Claims:We claim,
1. An unmanned aerial vehicle (UAV) (100) comprising:
a fuselage (101);
a tail connected to the fuselage (101);
a wing (103) attached to the fuselage (101), wherein the wing (103) comprises a plurality of I-sections (119); and
at least one battery (107) removably attached to the plurality of I-sections (119), via at least one battery fixture.
2. The UAV (100) of claim 1, wherein the battery fixture comprises a battery base plate (111) and a battery plate (109) attached to the plurality of I-sections (119).
3. The UAV (100) of claim 2, wherein the battery plate (109) corresponds to a continuous plate consisting of at least one hole of a size greater than a size of the at least one battery (107).
4. The UAV (100) of claim 2, wherein the battery base plate (111) is configured to hold the at least one battery (107).
5. The UAV (100) of claim 2, wherein the battery base plate (111) includes a plurality of weight reduction holes to reduce a weight of the UAV (100), and surface area to hold the at least one battery (107).
6. The UAV (100) of claim 2, wherein the battery base plate (111) and the battery plate (109) are connected via at least two bolts and at least two nuts.
7. The UAV (100) of claim 2, wherein the plurality of I-sections (119) includes at least one slot (121) to provide attachment points for the battery plate (109).
8. The UAV (100) of claim 1, wherein the plurality of I-sections (119) is configured to withstand additional loading from the at least one battery (107).
9. The UAV (100) of claim 1, further comprising an electric propulsion system.
10. The UAV (100) of claim 1, wherein the at least battery (107) corresponds to one of a lithium-ion battery, a lithium polymer battery, a nickel metal hydride battery, or a zinc-bromide flow battery.
, Description:PREAMBLE TO THE DESCRIPTION:
The following specification particularly describes the invention and the manner in which it is performed.
DESCRIPTION OF THE INVENTION:
Technical Field of the Invention
[0001] The present disclosure generally relates to an unmanned aerial vehicle (UAV). In particularly, the present disclosure relates to the UAV with batteries placed in wings of the UAV.
Background of the Invention
[0002] Unmanned aerial vehicles (UAVs) are remotely piloted or self-piloted aircraft that can carry communications equipment, cameras, sensors, or other payloads. The UAVs may fly autonomously based on pre-programmed flight plans or complex dynamic automation systems. Additionally or alternatively, the UAVs may be remotely controlled. With rapid advancements in the UAVs, the UAVs are employed for various applications where the use of manned flight vehicles is not appropriate or is not feasible. Such applications may include military situations, such as surveillance, reconnaissance, target acquisition, data acquisition, communications relay, or supply flights. Currently, a wide variety of UAV shapes, sizes, and configurations exist. However, performance of the existing UAVs is limited or suboptimal due to characteristics such as high drag, low-endurance, and complex design of the UAV.
[0003] Accordingly, there is a need for a configuration of the UAV that improves the performance of the UAV.
Summary of the invention
[0004] In order to solve the foregoing problem, the present disclosure provides an unmanned aerial vehicle (UAV) with batteries integrated in wings of the UAV. According to some embodiments, the UAV comprises a fuselage, a tail connected to the fuselage, and a wing attached to the fuselage, wherein the wing comprises a plurality of I-sections. The UAV further comprises at least one battery removably attached to the plurality of I-sections, via at least one battery fixture.
[0005] According to some embodiments, the battery fixture comprises a battery base plate and a battery plate attached to the plurality of I-sections.
[0006] According to some embodiments the battery plate corresponds to a continuous plate consisting of at least one hole of a size greater than a size of the at least one battery.
[0007] According to some embodiments, the battery base plate is configured to hold the at least one battery.
[0008] According to some embodiments, the battery base plate includes a plurality of weight reduction holes to reduce the weight of the UAV. According to some embodiments, the battery base plate and the battery plate are connected via at least two bolts and at least two nuts.
[0009] According to some embodiments the plurality of I-sections includes at least one slot each to provide attachment points for the battery plate.
[0010] According to some embodiments, the plurality of I-sections is configured to withstand additional loading from the at least one battery.
[0011] According to some embodiments, the UAV further comprises an electric propulsion system.
[0012] According to some embodiments, the at least one battery may be, for example, a lithium-ion battery, a lithium polymer battery, a Lithium Iron Phosphate Battery, a nickel metal hydride battery, or a zinc-bromide flow battery.
Object of the invention
[0013] It is an objective of some embodiments to utilize the empty space in wing of an unmanned aerial vehicle (UAV) to increase the amount of battery carried onboard an UAV. It is also an objective of some embodiments to provide a design of a battery fixture using which the batteries can be placed in the wing of the UAV. Additionally, it is an objective of some embodiments to reduce drag and weight of the UAV to improve endurance of the UAV, so that the UAV can be configured to fly longer distances or for a longer duration. Additionally, or alternatively, it is object of some embodiments to improve performance of the UAV without affecting handling quality.
[0014] These and other objects and characteristics of the present invention will become apparent from the further disclosure to be made in the detailed description given below.
Brief Description of Drawings
[0015] The foregoing and other aspects of embodiments will become more apparent from the following detailed description of embodiments when read in conjunction with the accompanying drawings. In the drawings, like reference numerals refer to like elements.
[0016] In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It is apparent, however, to one skilled in the art that the embodiments of the invention may be practiced without these specific details or with an equivalent arrangement. In other instances, well-known structures and devices are shown in block diagram form in order to avoid unnecessarily obscuring the embodiments of the invention.
[0017] FIG. 1A shows a perspective view of an unmanned aerial vehicle (UAV), according to one embodiment of the present disclosure.
[0018] FIG. 1B shows a schematic for placement of batteries in wing of the UAV, according to one embodiment of the present disclosure.
[0019] FIG. 1C shows exemplary I-sections, according to one embodiment of the present disclosure.
[0020] FIG. 2 shows a bottom view of the wing incorporated with the batteries, according to one embodiment of the present disclosure.
Detailed Description of the Invention
[0021] Reference will now be made in detail to the description of the present subject matter, one or more examples of which are shown in figures. Each example is provided to explain the subject matter and not a limitation. Various changes and modifications obvious to one skilled in the art to which the invention pertains are deemed to be within the spirit, scope and contemplation of the invention.
[0022] The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any aspect described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other aspects.
[0023] FIG. 1A shows a perspective view of an unmanned aerial vehicle (UAV) (100), according to one embodiment of the present disclosure. The term unmanned aerial vehicle, as used herein, refers to a variety of winged pilotless air vehicles. The term unmanned aerial vehicle, as used herein, may also refer to remotely-piloted airplanes, such as drones.
[0024] The UAV (100) includes a fuselage (101). The fuselage (101) encloses different components of the UAV (100). For example, the fuselage (101) may include electricity-consuming components and a payload. The electricity-consuming components may include electronics and electrical equipment, such as a radar equipment, communications equipment, electro-optical and other types of sensors, flight control actuators, and a radar jamming equipment. The payload may include any components or equipment to be carried by the UAV (100). For instance, if the UAV (100) is a reconnaissance vehicle, the payload may include a camera equipment or sensors. There may be many possible payloads for the UAV (100), depending on the mission profile the UAV (100) is expected to complete. The UAV (100) further includes wing (103) attached to the fuselage (101). Additionally, the UAV (100) includes a tail (105) attached to the fuselage (101). The UAV (100) may include other components that make up these different structures. For example, the fuselage (101), the wing (103), and the tail (105) may include ribs, spars, cords, fairings, skin panels, and other structural components.
[0025] Further, in some embodiments, the UAV (100) includes an electric propulsion system. The electric propulsion system is configured to propel the UAV (100). The electric propulsion system may include an electric motor and a blade unit. The blade unit may, for example, include a ducted fan, a propeller, or some other suitable type of blade unit configured to impart momentum to surrounding air producing thrust energy. It is to be noted that a general configuration of the UAV (100) shown in FIG. 1A is an example for illustration purposes only, and shape, location, and/or other characteristics of various parts of the UAV (100) may be suitably varied.
[0026] Further, in some embodiments, the UAV (100) includes batteries. The batteries may be connected to the electricity-consuming components to provide electrical energy for operating the electricity-consuming components. According an embodiment, the batteries can be placed in the wing (103). For instance, the batteries may be placed in the wing (103) as described below with reference to FIG. 1B.
[0027] FIG. 1B shows a schematic for placement of batteries (107) in the wing (103), according to one embodiment of the present disclosure. The batteries (107) may include one or more of a lithium-ion battery, a lithium-ion polymer battery, a nickel metal hydride battery, a zinc-bromide flow battery, and the like. The wing (103) may include an internal structure (117) that comprises of spars, ribs, and stringers. Since it is intended to place the batteries (107) in the wing (103), the wing (103) needs to withstand weight of the batteries (107). To that end, in an embodiment, the internal structure (117) of the wing (103) is provided with I-sections that run through the wing (103).
[0028] FIG. 1C shows exemplary I-sections (119), according to one embodiment of the present disclosure. FIG. 1B and FIG. 1C are explained in conjunction with each other. The I-sections (119) act as main load bearing structures apart from leading-edge spar, to withstand wing loading that is acting on the UAV (100). A size of I-sections (119) is determined based on the weight it should support. The I-sections (119) include slots (121). The slots (121) are cut in such a manner that a tensile edge of the I-sections (119) is away from the slots (121), thereby the slots (119) don’t propagate into crack. During wing flexure, a compressive side of the I-sections (119) clenches more onto the ribs for better rigidity.
[0029] The batteries (107) may be removably attached to the I-sections (119), via a battery fixture. The battery fixture comprises a battery plate (109) and a battery base plate (111). The battery plate (109) may be attached to the I-sections (119). In particular, the slots (121) of the I-sections (119) act as attaching points for the battery plate (109), and the battery plate (109) may be fixed to the I-sections (119) at the slots (121). The batteries (107) are attached to the battery plate (109) fixed to the I-sections (119).
[0030] According to some embodiments, the battery plate (109) attached to the I-sections (119) also assists in reducing bending/flexure stresses, which the I-sections (119) experience at a bottom part of the wing (103), by providing additional tensile strength. Also, the entire weight of the batteries (119) may be transferred to root by the I-sections (119).
[0031] In an embodiment, the battery plate (109) may correspond to a continuous plate consisting of holes, wherein each hole is of a size greater than the size of the battery. Such a configuration allows the batteries (119) fixed to the battery base plate to be able to slide in to the wing and provide an attachment for the battery base plate attached to the I-sections (119). The battery plate (109) is made of any material strong enough to hold the load of the batteries (107). For example, the battery plate (109) may be made of materials such as, but not limited to, wood or aluminium.
[0032] The battery plate (109) and the battery base plate (111) are connected via bolts (113) and nuts (115). In an embodiment, the battery plate (109) and the battery base plate (111) are connected via M3 bolts and M3 nuts. The battery base plate (111) provides rigidity to the internal structure (117) and holds the batteries (107) up in the wing (103) rather than letting the batteries (107) rest on wing skin or outer surface. Further, in an embodiment, the battery base plate (111) includes weight reduction holes to reduce the weight of the UAV (100) and maximising the surface area to hold the batteries (107). The battery base plate (111) may be made of any material strong enough to hold the load of the batteries (119). For example, the battery plate (109) may be made of materials such as, but not limited to, wood or aluminium.
[0033] The battery fixture, comprising the battery plate (109) and the battery base plate (111), may be custom designed for dimensions of the battery that is to be used for the UAV (100). In an embodiment, a common design of the batteries (107) for the UAV (100) is selected during initial sizing estimates, which in turn provides a base plate dimensions for placing the batteries (107). When required, the batteries (107) can be placed and secured upon battery base plates equally distributed on either wing to maintain weight balance of the UAV (100).
[0034] FIG. 2 shows a bottom view (200) of the wing (103) incorporated with the batteries (107), according to one embodiment of the present disclosure.
[0035] Such a design of placing the batteries (107) in the wing (103) allows utilizing an empty space in the wing (103) to increase amount of battery carried onboard the UAV. The increase in the battery mass and power enables the UAV (100) to fly longer distances or for a longer duration. Thereby, endurance of the UAV (100) is improved. Additionally, since the batteries (107) are placed in the wing (103) instead of placing in the fuselage (101), fuselage size and frontal area opposing the airflow over the UAV (100) may be reduced, thereby decreasing overall drag and structural weight of the UAV (100). The decrease in the overall drag increases the endurance of the UAV (100) which in turn reduces operational costs.
[0036] Further, more efficient use of space is provided, with the ability to locate additional equipment within the fuselage (101), or to make the fuselage (101) smaller, due to the placement of the batteries (107) within the wings. Certain components such as heat insulation or batteries within the fuselage (101) may be omitted, thus resulting in a savings of size, weight, cost, and complexity.
[0037] Furthermore, the placement of additional weights (i.e., the weight of the batteries (107)) in the wing (103) and close to root section, reduces the flex of the wing (103). Thus, the risk of ‘flapping’ during flight may be reduced. Additionally, the placement of the additional weights does not affect longitudinal static stability characteristics of the UAV (100), as the additional weight is along wing span and placed relatively close to a CG position. To that end, ability of the UAV (100) to fly further is increased without affecting the longitudinal stability of the UAV (100).
[0038] The proposed design of placing the batteries (107) in the wing (103), as described above, allows easy replacement and/or the servicing of the batteries (107), without a need for opening or disassembling the fuselage (101). In addition, battery capacity can be varied based on a mission requirements for the UAV (100). For example, if the UAV (100) needs to be configured for a flight duration of one hour, then one or more batteries of capacity required for the one-hour flight duration may be placed. Likewise, if the UAV (100) needs to be configured for a flight duration of ten hours, then one or more batteries of capacity required for the ten hours flight duration may be placed. This makes the UAV (100) adaptable to different mission profiles, thus providing versatility to the UAV (100).
[0039] In some embodiments, solar cells may be placed on the wing (103). Since the batteries (107) are placed in the wing (103), the distance between the solar cells and the batteries (107) is decreased. Thereby, impendence loss during recharging the batteries (107) in flight is reduced, thus improving charge characteristics. In addition, by placing the batteries (107) away from GNC (guidance, navigation, Control) avionics placed in the fuselage (101), electro-magnetic interference (EMI) is reduced.
[0040] Therefore, the embodiments of the present invention significantly improve the performance of the UAV (100).
[0041] The many features and advantages of the invention are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of the invention which fall within the true spirit and scope of the invention. Further, since numerous modifications and variations will readily occur to those skilled in the art, it is not desired to limit the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the invention.