Unmanned aerial vehicle wing pylon system

Abstract

To provide a system capable of corresponding to an additional weight and / or volume.SOLUTION: In one embodiment, systems and methods include an aerial vehicle comprising a body, a first wing coupled to the body, and a second wing coupled to the body, in which the second wing has a length greater than the first wing, the first wing and the second wing each comprise a plurality of segments, and the second wing comprises a wing pylon system. The wing pylon system comprises one of the plurality of segments of the second wing, a payload, and a pylon coupling the payload to the one of the plurality of segments, the pylon being disposed underneath the one of the plurality of segments, and the payload being disposed underneath the pylon. A center of lift and a center of gravity for the aerial vehicle are aligned and they are each offset from a central axis of the body.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present disclosure relates generally to unmanned aerial vehicles, and more specifically, to a WING PYLON SYSTEM for unmanned aerial vehicles. [Background technology]

[0002] Traditionally, internal combustion engines have been used to power aircraft. Unmanned aerial vehicles can use batteries and alternative power sources or generators to provide power for lower cost, less maintenance, and smaller system mass. The fuselage and wings of an aircraft are typically designed to support a desired weight and volume. Summary of the Invention [Problem to be solved by the invention]

[0003] However, as demands change, problems may arise with the additional required weight and / or volume.

[0004] For an aid in understanding the present disclosure, reference is made to the following descriptions taken in conjunction with the accompanying drawings, in which: [Brief description of the drawings]

[0005] [Figure 1] 1 illustrates an exemplary vehicle in accordance with certain embodiments. [Figure 2A] 2 illustrates an example wing pylon system for the example vehicle of FIG. 1 in accordance with certain embodiments. [Figure 2B] 2 illustrates an example wing pylon system for the example vehicle of FIG. 1 in accordance with certain embodiments. [Figure 3A] 1 illustrates a front view of an exemplary vehicle with an exemplary fuel system, in accordance with certain embodiments. [Figure 3B] 1 illustrates a front view of an exemplary vehicle with an exemplary fuel system, in accordance with certain embodiments. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0006] To aid in a better understanding of the present disclosure, the following examples of specific embodiments are provided. The following examples are not to be construed as limiting or defining the scope of the present disclosure. The embodiments of the present disclosure and its advantages are best understood by referring to Figures 1 through 3B, in which like numbers are used to indicate like and corresponding elements. Various systems and methods are described herein that enable the utilization of one or more batteries to provide electrical power and structural support to an aircraft.

[0007] FIG. 1 illustrates an exemplary vehicle 100. The vehicle 100 may be any suitable vessel configured for transportation, such as an aircraft. The vehicle 100 may include a body 102 (e.g., a fuselage), a first wing 104, and a second wing 106. As illustrated, both the first wing 104 and the second wing 106 may be coupled to the body 102, and the first wing 104 may be disposed opposite the second wing 106. The first wing 104 and the second wing 106 may extend laterally away from the body 102 and may be configured to generate lift for the vehicle 100. The vehicle 100 may be any suitable size, height, shape, and any combination thereof. In an embodiment, the body 102 may be cylindrical, and the first wing 104 and the second wing 106 may be generally rectangular. As illustrated, the vehicle 100 may further include a first tank 108.

[0008] The first tank 108 may be operable to contain or store fuel used to power the vehicle 100. Without limitation, the first tank 108 may be operable to contain any suitable volume of fuel, such as approximately 8.6 liters. In an embodiment, the fuel may be any suitable fluid for generating energy, such as propane. For example, the first tank 108 may be fluidly connected to the body 102 and operable to direct fuel to the body 102 to be consumed to generate energy. As shown, the first tank 108 may be disposed along the first wing 104. In one or more embodiments, the first tank 108 may alternatively be disposed along the second wing 106 instead of the first wing 104. The first tank 108 may be secured to the first wing 104 or the second wing 106 by any suitable method, including, without limitation, the use of fasteners, welding, adhesives, interlocking components, an interference fit, and any combination thereof. In embodiments, suitable fasteners may include studs, bolts, nuts, washers, screws, nails, rivets, brackets, clamps, etc. In one or more embodiments, first tank 108 may be configured to contain any suitable payload to be transported by vehicle 100, rather than containing fuel consumed by vehicle 100.

[0009] The first tank 108 may be offset from the body 102 by any suitable distance. The first tank 108 may be of any suitable size, height, shape, and any combination thereof. With reference to FIG. 1, the first tank 108 may be generally cylindrical. In an embodiment, the first tank 108 may be constructed of any suitable material, including, but not limited to, metal, non-metal, polymer, ceramic, composite material, and any combination thereof. Without being limited thereto, the first tank 108 may be constructed of a carbon fiber material. The first tank 108 may include a tail cone 110 disposed at a distal end of the first tank 108 configured to improve the aerodynamics of the airflow around the first tank 108 during flight of the vehicle 100.

[0010] As shown, the vehicle 100 may further include one or more ailerons 112, a first tail stabilizer 114, and a second tail stabilizer 116. The one or more ailerons 112 may be configured to deflect upward and downward. Each of the one or more ailerons 112 may be a hinged flight control surface that forms part of a trailing edge of a respective wing of the aircraft. The one or more ailerons 112 may be used in pairs to control the roll (or movement about the longitudinal axis of the aircraft) of the aircraft. For example, there may be at least one aileron 112a disposed on the first wing 104 and at least one aileron 112b disposed on the second wing 106. The ailerons 112a, 112b may operate as a pair such that as one is moved downward the other is moved upward, with a lowering aileron increasing the lift of its respective wing and a raising aileron decreasing the lift of its respective wing, creating a rolling moment about the longitudinal axis of the vehicle 100.

[0011] Each of the first tail stabilizer 114 and the second tail stabilizer 116 may be disposed aft or distal to the body 102 and may be fixably coupled to the body 102. In an embodiment, the first tail stabilizer 114 may be a horizontal stabilizer of the vehicle 100. The first tail stabilizer 114 may be used to maintain the longitudinal balance (or "pitch") of the vehicle 100. The first tail stabilizer 114 may exert a vertical force at a predetermined distance from the body 102 to obtain a desired sum of zero pitch moments about the center of gravity. The vertical force exerted by the first tail stabilizer 114 may vary with flight conditions, in particular according to wing deflections that affect the aircraft's lift coefficient and the location of the center of pressure, and with the location of the center of gravity (which may vary with the aircraft's load and fuel consumption). The second tail stabilizer 116 may be a vertical stabilizer. The second tail stabilizer 116 may provide directional (or "yaw") stability and may include a fixed fin and a movable control rudder hinged to the trailing edge of the fin.

[0012] Although this disclosure uses the example of vehicle 100 as an example application of the methods and systems described herein, this disclosure contemplates any suitable device or structure that may incorporate first tank 108. For example, vehicle 100 may be any type of vehicle, including an aircraft, a land craft, a water craft, a train, a hovercraft, and a helicopter.

[0013] 2A-2B illustrate an exemplary wing pylon system 200 for a vehicle 100 (see FIG. 1). The wing pylon system 200 may be a modular component configured to be integrated into the first wing 104 (see FIG. 1) and / or the second wing 106 (see FIG. 1). For example, the first wing 104 and / or the second wing 106 may be structurally comprised of multiple segments (described further below) that span the length of the respective wing and make up the configuration of the wing. In one or more embodiments, the wing pylon system 200 may be designated as one of the multiple segments and incorporated into the first wing 104 and / or the second wing 106.

[0014] As shown, the wing pylon system 200 may comprise a wing segment 202, a payload 204, and a pylon 206. The wing segment 202 may be a portion of the first wing 104 or the second wing 106. The wing segment 202 may comprise any suitable length of the first wing 104 or the second wing 106. In an embodiment, the first wing 104 and / or the second wing 106 may be divided or sectioned into a plurality of segments (where the wing segment 202 is one of the plurality of segments) that are coupled or secured together to form the wing structure. The wing segment 202 may be configured to be substantially the same or similar in size as the remaining plurality of segments. The wing segment 202 may be configured to couple to the body 102 (see FIG. 1 ) of the vehicle 100 and / or to the remaining plurality of segments for either the first wing 104 or the second wing 106. In an embodiment, the wing segment 202 may be coupled and securely assembled within the first wing 104 or the second wing 106 by any suitable method including the use of fasteners, welding, adhesives, interconnecting components, interference fits, and any combination thereof. In an embodiment, suitable fasteners may include studs, bolts, nuts, washers, screws, nails, rivets, brackets, clamps, etc.

[0015] In an embodiment, the pylon 206 may be located under the wing segment 202. In one or more embodiments, the pylon 206 may be located about any other suitable location along the wing segment 202, such as above, in front of, or behind the wing segment 202. The pylon 206 may be configured to connect the frame of the aircraft (i.e., one of the first wing 104 or the second wing 106) to the article or object to be transported (such as the payload 204). In one or more embodiments, the pylon 206 may be secured to the underside of the wing segment 202 by one or more fasteners, by welding, or by a combination thereof. The pylon 206 may be aerodynamically designed to reduce air resistance. The pylon 206 may be of any suitable size, height, shape, and any combination thereof. In further embodiments, the pylon 206 may be constructed of any suitable material, including, but not limited to, metal, non-metal, polymer, ceramic, composite, and any combination thereof. The pylon 206 may be, but is not limited to, a wedge adapter or a stub wing pylon. The pylon 206 may be configured to securely attach the payload 204 to the vehicle 100.

[0016] In one or more embodiments, the payload 204 may be disposed beneath the pylon 206. In one or more embodiments, the payload 204 may be disposed about any other suitable location along the pylon 206. The payload 204 may be secured to the pylon 206 by one or more fasteners, by welding, or by a combination thereof. In an embodiment, the payload 204 may be the first tank 108 configured to contain fuel for the vehicle 100, as described above. In other embodiments, the payload 204 may not contain fuel consumed by the vehicle 100, but may be configured to contain any suitable payload to be transported by the vehicle 100. As with the first tank 108, the payload 204 may be any suitable size, height, shape, and any combination thereof. In further embodiments, the payload 204 may be constructed of any suitable material, including, but not limited to, metal, non-metal, polymer, ceramic, composite, and any combination thereof. As shown, payload 204 may include a tail cone 110 disposed at a distal end of payload 204 and configured to improve the aerodynamics of airflow around payload 204 during flight of vehicle 100. In an embodiment, tail cone 110 may extend away from payload 204.

[0017] 3A-3B show a comparison of front views of vehicle 100 with and without wing pylon system 200. For example, vehicle 100 depicted in FIG. 3A does not include wing pylon system 200, and vehicle 100 depicted in FIG. 3B includes wing pylon system 200. Further in this example, vehicle 100 in FIG. 3A may have three separate wing segments for each wing, and second wing 106 in FIG. 3B may have four separate wing segments, one of which is wing pylon system 200. In one or more embodiments, vehicle 100 may include a center of lift and center of gravity that typically coincides with central axis 300 of vehicle 100. By including first tank 108 (see FIG. 1) or some other similar payload, the center of gravity may be shifted laterally and offset from central axis 300, as shown in FIG. 3A. If the center of lift and center of gravity do not coincide, problems may occur in the operation of the vehicle 100, such as balance and stability of the vehicle 100. Rather than including the first tank 108, the vehicle 100 may incorporate the wing pylon system 200. By including the wing pylon system 200, the payload 204 (see FIGS. 2A-2B) may function as the first tank 108. Each wing incorporating the wing pylon system 200 may be configured with a greater length than a wing that does not incorporate the wing pylon system 200. For example, as shown in FIG. 3B, the second wing 106 incorporating the wing pylon system 200 may be configured with a greater length than the first wing 104. Furthermore, the integration of the wing pylon system 200 with the second wing 106 may increase the lift of the wing and move both the center of gravity and the center of lift in a symmetrical direction to balance the lift and weight of the vehicle 100.

[0018] The second wing 106 with the wing pylon system 200 can offset the effect of weight on the wing. In embodiments, if the load on a given wing is increased, that wing must work harder and fly faster, which creates more drag. The addition of the wing pylon system 200 can offset the effect of weight and keep the wing loading below or substantially the same as the wing loading of the original aircraft without the added load. In these embodiments, the vehicle 100 can further include a first tail stabilizer 114 (see FIG. 1 ) of increased size to accommodate the offset center of gravity and lift. For example, and without limitation, the area of ​​the second wing 106 of the vehicle 100 without the added load (i.e., without the first tank 108) is approximately 13.8 ft 2 . 2 (1.28m 2 ), the vehicle 100 weighs approximately 48 pounds (21.8 kg), and the second wing 106 has a wing loading of 3.5 pounds / ft 2 (17.1kg / m 2 For a vehicle 100 with additional loading, such as a first tank 108 attached to the second wing 106, the center of gravity is offset, the weight of the vehicle 100 increases to approximately 54 pounds (24.5 kg), and the wing loading of the second wing 106 is 3.9 pounds / ft 2 (19.0kg / m 2 For a vehicle 100 having a wing pylon system 200 included on the second wing 106, the area of ​​the second wing 106 may be approximately 15.8 ft 2 (1.47m 2 ), the vehicle 100 weighs approximately 54 pounds (24.5 kg), and the second wing 106 has a wing loading of 3.4 pounds / ft 2 (16.6kg / m 2 ) may occur.

[0019] The present disclosure may provide numerous advantages, such as various technical advantages, each of which has been described with respect to the various embodiments and examples disclosed herein. Other technical advantages will be readily apparent to those skilled in the art from the accompanying drawings, specification, and claims. Furthermore, although certain advantages are enumerated in the present disclosure, various embodiments may include all, some, or none of the enumerated advantages.

[0020] As used herein, "or" is inclusive and not exclusive, unless expressly indicated otherwise or relevantly implied otherwise. Thus, as used herein, "A or B" means "A, B, or both," unless expressly indicated otherwise or relevantly implied otherwise. Furthermore, "and" is jointly and severally, unless expressly indicated otherwise or relevantly implied otherwise. Thus, as used herein, "A and B" means "A and B, jointly or severally," unless expressly indicated otherwise or relevantly implied otherwise.

[0021] The scope of the present disclosure encompasses all changes, substitutions, variations, alterations, and modifications to the exemplary embodiments described or illustrated herein that would be understood by a person skilled in the art. The scope of the present disclosure is not limited to the exemplary embodiments described or illustrated herein. Moreover, although the present disclosure has been described and illustrated herein with each embodiment including certain components, elements, features, functions, operations, or steps, any of these embodiments may include any combination or permutation that would be understood by a person skilled in the art of any of the components, elements, features, functions, operations, or steps described or illustrated anywhere herein. Furthermore, in the claims, a reference to an apparatus or system or an apparatus or system component being adapted, arranged, including a function, configured, enabled, operable, or operating to perform a particular function includes the apparatus, system, component, or that particular function being activated, turned on, or unlocked, so long as the apparatus, system, or component is adapted, arranged, including a function, configured, enabled, operable, or operating. Additionally, although this disclosure describes or illustrates particular embodiments that provide certain advantages, a particular embodiment may provide none, some, or all of these advantages. [Explanation of symbols]

[0022] 100 Means of transportation 102 Main unit 104 First Wing 106 Second Wing 108 First Tank 110 Tail Cone 112 Aileron 112a 1st aileron 112b 2nd aileron 114 First Tail Stabilizer 116 Second tail stabilizer 200 Wing Pylon System 202 Wing Segment 204 Payload 206 Pylon 300 center axis

Claims

1. An unmanned aerial vehicle, The main unit and A first wing attached to the main body, A second wing, coupled to the main body and positioned opposite the first wing, wherein the second wing has a greater length than the first wing, and each of the first and second wings comprises a plurality of segments, and the second wing comprises a wing pylon system, Equipped with, The aforementioned wing pylon system is A wing segment which is one of the plurality of segments of a second wing, wherein the wing segment is positioned between the body and another of the plurality of segments of the second wing located at the distal end of the second wing, A tank configured to contain fuel used to supply sufficient power to the aforementioned unmanned aerial vehicle, wherein the fuel is propane, the tank and A pylon connecting the tank to the wing segment, wherein the pylon is positioned below the wing segment and the tank is positioned below the pylon, Equipped with, An unmanned aerial vehicle in which the center of lift and the center of gravity are offset from the central axis of the main body, and the center of lift and the center of gravity are aligned.

2. At least one aileron located on the first wing, configured to deflect upward and downward, The second wing comprises at least one aileron configured to deflect upward and downward, The unmanned aerial vehicle according to claim 1, further comprising:

3. The unmanned aerial vehicle according to claim 1, wherein the tank is configured to hold the fuel in a volume of about 8.6 liters.

4. A horizontal tail stabilizer is positioned at the rear of the main body and fixedly coupled to the main body, The system further comprises a vertical tail stabilizer positioned at the rear of the main body and fixedly coupled to the main body, The unmanned aerial vehicle according to claim 1, wherein the horizontal tail stabilizer is larger than the vertical tail stabilizer.

5. The unmanned aerial vehicle according to claim 1, wherein the second wing has a greater number of segments than the first wing.

6. The unmanned aerial vehicle according to claim 1, wherein the wing pylon system comprises the wing segment, the tank, and the pylon.

7. The unmanned aerial vehicle according to claim 1, wherein the pylon is fixed to the underside of the wing segment by welding, and the tank is fixed to the pylon by welding.

8. The unmanned aerial vehicle according to claim 1, wherein the wing pylon system further comprises a tail cone coupled to the tank and extending away from the tank.

9. An unmanned aerial vehicle, The main unit and A first wing attached to the main body, A second wing, coupled to the main body and positioned opposite the first wing, comprises a plurality of segments and a wing pylon system, and the second wing has a longer length than the first wing. Equipped with, The aforementioned wing pylon system is A wing segment which is one of the plurality of segments of the second wing, wherein the wing segment is positioned between the body and another of the plurality of segments of the second wing located at the distal end of the second wing, A tank configured to contain fuel used to supply sufficient power to the aforementioned unmanned aerial vehicle, wherein the fuel is propane, the tank and A pylon connecting the tank to the wing segment, Equipped with, An unmanned aerial vehicle, wherein the pylon is positioned below the wing segment and the tank is positioned below the pylon.

10. The unmanned aerial vehicle according to claim 9, further comprising at least one aileron located on the first wing, configured to deflect upward and downward.

11. The unmanned aerial vehicle according to claim 10, further comprising at least one aileron located on the second wing, configured to deflect upward and downward.

12. The unmanned aerial vehicle according to claim 9, wherein the wing pylon system comprises the wing segment, the tank, and the pylon.

13. The unmanned aerial vehicle according to claim 9, wherein the tank is configured to hold the fuel in a volume of about 8.6 liters.

14. The unmanned aerial vehicle according to claim 9, wherein the wing pylon system further comprises a tail cone coupled to the tank and extending away from the tank.

15. An unmanned aerial vehicle, The main unit and A first wing attached to the main body, A second wing, coupled to the main body and positioned on the opposite side of the first wing, the second wing comprises a plurality of segments and a wing pylon system, Equipped with, The aforementioned wing pylon system is A wing segment which is one of the plurality of segments of the second wing, wherein the wing segment is positioned between the body and another of the plurality of segments of the second wing located at the distal end of the second wing, A tank configured to contain fuel used to supply sufficient power to the aforementioned unmanned aerial vehicle, wherein the fuel is propane, the tank and A pylon connecting the tank to the wing segment, Equipped with, The pylon is positioned below the wing segment, and the tank is positioned below the pylon. An unmanned aerial vehicle in which the center of lift and the center of gravity are offset from and aligned with the central axis of the main body.

16. The wing pylon system according to claim 15, wherein the pylon is fixed to the underside of the segment by one or more fasteners or welds, and the tank is fixed to the pylon by one or more additional fasteners or welds.

17. The wing pylon system according to claim 15, wherein the tank is configured to hold the fuel in a volume of about 8.6 liters.

18. The wing pylon system according to claim 15, wherein the wing pylon system comprises the wing segment, the tank, the pylon, and a tail cone extending away from the tank and coupled to the tank.

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