PatSeer

OPEN COIL SPRING AND TORSIONAL SPRING ASSISTED HINGE WING RELEASE MECHANISM FOR SCIENCE VEHICLE
Pub. No. IN201711017127A
App. No. IN201711017127
App. No. Original IN201711017127
Appl. Date 16-May-2017
Pub. Date 23-Nov-2018
Inventor(s) DR, DR PARAS CHAWLA, DR RAJDEEP SINGH, CHETAN CHADHA, MR HITESH VOHRA, MR DIWAKAR SINGH, MR SANKET SHARMA, MR SAHIL SHARMA, MR UDISH KAPOOR, MS MINAL PARMAR, 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. Further, the wing arrangement comprises a left wing having a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein and a right wing having a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein.

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 left wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein; and a right wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein, wherein, said body comprises a connecting link having a first end coupled to said first hinge of said left wing and a second end coupled to said first hinge of said right wing.

2. An aerial vehicle as claimed in claim 1, wherein said aerial vehicle further comprises a plurality of wheel assembly.

3. An aerial vehicle as claimed in claim 1, wherein one of said plurality of wheel assembly is coupled to said first wing profile of said left wing.

4. An aerial vehicle as claimed in claim 1, wherein one of said plurality of wheel assembly is coupled to said first wing profile of said right wing.

5. An aerial vehicle as claimed in claim 1, wherein said aerial vehicle further comprises of a tail, said tail comprising: a left fin connected to said body via a hinge having a spring; a vertical fin coupled to said body; and a right fin connected to said body via a hinge having a spring. 14.

6. An aerial vehicle as claimed in claim 1, wherein said first spring and second spring of said left wing and said spring of said left fin and said first spring and said second spring of said right wing and said spring of said right fin is a torsional spring.

7. An aerial vehicle as claimed in claim 1, wherein said connecting link is a coil spring.

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

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

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

Aerial reconnaissance is as old as the flight itself, but large-scale reconnaissance is generally limited by the availability of manpower and aircraft. Furthermore, it is expensive to keep a manned aircraft in the air, and in certain circumstances, it may even be particularly dangerous for example if the reconnaissance is being carried out over volatile geographic area. In recent years, unmanned aerial vehicles and micro-vehicles such as gliders have been developed. The gliders are much smaller than a conventional aircraft because it does not have to carry a human pilot. Further, such unmanned aerial includes design parameters that are configured to provide the necessary lift and control to overcome the drag and weight of a vehicle during flight. Also, they are well known to be used for delivering a payload to a predetermined area which is inaccessible by human beings. 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

A conventional fixed wing glider is thrown hard in an attempt to gain more altitude from the launch; the wings produce much more lift than the plane needs. Since the lift of a wing increases with the square of the velocity, increased velocity at launch means more lift which tends to cause the glider to loop in the air. Moreover, one of the limitations in the use of an autonomous flying wing is ease of deployment, in particular, the number of such flying wings that can be deployed from a single conventional aircraft or that can be stored in a single conventional underwing pod.

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

OBJECT OF THE INVENTION The principal object of the present invention is to provide an adjustable passive wings arrangement of an aerial vehicle a self-deployable arrangement that has a reduced weight and rigid structure to provide stability to wings in case of shocks.

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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. 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 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 left wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein; and

a right wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein,

wherein, said body comprises a connecting link having a first end coupled to said first hinge of said left wing and a second end coupled to said first hinge of said right wing.

According to a further embodiment of the present invention, said aerial vehicle further comprises a plurality of wheel assembly. Further, one of said plurality of

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wheel assembly is coupled to said first wing profile of said left wing and one of said plurality of wheel assembly is coupled to said first wing profile of said right wing.

According to an embodiment of the present invention, said aerial vehicle further comprises of a tail, said tail comprising a left fin connected to said body via a hinge having a spring, a vertical fin coupled to said body, and a right fin connected to said body via a hinge having a spring.

According to an embodiment of the present invention, said first spring and second spring of said left wing and said spring of said left fin and said first spring and said second spring of said right wing and said spring of said right fin is a torsional spring.

According to an embodiment of the present invention, said connecting link is a coil spring.

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 longitudinal direction and a lateral direction to said body of said aerial vehicle.

According to an embodiment of the present invention, said the 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

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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 top view of an aerial vehicle of FIG. 1, in accordance with an embodiment of the present disclosure;

FIG.3 illustrates a bottom view of an aerial vehicle of FIG. 1, in accordance with an embodiment of the present disclosure;

FIG.4 illustrates a schematic illustration of a hinge of a wing arrangement of the aerial vehicle of FIG.1, in accordance with an embodiment of the present disclosure; and

FIG.5 illustrates a schematic illustration of an aerial vehicle with folded 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

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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.

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

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

a left wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein; and

a right wing comprising a first wing profile and a second wing profile, wherein a first end of said first wing profile is coupled to said body via a first hinge comprising a first spring therein, and a second end of said first wing profile is coupled to a first end of said second wing profile via a second hinge comprising a second spring therein,

wherein, said body comprises a connecting link having a first end coupled to said first hinge of said left wing and a second end coupled to said first hinge 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 and a wing arrangement 03. Further, the wing arrangement 03 includes a left wing 04 having a first hinge 05, a first wing profile 06, a second hinge 07 and a second wing profile 08, and a right wing 09 having a first hinge 10, a first wing profile 11, a second

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hinge 12 and a second wing profile 13. Furthermore, the aerial vehicle 01 includes a plurality of wheel assembly 14 and 15. Additionally, as shown the aerial vehicle 01 comprises a tail 16 having a left fin 17, a vertical fin 18 and a right fin 19.

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. Moreover, the wing arrangement 03 of the aerial vehicle 01 needs to be folded manually. Further, the wing arrangement 03 of the aerial vehicle 01 is a self-locking arrangement. Furthermore, the wing arrangement 03 of the aerial vehicle 01 comprises a particular number of restoring elements, such as a spring.

According to an embodiment, the wing profile (06, 08, 11 and 13) of the left wing 04 and the right wing 09 of the wing arrangement 03 are made of materials that are light weight and durable. In an example, the materials may be wood, plastic, metal, alloys, other composite materials such as glass, carbon fiber, aramid fibers, etc. Furthermore, the left wing 04 and the right wing 09 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 wing profile 06 of the left wing 04 comprises a first end 20 and a second end 21 and the second wing profile 08 comprises a first end 22 and a second end 23. Furthermore, the first wing profile 06 is coupled to the body 02 via the first hinge 05. Specifically, the first end 20 of the first wing profile 06 is coupled to the first hinge 05. In an embodiment, the first hinge 05 is bolted with the first wing profile 06 at the first end 20 and the body 02 of the aerial vehicle 01. Additionally, the second end 21 of the first wing profile 06 is coupled to the first end 22 of the second wing profile 08 via the second hinge 07. Further, in an embodiment, the second hinge 07 is bolted to the second end 21of the first wing profile 06 and the first end 22 of the second wing profile 08.

According to an embodiment, the first wing profile 11 right wing 09 comprises a first end 24 and a second end 25 and the second wing profile 13 comprises a first end 26 and a second end 27. Furthermore, the first wing profile 11 is coupled to the body 02 via the first hinge 10. Specifically, the first end 24 of the first wing

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profile 11 is coupled to the first hinge 10. In an embodiment, the first hinge 10 is bolted with the first wing profile 11 at the first end 24 and the body 02 of the aerial vehicle 01. Additionally, the second end 25 of the first wing profile 11 is coupled to the first end 26 of the second wing profile 13 via the second hinge 12. Further, in an embodiment, the second hinge 12 is bolted to the second end 25 of the first wing profile 11 and the first end 26 of the second wing profile 13.

In an embodiment, the hinges (05, 07, 10, and 12) used herein comprises of the general mechanical parts. In an example, the general mechanical parts of the hinges include leaf, knuckle, pin, bolting slot and so forth. In another embodiment, the hinges (05, 07, 10, and 12) may comprise of various shapes, sizes. Furthermore, the hinges (05, 07, 10, and 12) may be of multiple types such as spring hinge, barrel hinge, pivot hinges, mortise hinges, case hinges and so forth.

In an embodiment, the first hinge 05 and the second hinge 07 of the left wing 04 includes a first spring and a second spring respectively. In another embodiment, the first hinge 10 and the second hinge 12 of the right wing 09 includes a first spring and a second spring respectively. In an embodiment, the springs used in the first hinge 05 and the second hinge 07 of the left wing 04 and the first hinge 10 and the second hinge 12 of the right wing 09 is a torsional spring. Furthermore, the springs enables the left wing 04 and right wing 09 to adjust itself passively but holds it stiffed against over adjustment to avoid stalling.

According to an embodiment, the left fin 17 and the right fin 19 of the tail 16 of aerial vehicle 01 is attached to the body 02 via hinges. Specifically, a hinge 28 is used to couple the left fin 17 to the body 02, and a hinge 29 is used to couple the right fin 19 to the body 02. In an embodiment the hinges 28 and 29 are similar to the aforesaid hinges, i.e. the hinges 28 and 29 are may have the similar make and model with respect to hinges used on the left wing 04 and the right wing 09. Furthermore, the vertical fin 18 is a rudder.

According to an embodiment, the wheel assembly 14 and 15 is attached to the left wing 04 and the right wing 09 respectively. The wheel assembly comprises of extended links and wheels. Specifically, the wheel assembly 14 coupled to the left wing 04 comprises an extended link 30 and a wheel 31. Similarly, the wheel assembly 15 coupled to the right wing 09 comprises an extended link 32 and a wheel 33.

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With reference to the drawings specifically to FIG.2, illustrates a top view of an aerial vehicle 01 of FIG. 1, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises the body 02, the wing arrangement 03 having the left wing 04 including the first hinge 05 and the first wing profile 06, right wing 09 including the first hinge 10 and the first wing profile 11, the tail 16 including the left fin 17 the vertical fin 18 and the right fin 19 and a connecting link 34.

In an embodiment, the connecting link 34 is arranged within the body 02 of the aerial vehicle 01. Specifically, the connecting link 34 comprises a first end coupled to the first hinge 05 of the left wing 04 and a second end of the connecting link 34 is coupled to the first hinge 10 of the right wing 09. In an embodiment, the connecting link 34 is an open coil spring embedded inside the body 02. Further, the connecting link 34 is operable to help in unfolding the wings 04 and 09. Additionally, the connecting link 34 may comprise of various shapes, sizes, and elasticity.

In an embodiment, the connecting link 34 is placed inside the body 02 of the aerial vehicle 01 is coupled with a spring holder to transfer energy from spring to wing frame and vice versa. In an embodiment, the connecting link 34, stores energy when the wing arrangement is in folded state.

With reference to the drawings specifically to FIG.3, illustrates a bottom view of an aerial vehicle 01 of FIG. 1, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises the body 02, the wing arrangement 03 having the left wing 04 including the first hinge 05 and the first wing profile 06, a second hinge 07 and a second wing profile 08, the right wing 09 including the first hinge 10 and the first wing profile 11, a second hinge 12 and a second wing profile 13, the tail 16 and a connecting link 34. In this embodiment, the wing arrangement 03 may include the aerofoil geometry of wings, such as the left wing 04 and the right wing 09. In an embodiment, the wing arrangement 03 has an increase wing span.

With reference to the drawings specifically to FIG.4, illustrates schematic illustration of a hinge of a wing arrangement of the aerial vehicle of FIG.1, in accordance with an embodiment of the present disclosure. As shown, the hinge includes a spring 35 arranged herein. In this embodiment, the hinge may be any

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one of the hinges (05, 07, 10, and 12) used in the wing arrangement 03 and /or the tail of the aerial vehicle 01. In an embodiment, the spring 35 is a torsional spring. In an embodiment, the spring 35 may comprise of various shapes, sizes, and elasticity.

With reference to the drawings specifically to FIG.5, illustrates a schematic illustration of an aerial vehicle with folded wing arrangement, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises a body 02 and a wing arrangement 03. Further, the wing arrangement 03 includes a left wing 04 having a first hinge 05, a first wing profile 06, a second hinge 07 and a second wing profile 08, and a right wing 09 having a first hinge 10, a first wing profile 11, a second hinge 12 and a second wing profile 13. Furthermore, the aerial vehicle 01 includes a plurality of wheel assembly 14 and 15. Additionally, as shown the aerial vehicle 01 comprises a tail 16 having a left fin 17, a vertical fin 18 and a right fin 19. In this embodiment, the wings arrangement 03 of the aerial vehicle 01 is operable to unfold in a longitudinal direction and a lateral direction to the body 02 of the aerial vehicle 01.

In an embodiment, the wing arrangement is folded in longitudinal direction manually. Further, while manual folding the left wing 04, the second wing profile 08 is folded towards the first wing profile 06 assisted by the second hinge 07 and against the expansion of the second spring 07 (torsional spring), thereby storing the energy in the second spring. Furthermore, as the first wing profile 06 is folded it press the left fin 17 in a folded configuration, allowing the wheel assemble 14 to be positioned close to the body 02 of the aerial vehicle 01. Additionally, first wing profile 06 is folded with the help of the first hinge 05 and against the expansion of the first spring (torsional spring), thereby storing the energy in the first spring. Moreover, the left fin 17 folds with the help of the associated hinge and thereby compressing the spring arranged therein and storing energy within. Furthermore, in this embodiment, the right wing 09 is folded is a similar fashion as the left wing 04, i.e. the second wing profile 13 is folded towards the first hinge 10 with assisted by the second hinge 12 and against the expansion of the second spring (torsional spring), thereby storing the energy in the second spring. Further, as the first wing profile 10 is folded it press the left fin 19 in a folded configuration, allowing the wheel assemble 15 to be positioned close to the body 02 of the aerial vehicle 01. Additionally, first wing profile 10 is folded with the help of the first hinge 10 and

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against the expansion of the first spring (torsional spring), thereby storing the energy in the first spring. Moreover, the right fin 19 folds with the help of the associated hinge, and thereby compressing the spring arranged therein and storing energy within.

In an embodiment, whilst folding the wing arrangement 03 in the lateral direction the connecting link 34 is rendered in close coil condition and the first wing profile 06 and 11 is rotated in longitudinal direction (pitching of wing) which builds tension in close coil spring and thereby folding the wing arrangement 03 within minimum space as a whole.

In an embodiment, the aerial vehicle 01 after being manually folded is placed within a container. Furthermore, whilst the aerial vehicle 01is released from the container energy stored in each spring is released in the form of desired motion in the desired direction which results in proper unfolding of wings arrangement 03 with minimum effect of jerk and shock, thereafter the aerial vehicle 01 is rendered ready to sail on air with negligible degree of free fall after released. Further, when released the aerial vehicle 01 forms a rigid wing profile with versatile wing frame with actual aerofoil geometry of wings.

In a specific embodiment, the present invention seeks to provide an aerial vehicle 01, such as a glider, including a body 02 and a wing arrangement 03 coupled to the body of the aerial vehicle, the wing arrangement includes a left wing 04 comprising a first wing profile 05 and a second wing profile 08, wherein a first end 20 of the first wing profile 05 is coupled to the body 02 via a first hinge 06 comprising a first spring therein, and a second end 21 of the first wing profile 05 is coupled to a first end 22 of the second wing profile 08 via a second hinge 07 comprising a second spring therein, and right wing 09 comprising a first wing profile 11 and a second wing profile 13, wherein a first end 24 of the first wing profile 11 is coupled to the body 02 via a first hinge 10 comprising a first spring therein, and a second end 25 of the first wing profile 11 is coupled to a first end 26 of the second wing profile 13 via a second hinge 12 comprising a second spring therein, wherein, the body 02 includes a connecting link 34 having a first end coupled to the first hinge 05 of the left wing 04 and a second end coupled to the first hinge 10 of the right wing 09. Moreover, the connecting link 34 may be a coil spring. Additionally, the first spring and second spring of the left wing 04 and the spring of the left fin and the first spring and the second spring of the right wing 09 and the spring of the right fin is a

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torsional spring. The aerial vehicle 01 further comprises a plurality of wheel assembly 14 and 15, wherein the wheel assembly 14 is coupled to the first wing profile 05 of the left wing 04 and the wheel assembly 15 is coupled to the first wing profile 05 of the right wing 09. Additionally, the aerial vehicle further comprises of a tail 16 including a left fin 17 connected to said body 01 via a hinge having a spring, a vertical fin 18 coupled to said body 01 and a right fin 19 connected to said body 01 via a hinge having a spring. Moreover, the wing arrangement 03 is a self-deployable arrangement, further; the wings arrangement 04 of said aerial vehicle 01 is operable to unfold in a lateral direction and a transverse direction to the body 02 of the aerial vehicle 01.

Further, the preset disclosure provides the aerial vehicle which comprises 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 helps in gliding. Moreover, the mechanism provides a desired of wings spans to operate to its maximum limit and helps the aerial vehicle to glide at desired glide ratio. Moreover, the aerial vehicle provides a rigid portion which supports the weight of over mounted elements like solar sheets in an 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