AU2021103223A4

AU2021103223A4 - An adjustable anti-vortex contour wingtip device

Info

Publication number: AU2021103223A4
Application number: AU2021103223A
Authority: AU
Inventors: Asad Ahmed R.; Alex T. Biju; Prasad Virabasavanna Kumbhar; Syam Narayanan S.; Bibin Jino S.; Swetha Shree. J
Original assignee: Technology And Science Hindustan Institute Of; KCG College of Technology
Current assignee: Technology And Science Hindustan Institute Of; KCG College of Technology
Priority date: 2021-06-09
Filing date: 2021-06-09
Publication date: 2022-03-24
Anticipated expiration: 2029-06-09

Abstract

The present invention generally relates to an adjustable anti-vortex contour wingtip device. The device comprises an open coffee cup-like structure body made of 2 way-shape memory alloy; an outer layer of SMA coaxially engaged with an outer side of structure body to be flat at higher temperature and circular at a lower temperature; an inner layer concentrically imposed to an inner side of structure body to be flat at lower temperature and circular at a higher layer; a conical helix strip of SMA fabricated to inner layer to decide direction of the vortex and to adjust strength with the help of pitch of conical helix; an insulator filled in between space of double-layered SMA to transmit force; a pair of Peltier modules placed between layers to provide higher and lower temperatures; and an additional layer connecting structure body and surface of a wing to make it smooth after transformation. 16 'Big IL T 07 LM tu LA. AL

Description

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AL AN ADJUSTABLE ANTI-VORTEX CONTOUR WINGTIP DEVICE FIELD OF THE INVENTION

The present invention relates to an adjustable anti-vortex contour wingtip device. In more details, the present invention relates to an anti icing device at the wingtips.

BACKGROUND OF THE INVENTION

Wind turbines are mechanical energy machines which is used to convert kinetic energy into mechanical energy. This wind turbine can be regarded as a windmill if the mechanical energy directly causes the son to pull water or grind wheat via machinery. Similarly, if mechanical energy is transferred to electrical energy, this equipment is known as a wind-driven generator or wind power plant.

The airfoil (airfoil) of the blade form is used in wind turbines to generate lift and capture power from moving air, which is then delivered to the rotor. At the root end of the rotor, the blade is usually fixed, and it extends radially to the free distal end. The leading edge or front of the blade connects the blade's most front point of air entrance at initially. After the suction face of the blade and the pressure side, the air-flow that is split by the leading edge is united again at the back or trailing edge position of the blade. Along normal air-flow, the chord line is intersected by the leading edge and trailing edge of the direction connection blade of the blade. The term "wing chord" refers to the length of a chord line.

The outboard end of the blade is known as the tip, and the distance from the tip to the root of the blade's opposite end is known as the span (span). Because many blades alter their wing chord from root to tip, the root wing chord is called the root wing chord, and the tip wing chord is called the tip wing chord near the wing chord length the root. When looking perpendicular to the flow direction, the shape of the resultant blade is called wing plane shape (planform).

In one prior art solution (CN101344068B), wind turbine blade tip vortex breakers is disclosed. The present invention relates to a wind turbine blade tip vortex breakers, particularly, a wind turbine includes a tower supporting a drive train with a rotor, at least one blade extending radially from the rotor; and a plurality of substantially flat flaps extending substantially perpendicular from a suction surface of the blade and along different chord lines near a tip of the blade.

In the view of the forgoing discussion, it is clearly portrayed that there is a need to have an adjustable anti-vortex contour wingtip device.

SUMMARY OF THE INVENTION

The present disclosure seeks to provide an adjustable anti-vortex contour wingtip device for increasing aircraft's endurance, range, and fuel efficiency, and protecting against dangers caused by wingtip vortices.

In an embodiment, an adjustable anti-vortex contour wingtip device is disclosed. The device includes an open coffee cup-like structure body made of 2 way-shape memory alloy (SMA). The device further includes an outer layer of shape memory alloy (SMA) coaxially engaged with an outer side of the structure body to be flat at higher temperature and circular at a lower temperature. The device further includes an inner layer concentrically imposed to an inner side of the structure body to be flat at lower temperature and circular at a higher layer. The device further includes a conical helix strip of SMA fabricated to the inner layer to decide direction of the vortex and to adjust strength with the help of pitch of the conical helix. The device further includes an insulator filled in between space of double-layered SMA to transmit force and is able to deform. The device further includes a pair of Peltier modules placed between the inner and outer layers to provide higher and lower temperatures. The device further includes an additional layer connecting the structure body and surface of a wing to make it smooth after transformation.

In an embodiment, the strip is sliced into several small squares so that it doesn't cause any issued during transformation.

In an embodiment, front portion of the structure body is covered with a rubber sheet.

In an embodiment, a two-way shape memory alloy is used that remembers two shapes one at a high temperature and the other at a lower temperature, wherein Peltier module is used to provide the temperatures and SMA offers pseudo plastic properties which minimize creep and fatigue.

In an embodiment, the device further comprises a printed circuit board (PCB) to control the transformation automatically concerning the velocity of the aircraft.

In an embodiment, the device further comprises two phases of operation, classified based on cruise velocity.

In an embodiment, a first phase is a circular phase, which operates below cruise velocity, where induced drag dominates, so this phase's main intention is just to minimize the induced drag.

In an embodiment, wingtip vortices always have a specific direction, so the basic idea is to create a vortex in the counter direction with almost the strength as that of the formed wingtip vortex, wherein headwind due to the relative motion of the aircraft to produce the counter vortex.

In an embodiment, second phase is the flat phase where the parasite drag dominates, there the main concern will be minimizing the parasite drag, to be specific form drag.

In an embodiment, when velocity is less than cruise velocity the device goes in a circular phase once it crosses the cruise velocity the Peltier module heats the upper layer and cools the lower layer, thus the device transforms into a flat structure, and when the velocity is less than cruise velocity the Peltier modules cools the upper layer and heats the lower layer and the device transforms to circular phase.

An object of the present disclosure is to efficiently reduce induced drag by cancelling wingtip vortices with minimal impact on shape drag.

Another object of the present disclosure is to increase the aircraft's endurance, range, and fuel efficiency.

Another object of the present disclosure is to protect against dangers caused by wingtip vortices.

Another object of the present disclosure is to develop anti-icing device for wingtips.

Yet another object of the present invention is to develop expeditious and cost-effective adjustable anti-vortex contour wingtip device.

To further clarify advantages and features of the present disclosure, a more particular description of the invention will be rendered by reference to specific embodiments thereof, which is illustrated in the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. The invention will be described and explained with additional specificity and detail with the accompanying drawings. BRIEF DESCRIPTION OF FIGURES

These and other features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:

Figure 1 illustrates a block diagram of an adjustable anti-vortex contour wingtip device in accordance with an embodiment of the present disclosure; Figure 2 illustrates an intuitive picturization of the circular phase in accordance with an embodiment of the present disclosure; Figure 3 illustrates NX10 CAD - Design in accordance with an embodiment of the present disclosure; Figure 4 illustrates adjustable Anti-Vortex Contour Wingtip internal structure in accordance with an embodiment of the present disclosure; and Figure 5 illustrates transformation stages of Adjustable Anti-Vortex Contour wingtips in accordance with an embodiment of the present disclosure.

Further, skilled artisans will appreciate that elements in the drawings are illustrated for simplicity and may not have necessarily been drawn to scale. For example, the flow charts illustrate the method in terms of the most prominent steps involved to help to improve understanding of aspects of the present disclosure. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the drawings by conventional symbols, and the drawings may show only those specific details that are pertinent to understanding the embodiments of the present disclosure so as not to obscure the drawings with details that will be readily apparent to those of ordinary skill in the art having benefit of the description herein.

DETAILED DESCRIPTION

For the purpose of promoting an understanding of the principles of the invention, reference will now be made to the embodiment illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended, such alterations and further modifications in the illustrated system, and such further applications of the principles of the invention as illustrated therein being contemplated as would normally occur to one skilled in the art to which the invention relates.

It will be understood by those skilled in the art that the foregoing general description and the following detailed description are exemplary and explanatory of the invention and are not intended to be restrictive thereof.

Reference throughout this specification to "an aspect", "another aspect" or similar language means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present disclosure. Thus, appearances of the phrase "in an embodiment", "in another embodiment" and similar language throughout this specification may, but do not necessarily, all refer to the same embodiment.

The terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process or method that comprises a list of steps does not include only those steps but may include other steps not expressly listed or inherent to such process or method. Similarly, one or more devices or sub-systems or elements or structures or components proceeded by "comprises...a" does not, without more constraints, preclude the existence of other devices or other sub-systems or other elements or other structures or other components or additional devices or additional sub-systems or additional elements or additional structures or additional components.

Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The system, methods, and examples provided herein are illustrative only and not intended to be limiting.

Embodiments of the present disclosure will be described below in detail with reference to the accompanying drawings.

Referring to Figure 1, a block diagram of an adjustable anti-vortex contour wingtip device is illustrated in accordance with an embodiment of the present disclosure. The device 100 includes an open coffee cup-like structure body 102 made of 2 way-shape memory alloy (SMA). The body 102 is having two opening i.e. inlet and outlet for air passage.

In an embodiment, an outer layer 104 of shape memory alloy (SMA) is coaxially engaged with an outer side of the structure body 102 to be flat at higher temperature and circular at a lower temperature. The outer layer 104 is having smooth surface which allows air to pass very easily.

In an embodiment, an inner layer 106 is concentrically imposed to an inner side of the structure body 102 to be flat at lower temperature and circular at a higher layer. The inner layer 106 is made up of shape memory alloy (SMA).

In an embodiment, a conical helix strip 108 of SMA is fabricated to the inner layer 106 to decide direction of the vortex and to adjust strength with the help of pitch of the conical helix.

In an embodiment, an insulator 110 is filled in between space of double-layered SMA to transmit force and is able to deform. In an embodiment, a pair of Peltier modules 112 are placed between the inner and outer layer 104 to provide higher and lower temperatures.

In an embodiment, an additional layer 114 is connecting the structure body 102 and surface of a wing to make it smooth after transformation.

In an embodiment, the strip 108 is sliced into several small squares so that it doesn't cause any issued during transformation.

In an embodiment, front portion of the structure body 102 is covered with a rubber sheet.

In an embodiment, a two-way shape memory alloy is used that remembers two shapes one at a high temperature and the other at a lower temperature, wherein Peltier module 112 is used to provide the temperatures and SMA offers pseudo plastic properties which minimize creep and fatigue.

In an embodiment, the device further comprises two phases of operation, classified based on cruise velocity. The device is connected at the distal end of the wings of the flight.

In an embodiment, when velocity is less than cruise velocity the device goes in a circular phase once it crosses the cruise velocity the Peltier module 112 heats the upper layer and cools the lower layer, thus the device transforms into a flat structure, and when the velocity is less than cruise velocity the Peltier modules 112 cools the upper layer and heats the lower layer and the device transforms to circular phase.

Figure 2 illustrates an intuitive picturization of the circular phase in accordance with an embodiment of the present disclosure. The device is a double-layer bottom open coffee cup-like structure made of 2 way-Shape Memory Alloy (SMA). The outer layer 104 of SMA has been programmed to be flat at higher temperature and circular at a lower temperature and the inner layer 106 is programmed to be flat at lower temperature and circular at a higher layer. A conical helix strip 108 made of SMA is attached to the inner layer 106. This strip 108 decides the direction of the vortex and the strength can be adjusted with the help of the pitch of this conical helix. the strip 108 is sliced into several small squares so that it doesn't cause any issued during transformation. Space between the double-layered SMA is filled using an insulator 110, which can deform as well as can transmits force. A pair of Pelitier Modules are placed between the SMA layers to provide higher and lower temperatures. The front portion of the device is covered with a rubber sheet. There is an additional layer 114 connecting the device and the surface of the wing to make it smooth after transformation. We also have programmed PCB to control the transformation automatically concerning the velocity of the aircraft.

Pelitier Module is a device that works under the pelitier effect. It's a type of thermoelectric effect that is observed in an electric circuit, when current is made to flow through a circuit consisting of two different types of conductors, a heating or cooling effect is observed at the junctions between the two materials thus the device produces a very high temperature at one side and a very low temperature at the other side, thus it becomes a perfect device for our purpose.

A two-way shape memory alloy is used that remembers two shapes one at a high temperature and the other at a lower temperature. Peltier module 112 is used to provide these temperatures. We are using SMA because of its pseudoplastic properties which minimize creep and fatigue. And its shape memory effect. No other materials to date can regain the circular structure are effective as shape memory alloys.

Basic working principle:

The device has two phases of operation, classified based on cruise velocity. The first phase is the circular phase, which operates below cruise velocity, where induced drag dominates, so this phase's main intention is just to minimize the induced drag. The wingtip vortices always have a specific direction, so the basic idea is to create a vortex in the counter direction with almost the strength as that of the formed wingtip vortex. The device takes advantage of the headwind due to the relative motion of the aircraft to produce the counter vortex. As the velocity of free stream air is directly proportional to induced drag, we can design the device to produce a counter vortex with almost the same strength as that of the wingtip vortex. Apart from the cancellation of the wingtip vortices, the device will also act like an infinity structure too.

The second phase is the flat phase where the parasite drag dominates, there the main concern will be minimizing the parasite drag, to be specific form drag. For this, we will transform the circular structure into a flat structure with the help of a two-way-Shape memory alloy, Peltier Module 112, and a transformation circuit. And thus, the device minimizes the induced drag with negligible form drag. Figure.1 depicts an inductive picturization of the circular phase.

When the velocity is less than cruise velocity the device will be in a circular phase once it crosses the cruise velocity the Peltier module 112 heats the upper layer and cools the lower layer, thus the device will transform into a flat structure, and when the velocity is less than cruise velocity the Peltier modules 112 cools the upper layer and heats the lower layer and the device will transform to circular phase.

The device ensures maximum cancelation of wingtip vortices and with minimum form drag, thus the endurance and range of the aircraft are improved. The fuel consumption decreases. Averts dangers due to wingtip vortices. Anti-Icing effect at wingtips.

Figure 3 illustrates NX10 CAD - Design in accordance with an embodiment of the present disclosure. Figure 3 illustrates top view and side view of the anti-vortex contour wingtip. Figure 3b shows the placement of the anti-vortex contour wingtip device.

Figure 4 illustrates adjustable Anti-Vortex Contour Wingtip internal structure in accordance with an embodiment of the present disclosure. Material of internal surface and external surface is same, but the material of spiral is different from that of the internal surface and external surface.

Figure 5 illustrates transformation stages of Adjustable Anti-Vortex Contour wingtips in accordance with an embodiment of the present disclosure. Figure 5a shows two states of the device, wherein the two states are circular state and flat state. The circular state helps the flight to generate a thrust opposite to the direction of flying in order to slow down the speed of the flight. The flat state promotes the flying of the flight without any oppose. When the velocity is less than cruise velocity the device will be in a circular state, once it crosses the cruise velocity the Peltier module 112 heats the upper layer and cools the lower layer, thus the device will transform into a flat structure, and when the velocity is less than cruise velocity the Peltier modules 112 cools the upper layer and heats the lower layer and the device will transform to circular phase.

Figure 5b shows circuit diagram of the device. A battery is connected with the PCB and Peltier module 112 is connected in series with the battery. Data of velocity of air craft is stored in the control unit which is connected with the PCB.

The drawings and the forgoing description give examples of embodiments. Those skilled in the art will appreciate that one or more of the described elements may well be combined into a single functional element. Alternatively, certain elements may be split into multiple functional elements. Elements from one embodiment may be added to another embodiment. For example, orders of processes described herein may be changed and are not limited to the manner described herein. Moreover, the actions of any flow diagram need not be implemented in the order shown; nor do all of the acts necessarily need to be performed. Also, those acts that are not dependent on other acts may be performed in parallel with the other acts. The scope of embodiments is by no means limited by these specific examples. Numerous variations, whether explicitly given in the specification or not, such as differences in structure, dimension, and use of material, are possible. The scope of embodiments is at least as broad as given by the following claims.

Benefits, other advantages, and solutions to problems have been described above with regard to specific embodiments. However, the benefits, advantages, solutions to problems, and any component(s) that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as a critical, required, or essential feature or component of any or all the claims.

Claims

WE CLAIM

1. An adjustable anti-vortex contour wingtip device, the device comprises: an open coffee cup-like structure body made of 2 way-shape memory alloy (SMA); an outer layer of shape memory alloy (SMA) coaxially engaged with an outer side of the structure body to be flat at higher temperature and circular at a lower temperature; an inner layer concentrically imposed to an inner side of the structure body to be flat at lower temperature and circular at a higher layer; a conical helix strip of SMA fabricated to the inner layer to decide direction of the vortex and to adjust strength with the help of pitch of the conical helix; an insulator filled in between space of double-layered SMA to transmit force and is able to deform; a pair of Peltier modules placed between the inner and outer layers to provide higher and lower temperatures; and an additional layer connecting the structure body and surface of a wing to make it smooth after transformation.

2. The device as claimed in claim 1, wherein the strip is sliced into several small squares so that it doesn't cause any issued during transformation.

3. The device as claimed in claim 1, wherein front portion of the structure body is covered with a rubber sheet.

4. The device as claimed in claim 1, wherein a two-way shape memory alloy is used that remembers two shapes one at a high temperature and the other at a lower temperature, wherein Peltier module is used to provide the temperatures and SMA offers pseudoplastic properties which minimize creep and fatigue.

5. The device as claimed in claim 1, comprises a printed circuit board (PCB) to control the transformation automatically concerning the velocity of the aircraft.

6. The device as claimed in claim 1, comprises two phases of operation, classified based on cruise velocity.

7. The device as claimed in claim 1, wherein a first phase is a circular phase, which operates below cruise velocity, where induced drag dominates, so this phase's main intention is just to minimize the induced drag.

8. The device as claimed in claim 1, wherein wingtip vortices always have a specific direction, so the basic idea is to create a vortex in the counter direction with almost the strength as that of the formed wingtip vortex, wherein headwind due to the relative motion of the aircraft to produce the counter vortex.

9. The device as claimed in claim 1, wherein second phase is the flat phase where the parasite drag dominates, there the main concern will be minimizing the parasite drag, to be specific form drag.

10. The device as claimed in claim 1, wherein when velocity is less than cruise velocity the device goes in a circular phase once it crosses the cruise velocity the Peltier module heats the upper layer and cools the lower layer, thus the device transforms into a flat structure, and when the velocity is less than cruise velocity the Peltier modules cools the upper layer and heats the lower layer and the device transforms to circular phase.

Figure 2

Figure 4