The Experts below are selected from a list of 18 Experts worldwide ranked by ideXlab platform
Bhat M. Seetharama - One of the best experts on this subject based on the ideXlab platform.
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Modeling and closed loop flight testing of a fixed wing micro air vehicle
'MDPI AG', 2018Co-Authors: Kandath Harikumar, Bera Titas, Dhall Sidhant, Pushpangathan Jinraj, Bhat M. SeetharamaAbstract:This paper presents the nonlinear six degrees of freedom dynamic Modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space Models are obtained about trim conditions. The variations in short period Mode, phugoid Mode, Dutch Roll Mode, Roll Subsidence Mode and spiral Mode with respect to different trim operating conditions is presented. A stabilizing static output feedback contRoller is designed using the obtained Model. Successful closed loop flight trials are conducted with the static output feedback contRoller.Published versio
M. Seetharama Bhat - One of the best experts on this subject based on the ideXlab platform.
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Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle
Micromachines, 2018Co-Authors: Harikumar Kandath, Jinraj V. Pushpangathan, Titas Bera, Sidhant Dhall, M. Seetharama BhatAbstract:This paper presents the nonlinear six degrees of freedom dynamic Modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space Models are obtained about trim conditions. The variations in short period Mode, phugoid Mode, Dutch Roll Mode, Roll Subsidence Mode and spiral Mode with respect to different trim operating conditions is presented. A stabilizing static output feedback contRoller is designed using the obtained Model. Successful closed loop flight trials are conducted with the static output feedback contRoller.
Kandath Harikumar - One of the best experts on this subject based on the ideXlab platform.
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Modeling and closed loop flight testing of a fixed wing micro air vehicle
'MDPI AG', 2018Co-Authors: Kandath Harikumar, Bera Titas, Dhall Sidhant, Pushpangathan Jinraj, Bhat M. SeetharamaAbstract:This paper presents the nonlinear six degrees of freedom dynamic Modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space Models are obtained about trim conditions. The variations in short period Mode, phugoid Mode, Dutch Roll Mode, Roll Subsidence Mode and spiral Mode with respect to different trim operating conditions is presented. A stabilizing static output feedback contRoller is designed using the obtained Model. Successful closed loop flight trials are conducted with the static output feedback contRoller.Published versio
Harikumar Kandath - One of the best experts on this subject based on the ideXlab platform.
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Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle
Micromachines, 2018Co-Authors: Harikumar Kandath, Jinraj V. Pushpangathan, Titas Bera, Sidhant Dhall, M. Seetharama BhatAbstract:This paper presents the nonlinear six degrees of freedom dynamic Modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space Models are obtained about trim conditions. The variations in short period Mode, phugoid Mode, Dutch Roll Mode, Roll Subsidence Mode and spiral Mode with respect to different trim operating conditions is presented. A stabilizing static output feedback contRoller is designed using the obtained Model. Successful closed loop flight trials are conducted with the static output feedback contRoller.
Bera Titas - One of the best experts on this subject based on the ideXlab platform.
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Modeling and closed loop flight testing of a fixed wing micro air vehicle
'MDPI AG', 2018Co-Authors: Kandath Harikumar, Bera Titas, Dhall Sidhant, Pushpangathan Jinraj, Bhat M. SeetharamaAbstract:This paper presents the nonlinear six degrees of freedom dynamic Modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space Models are obtained about trim conditions. The variations in short period Mode, phugoid Mode, Dutch Roll Mode, Roll Subsidence Mode and spiral Mode with respect to different trim operating conditions is presented. A stabilizing static output feedback contRoller is designed using the obtained Model. Successful closed loop flight trials are conducted with the static output feedback contRoller.Published versio
