Conference Papers

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Author: search.filters.author.Jeppu, Y.V.Has files: No

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    System simulation approach for helicopter autopilot
    (Institute of Electrical and Electronics Engineers Inc., 2014) Jamadagni, C.S.; Chethan, C.U.; Jeppu, Y.V.; Kamble, S.B.; Desai, V.
    This paper discusses an approach for system simulation of an autopilot system designed for a Bell helicopter model. The flight controls for the helicopter is designed in Matlab/Simulink and the same is visualized in X-Plane flight simulator. The approach involves software in loop simulation method where controls are designed in Matlab/Simulink and the responses are observed on X-Plane plant. The interaction between the Matlab/Simulink and X-Plane is through UDP. A parameter identification of the X-Plane model is carried out from data obtained through UDP. This simulation setup is a good way to learn the intricacies of systems development, plant identification and control. © 2014 IEEE.
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    Characterization of aircraft electro hydrostatic actuator using virtual instrumentation
    (Institute of Electrical and Electronics Engineers Inc., 2015) Sp, K.; Desai, V.; Jeppu, Y.V.
    In Aerospace industry, implementation of Automated Test System (ATS) at the assembly and manufacturing floor improves characterization accuracy and plays a vital role to substantiate the airworthiness of the aircraft components. It is very useful in realizing high quality standards of aircraft components by virtue of meeting predefined acceptance test criteria. This paper outlines comprehensive design and development of the noise and vibration monitoring system at assembly and manufacturing floor for characterization of Electro Hydrostatic Actuator (EHA) of aircraft using progressions in virtual instrumentation. In aircraft, the flight control actuation system are powered by centralized hydraulic pumps that are driven by the aircraft engine, while the back-up system are driven by electric or ram turbines. Distributed control of electric actuators with integration of control function in Flight Control Computer (FCC) and power electronics is a cost effective approach. EHA does also play a significant role in electrical actuation system, which use distributed electric power drive in driving a hydraulic transmission system. Hence, before integrating with the primary flight control actuation systems in aircraft, EHA's are required to be subjected to noise and vibration characterization, as part of assembly and manufacturing level testing. This method is intended at replacing the monotonous and time consuming traditional method of noise and vibration characterization of the electric actuators at assembly and manufacturing floor and to improve the reliability of the electric actuation components supplied to the aircraft manufacturers. The tests have been performed using a LabVIEW controlled virtual instrument measurement system that monitored the noise and vibration waveform with reference to the tacho signal. © 2014 IEEE.
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    Arguing formally about flight control laws
    (Institute of Electrical and Electronics Engineers Inc., 2015) Jeppu, N.Y.; Jeppu, Y.V.; Murthy, N.
    Flight control law software have errors. Some are found during the extensive testing and certification process and others pass through causing accidents. The testing of flight control software indicates that the code and the model match. But it is very difficult to ensure if the model was correct in the first place. Model checkers like Mathworks Simulink Design Verifier check the models against formally defined conditions and system behavior. The tool can come up with counterexamples that can fail an assertion or proof. A study is done on how easy or difficult it is to teach engineering students this formal process. The problem statement, the Simulink models and the outcome of the study in terms of advantages and disadvantages of using Simulink Design Verifier is highlighted in this preliminary study. © 2015 IEEE.
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    System identification for helicopter longitudinal dynamics model - Best practices
    (Institute of Electrical and Electronics Engineers Inc., 2015) Kamble, S.B.; Desai, V.; Jeppu, Y.V.; Prajna
    For estimation of mathematical model and parameters of a system, the system identification has been widely applied in various domains such as the automatic control, aviation, spaceflight, civil and mechanical engineering, medicine, biology, chemical processes, marine ecology, geology etc. The main aim of this work is to perform preliminary studies to design a control law for helicopter model making it as autopilot. X-plane flight simulator will be used with Matlab wherein the estimated model is imported and simulated for its practical behavior. A longitudinal state-space model of the Puma, SA330 research helicopter is used as a reference model. First, the model is described and with standard reference input test signals, output data set is generated, then this input-output dataset is used for system identification purpose. Both traditional methods such as subspace & prediction-error minimization (PEM) method along with modern ways of identification methods such as neural networks are used. A practical comparison between used identification methods and best suitable type of input for estimation is discussed. © 2015 IEEE.