PrandtlPlane Joined Wing: Body Freedom Flutter, Limit Cycle Oscillation and Freeplay Studies

Rauno Cavallaro, Andrea Iannelli, Luciano Demasi, Rocco Bombardieri

Research output: Chapter in Book/Report/Conference proceedingConference Contribution (Conference Proceeding)

Abstract

Dynamic aeroelastic behaviour of a joined-wing PrandtlPlane configuration is here investigated. The baseline model is obtained from a configuration previously designed by partner Universities through several multi disciplinary optimizations and several ad-hoc analyses, including also detailed studies on the layout of control architecture. This represented an ideal starting point since, due to the novel design, realistic layout of the mobile surfaces, stiffness and inertia distributions are not available nor easily determinable. An equivalent structural model has then been adopted to qualitatively retain similar aeroelastic properties with great benefits for the applicability of results.

Flutter and post-flutter regimes, including limit cycle oscillations (LCOs) are studied. A detailed analysis of the energy transfer between fluid and structure is carried out and the areas in which energy is extracted from the fluid are identified, to gain insights on the mechanism leading to the aeroelastic instability.

from an existing design of mobile surfaces on the baseline configuration, freeplay is considered and its effects on the aeroelastic stability properties of the system are investigated.

Both cantilever and free flying configurations are analyzed. Fuselage inertial effects are modeled and the aeroelastic properties studied considering plunging and pitching rigid body modes. For this configuration a positive interaction between elastic and rigid body modes turns the design in a flutter free one (in the range of considered speeds).

To understand the sensitivity of the system and gain insight, fuselage mass and moment of inertia are selectively varied. For a fixed pitching moment of inertia, larger fuselage mass favours the body freedom flutter. When the moment of inertia is varied, a change of critical properties is observed. For smaller values the pitching mode becomes unstable, and coalescence is observed between pitching and first elastic modes. Increasing pitching inertia, the above criticality is posticipated and, in the meanwhile, second elastic mode becomes unstable at progressively lower speeds. For larger inertial values “cantilever” flutter properties, having coalescence of first and second elastic modes, are recovered.
Original languageEnglish
Title of host publication56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages37
ISBN (Electronic)9781624103421
DOIs
Publication statusPublished - 5 Jan 2015
Event56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015 - Kissimmee, United States
Duration: 5 Jan 20159 Jan 2015

Conference

Conference56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015
CountryUnited States
CityKissimmee
Period5/01/159/01/15

Keywords

  • Body Freedom Flutter
  • Freeplay
  • Joined Wings

Fingerprint Dive into the research topics of 'PrandtlPlane Joined Wing: Body Freedom Flutter, Limit Cycle Oscillation and Freeplay Studies'. Together they form a unique fingerprint.

Cite this