TY - GEN
T1 - A Comparative Analysis of Longitudinal and Lateral Directional Dynamics of Aircraft from Different Classes
AU - Hegde, Navya Thirumaleshwar
AU - George, V. I.
AU - Nayak, C. Gurudas
PY - 2019/6
Y1 - 2019/6
N2 - The comparative study and analysis of five different aircrafts namely, Cessna 182 (Class I), Beech 99 (Class II), Cessna T37A (Class II), Boeing 747 200 (Class III), McDonnell Douglas F4 (Class IV) at different flight conditions is presented in this paper. The mathematical model and dynamic characteristics of a generic aircraft is simulated, where some assumptions are made while deriving the models. The aircraft dynamic characteristics are derived as MATLAB functions and simulated. It gives full 6DoF aircraft mathematical modelling using Euler angles, trimming at desired flight conditions and generation of linearized model. Simulation results shows that the stability of longitudinal/lateral directional dynamics depends on the aircraft geometric parameters, inertial characteristics and flight conditions. Greater the value of ωNSP, higher the airspeed, resulting in faster dynamics of short period mode. As the altitude decreases, magnitude of ωNSP also decreases with increase in air density. The aircraft of lower size and weight associated with smaller value of Iyy leads to greater value of ωNSP. At low subsonic flight conditions (high values of CL1, low values for CDu) the value of ζPH is less as compared to the aircraft at higher subsonic conditions (lower values of CL1, higher values for CDu).
AB - The comparative study and analysis of five different aircrafts namely, Cessna 182 (Class I), Beech 99 (Class II), Cessna T37A (Class II), Boeing 747 200 (Class III), McDonnell Douglas F4 (Class IV) at different flight conditions is presented in this paper. The mathematical model and dynamic characteristics of a generic aircraft is simulated, where some assumptions are made while deriving the models. The aircraft dynamic characteristics are derived as MATLAB functions and simulated. It gives full 6DoF aircraft mathematical modelling using Euler angles, trimming at desired flight conditions and generation of linearized model. Simulation results shows that the stability of longitudinal/lateral directional dynamics depends on the aircraft geometric parameters, inertial characteristics and flight conditions. Greater the value of ωNSP, higher the airspeed, resulting in faster dynamics of short period mode. As the altitude decreases, magnitude of ωNSP also decreases with increase in air density. The aircraft of lower size and weight associated with smaller value of Iyy leads to greater value of ωNSP. At low subsonic flight conditions (high values of CL1, low values for CDu) the value of ζPH is less as compared to the aircraft at higher subsonic conditions (lower values of CL1, higher values for CDu).
UR - https://www.scopus.com/pages/publications/85072819323
UR - https://www.scopus.com/pages/publications/85072819323#tab=citedBy
U2 - 10.1109/ICECA.2019.8822119
DO - 10.1109/ICECA.2019.8822119
M3 - Conference contribution
T3 - Proceedings of the 3rd International Conference on Electronics and Communication and Aerospace Technology, ICECA 2019
SP - 584
EP - 589
BT - Proceedings of the 3rd International Conference on Electronics and Communication and Aerospace Technology, ICECA 2019
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 3rd International Conference on Electronics and Communication and Aerospace Technology, ICECA 2019
Y2 - 12 June 2019 through 14 June 2019
ER -