The paper presents a detailed study on how the results obtained from an inverse simulation algorithm based on the integration method are affected by the modelling approach. In particular, 9 rotor blade dynamic models, 3 main rotor inflow models and 3 fuselage aerodynamic databases are differently combined in order to obtain as many as 13 different helicopter simulation models, which are analyzed in 3 manoeuvres: a hurdle-hop, a slalom and a lateral repositioning. This large amount of results will allow for a consistent evaluation of the most critical situations in which a reduction in model complexity results into an unsatisfactory prediction of the expected vehicle behaviour. On the other side, a minimum level of complexity that allows for a convenient description of rotorcraft dynamics in different tasks will be identified, thus allowing for the definition of a minimum set of vehicle data that allows for a consistent performance prediction as soon as possible during the design process. © 2010 Association Aeronautique et Astronautique de France. All rights reserved.
Modelling Issues in Helicopter Inverse Simulation / G., Avanzini; DE MATTEIS, Guido; A., Torasso. - 1:(2010), pp. 341-350. (Intervento presentato al convegno 36th European Rotorcraft Forum tenutosi a Parigi).
Modelling Issues in Helicopter Inverse Simulation
DE MATTEIS, GUIDO;
2010
Abstract
The paper presents a detailed study on how the results obtained from an inverse simulation algorithm based on the integration method are affected by the modelling approach. In particular, 9 rotor blade dynamic models, 3 main rotor inflow models and 3 fuselage aerodynamic databases are differently combined in order to obtain as many as 13 different helicopter simulation models, which are analyzed in 3 manoeuvres: a hurdle-hop, a slalom and a lateral repositioning. This large amount of results will allow for a consistent evaluation of the most critical situations in which a reduction in model complexity results into an unsatisfactory prediction of the expected vehicle behaviour. On the other side, a minimum level of complexity that allows for a convenient description of rotorcraft dynamics in different tasks will be identified, thus allowing for the definition of a minimum set of vehicle data that allows for a consistent performance prediction as soon as possible during the design process. © 2010 Association Aeronautique et Astronautique de France. All rights reserved.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
