Claims:The scope of the invention is defined by the following claims:

Claim:
1. A layered transforming wing comprising:
a) A corrugated surface (2) is provided to reduce the stiffness of the wing during major loading conditions and it is covered by a layer (4).
b) A hinge support (3) is present at the trailing edge of the wing to withstand deformation without comprising the smoothness of the wing.
c) An actuator-piezoelectric (1) is attached to the corrugated surface (2) to perform the morphing operation.
2. As mentioned in claim 1, reduction of stiffness of the wing allows it to deflect without undergoing plastic deformation.
3. According to claim 1, elastomer matrix material Rhodorsil V.330 CA-35 is used to fabricate the wing structures to withstand stresses and strains. , Description:Field of Invention
The present invention pertains to deflect generate additional lift without using control surfaces like ailerons.
Background of the Invention
The term morphing is nothing but changing the shape of a wing either chord wise or span wise to acquire the desired aerodynamic properties. It means we can change the wing into desired aerodynamic shape to increase the flight performance at different flight phases such as, take off, landing and cruise conditions. The concept of morphing wing has begun by Wright brothers in 1903. They flew the Wright Flyer from Kitty Hawk, North Carolina for 12 seconds and covered distance of 120 feet. The fight involved wing twisting phenomena and this theory was first tested by flying a kite. But this theory has not used in structural applications because morphing wing has flexible wing properties and light weight, this means the wing will easily flutter and plain cannot attend higher speed.
After many years of research, Scientists have studied the bird flight and observed that birds like swift and albatross shows the fascinating aerodynamic properties which can be used in structural applications. Albatross gain energy from wind and can glide for hours over longer distances with its large flexible wings and have minimum drag. Swifts can stay up in air up to 10 months without any rest. Due the smaller Aspect Ratio the maneuverability is high and has a better aerodynamic performance at higher speeds. They also adjust their shape of wings to glide efficiently and make faster turns.
With these many parameters can be developed such as, low fuel consumption, manoeuvrability, carrying capacity, range, durability, maximum speed, stability to increase the flight efficiency and expand the mission profiles. We can also change the wing plane form and its geometric parameters. Yet, none of them has been used in structural applications due to the current technology and less availability of the resources. So, they have entrusted this to the future generations.
For instance, US9856012B2 discloses a morphing wing for an aircraft includes first and second structural ribs with four active members and four passive members connected there between. First and second active members and third and fourth active members attach at first and second positions. The first and third active members and the second and fourth active members attach at third and fourth positions. A first passive member connects between third and fifth positions. A second passive member connects between second and seventh positions. A third passive member connects between fourth and sixth positions. US20190256189A1 discloses Geometric morphing wing with adaptive corrugated structure. An airfoil member includes an airfoil skin, a trailing edge member, a spar member extending in a lateral direction within the airfoil skin, and an airfoil member morphing device configured to modify a shape of the airfoil skin. The device includes at least one motor or actuator, an airfoil skin support sheet attached to the spar member and corrugated to define alternating upper and lower lines of contact with inner surfaces of the rearward upper skin and rearward lower skin.

Summary of the Invention
In light of the mentioned drawbacks in the prior art, the present invention aims to control the production of lift by using layered transforming wing with a new approach i.e., by applying a corrugated portion to the upper surface of the wing.
The specific objective of the invention is to design a layered transforming wing in order to generate additional lift without using control surfaces like ailerons.
A further specific objective of the invention is preventing the production of turbulence formed by corrugated portion by adding a layer and also to alter the limitations of conventional wing.
Brief Description of Drawings
The invention will be described in detail with reference to the exemplary embodiments shown in the figures wherein:
Figure 1 Pictorial representation of layered transforming wing
Detailed Description of the Invention
In order to increase or decrease the camber and deflect the trailing edge we corrugate the surface of the wing. Corrugated wing is a foldable wing with elastic nature and it can undergo compression and expansion at different flight conditions. The wing corrugation provides spanwise bending stiffness, preventing wing to fracture by allowing wing twist and wing camber formation. However, due to the surface irregularity high drag and turbulence is generated. Considering the advantages, the wing will be partially corrugated and we are finding the counter measures to reduce turbulence at the corrugated part.
For the morphing wing, corrugated skin plays a vital role as it has all the desired properties such as flexibility, elasticity etc.
Aerodynamics on the corrugated morphing wing is very complicated as the flow variation takes places easily near corrugated part. Aerodynamic properties change constantly during compression and expansion. The leading edge of the wing is corrugated and the rest of the wing has the rigid property. When the corrugated skin expanded through the trailing edge, the actuators help to deflect the trailing edge up to 10 degrees angle of attack so that the low pressure is generated in the lower surface of the wing which produces lift. And, when the trailing edge is deflected towards the upper surface of wing the negative lift is generated and can be used during stalling conditions. By this varying camber, take-off and landing phases of the flight can be done efficiently. Control surfaces like ailerons are not needed and cl vs. alpha curve will be negative. However, the coefficient of lift will be higher when compared to the normal wing and due to the corrugated part turbulence is generated and the flow get separated which is the major problem the project. Boundary layer gets separated at the leading edge and in order to prevent the negative lift we need to re-energize the boundary layer.
Materials used for the wing should sustain various compressive, tensile, shear, impact loads and can undergo twisting. And there are few materials which meet the requirements. They are, Thermoplastic polyurethanes, Co polyester elastomer, Shape memory polymer, Woven materials made out of elastane yarns, piezoelectric ceramics. These materials have the properties i.e., elastic, flexible, high recovery, resistant to different weather conditions, hardness number is high to handle aerodynamic loads, high energy density, ease to control.
UAV’S showed that the flight control system weight could be reduced by 40% while simultaneously dropping the drag and power consumption. In 2000, by shape memory alloy filaments, the pitch of two different wings could be altered yet they consumed so much power that weight of the power supply doubled.
There are various approaches of wing deformation. Such as, Wing twisting, Camber variation, Platform area variation, Sweep variation, Wing folding. For deformation of wings with significant thickness often requires large control because not only do the air loads provide resistance but also it should overcome the inherent stiffness of the structure. Using ribs and spars imposes stout requirements on the actuators which induce the wing deformation. If conventional actuators were used, this would imply relatively heavy, bulky actuators are needed to induce deformation. Instead of using a design structure with high level of inherent stiffness, a complaint structure can be used to reduce energy. However, a simple mechanism is needed which magnifies both force and deflection while maintaining low weight and power consumption.
3 Claims & 1 Figure