WO2019058312A1

WO2019058312A1 - A maneuverable aerial floating solar structure

Info

Publication number: WO2019058312A1
Application number: PCT/IB2018/057283
Authority: WO
Inventors: Ravi Shankar
Original assignee: Ravi Shankar
Priority date: 2017-09-25
Filing date: 2018-09-21
Publication date: 2019-03-28

Abstract

The present disclosure relates to the field of maneuverable aerial floating solar structure which is mobile in nature, and is simple in configuration. The structure comprises a balloon, a flexible solar panels, a support arrangement, a fuselage, a plurality of arms, and a plurality of propellers. A floating media is entrapped within the balloon. The flexible solar panels is securely disposed on the balloon. The flexible solar panels includes a plurality of solar panels coupled with each other by a coupling means, and is further configured to generate a solar power. The support arrangement is configured at an operative bottom of the balloon. The fuselage is coupled to the support arrangement via a plurality of support cables. The plurality of arms is coupled to the fuselage and each of the propeller is mounted on a free end of each of the arms.

Description

A MANEUVERABLE AERIAL FLOATING SOLAR STRUCTURE

THIS APPLICATION IS A PATENT OF ADDITION TO INDIAN PATENT APLLICATION NO. 201721014708 FILED ON APRIL 25^th, 2017.

FIELD The present disclosure relates to the field of solar panels. More specifically, the present disclosure relates to the field of maneuverable aerial floating solar structure.

BACKGROUND

Indian patent application number 201721014708 discloses a floating solar structure which is used for supplying power to a remotely located load. The floating solar structure, as disclosed in Indian patent application number 201721014708, uses a balloon, a floating media, a flexible solar panel, and a support arrangement. The flexible solar panel is securely disposed on the balloon which contains the floating media entrapped therewithin. The support arrangement is configured at an operative bottom of the balloon to securely hold the flexible solar panel on the balloon. However, the floating solar structure, of Indian patent application number 201721014708, is kept stationary by means of an anchor.

There is, therefore, felt a need to provide a maneuverable aerial floating solar structure. OBJECTS

Some of the objects of the present disclosure, which at least one embodiment herein satisfies, are as follows:

An object of the present disclosure is to provide a maneuverable aerial floating solar structure.

Another object of the present disclosure is to provide a maneuverable aerial floating solar structure, which is mobile in nature and provides an economical mode of transport. Yet another object of the present disclosure is to provide a maneuverable aerial floating solar structure, which is cost effective. Still another object of the present disclosure is to provide a maneuverable aerial floating solar structure, which provides multiple layers of safety.

Yet another object of the present disclosure is to provide a maneuverable aerial floating solar structure, which has simple configuration. Other objects and advantages of the present disclosure will be more apparent from the following description, which is not intended to limit the scope of the present disclosure.

SUMMARY

The present disclosure envisages a maneuverable aerial floating solar structure comprising a floatable balloon, a plurality of flexible solar panels, a fuselage, and a maneuvering unit. In an embosiment, a floating media is entrapped within the floatable balloon to levitate the floatable balloon above the ground. In another embodiment, the floating media is a helium gas.

The plurality of flexible solar panels is securely disposed on the floatable balloon and is configured to generate a solar power. Each of the solar panels is coupled with each other by a coupling means. In an embodiment, the shape of the solar panels is selected from the group consisting of a hexagon, a square, a rectangle, a triangle, a circle, a trapezoid, and any geometrical or non-geometrical shape thereof. In another embodiment, the coupling means have at least one O-ring.

The fuselage is coupled to the floatable balloon. The maneuvering unit is configured to provide mobility to the structure. The maneuvering unit includes a plurality of arms, a plurality of propellers and a swiveling mechanism. The plurality of arms is coupled to the fuselage and each of the propellers is mounted on a free end of each of the arms. The swiveling mechanism is configured to angularly displace the arms at a pre-defined angle with respect to the fuselage to provide controlled mobility of the structure in a desired direction. In an embodiment, the fuselage includes an input means and a control unit. The input means is configured to receive at least one operating command from an operator, and further configured to generate at least one operating signal. The control unit is configured to cooperate with the input means to receive at least one operating signal, and is further configured to generate a navigating signal to determine navigating propellers from the plurality of propellers. The control unit is configured to control the mobility of the structure by controlling the navigating propellers.

In another embodiment, the control unit is configured to generate a power generation signal to control the operation of the non-navigating propellers from the plurality of propellers. The non-navigating propellers are configured to generate an auxiliary power.

In still another embodiment, a power supply unit is configured to provide power to the plurality of propellers and is further configured to be charged by at least one of the solar power and the auxiliary power.

In yet another embodiment, an emergency landing unit is configured to detect malfunctioning of the structure, and is further configured to facilitate controlled landing of the fuselage upon detection of malfunctioning of the structure. The emergency landing unit is configured to deploy a first set of parachutes in the event of malfunctioning of the structure. The emergency landing unit includes deployment of a second set of parachutes subsequent to the failure of the first set of parachutes, and deployment of a third parachute subsequent to the failure of the second set of parachutes.

In still another embodiment, a support arrangement is configured at an operative bottom of the floatable balloon. In an embodiment, the support arrangement includes a pair of spaced apart rings interconnected via a plurality of wires and a plurality of support cables. A first ring of the pair of rings is configured to securely hold the flexible solar panels on the floatable balloon. A second ring is configured to provide mechanical coupling to the fuselage with the balloon via the plurality of support cables.

BRIEF DESCRIPTION OF THE ACCOMPANYING DRAWING

The maneuverable aerial floating solar structure, of the present disclosure will now be described with the help of the accompanying drawing, in which: Figure 1 illustrates an isometric view of a maneuverable aerial floating solar structure;

Figure 2 illustrates a side view of the maneuverable aerial floating solar structure of Figure

1; Figure 3 illustrates a bottom view of the maneuverable aerial floating solar structure of Figure 1;

Figure 4 illustrates an isometric view of a plurality of flexible solar panels mounted on the maneuverable aerial floating solar structure of Figure 1; and

Figure 5 illustrates an operative top portion of the maneuverable aerial floating solar structure of Figure 1.

LIST OF REFERENCE NUMERALS

100 - Structure

102 - Balloon

104 - Support Arrangement

106 - Support Cables

108 - Flexible Solar Panels

108a - Solar Panels

108b - Coupling Means

110 - Fuselage

112 - Propellers

114 - Loop

116 - Wheels

118 - Arms

120 - First Set Of Parachutes

122 - Second Set Of Parachutes

124 - Third Parachute

202 - First Ring 204 - Second Ring

206 Wires

DETAILED DESCRIPTION

The present disclosure envisages a maneuverable aerial floating solar structure. An embodiment of the maneuverable aerial floating solar structure, of the present disclosure is now being described with reference to the accompanying drawing. The description provided is purely by way of example and illustration.

An embodiment of the maneuverable aerial floating solar structure, of the present disclosure is now being described in detail with reference to Figure 1 through Figure 5. Figure lillustrates an isometric view of a maneuverable aerial floating solar structure 100.

Figure 2 illustrates a side view of the maneuverable aerial floating solar structure 100.

Figure 3 illustrates a bottom view of the maneuverable aerial floating solar structure 100.

Figure 4 illustrates an isometric view of a plurality of flexible solar panels 108 mounted on the maneuverable aerial floating solar structure 100. Figure 5 illustrates an operative top portion of the maneuverable aerial floating solar structure 100.

The maneuverable aerial floating solar structure 100 (hereinafter referred as "structure 100") comprises a floatable balloon 102 (hereinafter also referred as "balloon 102"), a plurality of flexible solar panels 108, a support arrangement 104, a fuselage 110, and a maneuvering unit (not shown in figures). A floating media is entrapped within the balloon 102. In an embodiment, the floating media is a helium gas.

The plurality of flexible solar panels 108 is securely disposed on the balloon 102. The flexible solar panels 108 are configured to generate a solar power. Each flexible solar panels 108 are coupled to each other by a coupling means 108b, thereby providing flexibility. In an embodiment, the shape of the solar panels 108a is selected from the group consisting of a hexagon, a square, a rectangle, a triangle, a circle, a trapezoid, and any geometrical or non- geometrical shape thereof. In another embodiment, the coupling means 108b have at least one O-ring. The support arrangement 104 is configured at an operative bottom of the balloon 102. In an embodiment, the support arrangement 104 includes a pair of spaced apart rings (202, 204) interconnected via a plurality of wires 206, and a plurality of the support cables. A first ring 202, of the pair of rings (202, 204), is configured to securely hold the plurality of flexible solar panels 108 which are mounted on the balloon 102. A second ring is configured to provide mechanical coupling to the fuselage 110 with the balloon 102 via the plurality of support cables 106. In an embodiment, at least one loop 114 is configured at an operative bottom of the support arrangement 104. The at least one support cable 106 is secured to the at least one loop 114, thereby enabling the mechanical coupling of the balloon 102 with the fuselage 110.

The maneuvering unit includes a plurality of arms 118, a plurality of propellers 112 and a swiveling mechanism. The plurality of arms is coupled to the fuselage 110. Each propeller 112 is mounted on a free end of each of the arms 118. The plurality of arms 118 is configured to securely support the plurality of propellers 112. The plurality of propellers 112 is configured to provide controlled mobility, take-off, and landing of the structure 100.

In an embodiment, the fuselage 110 includes an emergency landing unit (not shown in figures), an input means (not shown in figures), a control unit (not shown in figures), a release mechanism (not shown in figures), a plurality of control panels (not shown in figures), a cockpit (not shown in figures), a pantry (not shown in figures), at least one lavatory (not shown in figures), and a plurality of seating arrangements (not shown in figures).

In an operative configuration, the input means is configured to receive at least one operating command by a remote device, from an operator and is further configured to generate at least one operating signal. The control unit is configured to cooperate with the input means to receive at least one operating signal. The control unit is further configured to generate a navigating signal to determine navigating propellers 112 from the plurality of propellers 112. The swiveling mechanism is configured to angularly displace the arms 118 of the structure at a pre-defined angle with respect to the fuselage 110, based on the navigating signal. The control unit is configured to control the mobility of the structure in a desired direction during propulsion, by controlling the operation of the navigating propellers. In an embodiment, the control unit is also configured to generate a power generation signal and further configured to control the operation of non-navigating propellers from the plurality of propellers 112, to generate an auxiliary power.

Further, the fuselage 110 includes a power supply unit (not shown in figures). The power supply unit includes at least one battery. At least one battery is further configured to provide power to the plurality of propellers 112. The at least one battery is further configured to be charged by at least one of the solar power and the auxiliary power. In an embodiment, the solar power generated by the plurality of flexible solar panels 108 and the auxiliary power generated by non-navigating propellers, is supplied to the battery by means of an electrically conductive cable (not shown in figures).

The emergency landing unit is configured to detect malfunctioning of the structure 100. When the malfunctioning of the structure 100 is detected, the release mechanism is configured to detach the fuselage 110 from the support arrangement 104, thereby releasing the fuselage 110. Once the fuselage 110 is released from the support arrangement 104, the emergency landing unit gets activated. In an embodiment, the emergency landing unit includes a first set of parachutes 120, a second set of parachutes 122, and a third parachute 124. The emergency landing unit is configured to facilitate steady landing of the fuselage 110. Each of the first set of parachutes 120, the second set of parachutes 122, and the third parachute 124 are housed within a plurality of housing configured at an operative top surface of the fuselage 110. In an embodiment, the first set of parachutes 120 and the second set of parachutes 122 are alternately arranged along the periphery of the fuselage 110. In another embodiment, the third parachute 124 is centrally located with respect to the fuselage 110.

In an operative configuration, initially when the malfunctioning of the structure is detected by the emergency landing unit, the first set of parachutes 120 are deployed wherein the first set of parachutes is configured to facilitate steady landing of the fuselage 110. In an embodiment, in an event of failure or malfunctioning of the first set of parachutes 120, the second set of parachutes 122 are deployed. Further, in an event when the second set of parachutes 122 fails to control the landing of the fuselage 110, the third parachute 124 is deployed.

In an embodiment, the fuselage also includes a surveillance unit (not shown in the figures). The surveillance unit may include at least one camera. The at least one camera is configured to capture and monitor the activities on the ground such as behavior of traffic on the ground, military purpose applications and the like. In another embodiment, the at least one camera is selected from the group consisting of an infrared camera, a day and night camera, and a PTZ (Pan, tilt and zoom) camera.

In an embodiment, a plurality of wheels 116 is coupled to the operative bottom of the fuselage 110. The plurality of wheels 116 is connected to the fuselage 110 via a suspension mechanism (not shown in the figures). The suspension mechanism is configured to provide the cushioning effect and bear the load of the structure 100 during take-off and landing. In an operative configuration, the plurality of wheels 116 is configured to retract after takeoff and retrieve before landing. The structure 100 of the present disclosure is cost effective, simple in configuration, and also provides an economical mode of aerial transport.

TECHNICAL ADVANCEMENTS

The present disclosure described herein above has several technical advantages including, but not limited to, the realization of a maneuverable aerial floating solar structure that: · is mobile in nature;

• is cost effective;

• provides an economical mode of transport;

• provides multiple layer of safety; and

• has simple configuration. The embodiments herein and the various features and advantageous details thereof are explained with reference to the non-limiting embodiments in the following description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein. The foregoing description of the specific embodiments will so fully reveal the general nature of the embodiments herein that others can, by applying current knowledge, readily modify and/or adapt for various applications such specific embodiments without departing from the generic concept, and, therefore, such adaptations and modifications should and are intended to be comprehended within the meaning and range of equivalents of the disclosed embodiments. It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the embodiments as described herein.

Throughout this specification the word "comprise", or variations such as "comprises" or "comprising", will be understood to imply the inclusion of a stated element, integer or step, or group of elements, integers or steps, but not the exclusion of any other element, integer or step, or group of elements, integers or steps. The use of the expression "at least" or "at least one" suggests the use of one or more elements or ingredients or quantities, as the use may be in the embodiment of the disclosure to achieve one or more of the desired objects or results.

Any discussion of documents, acts, materials, devices, articles or the like that has been included in this specification is solely for the purpose of providing a context for the disclosure. It is not to be taken as an admission that any or all of these matters form a part of the prior art base or were common general knowledge in the field relevant to the disclosure as it existed anywhere before the priority date of this application.

While considerable emphasis has been placed herein on the components and component parts of the preferred embodiments, it will be appreciated that many embodiments can be made and that many changes can be made in the preferred embodiments without departing from the principles of the disclosure. These and other changes in the preferred embodiment as well as other embodiments of the disclosure will be apparent to those skilled in the art from the disclosure herein, whereby it is to be distinctly understood the foregoing descriptive matter is to be interpreted merely as illustrative of the disclosure and not as a limitation.

Claims

CLAIMS:

1. A maneuverable aerial floating solar structure (100) comprising:

• a floatable balloon ( 102) ;

• a plurality of flexible solar panels (108) securely disposed on said floatable balloon (102), and configured to generate a solar power;

• a fuselage (110) coupled to said floatable balloon (102); and

• a maneuvering unit configured to provide mobility to said structure, said maneuvering unit includes:

I. a plurality of arms (118) coupled to said fuselage (110);

II. a plurality of propellers (112), wherein each of said propellers (112) is mounted on a free end of each of said arms (118); and

III. a swiveling mechanism configured to angularly displace said arms

(118) at a pre-defined angle with respect to said fuselage (110) to provide controlled mobility to said structure (100) in a desired direction.

2. The structure (100) as claimed in claim 1, wherein said fuselage (110) includes:

• an input means configured to receive at least one operating command from an operator, and further configured to generate at least one operating signal; and

• a control unit configured to cooperate with said input means to receive said at least one operating signal, and further configured to generate a navigating signal to determine navigating propellers from said plurality of propellers (112), said control unit configured to control the mobility of said structure (100) by controlling said navigating propellers (112).

3. The structure (100) as claimed in claim 2, wherein said control unit is configured to generate a power generation signal, to control the operation of non-navigating propellers from said plurality of propellers (112), wherein said non-navigating propellers are configured to generate an auxiliary power.

4. The structure (100) as claimed in claim 3, which includes a power supply unit configured to provide power to said plurality of propellers (112), and further configured to be charged by at least one of said solar power and said auxiliary power.

5. The structure (100) as claimed in claim 1, which includes an emergency landing unit configured to detect malfunctioning of said structure (100), and further configured to facilitate controlled landing of said fuselage (110) upon detection of malfunctioning of said structure (100), wherein said emergency landing unit is configured to deploy:

• a first set of parachutes (120) in the event of malfunctioning of said structure (100);

• a second set of parachutes (122) subsequent to failure of said first set of parachutes (120); and

• a third parachute (124) subsequent to failure of said second set of parachutes (122).

6. The structure (100) as claimed in claim 1, which includes a support arrangement (104) configured at an operative bottom of said floatable balloon (102), said support arrangement (104) includes:

• a pair of spaced apart rings (202, 204) interconnected via a plurality of wires (206); and

• a plurality of support cables (106),

wherein, a first ring (202) of said pair of rings (202, 204) is configured to securely hold said flexible solar panels (108) on said floatable balloon (102), and a second ring (204) of said pair of rings (202, 204) is configured to provide mechanical coupling to said fuselage (110) with said floatable balloon (102) via said plurality of support cables (106).

7. The structure (100) as claimed in claim 1, which includes a floating media entrapped within said floatable balloon (102) to levitate said floatable balloon (102) above the ground, wherein said floating media is a helium gas.

8. The structure (100) as claimed in claim 1, wherein the shape of said flexible solar panels (108a) is selected from the group consisting of a hexagon, a square, a rectangle, a triangle, a circle, a trapezoid, and any geometrical or non-geometrical shape thereof.

9. The structure (100) as claimed in claim 1, wherein each of said flexible solar panels (108) are coupled with each other by a coupling means (108b).

10. The structure (100) as claimed in claim 9, wherein said coupling means (108b) has at least one O-ring.