Shape control of a morphing structure (rotor blade) using a shape memory alloy actuator system

Wind Tunnel tests of a NiTinol based actuator have been conducted for the reconfigurable rotor blade program. The purpose of the test was to demonstrate the potential to improve rotorcraft performance by optimizing the configuration of major structures in flight. The actuator is integrated into the rotor blade as a structural element controlling blade twist. A three-blade scale rotor was tested in a Boeing wind tunnel. The tests validated actuator design and performance by demonstrating simultaneous blade twist and control of twist position over the entire test matrix. A description of system requirements and compromises associated with the actuator and its integration into the rotor blade are provided and discussed. Test results showed that the RRB actuators were able to successfully twist the blade, control the twist between one twist state and the other, and simultaneously control three rotor blades to change state within two seconds of each other despite unanticipated electrical noise in the system.

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“…A more detailed discussion of the control system design and testing is the subject of a separate paper [3] .…”

Section: Condenser Thermosyphon Heat Finmentioning

confidence: 99%

Development of a ¼-scale NiTinol actuator for reconfigurable structures

Arbogast

Ruggeri

Bussom

2008

Industrial and Commercial Applications of Smart Structures Technologies 2008

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“…Specific examples are single (10)(11)(12) or segmented (13,14) morphing trailing edges to control the lift produced by the profile, a morphing leading edge to increase the lift-to-drag ratio (15) , a morphing wingtip to improve manoeuvrability (16) , a composite flexible extrados designed for subsonic cruise flight conditions (17,18) , a variable-sweep wing controlled by SMA ribbons on the spar (19) and a variable-camber wing with SMA torsion tubes and wires (20) . There has also been significant research in rotorcraft technology with SMAs, including rotor blade twisting and tip morphing (21)(22)(23)(24) . A global optimisation study was carried out in Ref.…”

Section: Introductionmentioning

confidence: 99%

Development of an actuated corrugated laminate for morphing structures

et al. 2020

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This paper presents the design, manufacturing and experimental assessment of a morphing element consisting of a composite corrugated panel that hosts a diffused actuation system based on Shape Memory Alloy (SMA) actuators. The characterisation of the SMA actuators is reported and the system performance is predicted through an analytical model and finite element analyses. Two versions of the actuated system are proposed, with different methods for the physical integration of the SMA wires into the composite part. Manufacturing and testing of specimens with different wire densities are reported. Correlation with experiments validates the analytical and numerical approaches adopted for the design and analyses. The results confirm the potential of the concept proposed for developing corrugated panels that can be contracted in a predefined direction by a load-bearing actuation system, but still retain high stiffness and strength properties in other directions.

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“…It was determined that the heat treatment of the torque tube influences the actuation behaviour. An active twist rotor blade made of shape memory alloys was tested by Bushnell et al [12]. Pagano et al [13] developed a twist morphing concept for a helicopter rotor blade based on using a SMA rod.…”

Section: Introductionmentioning

confidence: 99%

Lag-twist coupling sensitivity and design for a composite blade cross-section with D-spar

Amoozgar

Shaw

Zhang

et al. 2019

Aerospace Science and Technology

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In this paper, the effect of various parameters of a specific rotor blade cross-section on the effectiveness of a twist morphing concept is investigated. Then, by considering different constraints, a cross-section consistent with this morphing concept with high lag-twist coupling and low extension-twist, is developed. This lag bending-torsion coupling is used to change the twist of the blade during the flight, while the high values of extension-twist coupling is avoided. To this end, a concentrated mass is added to the blade, where its chordwise location varies in flight. When the mass moves in the chordwise direction, a local lag bending is introduced into the blade. This in-plane bending moment then changes the blade twist distribution through lag-twist coupling induced through stiffness tailoring in the blade cross-section. Therefore, this coupling plays an important role in this morphing concept. The one-dimensional dynamics of the blade is modelled by using the geometrically exact fully intrinsic bean equations while the 2D crosssectional stiffness values are determined by using the VABS software. First, a blade which resembles the BO-105 main rotor blade in the fundamental frequencies is designed. Then, the effect of various parameters of the crosssection on the fundamental frequencies, the lag-twist coupling, and the extension-twist coupling are determined. It is found that the skin of the spar has the highest contribution to both the extension-twist and the lag-twist coupling. Finally, a cross-section compatible with the proposed morphing concept is designed and it is demonstrated that the twist of the blade may be changed significantly.

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Shape control of a morphing structure (rotor blade) using a shape memory alloy actuator system

Cited by 14 publications

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Development of a ¼-scale NiTinol actuator for reconfigurable structures

Development of a ¼-scale NiTinol actuator for reconfigurable structures

Development of an actuated corrugated laminate for morphing structures

Lag-twist coupling sensitivity and design for a composite blade cross-section with D-spar

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