of this flight control system, as well as selected results of the in‐flight tests conducted on board of the PZL‐110 “Koliber” aircraft, are presented. Results obtained confirm that design assumptions of the navigation and control system and research methodology have been appropriate and APC‐4 autopilot can be used on UAVs board.