PatSeer

RIGID FIVE BAR CHAIN RETRACTABLE UNFOLDING WING MECHANISM FOR PASSIVELY CONTROLLED SCIENCE VEHICLE
Pub. No. IN201711017092A
App. No. IN201711017092
App. No. Original IN201711017092
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, 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 B60K6/12
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 left wing comprising a first link, a second link, a third link and a fourth link, a right wing comprising a first link, a second link, a third link and a forth link and an elastic cord coupled to said first link, second link of said left wing and said first link, second link of said right wing.

CLAIMS

1. An aerial vehicle comprising: a body; and an wing arrangement coupled to said body of said aerial vehicle, said wing arrangement comprising: a left wing comprising a first link, a second link, a third link and a fourth link, wherein first ends of said first link and said second link are pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link; a right wing comprising a first link, a second link, a third link and a forth link, wherein a first end of said first link and said second link is pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link; and an elastic cord coupled to said first link, second link of said left wing and said first link, second link of said right wing.

2. An aerial vehicle as claimed in claim 1, wherein said first link and said second link of said left wing and said first link and said second link of said right wing are coupled using rolling pin.

3. An aerial vehicle as claimed in claim 1, wherein said left wing and said right wing is positioned vertically opposite to each other.

4. An aerial vehicle as claimed in claim 1, wherein said wing arrangement is a self deployable arrangement. 14.

5. An aerial vehicle as claimed in claim 1, wherein said wings arrangement of said aerial vehicle is operable to unfold in a lateral direction and a transverse direction to said body of said aerial vehicle.

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

7. 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. Further, such unmanned aerial vehicles are well known to be used for delivering payload to a predetermined area to an area which is not accessible by human beings, and/or that the conditions in the area put humans in too great of a risk to deliver the payload. Moreover, such unmanned aerial vehicles may be equipped with a motor and capable of flight on their own with full maneuvering capability; and non-motorizes unmanned aerial vehicles lacking a motor which are configured for being dropped or deployed from a carrier. Typically, such unmanned aerial vehicles are convertible and the parts of such unmanned aerial vehicles may be removed and attached for providing a better portability.

However, in unmanned aerial vehicles, particularly in glider considerable effort and time is involved in unfolding and preparing the hang glider for flight. Parts must be bolted together and cables tensioned after the glider has been transported to its take-off location. In like manner after flight the process must be reversed so that it may be transported. The current state of the art is such that parts have to be detached and the sail cloth rolled and cables coiled so that as much as half an hour may be involved in preparing the glider at or near the take-off site. Moreover, 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.

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

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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 when folded, and an increased wingspan when in an unfolded state and have a reduced number of elastic cords, springs, attachment points required for unfolding the wings to its maximum unfolded limit. Another object of the present invention is to provide a rigid portion which supports the weight of over mounted elements without any increase loads on joint Another object of the present invention is to provide an aerial vehicle with reduced weight and simple and rigid structure to provide stability to wings in case of shocks. 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

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

a left wing comprising a first link, a second link, a third link and a fourth link, wherein first ends of said first link and said second link are pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link;

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a right wing comprising a first link, a second link, a third link and a forth link, wherein a first end of said first link and said second link is pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link; and

an elastic cord coupled to said first link, second link of said left wing and said first link, second link of said right wing.

According to a further embodiment of the present invention, said first link and said second link of said left wing and said first link and said second link of said right wing are coupled using rolling pin.

According to an embodiment of the present invention, said left wing and said right wing is positioned vertically opposite to each other.

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

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

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.

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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, 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 the wing arrangement of the elastic cord.

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”,

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“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.

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

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

a body; and

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

a left wing comprising a first link, a second link, a third link and a fourth link, wherein first ends of said first link and said second link are pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link;

a right wing comprising a first link, a second link, a third link and a forth link, wherein a first end of said first link and said second link is pivotally coupled to said body of said aerial vehicle, and wherein a second end of said first link is coupled to a first end of said forth link, and a second end of said second link is coupled to a first end of said third link, and wherein a second end of said third link is coupled to said forth link; and

an elastic cord coupled to said first link, second link of said left wing and said first link, second link of said right wing.

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. Furthermore, the wing arrangement 03 includes a left wing 04 having a first link 05, a second link 08, a third link 11 and a fourth link 14.

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Additionally, the first link 05 of the left wing 04 comprises a first end 06 and a second end 07, the second link 08 of the left wing 04 comprises a first end 09 and a second end 10, the third link 11 of the left wing 04 comprises a first end 12 and a second end 13, the fourth link 14 of the left wing 04 comprises a first end 15 and a second end 16. Moreover, the wing arrangement 03 includes a right wing 17 having a first link 18, a second link 21, a third link 24 and a fourth link 27. Further, the first link 18 of the right wing 17 comprises a first end 19 and a second end 20, the second link 21 of the right wing 17 comprises a first end 22 and a second end 23, the third link 24 of the right wing 17 comprises a first end 25 and a second end 26, the fourth link 27 of the right wing 17 comprises a first end 28 and a second end 29. Furthermore, the wing arrangement 03 includes comprises of an elastic cord 30.

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 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 elastic cords 30. 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 links (05, 08, 11, 14, 18, 21, 24 and 27) of the left wing 04 and the right wing 17 of the wing arrangement 03 are 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. Furthermore, the left wing 04 and the right wing 17 of the wing arrangement 03 are positioned vertically opposite to each other, and is structurally similar to each other.

According to an embodiment, the first ends 06, 09 of the first link 05 and the second link 08 of the left wing 04 are pivotally coupled to the body 02 of said aerial vehicle 01. Furthermore, the first ends 19, 20 of the first link 18 and the second link 21 of the right wing 17 are also pivotally coupled to the body 02 of said aerial vehicle 01. Specifically, the first link 05 and the second link 08 of the left wing 04 and the first

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link 18 and the second link 21 of the left wing 17 are pivotally coupled to the body 02 of said aerial vehicle 01 using the rolling pin. In another embodiment, the left wing 04 and the right wing 17 are coupled using arrangement providing a pivotal movement, such as rotatable clamp.

In one embodiment, in the left wing 04, the second end 07 of the first link 05 is coupled to the first end 15 of said fourth link 14 in a manner that allows a lateral movement of the fourth link 14 with respect to the first link 05. Specifically, the fourth link 14 is coupled to the first link 05 using a male-female joint. In an example, the first end 15 of said fourth link 14 may comprise of a male connector that fits into a female connector designed at the second end 07 of the first link 05 to holster the male connector. In such example a linchpin may arranged to pass through the female connector and the male connector, when placed within each other. Furthermore, in the in the right wing 17, the first link 18 and the fourth link 27 is connected in a similar manner as the first link 05 and the fourth link 14, of the left wing 04. Specifically, the second end 20 of the first link 18 comprises a female connector and the first end 28 of the fourth link 14 comprises a male connector that fits into the female connector of the second end 20 of the first link 18, the a linchpin may arranged to pass through the female connector of the first link 18 and the male connector of the fourth link 14, when placed within each other.

In one embodiment, in the left wing 04, the second end 10 of the second link 08 is coupled to the first end 12 of the third link 11. Specifically, the second link 08 is coupled to the third link 11 using a male-female joint. In an example, the second end 10 of the second link 08 comprises a female connector to holster a male connector formed at the first end 12 of the third link 11. Furthermore, in such example a linchpin may be arranged to pass through the female connector and the male connector, when placed within each other to provide a degree of freedom for the lateral movement of the links. Furthermore, in the right wing 17, the second link 21 and the third link 24 is connected in a similar manner as the second link 08 and the third link 11. Specifically, the second end 23 of the second link 21 comprises a female connector to holster a male connector formed at the first end 25 of the third link 24. Furthermore, in such example a linchpin may be arranged to pass through the female connector and the male connector, when placed within each other to provide a degree of freedom for the lateral movement of the links.

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In an embodiment, in the left wing 04, the second end 13 of the third link 11 is coupled to the fourth link 14. Specifically, the third link 11 is coupled to a portion of the fourth link 14 that is equidistance form the two ends 15 and 16. In an embodiment, the third link 11 may be coupled to the fourth link 14 anywhere along the length. More specifically, the fourth link 14 is coupled to the third link 11 using a male-female joint. In an example, the fourth link 14 may comprise a female connector wherein a male connector formed at the second end 13 of the third link 11 fits onto. In another example, the linchpin may be arranged to pass through the female connector and the male connector, when placed within each other to provide a degree of freedom for the lateral movement of the links. Furthermore, in the right wing 17, the third link 24 is coupled to the fourth link 27 is connected in a similar manner as the third link 11 and the fourth link 14 of the left wing 04. Specifically, the fourth link 14 comprises a female connector that holsters a male connector formed at the second end 26 of the third link 24. Furthermore, a linchpin may be arranged to pass through the female connector and the male connector, when placed within each other to provide a degree of freedom for the lateral movement of the links.

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. Furthermore, the wing arrangement 03 includes a left wing 04 having a first link 05, a second link 08, a third link 11, a fourth link 14, a right wing 17 having a first link 18, a second link 21, a third link 24 and a fourth link 27 and an elastic cord 30.

In an embodiment, the left wing 04 and the right wing 17 of the wings arrangement 03 of said aerial vehicle 01 is operable to fold and unfold in the lateral direction and a transverse direction with respect to the body 02 of the aerial vehicle 01. Specifically, the wings arrangement 03 of said aerial vehicle 01 provides a dual folding mechnism. In an example, the left wing 04 and the right wing 17 of the wings arrangement 03 may be folded in a lateral direction with respect to the body 02 of the aerial vehicle 01, thereafter to provide a more compact structure, the wings arrangement 03 may be futher folded in the transverse direction to roll along the body 02 of the aerial vehicle 01.

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In an embodiment, the folding of the wings arrangement 03 of said aerial vehicle 01 in the lateral direction forms a structure wherein the second end 07 of the first link 05 and the second end 13 of the third link 11 move towards the opposite direction with respect to each other, further, the second end 20 of the first link 18 and the second end 26 of the third link 24 move towards the opposite direction with respect to each other. Furthermore, the fourth link 14 of the left wing 04 and the fourth link 27 of the right wing 17 is positioned parallelly to the body 02 of the aerial vehicle 01, moreover the fourth link 14 is positioned on the left side of the the body 02 and the fourth link 27 is positioned on the right side of the the body 02.

With reference to the drawings specifically to FIG.3, illustrates a schematic illustration of an aerial vehicle 01 with the wing arrangement 03 of the elastic cord 30 , in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises the body 02, the wing arrangement 03. Furthermore, the wing arrangement 03 includes a left wing 04 having a first link 05, a third link 11, a fourth link 14 and an elastic cord 30.

In an embodiment, the elastic cord 30 extends from the first link 05 of the left wing 04 to the second link 08 of the left wing 04 and thereafter connecting to the first link 18 said right wing 17 and extending to the second link 21 of said right wing 17. Furthermore, the elastic cord 30 may comprise of various shapes, sizes, and elasticity. Additionally, the elastic cord 30 may be elastic shock cord, a rope, or a cable. Moreover, the elastic cord 30 may be a braided cord of cotton, nylon, polyester, polypropylene and so forth.

In an embodiment, the first link 05, the second link 08 of the left wing 04 and the first link 18, second link 21 of the right wing 17 comprises an potruding member coupled on each of the links. Specifically, the potruding member may comprise of a persering to allow the elastic code 30 to passing through it.

In another embodiment, the aerial vehicle 01 may comprise of a spring arrangement. Specifically, the spring arrangement may be associated with the first link 05 of the left wing 04 and the first link 18 of the right wing 17.

In one embodiment, in the transverse direction of folding the wing arrangement 03 one pin like element, such as the protruding element, is placed with glider body having single degree of freedom towards roll of glider and the wing mechanism 03

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is attached over it. Moreover the elastic cord 30 is attached to its projection, between two pin like elements situated on either side of the aerial vehicle 01. When roll is given in relative respected direction to fold wings 04 and 17, the elastic cord 30 get stretched and stored a certain amount of force in it.

In another embodiment, the lateral direction of folding the wing arrangement 03, the elastic cord 30 is tied to the links which get stretched when both links move in the respected direction and it will store a certain amount of force in lateral direction.

Furthermore, the wing mechanism 03 is designed for unfolding of folded wings only therefore when folded manually it stores some energy in it as a force and when surrounding load is removed, stored force get released which exerts force on links as a result links will tends to move and due to their co-related simultaneous motion wings will open to its full extent and wings will be ready to glide. Moreover, 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.

Further, the preset disclosure provides the aerial vehicle which comprises of a .self unfolding mechanism for large wings of a small or medium sized aerial vehicle such as glider that can be used as science vehicle (payload) which can be used in planetary missions to collect atmospheric or geographic data. The mechanism is so thought that it could be confined to a minimum space and allows a large wing span that help in gliding without the use of proper aerofoil shape of the wing. Further, as the aerial vehicle excludes the aerofoil shape the wings can be made of a flexible sheet, plausibly decreasing mass and providing ease of designing and manufacturing difficulties. Moreover, the mechanism includes five bar links which are assembled in such a way that when two links are operated by an elastic cord, all other links will go under simultaneous relative motion which as an combined effect creates a special arrangements of links, hence a desired profile of wings would be obtained when links will operate to its maximum limit and helps the glider to glide

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at desired glide ratio. Moreover, the aerial vehicle provides a rigid portion which supports the weight of over mounted elements like solar sheets in efficient way without any increase loads on joint. Furthermore, the aerial vehicle may be used as a miniature satellite for efficiently perform inter-planetary missions, large test volume of atmosphere, navigating into remote areas.

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