PatSeer

SEMI-FLEXIBLE SIMULTANEOUS DUAL MOTION FOLDABLE WING MECHANISM FOR GLIDERS
Pub. No. IN201711017091A
App. No. IN201711017091
App. No. Original IN201711017091
Appl. Date 16-May-2017
Pub. Date 23-Nov-2018
Inventor(s) DR, DR PARAS CHAWLA, DR RAJDEEP SINGH, MR DIWAKAR SINGH, MR SANKET SHARMA, MR SAHIL SHARMA, MR UDISH KAPOOR, MR HITESH VOHRA, MS MINAL PARMAR, MR CHETAN CHADHA, MS TANVI KAKKAR
Assignee Norm. CHANDIGARH GROUP OF COLLEGES (LANDRAN KHARARBANUR ROAD SECTOR 112 GREATER MOHALI PUNJAB 140307 (INDIA) PUNJAB INDIA, IN)
Current Assignee CHANDIGARH GROUP OF COLLEGES (LANDRAN KHARARBANUR ROAD SECTOR 112 GREATER MOHALI PUNJAB 140307 (INDIA) PUNJAB INDIA, IN)
Current Owner CHANDIGARH GROUP OF COLLEGES
IPC G01M9/06
ABSTRACT
Disclosed is an aerial vehicle comprising a body and a wing arrangement coupled to said body of said aerial vehicle. The wing arrangement comprises a pair of first links and a pair of second links, a pair of rollable pins to connect said pair of first links to said body of said aerial vehicle, a pair of first elastic cords coupled to said pair of first links and said body of said aerial vehicle, and a pair of second elastic cords coupled to said pair of second links and said body of said aerial vehicle. Furthermore, said pair of first elastic cords and said pair of second elastic cords provides a folding and unfolding mechanism to said pair of first links and said pair of second links of said arrangement. Fig. 1 for Abstract Dated this 16th day of May 2017 SARASIJA IN/PA/1803_____ Agent for the Applicant

CLAIMS

1. An aerial vehicle comprising: a body; and a wing arrangement coupled to said body of said aerial vehicle, said wing arrangement comprising: a pair of first links and a pair of second links, wherein a second link of said pair of second links is pivotally arranged on a first link of said pair of first links; a pair of rollable pins to connect said pair of first links to said body of said aerial vehicle; a pair of first elastic cords coupled to said pair of first links and said body of said aerial vehicle; and a pair of second elastic cords coupled to said pair of second links and said body of said aerial vehicle, wherein said pair of first elastic cords and said pair of second elastic cords provides a folding and unfolding mechanism to said pair of first links and said pair of second links of said arrangement.

2. An aerial vehicle as claimed in claim 1, wherein said wings arrangement of said aerial vehicle is operable to fold in a transverse direction to the body of said aerial vehicle.

3. An aerial vehicle as claimed in claim 1, wherein said wing arrangement further comprises a spring to unfold said wing arrangement.

4. An aerial vehicle as claimed in claim 3, wherein said spring of said wing arrangement is a spiral spring.

5. An aerial vehicle as claimed in claim 1, wherein said wing arrangement further comprises a plurality of third link. 13.

6. An aerial vehicle as claimed in claim 5, wherein said third link is angularly coupled to said pair of second link of said wing arrangement.

7. An aerial vehicle as claimed in claim 5, wherein said third link of said wing arrangement is an adjustable link.

8. An aerial vehicle as claimed in claim 1, wherein said wing arrangement is a self unfolding arrangement.

9. An aerial vehicle as claimed in claim 1, wherein said wings of said aerial vehicle is made of flexible sheets.

10. An aerial vehicle as claimed in claim 1, wherein said aerial vehicle is a glider.


DESCRIPTION
FIELD OF THE INVENTION The present disclosure relates to the aerial vehicle, and more particularly, embodiments of the disclosure relate to a wing arrangement for aerial vehicles.

BACKGROUND OF THE INVENTION

Aerodynamic vehicles, such as unmanned aerial vehicles such as a glider, include design parameters that are configured to provide the necessary lift and control to overcome the drag and weight of a vehicle during flight. A glider is often recognized as a small plane. A glider is heavier than aero-plane that is supported in flight by the dynamic reaction of the air against its lifting surfaces, and whose free flight does not depend on an engine. Most gliders do not have an engine, although motor-gliders have small engines for extending their flight. Gliders are aerodynamically streamlined and are capable of soaring in rising air. Gliders have wide application across the world; they are very popular in air sports of gliding, hang gliding and paragliding.

Conventionally, the wings of a glider have an aerofoil shape and a continuous structure. Such structure often causes problems for the glider to attain a stable flight path. Further, due to the wing structure of a conventional glider, they are often cumbersome to carry around and cannot fit into a compact storage structure. Moreover, the materials used in the construction of the glider often restrict an unmanned glider, operating without an engine, to fly more efficiently.

Therefore, in light of the foregoing discussion, there exist problems associated with conventional aerial vehicles such as gliders.

OBJECT OF THE INVENTION The principal object of the present invention is to provide an adjustable passive wings arrangement of an aerial vehicle which is sensitive and smart to its surroundings and adapt itself simultaneously to add stability to the flight. Another object of the present invention is to provide a wing arrangement having a dual degree of freedom which allows the wing arrangement to be more compact

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when folded, and an increased wingspan when in a unfolded state.

Another object of the present invention is to provide an aerial vehicle with reduced weight and simple structure. The foregoing and other objects, features and advantages of the present invention will become readily apparent upon further review of the following detailed description of the preferred embodiment as illustrated in the accompanying drawings. SUMMARY OF THE INVENTION The present disclosure relates to a wing arrangement of an aerial vehicle.

According to an embodiment of the present disclosure, there is provided an aerial vehicle comprising:

a body; and

a wing arrangement coupled to said body of said aerial vehicle, said wing arrangement comprising:

a pair of first links and a pair of second links, wherein a second link of said pair of second links is pivotally arranged on a first link of said pair of first links;

a pair of rollable pins to connect said pair of first links to said body of said aerial vehicle;

a pair of first elastic cords coupled to said pair of first links and said body of said aerial vehicle; and

a pair of second elastic cords coupled to said pair of second links and said body of said aerial vehicle,

wherein said pair of first elastic cords and said pair of second elastic cords provides a folding and unfolding mechanism to said pair of first links and said pair of second links of said arrangement.

According to a further embodiment of the present invention, said wings arrangement of said aerial vehicle is operable to fold in a transverse direction to the body of said aerial vehicle.

According to an embodiment of the present invention, said wing arrangement further comprises a spring to unfold said wing arrangement.

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According to an embodiment of the present invention, said spring of said wing arrangement is a spiral spring.

According to a further embodiment of the present invention, said wing arrangement further comprises a plurality of third link.

According to an embodiment of the present invention, said third link is angularly coupled to said pair of second link of said wing arrangement.

According to an embodiment of the present invention, said third link of said wing arrangement is an adjustable link.

According to an embodiment of the present invention, said wing arrangement is a self unfolding arrangement.

According to an embodiment of the present invention, said wings of said aerial vehicle is made of flexible sheets.

According to an embodiment of the present invention, said aerial vehicle is a glider.

Embodiments of the present disclosure substantially eliminate or at least partially address the aforementioned problems in the prior art, and provides a foldable and a compact aerial vehicle.

Additional aspects, advantages, features and objects of the present disclosure would be made apparent from the drawings and the detailed description of the illustrative embodiments construed in conjunction with the appended claims that follow.

It will be appreciated that features of the present disclosure are susceptible to being combined in various combinations without departing from the scope of the present disclosure as defined by the appended claims. BRIEF DESCRIPTION OF DRAWINGS

The summary above, as well as the following detailed description of illustrative embodiments, is better understood when read in conjunction with the appended drawings. For the purpose of illustrating the present disclosure, exemplary constructions of the disclosure are shown in the drawings. However, the present disclosure is not limited to specific instrumentalities disclosed herein. Moreover,

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those in the art will understand that the drawings are not to scale. Wherever possible, like elements have been indicated by identical numbers.

Embodiments of the present disclosure will now be described, by way of example only, with reference to the following diagrams wherein:

FIG.1 illustrates a schematic illustration of an aerial vehicle, in accordance with an embodiment of the present disclosure;

FIG.2 illustrates a schematic illustration of an aerial vehicle with folded wing arrangement, in accordance with an embodiment of the present disclosure; and

FIG.3 illustrates a schematic illustration of an aerial vehicle with unfolded wing arrangement, in accordance with an embodiment of the present disclosure.

DETAILED DESCRIPTION

As required, detailed embodiments of the present invention are disclosed herein; however, it is to be understood that the disclosed embodiments are merely exemplary of the invention which may be embodied in various forms. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present invention in virtually any appropriately detailed structure.

Various other objects, advantages, and features of the invention will become more readily apparent to those skilled in the art from the following detailed description when read in conjunction with the accompanying drawings, in which like reference numerals designate like parts throughout the figures thereof.

Modifications to embodiments of the present disclosure described in the foregoing are possible without departing from the scope of the present disclosure as defined by the accompanying claims. Expressions such as “including”, “comprising”, “incorporating”, “have”, “is” used to describe and claim the present disclosure are intended to be construed in a non-exclusive manner, namely allowing for items, components or elements not explicitly described also to be present. Reference to the singular is also to be construed to relate to the plural.

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In one aspect, an embodiment of the present disclosure provides an arrangement for unfolding a wing of a small or medium sized glider. The arrangement for unfolding a wing is a self unfolding mechanism.

In one aspect, an embodiment of the present disclosure provides an aerial vehicle comprising:

a body; and

a wing arrangement coupled to said body of said aerial vehicle, said wing arrangement comprising:

a pair of first links and a pair of second links, wherein a second link of said pair of second links is pivotally arranged on a first link of said pair of first links;

a pair of rollable pins to connect said pair of first links to said body of said aerial vehicle;

a pair of first elastic cords coupled to said pair of first links and said body of said aerial vehicle; and

a pair of second elastic cords coupled to said pair of second links and said body of said aerial vehicle,

wherein said pair of first elastic cords and said pair of second elastic cords provides a folding and unfolding mechanism to said pair of first links and said pair of second links of said arrangement.

With reference to the drawings specifically to FIG.1, illustrates a schematic illustration of an aerial vehicle 01, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises a body 02, an wing arrangement 03, a pair of first links 04, 05 and a pair of second links 06, 07, a pair of rollable pins 08, 09, a pair of first elastic cords 10, 11, a pair of second elastic cords 12, 13, and a plurality of third link 14-17.

According to an embodiment, the aerial vehicle 01 is a science vehicle, for example, a payload used in planetary missions to collect atmospheric or geographic data. Specifically, the aerial vehicle 01 is a glider. Furthermore, the aerial vehicle 01 is a convertible glider, wherein the wing arrangement 03 attached to the body 02 of the aerial vehicle 01 is foldable. Additionally, the aerial vehicle 01 can be confined to a minimum space and allow a large wing span that helps in gliding without the

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use of proper aerofoil shape of wings. Moreover, the wing arrangement 03 of the aerial vehicle 01 comprises a particular number of restoring elements, such as the first elastic cords 10, 11, and the second elastic cords 12, 13 and spiral spring. Furthermore, the wing arrangement 03 of the aerial vehicle 01 is a self unfolding arrangement. Specifically, the restoring elements unfold the self-locking arrangement.

According to an embodiment, the pair of first links 04, 05 and the pair of second links 06, 07 of the wing arrangement 03 is arranged pivotally with each other. Specifically, the second link 06 of the wing arrangement 03 is arranged pivotally with the first links 04 and the second link 07 of the wing arrangement 03 is arranged pivotally with the first links 05. Furthermore, the pair of first links 04, 05 and the pair of second links 06, 07 is arranged pivotally with each other to provide a pivotal motion. In an embodiment, the pair of first links 04, 05 and the pair of second links 06, 07 of the wing arrangement 03 may be made of materials that are light weight and durable. In an example, the materials may be wood, metal, alloys, other composite materials such as glass, carbon fiber, aramid fibers, etc. In an embodiment, the length of the pair of first links 04, 05 may be lesser than the length of the pair of second links 06, 07. Furthermore, the portion of the first links 04, 05 wherein the second links 06, 07 are coupled, comprises is flexible/adjustable to provide a degree of freedom for the pivotal motion of the pair of second links 06, 07.

According to an embodiment, the pair of first links 04, 05 is connected to the body 02 of the aerial vehicle 01 via a pair of rollable pins 08, 09. Specifically, first links 04 of the wing arrangement 03 is coupled to the body 02 of the aerial vehicle 01 via the rollable pin 08 and the first links 05 of the wing arrangement 03 is coupled to the body 02 of the aerial vehicle 01 via the rollable pin 09.

In an embodiment, the pair of first links 04, 05 is coupled to the the body 02 of the aerial vehicle 01 via a pair of first elastic cords 10, 11. Specifically, the first elastic cord 10 is positioned between the first links 04 and the body 02 of the aerial vehicle 01 and the first elastic cord 11 is positioned between the first links 05 and the body 02 of the aerial vehicle 01. Furthermore, the first elastic cords 10, 11 may comprise of various shapes, sizes, and elasticity. Additionally, the first elastic cords 10, 11

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may be elastic shock cord, a rope, or a cable. Moreover, the first elastic cords 10, 11 may be a braided cord of cotton, nylon, polyester, polypropylene and so forth.

In an embodiment, the pair of second links 06, 07 is coupled to the the body 02 of the aerial vehicle 01 via a pair of second elastic cords 12, 13. Specifically, the second elastic cord 12 is positioned between the second link 06 and the body 02 of the aerial vehicle 01 and the second elastic cord 13 is positioned between the second link 07 and the body 02 of the aerial vehicle 01. Furthermore, the second elastic cords 12, 13 may comprise of various shapes, sizes and elasticity. Additionally, the second elastic cords 12, 13 may be elastic shock cord, a rope, or a cable. Moreover, the second elastic cords 12, 13 may be a braided cord of cotton, nylon, polyester, polypropylene and so forth.

Furthermore, the wing arrangement 03 is a semi-flexible wing structure. Moreover, the pair of first links 04, 05 on both sides of the body 02 of the aerial vehicle 01 are in direct contact with the pair of first elastic cords 10, 11 and operate simultaneously relative to glider body. Moreover, the pair of first elastic cords 10, 11 and the pair of second elastic cords 12, 13 provides a folding and unfolding mechanism to the pair of first links 04, 05 and the pair of second links 06, 07 of the wing arrangement 03.

In an embodiment, the wing arrangement 03 further comprises of a plurality of third link 14 – 17. Furthermore, the third links 14 – 17 are angularly coupled to the pair of second links 06, 07 of said wing arrangement 03. Moreover, the third links 14 – 17 are adjustable link. Additionally, the adjustable links 14 – 17 are operable to perform a pivotal motion to maneuver the flight path of the aerial vehicle 01.

With reference to the drawings specifically to FIG.2, illustrates a schematic illustration of an aerial vehicle 01 with folded wing arrangement 03, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises the body 02, the wing arrangement 03, the pair of first links 04, 05 and the pair of second links 06, 07, the pair of first elastic cords 10, 11, the pair of second elastic cords 12, 13, the plurality of third link 14-17 and a spring 18.

According to an embodiment, the spring 18 is located between the pair of first links 04, 05 of the wing arrangement 03 of the aerial vehicle 01. Furthermore, the spring

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18 is operable to unfold said wing arrangement 03. The spring 18 is a spiral spring. In an embodiment, the spring 18 may be torsion springs with its ends extending away from the spring in a non-helical shape. Moreover, the spring 18 is compressed to store potential energy. Additionally, the spring 18 may comprise of various shapes, sizes and elasticity. Furthermore, the spring 18 is used to unfold the wing which may be compressed in a transverse direction to the body 02 of said aerial vehicle 01.

In an embodiment, the pair of first links 04, 05 and the pair of second links 06, 07 is placed on either side of the body 02 of the aerial vehicle 01. In an embodiment, the folded condition of the wing arrangement 03 renders the pair of first elastic cords 10, 11 and the spring 18 in a stretched condition, and the pair of second elastic cords 12, 13 is in a relaxed condition. Furthermore, the aerial vehicle 01 needs to be folded manually and placed in the container. Moreover, the wing arrangement 03, stored in the folded condition may store a considerable amount of force and/or tension stored in the pair of first elastic cords 10, 11 and the spring 18. Furthermore, the tension stored in the pair of first elastic cords 10, 11 and the spring 18 tends to unfold. Therefore the aerial vehicle 01, in an unfolded condition, is placed in a container for storing purposes, the pair of second links 06, 07 presses against the wall of the container. Thus the wing arrangement 03 unfolds itself by using the tension stored in the pair of first elastic cords 10, 11 and the spring 18, when the aerial vehicle 01 is released from the container. Furthermore, the wing arrangement may release itself in both lateral and transverse direction. Moreover, the pair of second elastic cords 12, 13 stretches by the movement of the pair of second links 06, 07, which is moved by the movement of the pair of first links 04, 05 caused by the release of tension stored in the pair of first elastic cords 10, 11 and the spring 18. In an embodiment, the unfolding of the wing arrangement 03 of the aerial vehicle 01 will need approximately 0.5 to 0.75 sec

In an embodiment, the pair of second links 06, 07 tries to resist further motion after a desired point and the wing arrangement 03 get locked in its fully opened position as any further motion is restricted in all directions by the combined effect of all the restoring elements.

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With reference to the drawings specifically to FIG.3, illustrates a schematic illustration of an aerial vehicle 01 with unfolded wing arrangement 03, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises the body 02, the wing arrangement 03, the pair of first links 04, 05, the pair of second links 06, 07, the plurality of third link 14-17 and wing profile 19.

In an embodiment, the wing profile 19 of the wing arrangement 03 is made of flexible sheets. Furthermore, the wing profile 19 of the wing arrangement 03 may have a flat shape. Additionally, the flat shape of the wing profile 19 of the wing arrangement 03 provides a reduced mass and provides ease of designing and manufacturing the aerial vehicle 01.

In an embodiment, the aerial vehicle 01, the wing arrangement 03 is an adjustable arrangement which can be operated by the action of links such as the pair of first links 04, 05 and the pair of second links 06, 07. Furthermore, the action of links is operated by the action of force restored in elastic cords such as the pair of first elastic cords 10, 11 and the pair of second elastic cords 12, 13, and spring 18 attached to the links and the body 02. Further, as the wing profile 19 is made of flexible sheets and the aforesaid architecture of the wing arrangement 03 a degree of flexibility is attained. Therefore, the links may rotate and twist. In an embodiment, the links may twist by 8 to 10 degrees as a whole or ± 4 to 5 degrees from normal plane/ axis of the body 02 of the aerial vehicle 01. Therefore, the aerial vehicle 01 may be efficient to encounter the problems during the flight caused due to the in-appropriate angle of attack during deploy, turbulence, variable air currents, and air flow, etc. and maintain the stability of glider hence increase the glide ratio and decrease chances of unpredictable stalled flight.

In an embodiment, the present disclosure provides an aerial vehicle with a compact design and flexible passive controlled wings which not only increase wing span, folding capacity, and folding space but also provide stability by adjusting itself sensibly and smartly to its surrounding conditions and increase the stability of the aerial vehicle in the air. Furthermore, the disclosure provides an aerial vehicle that comprises an unfolding mechanism to enable folding in very small area as well as give us the maximum wing span by employing multiple links and attachment

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points. Moreover, the aerial vehicle provides control to the wing arrangement without any availability of rudders, flaps or any other active elements by providing some degree of freedom to the trailing and far end of wing which is more exposed to the air. In an embodiment, the present disclosure provides an aerial vehicle which may be used as science vehicles for space research operations whether operated on earth or other planets of our solar system. The aerial vehicle may also used as glider planes available in the market as toys for kids.

While the disclosure has been presented with respect to certain specific embodiments, it will be appreciated that many modifications and changes may be made by those skilled in the art without departing from the spirit and scope of the disclosure. It is intended, therefore, by the appended claims to cover all such modifications and changes as fall within the true spirit and scope of the disclosure.





















CLAIMS