Structural and mechanism design of an active trailing-edge flap blade

Lee, Jae‐Hwan; Natarajan, Balakumaran; Eun, WonJong; Viswamurthy, Sathyamangalam Ramanarayanan; Park, Jae-Sang; Kim, Taeseong; Shin, Sang Joon

doi:10.1007/s12206-013-0704-8

Cited by 9 publications

(7 citation statements)

References 9 publications

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“…Amplified Piezoelectric Actuators (APA) manufactured by CEDRAT technologies [13] represent an attractive option for the rotorcraft application [11], [12]. Although the actuator strokes are limited, the higher force and frequency requirements are well covered by such actuators [13].…”

Section: Actuator Selectionmentioning

confidence: 99%

Preliminary Design of a TE Morphing Surface for Rotorcraft

Zahoor

Breuker

Voskuijl

2020

AIAA Scitech 2020 Forum

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This paper presents an overview of the preliminary design process and findings aimed at morphing of trailing edge (TE) control surfaces for rotorcraft. A design methodology for a camber morphing control surface is presented, although twist can also be induced by applying differential camber of the morphing section span. The concept investigated relies on utilizing conventional aircraft structures and materials for morphing purposes; thus, in essence, has the potential to fulfil the conflicting requirements of lightweight, flexibility and strength at the same time. Based on this concept, the preliminary design work shows that an active trailing edge camber morphing mechanism can be designed after careful considerations of design and actuation requirements. The numerical results presented also indicate that such a morphing scheme increases the 2D aerodynamic efficiency.

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Section: Actuator Selectionmentioning

confidence: 99%

Preliminary Design of a TE Morphing Surface for Rotorcraft

Zahoor

Breuker

Voskuijl

2020

AIAA Scitech 2020 Forum

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“…The total piezoelectric strain of APA1000L generated by an electric field is expressed in Eq. (2). Using this equation, equivalent thermal expansion coefficient and equivalent temperature were obtained as follows.…”

Section: Static Load Analysis For the Actuatormentioning

confidence: 99%

“…The most widespread methods are bifilar absorbers, placed between the main rotor and the fuselage, or hydraulic control systems which generate vibrations on the fuselage aiming at eliminating the primary vibratory loads. The methods mentioned above, along with a noticeable increase in overall weight, are not capable of promptly responding to changes in flight conditions [2].…”

Section: Introductionmentioning

confidence: 99%

Design Improvements of Smart Active Trailing-edge Flap for Rotating Test

Kang

Eun

Lim

et al. 2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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In this paper, small-scaled blade prototypes with the flap-driving mechanism, called SNUF (Seoul National University Flap), were manufactured, and tested in order to realize vibratory load reduction in the rotor system. It was achieved by an active trailing-edge flap which is based on piezoelectric actuator. However, it turned out that the target value of the flap deflection angle was not accomplished in the previous designs. Therefore, the flap driving mechanism needs to be amended. Thus, a new piezoelectric actuator was selected to achieve the target deflection by considering the nonlinear relationship between flap deflection angle and the moment arm length. Re-selection of the actuator required increase of the blade inner space and its size. Therefore, it was required to validate the cross-sectional design of the improved blade configuration. So as to verify the structural integrity, crosssectional analysis was conducted by using UM/VABS. After achieving a satisfactory result of the non-rotating static test of the new flap-driving mechanism, a prototype blade will be manufactured and tested in the whirl tower.

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“…1 Benefiting from the rapid development of smart materials, active plain trailing-edge flaps emerged and provided a feasible solution for blade pitch controls as well as helicopter vibration and noise suppression. 2 In addition, rotorcraft engineers have proposed a number of concepts of actively controlled rotor such as Active Twist Rotor (ATR), 3,4 Active Flap Rotor (AFR), 5,6 Individual Blade Control (IBC) of rotor. [7][8][9] For the concepts above, the actuation systems are all installed in the rotating frame, so that an auxiliary slip ring of intensive maintenance and low reliability will be necessary for power transformation.…”

Section: Introductionmentioning

confidence: 99%

Dynamics research on actively controlled swashplateless rotor

Jin

Liu

Yang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study presents the design, dynamic model, and dynamics research of a new cyclic pitch control strategy in motor-driven rotorcraft. In this strategy, the control response and flapping feature of conventional rotor systems can be obtained by imposing (1) a lag-pitch coupling on rotor blade and (2) an additional sinusoidal rotational speed of rotor shaft without any actuators or swashplate. This study establishes a refined nonlinear dynamic model including the effects of pitch motion, and figures out the fundamental dynamic characteristics of this novel configuration. Analyses of its mechanical stability, dynamic responses and stability in hover are also conducted. The model in this research, compared with the previous linear model, improves the predicting accuracies of dynamic responses remarkably. A preliminary understanding of this novel rotor's dynamic mechanisms is gained by this study.

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Structural and mechanism design of an active trailing-edge flap blade

Cited by 9 publications

References 9 publications

Preliminary Design of a TE Morphing Surface for Rotorcraft

Preliminary Design of a TE Morphing Surface for Rotorcraft

Design Improvements of Smart Active Trailing-edge Flap for Rotating Test

Dynamics research on actively controlled swashplateless rotor

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