PatSeer

GLIDER WITH AUTOMATIC WING UNFOLDING MECHANISM
Pub. No. IN201611019875A
App. No. IN201611019875
App. No. Original IN201611019875
Appl. Date 09-Jun-2016
Pub. Date 16-Feb-2018
Inventor(s) DR RUCHI SINGLA, DR MOHIT SRIVASTAVA, DR POOJA SAHNI, MS JASHANDEEP KAUR, MS NAVJOT KAUR, MR GAURAV KUMAR, MR APAAR SETH, MR LAKSHAY TOMAR, MR PANKUSH THAPPA, MR PULKIT AGGARWAL, MR SHUBHAM GOGADE, MR PUNEET DHIMAN, MR VATAN THAKUR
Assignee Norm. CHANDIGARH GROUP OF COLLEGES CGC (LANDRAN KHARAR BANUR HIGHWAY SECTOR 112 LANDRAN SAHIBZADA AJIT SINGH NAGAR PUNJAB 140307 PUNJAB INDIA, IN)
Current Assignee CHANDIGARH GROUP OF COLLEGES CGC (LANDRAN KHARAR BANUR HIGHWAY SECTOR 112 LANDRAN SAHIBZADA AJIT SINGH NAGAR PUNJAB 140307 PUNJAB INDIA, IN)
Current Owner CHANDIGARH GROUP OF COLLEGES CGC
IPC A63H27/00
ABSTRACT
Disclosed is an aerial vehicle. The aerial vehicle comprises a fuselage, a linear slide arrangement coupled to the fuselage and a foldable wing arrangement. The foldable wing arrangement is coupled to the linear slide arrangement. Moreover, the linear slide arrangement is operable to deploy the foldable wing arrangement. Further, the foldable wing arrangement comprises a plurality of wings having a similar architecture and shape. Furthermore, the architecture of at least one wing of the plurality of wings comprises a wing frame including a first link, a second link, a third link and a fourth link, wherein each of the links comprises a first end and a second end, and wherein the links form a kinematic chain. FIG. 1 for Abstract

CLAIMS

1. An aerial vehicle comprising: a fuselage; a linear slide arrangement coupled to the fuselage; and a foldable wing arrangement coupled to the linear slide arrangement, wherein the foldable wing arrangement comprises a plurality of wings of similar architecture and shape, wherein the linear slide arrangement is operable to deploy the foldable wing arrangement.

2. An aerial vehicle as claimed in claim 1, wherein the architecture of at least one wing of the plurality of wings comprises a wing frame including a first link, a second link, a third link, a fourth link, a fifth link and a sixth link, wherein each of the links comprises a first end and a second end, and wherein the links form a kinematic chain.

3. An aerial vehicle as claimed in claim 1, wherein the linear slide arrangement further comprises a spring and a slider.

4. An aerial vehicle as claimed in claim 3, wherein the spring is contracted when the foldable wing arrangement is in a deployed state, and the spring is expanded when the foldable wing arrangement is not in the deployed state.

5. An aerial vehicle as claimed in claim 1, wherein the foldable wing arrangement is a self-expending arrangement.

6. An aerial vehicle as claimed in claim 1, wherein the aerial vehicle further comprises an assembly of electrical components.

7. An aerial vehicle as claimed in claim 6, wherein the assembly of electrical components are operable to detect physical parameters of a targeted location and capture image of the targeted location.

8. An aerial vehicle as claimed in claim 6, wherein the assembly of electrical components includes at least one of a sensor, a beacon, a camera and a micro controller.

9. An aerial vehicle as claimed in claim 1, wherein the aerial vehicle travels in a circular path.

10. An aerial vehicle as claimed in claim 1, wherein the aerial vehicle is made of light weight thermoplastic material.


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

In recent years, unmanned aerial vehicles and micro-vehicles such as gliders have been developed and used for various purposes. The gliders are much smaller than a conventional aircraft. Further, flying of gliders is an entertaining and educational activity participated in by numerous enthusiasts, both children, and adults. Further, such unmanned aerial include 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 common difficulty has been to launch the glider from the ground to an altitude high enough to allow for an extended flight time. Another difficulty has been to imitate the wing rotation on the swing wing aircraft currently popular especially on wide fuselage aircraft.

Further, a patent document, US 4,863,413 provides a model of a glider, wherein the body and wings of the glider are made of lightweight materials and the wings of the glider are foldable. The glider model also contains a spring.

Furthermore, another patent document, US20110226891 provides a model of a glider, wherein the body and wings of the glider are made of lightweight materials and the wings of the glider are foldable and in the shape of bat’s wings. Also, framework of wings is made of reinforced fiberglass.

However the above mentioned document does not mentions fitting the glider into a container of known dimensions. Moreover, launching a glider at the high speeds requires attaining altitude which is especially difficult due to the delicate wing structure and the relatively high wind resistance associated with airplanes built to glide at normal speeds. Furthermore, another limitation in using a glider is the ease of deployment, in particular, the deployment of the flying wings 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 a light weight aerial vehicle having a wing arrangement that is foldable to attain a compact size and is operable to self-deploy the wing arrangement.

Another object of the present invention is to provide a light weight aerial vehicle operable to detect physical parameters of a targeted location and capture image of the targeted location.

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 foldable wing arrangement of an aerial vehicle.

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

a fuselage;

a linear slide arrangement coupled to the fuselage; and

a foldable wing arrangement coupled to the linear slide arrangement, wherein the foldable wing arrangement comprises a plurality of wings of similar architecture and shape,

wherein the linear slide arrangement is operable to deploy the foldable wing arrangement.

According to an embodiment of the present invention, the architecture of at least one wing of the plurality of wings comprises a wing frame including a first link, a second link, a third link, a fourth link, a fifth link and a sixth link, wherein each of the links comprises a first end and a second end, and wherein the links form a kinematic chain.

According to an embodiment of the present invention, the linear slide arrangement further comprises a spring and a slider.

According to an embodiment of the present invention, the spring is contracted when the foldable wing arrangement is in a deployed state, and the spring is expanded when the foldable wing arrangement is not in the deployed state.

According to an embodiment of the present invention, the foldable wing arrangement is a self-expending arrangement.

According to a further embodiment of the present invention, the aerial vehicle further comprises an assembly of electrical components.

According to an embodiment of the present invention, the assembly of electrical components is operable to detect physical parameters of a targeted location and capture image of the targeted location.

According to an embodiment of the present invention, the assembly of electrical components includes at least one of a sensor, a beacon, a camera and a micro controller.

According to an embodiment of the present invention, the aerial vehicle travels in a circular path.

According to an embodiment of the present invention, the aerial vehicle is made of light weight thermoplastic material.

Embodiments of the present disclosure substantially eliminate or at least partially address the aforementioned problems in the prior art, and provides an aerial vehicle with a self-unfolding wing arrangement.

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

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

FIG.4 illustrates a linear slide arrangement of the aerial vehicle of FIG.1, in accordance with an embodiment of the present disclosure; and

FIG.5A-C illustrates deployment of the aerial vehicle of FIG.1, 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.

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

a fuselage;

a linear slide arrangement coupled to the fuselage; and

a foldable wing arrangement coupled to the linear slide arrangement, wherein the foldable wing arrangement comprises a plurality of wings of similar architecture and shape,

wherein the linear slide arrangement is operable to deploy the foldable wing arrangement.

With reference to the drawings, specifically 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 fuselage 02, linear slide arrangement 03 and a foldable wing arrangement 04. Further, the foldable wing arrangement 04 includes a left wing 05 and a right wing 24 having similar architecture and shape. Additionally, the left wing 05 comprises a first link 06 having a first end 07 and a second end 08, a second link 09 having a first end 10 and a second end 11, a third link 12 having a first end 13 and a second end 14, a fourth link 15 having a first end 16 and a second end 17, a fifth link 18 having a first end 19 and a second end 20, and a sixth link 21 having a first end 22 and a second end 23. Similarly, the right wing 24 comprises the same number of links.

With reference to the drawings, specifically FIG.2 illustrates a front view of the aerial vehicle 01 of FIG.1, in accordance with an embodiment of the present disclosure. As shown, the aerial vehicle 01 comprises a fuselage 02, linear slide arrangement 03 and a foldable wing arrangement 04. Furthermore as shown the fuselage of the aerial vehicle 01 includes an assembly of electrical component 25.

With reference to the drawings, specifically FIG.3 illustrates a frame of the aerial vehicle 01 of FIG.1, in accordance with an embodiment of the present disclosure. As shown the frame of the aerial vehicle 01 includes a fuselage 02, linear slide arrangement 03 and a foldable wing arrangement 04. Further, the foldable wing arrangement 04 includes a left wing 05 and a right wing 24 having similar architecture and shape. Additionally, the left wing 05 comprises a first link 06 having a first end 07 and 08, a second link 09 having a first end 10 and 11, a third link 12 having a first end 13 and 14, a fourth link 15 having a first end 16 and 17, a fifth link 18 having a first end 19 and 20, and a sixth link 21 having a first end 22 and 23. Similarly, the right wing 24 comprises the same number of links.

With reference to the drawings, specifically FIG.4 illustrates a linear slide arrangement 03 of the aerial vehicle 01 of FIG.1, in accordance with an embodiment of the present disclosure. As shown, the linear slide arrangement 03 includes a spring 26 and a slider 27. Furthermore, an association of the links of the wing arrangement 04 is shown, such as the association of the first link 06, the second link 09 and the third link 12 of left wing 05, within each other and with the spring 26 and the slider 27 of the linear slide arrangement 03.

With reference to the drawings, specifically FIG.5A-C illustrates a deployment of the aerial vehicle 01 of FIG.1, in accordance with an embodiment of the present disclosure. As shown, in FIG.5A the aerial vehicle 01 is placed within a container 28. Further, FIG.5B shows the aerial vehicle 01 partially released from the container 28. Furthermore, FIG.5C shows the aerial vehicle 01 completely released from the container 28.

In a specific embodiment, the present invention seeks to provide an aerial vehicle 01 comprises a fuselage 02, a linear slide arrangement 03 coupled to the fuselage 02, including a spring 26 and a slider 27; and a foldable wing arrangement 04 coupled to the linear slide arrangement 03, wherein the foldable wing arrangement 04 comprises a plurality of wings 05 and 24 of similar architecture and shape, wherein the architecture of at least one wing such as the left wing 05 of the plurality of wings 05 and 24 comprises a wing frame including a first link 06, a second link 09, a third link 12, a fourth link 15, a fifth link 18 and a sixth link 21, wherein each of the links comprises a first end and a second end such as 07, 08, 10, 11, 13, 14, 16, 17, 19, 20, 22, and 23, and wherein the links form a kinematic chain, further, the linear slide arrangement 03 is operable to deploy the foldable wing arrangement 04, moreover the spring 26 is contracted when the foldable wing arrangement 04 is in a deployed state, and the spring 26 is expanded when the foldable wing arrangement 04 is not in the deployed state, furthermore, the foldable wing arrangement 04 is a self-deployable arrangement. Additionally, the aerial vehicle 01 further comprises an assembly of electrical components 25, wherein the assembly of electrical components 25 is operable to detect physical parameters of a targeted location and capture image of the targeted location, further, the assembly of electrical components 25 includes at least one of a sensor, a beacon, a camera and a micro controller. Moreover, the aerial vehicle 01 travels in a circular path and is made of light weight thermoplastic material.

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 with the foldable wing arrangement 04 attached to the fuselage 02 of the aerial vehicle 01. Additionally, the aerial vehicle 01 can be confined to a minimum space and allow a large wing span that helps in gliding. Further, the aerial vehicle 01 can be folded and placed within a container such as a can, that can be approximately one third of the size of the aerial vehicle 01 in a unfolded state. Furthermore, the fuselage 02 is made of light weight thermoplastic, for example, the fuselage 02 is made of Acrylonitrile butadiene styrenemade (ABS).

According to an embodiment, the foldable wing arrangement 04 of the aerial vehicle 01 is a self-deployable arrangement. Specifically, the foldable wing arrangement 04 is operable to deploy automatically when released from a container holding the aerial vehicle 01. Furthermore, the foldable wing arrangement 04 of the aerial vehicle 01 is folded manually to attain a compact structure. In an embodiment, the foldable wing arrangement 04 when folded is snuggly arranged on the fuselage 02 of the aerial vehicle 01.

According to an embodiment, the foldable wing arrangement 04 of the aerial vehicle 01 comprises a plurality of wings such as the left wing 05 and the right wing 24. Further, the left wing 05 and the right wing 24 are of similar architecture and shape, i.e. the left wing 05 and the right wing 24 comprises an equal number of components having same size, shape, and connectivity. Moreover, the components of the left wing 05 and the right wing 24 are connected to each other in a similar fashion.

Furthermore, according to an embodiment, the left wing 05 comprises a first link 06 having a first end 07 and a second end 08, a second link 09 having a first end 10 and a second end 11, a third link 12 having a first end 13 and a second end 14, a fourth link 15 having a first end 16 and a second end 17, a fifth link 18 having a first end 19 and a second end 20, and a sixth link 21 having a first end 22 and a second end 23. Additionally, the first end 07 of the first link 06 is coupled to the slider 27 of the linear slide arrangement 03 and the second end 08 of the first link 06 is coupled to the second link 09. Further, the first end 10 of the second link 09 is coupled to one end of the linear slide arrangement 03 and the second end 11 of the second link 09 is coupled to the fourth link 15. Moreover, the first end 13 of the third link 12 is coupled to the first link 06 and the second end 14 of the third link 12 is coupled to the first end 16 of the fourth link 15. Furthermore, the second end 17 of the fourth link 15 is coupled to the fifth link 18. Additionally, the first end 19 of the fifth link 18 is coupled to a first end 22 of the sixth link 21. Moreover, the second end 23 of the sixth link 21 is coupled to the second link 09.

According to an embodiment, the first link 06, the second link 09, the third link 12, the fourth link 15, the fifth link 18 and the sixth link 21 are connected pivotally. Further, the links 06, 09, 12, 15, 18 and 21 to connected pivotally using a pivot pin. Furthermore, the links 06, 09, 12, 15, 18 and 21 are made of light weight thermoplastic, for example, the links 06, 09, 12, 15, 18 and 21 are made of Acrylonitrile butadiene styrenemade (ABS).

According to an embodiment, the links of the left wing 05 and the right wing 24 is connected in a kinematic chain. For example, the links 06, 09, 12, 15, 18 and 21 of the left wing 05 forms a kinematic chain when connected using a pivot pin. Specifically, the links of the left wing 05 and the right wing 24 is connected in a manner wherein one link move relative to one another.

According to an embodiment, the plurality of wings such as the left wing 05 and the right wing 24 of the foldable wing arrangement 04 uses flexible material to form the wing profile. The flexible material is made of material that is foldable and forms a rigid structure when stressed. Furthermore, the flexible material is made of material selected from the group including fabric, carbon fiber and so forth. Moreover, rods made of light weight thermoplastic run between the wing frame the end of the wing profile to provide rigidity to the wing profile when in operation. According to an embodiment, aerial vehicle 01 travels in a circular path. Furthermore, the wings are designed with tilted stab along with the shift in the center of mass of the design which further tilts the aerial vehicle 01 in preset circular path. Moreover, the wings are arranged in a way that when the aerial vehicle 01 is dropped from a height, it glides down tracing a circular path.

According to an embodiment, the spring 26 and the slider 27 of the linear slide arrangement 03 are coupled to each other. In another embodiment, the linear slide arrangement 03 comprises a track within which the spring 26 and the slider 27 is arranged therein. Further, one end of the spring 26 is coupled to an end of the track of the linear slide arrangement 03, and the other end of the spring 26 is coupled to the slider 27. Therefore, the first links of the left wing 05 and the right wing 24 of the foldable wing arrangement 04 is moved due to the manual folding of the foldable wing arrangement 04, the slider 27 moves along the track to stress the spring 26. It is appreciated that the slider 27 moves towards the end of the track which is opposite the end of the track that is coupled to one end of the spring. Additionally, the spring 26 remains in an expanded state when the string 26 is stressed, further, the spring 26 continues to be in such state when the aerial vehicle 01 is placed inside the container 28. However, the spring 26 automatically compress in the event wherein the aerial vehicle 01 is realised from the container 28. It may be understood that in the event wherein the aerial vehicle 01 is folded and placed in the container 28 an external force is applied while folding the foldable wing arrangement 04 and such force remain operational when placed inside the container 28, further, as the aerial vehicle 01 is realised from the container 28 the external force used to fold the foldable wing arrangement 04 in not in operation and thereby allowing the foldable wing arrangement 04 to unfold. According to an embodiment, the spring 26 is contracted when the foldable wing arrangement 04 is in a deployed state, and the spring 26 is expanded when the foldable wing arrangement 04 is not in the deployed state. Furthermore, the spring 26 used herein is a torsional spring. Moreover, the spring 26 may comprise of various shapes, sizes, and elasticity.

According to an embodiment, the container 28 is a hollow body for housing items therein. Specifically, the container 28 is a small or medium canister that is approximately one-third of the size of the aerial vehicle 01 with the foldable wing arrangement 04 in a unfolded state. Further, the container 28 includes the various shape and is made of various material. In a example, the container 28 may be cylindrical in shape and may be made of light weight polymer.

According to an embodiment, the aerial vehicle 01 comprises an assembly of electrical components 25. Specifically, the assembly of electrical components 25 is coupled to the fuselage 02 of the aerial vehicle 01. Furthermore, the assembly of electrical components 25 is operable to detect and/or to measure physical parameters of a targeted location and capture image of the targeted location. Specifically, the targeted location includes an area, and the physical parameters include the temperature and the pressure of the area. Furthermore, the assembly of electrical components 25 includes at least one of a sensor, a beacon, a camera and a micro controller. Additionally, the sensor includes air pressure sensor, temperature sensor, Pitot tube sensor. Further, the assembly of electrical components 25 includes a camera capture image of the targeted location. Moreover, the assembly of electrical components 25 includes GPS for locating the aerial vehicle 01. Furthermore, the assembly of electrical components 25 includes Arduino® to consider input from the sensors and relay the inputs to a base station

According to an embodiment, the assembly of electrical components 25 communicates with the base station. Further, the electrical components 25 communicates with the base station via. an individual network, or a collection of individual networks, interconnected with each other and functioning as a single large network. Such individual networks may be wired, wireless, or a combination thereof. Examples of such individual networks include, but are not limited to, Local Area Networks (LANs), Wide Area Networks (WANs), Metropolitan Area Networks (MANs), Wireless LANs (WLANs), Wireless WANs (WWANs), Wireless MANs (WMANs), the Internet, second generation (2G) telecommunication networks, third generation (3G) telecommunication networks, fourth-generation (4G) telecommunication networks, and Worldwide Interoperability for Microwave Access (WiMAX) networks. Furthermore, the aerial vehicle 01 is communicating with the base station continuously and sends the information gathered through the assembly of electrical components 25.

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. Furthermore, the foldable wing arrangement of the aerial vehicle may fit into a small container when folded. Moreover, the aerial vehicle may be used to capture images of target areas and measure various parameters like temperature, the pressure at different altitude. Additionally, the aerial vehicle follows the circular path flight path with a smooth landing. The foldable wing arrangement is so thought that it could be confined to a minimum space and allows a large wing span that helps in gliding. Moreover, the aerial vehicle provides a rigid portion which supports the weight of over mounted elements like solar sheets efficiently 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.