Long-endurance aircraft

Abstract

The invention provides a long-endurance aircraft, which belongs to the field of aircrafts and comprises an unmanned aerial vehicle, a power supply device and a battery storage device, a power supply device is arranged on the upper side of the unmanned aerial vehicle; a battery storage device is arranged on the lower side of the unmanned aerial vehicle; the power supply device comprises a battery mounting shell and a lifting push rod, the battery mounting shell is slidably connected to the upper side of the unmanned aerial vehicle, at least two battery mounting positions are arranged in the battery mounting shell, one end of the lifting push rod is connected with the unmanned aerial vehicle, and during working, the other end of the lifting push rod sequentially penetrates through the unmanned aerial vehicle and the battery mounting shell to abut against a battery; each battery storage device comprises a positioning mechanism and a moving mechanism, the positioning mechanism is mounted on the lower side of the unmanned aerial vehicle, the moving mechanism is slidably connected with the positioning mechanism, and at least two battery storage positions are arranged on the moving mechanism. The problem that battery replacement of the unmanned aerial vehicle is difficult is solved. The technical effect is that rapid battery replacement of the unmanned aerial vehicle in the air is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a long-endurance aircraft. Background Art

[0002] A drone is an aircraft controlled by radio remote control or autonomous program. It was first used in the military field for reconnaissance and strike missions. In recent years, with the advancement of technology, drones have also been widely used in civil and commercial fields, including agriculture, logistics distribution, photography, disaster relief, environmental monitoring, etc. The types of drones mainly include fixed-wing, rotary-wing and hybrid-wing, each of which has different characteristics and applicable scenarios. Fixed-wing drones have fast flight speeds and long battery life, and are suitable for large-scale patrols; rotary-wing drones have vertical take-off and landing and hovering functions, and are suitable for low-altitude photography and reconnaissance; hybrid-wing drones combine the advantages of fixed wings and rotary wings, and can take off and land vertically and fly efficiently.

[0003] However, existing drones still have some defects. For example, most drones need to replace batteries on the ground rather than in the air, which means that the drone must return to the ground for battery replacement after the battery is exhausted, which increases mission interruptions and operational complexity while making the drone's endurance more limited. Summary of the invention

[0004] The present invention provides a long-endurance aircraft, which is used to solve the defect that it is difficult to replace the battery of the UAV in the prior art, and realizes the rapid replacement of the battery of the UAV in the air.

[0005] The present invention provides a long-endurance aircraft, including a drone, a power supply device and a battery storage device;

[0006] A power supply device is provided on the upper side of the drone, and a battery storage device is provided on the lower side of the drone;

[0007] The power supply device includes a battery mounting shell and a lifting push rod. The battery mounting shell can be slidably connected to the upper side of the drone. At least two battery mounting positions are arranged in the battery mounting shell. One end of the lifting push rod is connected to the drone. When working, the other end of the lifting push rod passes through the drone and the battery mounting shell in turn to abut against the battery.

[0008] The battery storage device includes a positioning mechanism and a moving mechanism. The positioning mechanism is installed on the lower side of the drone. The moving mechanism is slidably connected to the positioning mechanism. At least two battery storage positions are arranged on the moving mechanism.

[0009] In addition, the long-endurance aircraft according to the present invention may also have the following additional technical features:

[0010] In some embodiments of the present invention, the power supply device further comprises a lower push rod;

[0011] One end of the lower push rod is connected to the lower side of the drone, and the other end of the lower push rod is connected to the battery mounting shell.

[0012] In some embodiments of the present invention, the power supply device further includes two protective covers and an opening and closing adjustment mechanism;

[0013] The two protective covers are rotatably connected to the drone and are arranged opposite to each other;

[0014] The battery installation shell is located inside the two protective covers, and the opening and closing adjustment mechanism is used to drive the two protective covers to open and close.

[0015] In some embodiments of the present invention, the opening and closing adjustment mechanism includes a support plate, a motor, a first connecting rod, a second connecting rod, and a third connecting rod;

[0016] A support plate is installed on the drone, and the motor is installed on one side of the support plate;

[0017] One end of the first connecting rod is connected to the output shaft of the motor, one end of the second connecting rod and one end of the third connecting rod are rotatably connected to the other end of the first connecting rod, the other end of the second connecting rod is rotatably connected to one of the protective covers, and the other end of the third connecting rod is rotatably connected to the other protective cover.

[0018] In some embodiments of the present invention, the positioning mechanism includes a top plate, an end positioning rod, and a middle positioning rod;

[0019] The top plate is mounted on the drone;

[0020] Two end positioning rods are installed at intervals at both ends of the top plate, and at least two middle positioning rods are installed at intervals in the middle of the top plate;

[0021] The combined shape of the four end positioning rods and the two middle positioning rods is a rectangle.

[0022] In some embodiments of the present invention, the moving mechanism includes a moving plate, an end stopper, and a battery retaining mechanism;

[0023] The movable plate is slidably connected to the end positioning rods and the middle positioning rod, and the movable plate is located below the top plate;

[0024] An end baffle is respectively arranged at both ends of the moving plate, and a battery retaining mechanism is arranged on the moving plate, and the battery retaining mechanism is located between the two end baffles.

[0025] In some embodiments of the present invention, the battery blocking mechanism includes a middle blocking rod, a blocking block and a motor housing;

[0026] The middle baffle is installed on the moving plate and is located between the two end baffles, and a stop block is arranged at one end of the middle baffle away from the moving plate;

[0027] A motor is arranged in the motor housing, and a stop block is connected to the output shaft of the motor.

[0028] In some embodiments of the present invention, a wind power generation device is also included, and the wind power generation device is arranged on both sides of the drone.

[0029] In some embodiments of the present invention, a wind power generation device includes a support, an impeller, and a wind power generator;

[0030] The bracket is connected to the drone, and a wind turbine is arranged in the bracket;

[0031] An impeller is arranged on the output shaft of the wind generator.

[0032] In some embodiments of the present invention, the wind power generation device further includes a steering gear, which is installed on the UAV, and a bracket is connected to an output shaft of the steering gear.

[0033] In summary, the present application includes the following beneficial technical effects: through the coordinated arrangement of the positioning mechanism, the moving mechanism, the battery storage position, the battery mounting shell and the lifting push rod, the rapid battery replacement of the UAV in the air is realized, the interruption of the UAV operation is avoided, the difficulty of the UAV operation is reduced, the convenience of battery replacement is increased, and the endurance of the UAV is increased. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference numerals are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0035] Figure 1 A three-dimensional diagram schematically illustrates a battery replacement process for a long-endurance aircraft according to some embodiments of the present invention.

[0036] Figure 2 A first view of a perspective view of a long endurance aircraft according to some embodiments of the present invention is schematically shown.

[0037] Figure 3 A second view of a perspective view of a long endurance aircraft according to some embodiments of the present invention is schematically shown.

[0038] Figure 4 A first view schematically illustrates a perspective view of a power supply device and a battery storage device for a long-endurance aircraft according to some embodiments of the present invention.

[0039] Figure 5A second view schematically illustrates a perspective view of the cooperation between a power supply device and a battery storage device of a long-endurance aircraft according to some embodiments of the present invention.

[0040] Figure 6 A third view schematically illustrates a perspective view of the cooperation between a power supply device and a battery storage device of a long-endurance aircraft according to some embodiments of the present invention.

[0041] Figure 7 A three-dimensional diagram schematically shows a power supply device and a wind power generation device of a long-endurance aircraft connected to a drone according to some embodiments of the present invention.

[0042] Figure 8 A third view schematically illustrates a perspective view of a long endurance aircraft according to some embodiments of the present invention.

[0043] Fig. 9 A perspective view of a drone of a long-endurance aircraft according to some embodiments of the present invention is schematically shown.

[0044] Fig.10 A first view schematically illustrates a perspective view of a power supply device of a long-endurance aircraft connected to a drone according to some embodiments of the present invention.

[0045] Fig.11 A second view schematically illustrates a perspective view of a power supply device of a long-endurance aircraft connected to a drone according to some embodiments of the present invention.

[0046] Fig.12 A three-dimensional diagram schematically shows the connection between the opening and closing adjustment mechanism and the protective cover of a long-endurance aircraft according to some embodiments of the present invention.

[0047] Fig.13 A perspective view schematically shows a bottom plate of a battery mounting case of a long-endurance aircraft according to some embodiments of the present invention.

[0048] Fig.14 A first view schematically illustrates a perspective view of a battery storage device for a long-endurance aircraft according to some embodiments of the present invention.

[0049] Fig.15 A perspective view schematically shows a battery storage device of a long-endurance aircraft according to some embodiments of the present invention without a top plate.

[0050] Fig.16 A second view schematically illustrates a perspective view of a battery storage device for a long-endurance aircraft according to some embodiments of the present invention.

[0051] Reference numerals:

[0052] 1. UAV, 11. No. 1 battery, 12. No. 2 battery, 13. No. 3 battery, 14. No. 1 spare battery, 15. No. 2 spare battery, 2. Main frame, 21. Lower plate, 22. Upper plate, 23. Through hole, 24. Slide hole, 25. Controller, 3. Power supply device, 31. Lifting push rod, 32. Opening and closing adjustment mechanism, 321. Support plate, 322. Motor, 323. First connecting rod, 324. Second connecting rod, 325. Third connecting rod, 33. Lower push rod, 34. Protective cover, 341. Cover body, 342. Heating plate, 343. Heat dissipation plate, 344. Solar panel, 345. First rotating rod, 346. Second rotating rod, 347. Rotating block, 348. Positioning hole, 35. Battery mounting shell, 351. Bottom plate, 3511. Plate body, 3512. Transition plate, 3513. Through hole , 352, baffle, 353, battery installation position, 354, power interface, 4, battery storage device, 41, positioning mechanism, 411, top plate, 412, end positioning rod, 413, middle positioning rod, 414, electric telescopic rod, 415, positioning groove, 416, sliding groove, 42, moving mechanism, 421, moving plate, 4211, sliding hole, 422, end baffle, 43, battery blocking mechanism, 431, middle blocking rod, 432, blocking block, 433, spring bead, 434, motor housing, 44, upper push rod, 441, first connecting block, 442, upper push rod body, 443, second connecting block, 45, battery storage position, 46, positioning slider, 5, wind power generation device, 51, servo, 52, bracket, 53, wind turbine, 54, impeller, 6, rotor frame, 7, rotor. DETAILED DESCRIPTION

[0053] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0054] It should be understood that the terms used herein are only for the purpose of describing specific example embodiments and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "" as used herein may also be meant to include plural forms. The terms "include", "comprise", "contain", and "have" are inclusive and therefore specify the presence of stated features, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not interpreted as necessarily requiring them to be performed in the specific order described or illustrated, unless the execution order is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0055] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teaching of the example embodiments.

[0056] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature as shown in the figure, such as "inside", "outside", "inner side", "outer side", "below", "below", "above", "above", etc. Such spatial relative terms are intended to include different orientations of the device in use or operation in addition to the orientation depicted in the figure. For example, if the device in the figure is flipped, then the element described as "below other elements or features" or "below other elements or features" will be subsequently oriented as "above other elements or features" or "above other elements or features". Therefore, the example term "below..." can include both upper and lower orientations. The device can be additionally oriented and rotated 90 degrees or in other directions and the spatial relative descriptors used in the text are interpreted accordingly.

[0057] like Figures 1 to 16 As shown, according to an embodiment of the first aspect of the present invention, a long-endurance aircraft is proposed, including a drone 1, a power supply device 3 and a battery storage device 4;

[0058] A power supply device 3 is provided on the upper side of the drone 1, and a battery storage device 4 is provided on the lower side of the drone 1;

[0059] The power supply device 3 includes a battery mounting shell 35 and a lifting push rod 31. The battery mounting shell 35 can be slidably connected to the upper side of the drone 1. At least two battery mounting positions 353 are arranged in the battery mounting shell 35. One end of the lifting push rod 31 is connected to the drone 1. When working, the other end of the lifting push rod 31 passes through the drone 1 and the battery mounting shell 35 in sequence to abut against the battery.

[0060] The battery storage device 4 includes a positioning mechanism 41 and a moving mechanism 42 . The positioning mechanism 41 is installed on the lower side of the drone 1 . The moving mechanism 42 is slidably connected to the positioning mechanism 41 . At least two battery storage positions 45 are arranged on the moving mechanism 42 .

[0061] In the above embodiment, it should be noted that, during operation, at least one of the at least two battery storage positions 45 on the drone 1 is vacant, and at least one of the remaining positions is equipped with a spare fully-charged battery.

[0062] The power supply device 3 includes at least two battery installation positions 353 of the battery installation shell 35, in which at least two batteries are arranged, one of the batteries is used to power the drone 1, and the remaining batteries are used as spare fully charged batteries.

[0063] The lifting push rod 31 is an electric telescopic rod.

[0064] When two drones 1 need to cooperate with each other to perform battery replacement, the drone 1 used for battery replacement is set directly above the drone 1 to be replaced, and the battery storage device 4 of the drone 1 used for battery replacement is installed directly above the battery mounting shell 35 of the power supply device 3 of the drone 1 to be replaced, and then one of the spare fully charged batteries in the battery mounting shell 35 is used to power the drone 1 to be replaced, and then the mobile mechanism 2 is used to drive the two battery storage positions 45 to move to one of the empty battery storage positions 45 and locate it directly above the low-power battery, and then the lifting push rod 31 is used to push the low-power battery into the empty battery storage position 45. At this time, the battery mounting position 353 of the low-power battery is idle, and then the mobile mechanism 2 is used to move the battery storage position 45 storing the spare fully charged battery and locate it directly above one of the empty battery mounting positions 353 so that the spare fully charged battery falls into the empty battery mounting position 353, completing the rapid battery replacement of the drone 1 in the air, and then the drone 1 used for battery replacement returns to the ground, and the drone 1 that has completed the battery replacement can continue to work.

[0065] In addition, it should be noted that the method of switching from powering the drone 1 with low power to powering the drone 1 with a fully charged spare battery is implemented in the same way as the power switching of a dual-power drone or a triple-power drone in the prior art.

[0066] The technical effect achieved by the above embodiment is: through the coordinated arrangement of the positioning mechanism 41, the moving mechanism 42, the battery storage position 45, the battery mounting shell 35 and the lifting push rod 31, the rapid battery replacement of the UAV in the air is realized, the interruption of the UAV operation is avoided, the difficulty of the UAV operation is reduced, and the convenience of battery replacement is increased.

[0067] Optional, such as Figures 1 to 8 and Figures 10 to 13 As shown, the power supply device 3 also includes a lower push rod 33;

[0068] One end of the push rod 33 is connected to the lower side of the drone 1 , and the other end of the push rod 33 is connected to the battery mounting case 35 .

[0069] In the above optional embodiments, it should be noted that the UAV 1 is a conventional rotor UAV, specifically including a main frame 2, a rotor frame 6 and a rotor 7. A plurality of rotor frames 6 are arranged in a circular array on the main frame 2, and a rotor 7 is connected to the end of each rotor frame 6 facing away from the main frame 2.

[0070] The main frame 2 includes a lower plate 21, an upper plate 22 and a controller 25. A plurality of rotor frames 6 are arranged in a circular array between the lower plate 21 and the upper plate 22. Each rotor frame 6 is connected to the lower plate 21 by bolts, and each rotor frame 6 is connected to the upper plate 22 by bolts. The lower plate 21 is connected to a controller by screwing, bonding or snapping. The motor, the lower push rod 33 and a plurality of batteries of the rotor 7 are electrically connected to the controller. One end of the lifting push rod 31 is connected to the lower plate 21, and a through hole 23 and a sliding hole 24 are spaced apart on the upper plate 22; the telescopic rod portion of the lifting push rod 31 is slidably inserted in the through hole 23 of the upper plate 22 and the battery mounting shell 35.

[0071] The battery mounting shell 35 includes a base plate 351 and multiple baffles 352. Multiple baffles 352, a wireless charging module and multiple power interfaces 354 are arranged at intervals on the base plate 351. A power interface 354 is arranged between every two baffles 352. A accommodating cavity between every two baffles 352 is a battery mounting position 353. A wireless charging module is arranged in each battery mounting position 353. The multiple power interfaces 354 and the multiple wireless charging modules are electrically connected to the controller 25. When a battery is arranged in the battery mounting position 353, the battery is plugged into the power interface 354.

[0072] The bottom plate 351 includes a plate body 3511 and a transition plate 3512. A plurality of baffles 352 are arranged on the plate body 3511 at intervals. The transition plate 3512 is integrally formed, welded or screwed on the lower side of the plate body 3511. One end of the lower push rod 33 is connected to the lower plate 21 by screwing, clamping or bonding. The transition plates 3512 of the telescopic rod portion of the lower push rod 33 are connected by screwing, clamping or bonding.

[0073] The plate body 3511 is provided with a through hole 3513 , and the telescopic rod portion of the lifting push rod 31 is slidably inserted into the through hole 23 of the upper plate 22 and the through hole 3513 on the plate body 3511 ; the power interface 354 is electrically connected to the controller 25 .

[0074] The beneficial effect of the above optional embodiment is that the battery mounting shell 35 can be reliably moved left and right through the setting of the lower push rod 33, thereby increasing the convenience of battery replacement.

[0075] Optional, such as Figures 1 to 8 and Figures 10 to 13 As shown, the power supply device 3 also includes two protective covers 34 and an opening and closing adjustment mechanism 32;

[0076] The two protective covers 34 are rotatably connected to the drone 1 and the two protective covers 34 are arranged opposite to each other;

[0077] The battery installation shell 35 is located inside the two protective covers 34 , and the opening and closing adjustment mechanism 32 is used to drive the two protective covers 34 to open and close.

[0078] Optional, such as Figures 1 to 8 and Figures 10 to 12 As shown, the opening and closing adjustment mechanism 32 includes a support plate 321, a motor 322, a first connecting rod 323, a second connecting rod 324 and a third connecting rod 325;

[0079] A support plate 321 is installed on the drone 1, and a motor 322 is installed on one side of the support plate 321;

[0080] One end of the first connecting rod 323 is connected to the output shaft of the motor 322, one end of the second connecting rod 324 and one end of the third connecting rod 325 are rotatably connected to the other end of the first connecting rod 323, the other end of the second connecting rod 324 is rotatably connected to one of the protective covers 34, and the other end of the third connecting rod 325 is rotatably connected to the other protective cover 34.

[0081] In the above optional embodiments, it should be noted that each protective cover 34 includes a cover body 341, a second rotating rod 346 and a rotating block 347, one end of the cover body 341 is provided with a first rotating rod 345 by screwing or welding, and the second rotating rod 346 is provided at the end of the upper plate 22 by welding or screwing, and the first rotating rod 345 and the second rotating rod 346 are rotatably connected by a rotating shaft.

[0082] In addition, if during the battery replacement process a fully charged battery that has fallen into the battery mounting position 353 does not completely contact the bottom wall of the battery mounting position 353, i.e., does not fully contact the corresponding power interface 354, the corresponding fully charged battery can be covered by the cover 341, and the pressure of the top wall inside the cover 341 can press the battery into the specified position, so that the battery is in full contact with the power interface 354, thereby ensuring the reliability of the battery replacement.

[0083] The inner wall of the cover body 341 is provided with a rotating block 347 by screwing, welding, clamping or bonding, the other end of the second connecting rod 324 is rotatably connected to the rotating block 347 of one of the protective covers 34 through a rotating shaft, and the other end of the third connecting rod 325 is rotatably connected to the rotating block 347 of the other protective cover 34 through a rotating shaft.

[0084] In addition, the protective cover 34 also includes a solar panel 344. The outer periphery of the cover body 341 is connected to the solar panel 344 by snap-fitting or screwing to achieve solar power generation. The solar panel 344 is electrically connected to the wireless charging module, thereby increasing the endurance of the drone 1.

[0085] The side of the cover body 341 can also be optionally plugged or screwed with an electric heating plate 342 or a heat sink 343. Specifically, when the ambient temperature is relatively low, that is, when the weather is relatively cold in winter, the side of the cover body 341 is provided with an electric heating plate 342, and the electric heating plate 342 is electrically connected to the controller 25 to ensure the performance of the battery. When the ambient temperature is relatively high, that is, when the weather is relatively hot in summer, the side of the cover body 341 is provided with a heat sink 343 to avoid the battery temperature being too high and affecting the battery performance; the motor 322 is electrically connected to the controller 25.

[0086] The beneficial effects of the above optional embodiments are: through the coordinated arrangement of the motor 322, the first connecting rod 323, the second connecting rod 324 and the third connecting rod 325, reliable control of the opening and closing of the two protective covers 34 is achieved. When the battery needs to be replaced, the protective cover 34 can be opened. When the drone 1 is working or placed, the protective cover 34 is closed to prevent dust from falling on the battery to ensure the performance of the battery.

[0087] Optional, such as Figures 1 to 6 and Figures 14 to 16 As shown, the positioning mechanism 41 includes a top plate 411, an end positioning rod 412 and a middle positioning rod 413;

[0088] The top plate 411 is mounted on the drone 1;

[0089] Two end positioning rods 412 are installed at intervals at both ends of the top plate 411, and at least two middle positioning rods 413 are installed at intervals in the middle of the top plate 411;

[0090] The combined shape of the four end positioning rods 412 and the two middle positioning rods 413 is a rectangle.

[0091] In the above optional embodiments, it should be noted that the top plate 411 is connected to the lower surface of the lower plate 21 by screw connection, welding, or clamping.

[0092] The positioning mechanism 41 also includes an electric telescopic rod 414. The sides of two diagonal end positioning rods 412 of the four end positioning rods 412 are connected to the electric telescopic rod 414 by screwing or clamping. A positioning groove 415 is provided at a point of each end positioning rod 412 away from the top plate 411. When working, the telescopic rod portion of the electric telescopic rod 414 passes through the positioning groove 415 and is inserted into the corresponding end positioning rod 412. A sliding groove 416 is provided on each end positioning rod 412 and each middle positioning rod 413. The movable plate 421 can be slidably connected to the multiple sliding grooves 416. A positioning hole 348 is provided on the side plate of each cover body 341. When the battery is replaced, the four side plates of the two cover bodies 341 are inserted into the positioning grooves 415 of the four end positioning rods 412 one by one, and then the telescopic rod portions of the two electric telescopic rods 414 are inserted into the corresponding positioning holes 348 to achieve the fixation of the relative position between the two drones 1.

[0093] The beneficial effect of the above optional embodiment is that reliable movement and reliable positioning of the position of the movable plate 421 are achieved through the coordinated arrangement of the top plate 411, the end positioning rod 412 and the middle positioning rod 413.

[0094] Optional, such as Figures 1 to 6 and Figures 14 to 16 As shown, the moving mechanism 42 includes a moving plate 421, an end stopper 422 and a battery stopper mechanism 43;

[0095] The movable plate 421 is slidably connected to the end positioning rod 412 and the middle positioning rod 413, and the movable plate 421 is located below the top plate 411;

[0096] An end baffle 422 is respectively disposed at both ends of the moving plate 421 . A battery retaining mechanism 43 is disposed on the moving plate 421 . The battery retaining mechanism 43 is located between the two end baffles 422 .

[0097] In the above optional embodiments, it should be noted that the distance between each end baffle 422 and the battery retaining mechanism 43 closest to the end baffle 422 is one battery storage position 45, and the distance between each two adjacent battery retaining mechanisms 3 is one battery storage position 45.

[0098] A sliding hole 4211 is provided on the movable plate 421, and the fixing mechanism 41 also includes a positioning slider 46, which is installed on the top plate 411 by screwing, welding or clamping. The end of the positioning slider 4211 away from the top plate 411 can be slidably inserted in the positioning sliding hole 4211 to ensure the reliability of the movement of the movable plate 421.

[0099] The beneficial effect of the above optional embodiment is that the spare fully-charged batteries can be reliably stored by means of the movable plate 421 , the end baffle plate 422 and the battery retaining mechanism 43 .

[0100] Optional, such as Figures 1 to 6 and Figures 14 to 16 As shown, the battery blocking mechanism 43 includes a middle blocking rod 431, a blocking block 432 and a motor housing 434;

[0101] The middle blocking rod 431 is installed on the moving plate 421 and is located between the two end blocking plates 422 . A stop block 432 is provided at one end of the middle blocking rod 431 away from the moving plate 421 .

[0102] A motor is disposed in the motor housing 434 , and a stop block 432 is connected to the output shaft of the motor.

[0103] In the above optional embodiment, it should be noted that the battery resistance mechanism 43 also includes a spring bead 433. A spring bead 433 is arranged in the middle of the middle barrier rod 431 to achieve preliminary positioning of the spare fully charged battery to avoid damage to the battery due to the battery falling too fast during the battery replacement process.

[0104] The spring ball 433 is a structure of a conventional spring and a ball.

[0105] The battery storage device 4 also includes an upper push rod 44, which includes a first connecting block 441, an upper push rod body 442 and a second connecting block 443. One end of the upper push rod body 442 is connected to the first connecting block 441 by screwing, and one end of the upper push rod body 442 is connected to the second connecting block 443 by screwing. The first connecting block 441 is connected to the top plate 411 by screwing, welding or clamping, and the second connecting block 443 is connected to the movable plate 421 by screwing, welding or clamping.

[0106] The upper push rod body 442 is an electric telescopic rod, and a driving part of the upper push rod body 442 is electrically connected to the controller 25 .

[0107] The beneficial effects of the above-mentioned optional embodiments are as follows: the coordinated arrangement of the middle blocking rod 431, the blocking block 432, the motor housing 434 and the motor ensures that when battery replacement is not required, the spare fully-charged battery used for battery replacement can be reliably blocked by the blocking block 432. When battery replacement is required, it is only necessary to drive the motor to drive the blocking block 432 to rotate to a position where it does not block the battery. The spare fully-charged battery used for battery replacement can fall into the battery mounting shell 35 below due to the action of gravity, which is very convenient and quick.

[0108] Optional, such as Figures 1 to 4 and Figure 7 and Figure 8 As shown, the UAV 1 also includes a wind power generation device 5 , and the wind power generation devices 5 are arranged on both sides of the UAV 1 .

[0109] The wind power generation device 5 includes a support 52, an impeller 54 and a wind power generator 53;

[0110] The bracket 52 is connected to the drone 1, and a wind turbine 53 is arranged in the bracket 52;

[0111] An impeller 54 is disposed on the output shaft of the wind generator 53 .

[0112] The wind power generation device 5 further includes a steering gear 51 , which is mounted on the UAV 1 , and a bracket 52 is connected to the output shaft of the steering gear 51 .

[0113] The steering gear 51 is electrically connected to the controller 25 , and the wind turbine 53 is electrically connected to the wireless charging module.

[0114] In the above optional embodiments, it should be noted that the wind turbine 53 adopts an existing miniature wind turbine, the servo 51 is installed on the lower plate 21 by screwing, welding or snapping, and the bracket 52 is connected to the output shaft of the servo 51 by screwing, welding or snapping.

[0115] The beneficial effects of the above optional embodiments are as follows: through the coordinated arrangement of the servo 51, the wind turbine 53 and the impeller 54, the impeller 54 can be made parallel to the ground when the drone 1 rises. Since a certain amount of wind force will be generated when the drone 1 rises, according to the working principle of the wind turbine, the rotation of the impeller 54 is driven by the wind to drive the blades to rotate, thereby driving the entire impeller 54 to rotate. When the wind blows through the blades of the impeller 54 of the wind turbine, the blades begin to rotate under the action of the wind force. In this process, the wind energy is converted into the rotational kinetic energy of the wind wheel 4. The rotation of the wind wheel is not directly driven by the wind, but by the asymmetry of the shape of the cross section of the blade, the wind velocity is different, and the pressure is different, resulting in a pressure difference between the upper and lower blades, and the lift is generated by the pressure difference, so that the wind wheel rotates 2. At the same time, the speed of rotation can be increased by a speed increaser so as to more efficiently drive the generator to generate electrical energy. The impeller 54 will also rotate accordingly. Therefore, during the ascent of the drone 1, the rotation of the impeller 54 can increase the lift of the drone 1 while also generating electricity. When the drone 1 moves forward and backward, the rotation of the impeller 54 can realize the power generation of the wind turbine 53, thereby supplying power to the battery, further improving the endurance of the drone 1.

[0116] The working principle of the device is as follows: take the power supply device 3 of the drone 1 to be replaced, which is provided with three batteries, namely, battery No. 1 11, battery No. 2 12, and battery No. 3 13, and the battery storage device 4 of the drone 1 used for replacing power, which is provided with two spare batteries, namely, battery No. 1 14 and battery No. 2 15 as an example: when battery No. 1 1 is low on power, battery No. 2 12 or battery No. 3 13 is started to ensure the normal operation of the drone 1, and then the drone 1 used for replacing power is moved to the top of the drone 1 to be replaced, and the motor 322 of the drone 1 to be replaced works to drive the two protective covers 34 to open, and then the two drones 1 are close to each other so that the positioning groove 415 of the drone 1 used for replacing power is mounted on the side panel of the cover body 341 of the drone 1 to be replaced, and then the telescopic rod part of the electric telescopic rod 414 is inserted into the positioning hole 348 to fix the positions of the two drones 1, and then the upper push rod 44 works to drive the moving The plate 421 moves to the vacant battery storage position 45 and is located directly above the No. 1 battery 11. The lifting push rod 31 then rises and pushes the No. 1 battery 11 into the vacant battery storage position 45. The motor then works to drive the blocking block 432 to rotate to achieve blocking of the No. 1 battery 11. The upper push rod 44 then works to drive the moving plate 421 to move to the vacant battery installation position 35 after the No. 1 battery 11 is detached and is located directly below the No. 1 spare battery 14 or the No. 2 spare battery 15. The blocking block 432 on the No. 1 spare battery 14 or the blocking block 432 on the No. 2 spare battery 15 is then opened so that the No. 1 spare battery 14 or the No. 2 spare battery 15 falls into the vacant battery installation position 35 after the No. 1 battery 11 is detached due to gravity. The telescopic rod portion of the electric telescopic rod 414 is then shortened and the two drones 1 are separated from each other. The motor 322 of the drone 1 to be replaced works to drive the two protective covers 34 to close and the replacement is completed.

[0117] The drone 1 of the present invention integrates wind power generation, solar power generation and aerial power exchange, thereby fully utilizing the advantages of wind energy, solar energy and aerial power exchange of aircraft, and maximizing the endurance.

[0118] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A long-endurance aircraft, characterized in that: It comprises a drone (1), a power supply device (3) and a battery storage device (4); The power supply device (3) is arranged on the upper side of the drone (1), and the battery storage device (4) is arranged on the lower side of the drone (1); The power supply device (3) comprises a battery mounting shell (35) and a lifting push rod (31); the battery mounting shell (35) is slidably connected to the upper side of the drone (1); at least two battery mounting positions (353) are arranged in the battery mounting shell (35); one end of the lifting push rod (31) is connected to the drone (1); when working, the other end of the lifting push rod (31) passes through the drone (1) and the battery mounting shell (35) in sequence to abut against the battery; The battery storage device (4) comprises a positioning mechanism (41) and a moving mechanism (42), wherein the positioning mechanism (41) is installed on the lower side of the drone (1), the moving mechanism (42) is slidably connected to the positioning mechanism (41), and at least two battery storage positions (45) are arranged on the moving mechanism (42).

2. The long-endurance aircraft according to claim 1, characterized in that: The power supply device (3) further comprises a lower push rod (33); One end of the lower push rod (33) is connected to the lower side of the drone (1), and the other end of the lower push rod (33) is connected to the battery mounting shell (35).

3. The long-endurance aircraft according to claim 2, characterized in that: The power supply device (3) also includes two protective covers (34) and an opening and closing adjustment mechanism (32); The two protective covers (34) are both rotatably connected to the drone (1) and the two protective covers (34) are arranged opposite to each other; The battery installation shell (35) is located inside the two protective covers (34), and the opening and closing adjustment mechanism (32) is used to drive the two protective covers (34) to open and close.

4. The long-endurance aircraft according to claim 3, characterized in that: The opening and closing adjustment mechanism (32) comprises a support plate (321), a motor (322), a first connecting rod (323), a second connecting rod (324) and a third connecting rod (325); The support plate (321) is mounted on the drone (1), and the motor (322) is mounted on one side of the support plate (321); One end of the first connecting rod (323) is connected to the output shaft of the motor (322), one end of the second connecting rod (324) and one end of the third connecting rod (325) are rotatably connected to the other end of the first connecting rod (323), the other end of the second connecting rod (324) is rotatably connected to one of the protective covers (34), and the other end of the third connecting rod (325) is rotatably connected to the other protective cover (34).

5. The long-endurance aircraft according to claim 1, characterized in that: The positioning mechanism (41) comprises a top plate (411), an end positioning rod (412) and a middle positioning rod (413); The top plate (411) is mounted on the drone (1); Two end positioning rods (412) are installed at intervals at both ends of the top plate (411), and at least two middle positioning rods (413) are installed at intervals in the middle of the top plate (411); The combined shape of the four end positioning rods (412) and the two middle positioning rods (413) is a rectangle.

6. The long-endurance aircraft according to claim 5, characterized in that: The moving mechanism (42) comprises a moving plate (421), an end stopper (422) and a battery stopper mechanism (43); The movable plate (421) is slidably connected to the end positioning rod (412) and the middle positioning rod (413), and the movable plate (421) is located below the top plate (411); One end baffle (422) is respectively provided at both ends of the movable plate (421), and the battery retaining mechanism (43) is provided on the movable plate (421), and the battery retaining mechanism (43) is located between the two end baffles (422).

7. The long-endurance aircraft according to claim 6, characterized in that: The battery blocking mechanism (43) comprises a middle blocking rod (431), a blocking block (432) and a motor housing (434); The middle blocking rod (431) is mounted on the movable plate (421) and is located between the two end blocking plates (422); the blocking block (432) is disposed at one end of the middle blocking rod (431) facing away from the movable plate (421); A motor is disposed in the motor housing (434), and the stop block (432) is connected to the output shaft of the motor.

8. The long-endurance aircraft according to claim 1, characterized in that: It also comprises a wind power generation device (5), and the wind power generation device (5) is arranged on both sides of the drone (1).

9. The long-endurance aircraft according to claim 8, characterized in that: The wind power generation device (5) comprises a bracket (52), an impeller (54) and a wind power generator (53); The bracket (52) is connected to the drone (1), and the wind turbine (53) is arranged inside the bracket (52); The impeller (54) is arranged on the output shaft of the wind generator (53).

10. The long-endurance aircraft according to claim 9, characterized in that: The wind power generation device (5) further comprises a steering gear (51), wherein the steering gear (51) is mounted on the drone (1), and the bracket (52) is connected to the output shaft of the steering gear (51).

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