A variable camber wing driven by a shape memory alloy cable and its design method

Abstract

The invention discloses a variable-camber wing driven by a shape-memory alloy cable, which comprises a shape-memory alloy flexible driver, a rigid frame at the front end of the wing, a skin, a superelastic flexible flap, a rigid tail and a Kevlar wire; the steps of the design method: (1) Design the shape memory alloy flexible actuator; (2) Select the appropriate wing airfoil; (3) Perform aerodynamic performance simulation on the wing and calculate the driving stroke of the shape memory alloy flexible actuator; (4) Calibrate the parameters of the wing hyperelastic material ; (5) Rigid reinforcement structure design inside the flap; (6) Honeycomb support structure design in the flexible area inside the flap; (7) Assembling different components into a whole. The variable camber wing of the present invention is deformed by a programmable DC stabilized power supply, and is applied to fields such as unmanned aerial vehicles and new energy wind power generator blades; the process control is convenient, the deformation is consistent, and can be adaptively changed according to the use environment.

Description

technical field [0001] The invention relates to a variable camber wing and a design method thereof, in particular to a variable camber wing driven by a shape memory alloy cable and a design method thereof. Background technique [0002] The use of new intelligent driving materials and intelligent structures to drive aircraft deformation has become a promising driving method, which provides new solutions for aircraft design in the fields of military reconnaissance, air strikes, medical rescue, and long-distance transportation. The variable camber wing can change its shape according to the actual flight conditions, thereby optimizing the aerodynamic shape, thereby achieving the goals of increasing lift, reducing drag, and reducing fuel consumption. [0003] The deformation of the wing from the initial state to the target bending state needs to be based on a specific driving structure and driving control conditions. There are two commonly used design methods: [0004] 1) One me...

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Problems solved by technology

However, since the flaps adopt a segmented design as a whole, when the flaps are unfolded, one or more gaps will be formed between the flaps, which will not only affect the aerodynamic performance of the wing surface but also increase the airflow resistance flowing through the flap surface. which in turn affects the fuel economy of the aircraft

[0005] 2) Another method is to use emerging structures or materials such as pneumatic artificial muscles, electroactive polymers, and dielectric elastomers to directly drive the flaps to bend and deform. However, this kind of deformation method also has disadvantages such as complex structural design, high maintenance cost, and poor fatigue life of material cycle deformation.

[0006] To sum up, there are still defects such as low reliability, complex structure and weak aerodynamic performance in various methods of researching the internal structure design of variable camber wings.

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