Modeling, Trimming and Simulation of a Full Scale Helicopter
Hassan, H., Bayoumy, A., El-Bayoumi, G., Abdelrahman, M. (2017). Modeling, Trimming and Simulation of a Full Scale Helicopter. EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), 1-14. doi: 10.21608/asat.2017.22367
Hassan Shahat Hassan; Amgad M. Bayoumy; Gamal M. El-Bayoumi; Mohamed Madbouly Abdelrahman. "Modeling, Trimming and Simulation of a Full Scale Helicopter". EKB Journal Management System, 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, 2017, 1-14. doi: 10.21608/asat.2017.22367
Hassan, H., Bayoumy, A., El-Bayoumi, G., Abdelrahman, M. (2017). 'Modeling, Trimming and Simulation of a Full Scale Helicopter', EKB Journal Management System, 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017), pp. 1-14. doi: 10.21608/asat.2017.22367
Hassan, H., Bayoumy, A., El-Bayoumi, G., Abdelrahman, M. Modeling, Trimming and Simulation of a Full Scale Helicopter. EKB Journal Management System, 2017; 17(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017): 1-14. doi: 10.21608/asat.2017.22367

Modeling, Trimming and Simulation of a Full Scale Helicopter

International Conference on Aerospace Sciences and Aviation Technology
Article 6, Volume 17, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 17 – April 11 - 13, 2017, April 2017, Page 1-14  XML PDF (820.93 K)
Document Type: Original Article
DOI: 10.21608/asat.2017.22367
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Authors
Hassan Shahat Hassan1; Amgad M. Bayoumy2; Gamal M. El-Bayoumi3; Mohamed Madbouly Abdelrahman3
1Teaching assistant, Aerospace Engineering-Cairo University, Cairo.
2Egyptian Armed Forces, Egypt.
3Professor, Aerospace engineering Cairo University, Cairo, Egypt.
Abstract
The complex configuration of helicopter guarantees that the vehicle modeling, trim and simulation are significantly more difficult than fixed-wing aircrafts. In this paper, general expressions for aerodynamic forces and moments, acting on helicopter due to its main and tail rotors at any flight conditions, are derived by using momentum and blade element theories. These complex expressions are inserted in the rigid body equations of motion, derived from Newton second law, to build a generic nonlinear mathematical model for single main and tail rotors helicopters; in order to obtain their responses to arbitrary control inputs. This model can be used in pilot training, control system design, and studying the helicopter stability characteristics. Trimming problem is solved at general flight conditions; arbitrary turn rate, flight path and side slip angles. The power required to fly helicopter at forward flight with several flight path angles is determined. The flight path angle required for helicopter autorotation condition is calculated at any forward speed. The mathematical model is solved by numerical integration (Runge-Kutta method) in the simulation code. The resulting trim conditions are verified by supplying the trim control inputs to the simulation code and verifying that the helicopter is flying in steady-state.
Keywords
Helicopter; mathematical model; Trim; Simulation
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