The adaptive honeycomb structure actuated by pneumatic muscle fibers is proposed in this paper. The FE model of
adaptive honeycomb structure is developed by use of ANSYS software. The elastics modulus of the developed pneumatic muscle fibers is experimentally determined and their output force is tested. The results show that the contraction ratio of the pneumatic muscle fibers with inner diameter of 2mm could reach up to 26.8% and the force could reach to a value of 27N when the applied pressure is 0.4MPa and the contraction ratio is zero. When the adaptive honeycomb has a certain load and an effective output displacement, the applied force must be greater than a certain value. The adaptive honeycomb must be consumed extra energy when the output displacement and force are produced.
The method for analyzing the static aeroelastic deformation of flexible skin under the air loads was developed. The effect
of static aeroelastic deformation of flexible skin on the aerodynamic characteristics of aerofoil and the design parameters
of skin was discussed. Numerical results show that the flexible skin on the upper surface of trailing-edge will bubble
under the air loads and the bubble has a powerful effect on the aerodynamic pressure near the surface of local
deformation. The static aeroelastic deformation of flexible skin significantly affects the aerodynamic characteristics of
aerofoil. At small angle of attack, the drag coefficient increases and the lift coefficient decreases. With the increasing
angle of attack, the effect of flexible skin on the aerodynamic characteristics of aerofoil is smaller and smaller. The
deformation of flexible skin becomes larger and larger with the free-stream velocity increasing. When the free-stream
velocity is greater than a value, both of the deformation of flexible skin and the drag coefficient of aerofoil increase
rapidly. The maximum tensile strain of flexible skin is increased with consideration of the static aeroelastic deformation.
As a novel bionic actuator, pneumatic artificial muscle has high power to weight ratio. In this paper, the experimental
setup to measure the static output force of pneumatic artificial muscle was designed and the relationship between the
static output force and the air pressure was investigated. Experimental result shows the static output force of pneumatic
artificial muscle decreases nonlinearly with increasing contraction ratio. A variable camber wing based on the pneumatic
artificial muscle was developed and the variable camber wing model was manufactured to validate the variable camber
concept. Wind tunnel tests were conducted in the low speed wind tunnel. Experimental result shows that the wing
camber increases with increasing air pressure.
As a novel bionic actuator, pneumatic artificial muscle has high power to weight ratio. In this paper, a variable camber
wing with the pneumatic artificial muscle is developed. Firstly, the experimental setup to measure the static output force
of pneumatic artificial muscle is designed. The relationship between the static output force and the air pressure is
investigated. Experimental result shows the static output force of pneumatic artificial muscle decreases nonlinearly with
increasing contraction ratio. Secondly, the finite element model of the variable camber wing is developed. Numerical
results show that the tip displacement of the trailing-edge increases linearly with increasing external load and limited
with the maximum static output force of pneumatic artificial muscles. Finally, the variable camber wing model is
manufactured to validate the variable camber concept. Experimental result shows that the wing camber increases with
increasing air pressure and that it compare very well with the FEM result.
A new concept of a morphing wing based on shape memory polymer (SMP) and its reinforced composites is proposed in
this paper. SMP used in this study is a thermoset styrene-based resin in contrast to normal thermoplastic SMP. During
heating, the wing curled on the aircraft can be deployed, providing main lift for a morphing aircraft to realize the stable
flight. Aerodynamic characteristics of the deployed morphing wing are calculated by using CFD software. The static
deformation of the wing under the air loads is also analyzed by using the finite element method. The results show that the
used SMP material can provide enough strength and stiffness for the application. Finally, preliminary testing is
conducted to investigate the recovery performances of SMP and its reinforced composites. During the test, the
deployment and the wind-resistant ability of the morphing wing are dramatically improved by adding reinforced phase to
the SMP.
In this paper, a variable camber wing, which comprises a flexible skin, a metal sheet, and a honeycomb structure, is
presented. Shape memory polymer (SMP) is selected for the use of flexible skins. Embedded heating wire springs act as
the activation system for the SMP. Experimental result shows that the inherent separation does not occur between the
heating elements and SMP upon elongation because of elasticity of wire springs. The deformation of SMP skins at
different temperature conditions is analyzed in order to establish the relationship between the deformation of the skin and
pre-strain applied in the SMP skin. Fibre Bragg Grating (FBG) sensors, with flexibility and small size, are bonded on the
surface of the metal sheet to measure the deflection on the some certain points. The relation of the strain on the upper
surface of metal sheet and the deflection of the trailing-edge is established to ensure the position of the bonded FBG
sensors. The curve shape of the bending metal sheet can be reconstructed using the calibration information.
The Macro Fiber Composite (MFC) is an actuator that offers high performance and flexibility. The application of MFC
in the field of driving biomimetic tail is discussed in the paper. Making full use of the d33 effect, a piece of aluminum
lamina with certain thickness is sticked in order to make the structures divided by the PZT fibers in MFC
dissymmetrical. When applying voltage on the MFC, the structure will have a certain bending angle which is utilized to
offer swinging power for the tail. In this paper, the ideal driving effect has been got with the limited driving force via the
study of material property, material thickness, shape and size of the metal piece connected to the MFC, method of
connection, the shape of the under water part of the fish. A reasonable shape and swinging strategy for biomimetic fish is
designed according to the observation to the movement of alive fish and the study of bionics. The results of the
experiment indicate that the largest extend of the tail's swinging angle in the air is 4 degree. The available frequency for
the fastest speed is 2.5Hz. Comparing with the traditional biomimetic fish, it has the advances of small cubage, little
noise, simple structure, and could be controlled in speed and extent because there is no motor inside. And the limit
ability of driving, the uncontrollable feature of floating and sinking, and the existence of the power wires need to be
solved in the coming research.
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