The Experts below are selected from a list of 312 Experts worldwide ranked by ideXlab platform

Sreenatha G Anavatti - One of the best experts on this subject based on the ideXlab platform.

  • state of the art intelligent Flight Control Systems in unmanned aerial vehicles
    IEEE Transactions on Automation Science and Engineering, 2018
    Co-Authors: Fendy Santoso, Matthew Garratt, Sreenatha G Anavatti
    Abstract:

    We discuss state-of-the-art intelligent robotic aircraft with the special focus on evolutionary autopilots for small unmanned aerial vehicles (UAVs). Under the umbrella of adaptive autopilots, we highlight the pros and cons of the most widely implemented intelligent algorithms against the navigational and maneuvering capabilities of small UAVs. We present several cutting-edge applications of bioinspired Flight Control Systems that have the capability of self-learning. We also highlight several research opportunities and challenges associated with each technique. Note to Practitioners —Soft computing methods have been widely implemented in numerous engineering applications. Recent advancements in computational technology have enabled the implementations of intelligent autopilots in real time. This paper aims to discuss many aspects of the developments and implementations of soft computing techniques in aerial robotics with the main focus on its Flight Control Systems.

Masaru Uchiyama - One of the best experts on this subject based on the ideXlab platform.

  • Flight Control Systems of a quad tilt rotor unmanned aerial vehicle for a large attitude change
    International Conference on Robotics and Automation, 2015
    Co-Authors: Atsushi Oosedo, Satoko Abiko, Shota Narasaki, Atsushi Kuno, Atsushi Konno, Masaru Uchiyama
    Abstract:

    Quad tilt rotor Unmanned Aerial Vehicle (UAV) solves the problem of underacuated system in general quadrotor UAV. The quad tilt rotor UAV can Control position and attitude independently by tilting directions of propellers. However, the Flight Control system in a wide range of attitudes has not been discussed yet, e.g. a UAV flying and hovering with a 90 [°] pitch angle and can flip over when the range of the tilting motor rotates wide enough. In this paper, we present the attitude transition Flight Control system for pitch angles ranging 0 [°] to 90 [°] since Flight condition with a 90 [°] pitch angle significantly differs from that in a conventional quadrotor UAV Flight, and then adequate Control system and sufficient experimental validation are necessary for stable Flight in a wide range of attitude conditions.

Fendy Santoso - One of the best experts on this subject based on the ideXlab platform.

  • state of the art intelligent Flight Control Systems in unmanned aerial vehicles
    IEEE Transactions on Automation Science and Engineering, 2018
    Co-Authors: Fendy Santoso, Matthew Garratt, Sreenatha G Anavatti
    Abstract:

    We discuss state-of-the-art intelligent robotic aircraft with the special focus on evolutionary autopilots for small unmanned aerial vehicles (UAVs). Under the umbrella of adaptive autopilots, we highlight the pros and cons of the most widely implemented intelligent algorithms against the navigational and maneuvering capabilities of small UAVs. We present several cutting-edge applications of bioinspired Flight Control Systems that have the capability of self-learning. We also highlight several research opportunities and challenges associated with each technique. Note to Practitioners —Soft computing methods have been widely implemented in numerous engineering applications. Recent advancements in computational technology have enabled the implementations of intelligent autopilots in real time. This paper aims to discuss many aspects of the developments and implementations of soft computing techniques in aerial robotics with the main focus on its Flight Control Systems.

Atsushi Oosedo - One of the best experts on this subject based on the ideXlab platform.

  • Flight Control Systems of a quad tilt rotor unmanned aerial vehicle for a large attitude change
    International Conference on Robotics and Automation, 2015
    Co-Authors: Atsushi Oosedo, Satoko Abiko, Shota Narasaki, Atsushi Kuno, Atsushi Konno, Masaru Uchiyama
    Abstract:

    Quad tilt rotor Unmanned Aerial Vehicle (UAV) solves the problem of underacuated system in general quadrotor UAV. The quad tilt rotor UAV can Control position and attitude independently by tilting directions of propellers. However, the Flight Control system in a wide range of attitudes has not been discussed yet, e.g. a UAV flying and hovering with a 90 [°] pitch angle and can flip over when the range of the tilting motor rotates wide enough. In this paper, we present the attitude transition Flight Control system for pitch angles ranging 0 [°] to 90 [°] since Flight condition with a 90 [°] pitch angle significantly differs from that in a conventional quadrotor UAV Flight, and then adequate Control system and sufficient experimental validation are necessary for stable Flight in a wide range of attitude conditions.

Francesco Schettini - One of the best experts on this subject based on the ideXlab platform.

  • impacts of safety on the design of light remotely piloted helicopter Flight Control Systems
    Reliability Engineering & System Safety, 2016
    Co-Authors: G Di Rito, Francesco Schettini
    Abstract:

    Abstract This paper deals with the architecture definition and the safety assessment of Flight Control Systems for light remotely-piloted helicopters for civil applications. The methods and tools to be used for these activities are standardised for conventional piloted aircraft, while they are currently a matter of discussion in case of light remotely-piloted Systems flying into unsegregated airspaces. Certification concerns are particularly problematic for aerial Systems weighing from 20 to 150 kgf, since the airworthiness permission is granted by national authorities. The lack of specific requirements actually requires to analyse both the existing standards for military applications and the certification guidelines for civil Systems, up to derive the adequate safety objectives. In this work, after a survey on applicable certification documents for the safety objectives definition, the most relevant functional failures of a light remotely-piloted helicopter are identified and analysed via Functional Hazard Assessment. Different architectures are then compared by means of Fault-Tree Analysis, highlighting the contributions to the safety level of the main elements of the Flight Control system (Control computers, servoactuators, antenna) and providing basic guidelines on the required redundancy level.

  • air data computation in fly by wire Flight Control Systems
    Journal of Aircraft, 2006
    Co-Authors: Fabio Cervia, Eugenio Denti, Roberto Galatolo, Francesco Schettini
    Abstract:

    The aim of air data Systems is the determination of Flight parameters (such as pressure altitude, Mach number, angles of attack and sideslip) from measurements of local pressures and of local flow angles on wings or fuselage provided by a proper set of sensors. The active and integrated use of Flight parameters in a full-authority fly-bywire Flight-Control system imposes redundant system architecture to achieve an adequate level of reliability and safety. In this paper a methodology for air data computation is proposed that allows the Flight parameters to be evaluated on the basis of data measured by four multifunction air data probes. It takes into account the effects of the modification of aircraft configuration during Flight, as well as the effects of aircraft maneuver. Finally, it includes dedicated algorithms for the management of redundancy, which are able to detect possible system failures and to provide consolidated outputs. The methodology has been implemented in the Matlab/Simulink environment and a preliminary comparison of the results with Flight test data showed satisfactory performance. Nomenclature a = asymptotic speed of sound C pfront i = frontal pressure coefficient of the ith probe C pslot i = slot pressure coefficient of the ith probe Config = aircraft configuration parameter d = (X s, 0, 0) = distance between the section of installation of the probes and the center of mass of the aircraft ffront = characteristic function of the stand alone probe for the frontal pressure fi = flow angle function of the ith probe f Li