This is a proposal for a research project that aims to fulfil the objectives as set up in the Call SP1-JTI-CS-2013-01-GRA-02-023. Therefore, will investigate advanced design and simulation methods for Load control and alleviation devices and high lift devices. The research will focus on novel methods for modelling of aerodynamic loads on flexible bodies, modelling of actuators and methods for coupled simulation. The novel methods will be evaluated in context of preliminary and detailed design studies of 4 mechanisms as specified in the call:
- Krueger Flap (GTF)
- Single Slotted Flap (GTF)
- LC&A devices
- Single Slotted Flap (TP)
NOVOTECH will be responsible for the preliminary design studies and knowledge transfer. LMS will be responsible for the detailed conceptual designs and management of the project.
The ASAM research project has investigated advanced design and simulation methods for load control and alleviation devices and high lift devices. The research focussed on novel methods for modelling of aerodynamic loads on flexible bodies, modelling of actuators and methods for concept configuration. Also, a method for sizing of composite structures has been established. Therefore, multi-body simulation tools have been extended and a composite structural sizing method has been developed.
The novel methods have been evaluated by preliminary and detailed conceptual design studies of 3 mechanisms, Krueger Flap, Single Slotted flap and load control and alleviation devices, for a Geared Turbo Fan regional aircraft. The load control and alleviation devices were a split aileron and mini tabs at trailing edge of the Single Slotted flaps. For each of these mechanisms, a preliminary design study and a detailed design has been performed. The preliminary design study performed the definition of the mechanism and actuation kinematics. The detailed design included the structural sizing of the flaps in unidirectional composite materials and sizing of other metal parts such as hinges, actuator supports and flap tracks. Integration of the mechanisms in the wing structure was also considered.
The design of the Single Slotted flaps of the Turbo-Prop aircraft was not performed due to unavailability of the required input data.