This article is focused on numerical investigations aimed to analyze the advantages induced on high aspect ratio wings by an unconventional roll control strategy based on wing twist morphing. The sailplane GROB G103-B was used as a reference for the performed analysis. The available data of the reference aircraft were exclusively related to its geometric, aerodynamic and global inertial properties; in order to build up the structural model for the wing, a “reverse engineering” was therefore carried out. Referring to CS-22 airworthiness requirements, a preliminary sizing of the wing structure was obtained by using elementary methods. The structural lay-out was then verified by means of a more advanced finite element analysis. The aeroelastic model of the wing was generated and the inertial contributes of empennages and fuselage were properly taken in account. Elastic aircraft roll dynamic was at first investigated considering conventional aileron-based control strategy. Extra-modes representative of several variable twist laws were then added to aircraft dynamic model in order to simulate wing twist morphing; roll dynamic based on wing twist morphing was finally analyzed. Conventional (aileron-based) and unconventional (wing twist morphing) roll control were compared from aerodynamic and aeroelastic standpoint and the benefits induced by the latter strategy were outlined.
Effectiveness of a roll-control strategy based on wing twist morphing / Pecora, Rosario; Angela, Iossa; William La, Neve; Amoroso, Francesco; Lecce, Leonardo. - (2009), pp. Section STR05 - p.37-Section STR05 - p.54. (Intervento presentato al convegno XX Congresso Nazionale AIDAA tenutosi a Milano (ITALY) nel June 29 - July 3, 2009).
Effectiveness of a roll-control strategy based on wing twist morphing
PECORA, ROSARIO;AMOROSO, FRANCESCO;LECCE, LEONARDO
2009
Abstract
This article is focused on numerical investigations aimed to analyze the advantages induced on high aspect ratio wings by an unconventional roll control strategy based on wing twist morphing. The sailplane GROB G103-B was used as a reference for the performed analysis. The available data of the reference aircraft were exclusively related to its geometric, aerodynamic and global inertial properties; in order to build up the structural model for the wing, a “reverse engineering” was therefore carried out. Referring to CS-22 airworthiness requirements, a preliminary sizing of the wing structure was obtained by using elementary methods. The structural lay-out was then verified by means of a more advanced finite element analysis. The aeroelastic model of the wing was generated and the inertial contributes of empennages and fuselage were properly taken in account. Elastic aircraft roll dynamic was at first investigated considering conventional aileron-based control strategy. Extra-modes representative of several variable twist laws were then added to aircraft dynamic model in order to simulate wing twist morphing; roll dynamic based on wing twist morphing was finally analyzed. Conventional (aileron-based) and unconventional (wing twist morphing) roll control were compared from aerodynamic and aeroelastic standpoint and the benefits induced by the latter strategy were outlined.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
