Modeling, Trimming and Simulation of a Full Scale Helicopter
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Date
2017-04
Journal Title
Journal ISSN
Volume Title
Type
Article
Publisher
ASAT
Series Info
17 th International Conference on AEROSPACE SCIENCES & AVIATION TECHNOLOGY;15 p
Scientific Journal Rankings
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.
Description
Keywords
University for Simulation., Trim, Mathematical Model, Helicopter