CN109319146A

CN109319146A - Novel flight equipment

Info

Publication number: CN109319146A
Application number: CN201810997582.3A
Authority: CN
Inventors: 不公告发明人
Original assignee: Ewatt Technology Co Ltd
Current assignee: Ewatt Technology Co Ltd
Priority date: 2018-08-29
Filing date: 2018-08-29
Publication date: 2019-02-12

Abstract

The invention discloses a kind of novel flight equipments, belong to air vehicle technique field, including fuselage, and the fuselage is provided with first side, second side, third side and ducted body；Fuel tank, the fuel tank are fixed in the ducted body；Connecting base, the connecting base are provided with the first fastening face and the second fastening face, and the connecting base is detachably connected by first fastening face and the second side；Internal combustion engine, the internal combustion engine pass through second fastening face and the connecting base detachable connection；Generator, the generator is fixedly connected by second fastening face with the connecting base, and is connect with the internal combustion engine；Battery, the battery are connect with the internal combustion engine and the generator respectively；Wherein, internal combustion engine further includes exhaust pipe；The unmanned plane further include: muffler, the muffler are connected with the exhaust pipe.Invention achieves the technical effects in the cruise duration for improving unmanned plane.

Description

Novel flight equipment

Technical Field

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to novel flight equipment.

Background

Unmanned aerial vehicle is called unmanned aerial vehicle for short, and is unmanned aerial vehicle operated by radio remote control equipment and self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device, an information acquisition device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. The airplane can take off like a common unmanned aerial vehicle or launch and lift off by a boosting rocket under the radio remote control, and can also be carried to the air by a mother airplane to launch and fly.

To many rotor unmanned aerial vehicle, many rotor unmanned aerial vehicle fuselage among the prior art adopts integrated into one piece's structure preparation to form. The aircraft normally takes off under the condition of an operator with specialized training and the onboard power, and the lifting force of the flight is provided with power for the motor and the propeller through an onboard storage battery. However, since the unmanned aerial vehicle consumes a large amount of electric energy in flight and the electric quantity of the storage battery is extremely limited, when the electric quantity of the storage battery is exhausted, the unmanned aerial vehicle is forced to stop flying, which results in short endurance time of the unmanned aerial vehicle.

In summary, in the existing unmanned aerial vehicle technology, there is a technical problem that the endurance time of the unmanned aerial vehicle is short.

Disclosure of Invention

The invention aims to solve the technical problem that the endurance time of the unmanned aerial vehicle is short in the working process of the unmanned aerial vehicle.

In order to solve the technical problem, the invention provides a novel flight device, wherein the unmanned aerial vehicle comprises: the device comprises a machine body, a first side surface, a second side surface, a third side surface and a hollow body, wherein the third side surface is positioned between the first side surface and the second side surface; the oil tank is fixedly arranged in the hollow body and is positioned between the first side surface and the second side surface; the connecting seat is provided with a first fastening surface and a second fastening surface and is detachably connected with the second side surface through the first fastening surface; the internal combustion engine is detachably connected with the joint seat through the second fastening surface and is communicated with the oil tank, so that fuel in the oil tank flows into the internal combustion engine to be combusted, and mechanical kinetic energy is generated; the generator is fixedly connected with the connecting seat through the second fastening surface and is connected with the internal combustion engine, so that the mechanical kinetic energy is transmitted to the generator through the internal combustion engine to generate electric energy; the battery is connected with the internal combustion engine and the generator respectively to store the electric energy to supply power for the unmanned aerial vehicle. The device comprises a first balance foot, a first support frame, a second balance foot and a second support frame; the first support frame is provided with a first support end, a second support end and a first middle section, the first support end is fixedly connected with the second side face, the second support end is fixedly connected with the first balance foot, the second support end is perpendicular to the first balance foot, and the first support end and the second support end are correspondingly arranged at two ends of the first middle section; the second supporting leg is provided with a third supporting end, a fourth supporting end and a second middle section, the third supporting end is fixedly connected with the second side face, the fourth supporting end is fixedly connected with the second balance leg, the fourth supporting end is perpendicular to the second balance leg, and the third supporting end and the fourth supporting end are correspondingly arranged at two ends of the second middle section. The unmanned aerial vehicle still includes:

the sealed lid sealed cover be provided with 5 with point assorted concave groove for when needs are opened sealed lid, correspond 5 fingers and put into and be located sealed 5 of lid in the concave groove, through pressing sealed lid makes flexible sealed lid take place deformation, then the hand is grabbed and is taken up sealed lid.

Optionally, the internal combustion engine comprises: the internal combustion engine is detachably connected with the second fastening surface through the first shell, the internal combustion engine is communicated with the oil tank through the oil inlet, the rotating shaft penetrates through the first shell, and the oil inlet is located in the first shell; the generator includes: second casing, coil and output, just the generator passes through the second casing with second fastening face fixed connection, the generator passes through the coil with pivot fixed connection, just the coil is located in the second casing.

Optionally, the drone further comprises: the rectifier is connected with the output end through the first wiring end; a controller connected to the rectifier through the second terminal; the battery includes: a first power transmission terminal and a second power transmission terminal, and the battery is connected through the first power transmission terminal and the third terminal, and the battery is connected through the second power transmission terminal and the spark plug.

Optionally, the first side surface is provided with a through hole and a base; the device further comprises: the sealing cover is hinged to the first side face through the base, and the oil tank is located between the sealing cover and the second side face.

Optionally, the internal combustion engine further comprises an exhaust pipe; the device further comprises: a muffler connected with the exhaust pipe.

Optionally, the battery is further provided with a third power transmission terminal; the device further comprises: a first power bank connected to the battery through the third power transmission terminal; the first motor is provided with a first mounting seat, a first driving shaft and a first input port, and the first motor is connected with the first electric regulator through the first input port; a first blade connected to the first motor by the first drive shaft; one end of the first connecting arm is fixedly connected with the third side face, and the other end of the first connecting arm is connected with the first motor through the first mounting seat; the third side surface is in a circular ring shape, the first electric regulator is located between the third power transmission end and the first mounting seat, and the first driving shaft is perpendicular to the rotating plane of the first blade.

Optionally, the battery is further provided with a fourth power transmission terminal; the device further comprises: a second power bank connected to the battery through the fourth power transmission terminal; the second motor is provided with a second mounting seat, a second driving shaft and a second input port, and the second motor is electrically connected with the second electricity through the second input port; a second blade connected to the second motor by the second drive shaft; one end of the second connecting arm is fixedly connected with the third side face, the other end of the second connecting arm is connected with the second motor through the second mounting seat, and the second electricity adjuster is located between the fourth power transmission end and the second mounting seat; the second blade and the first blade are symmetrically distributed relative to the circle center of the third side face, and the rotating planes of the second driving shaft and the second blade are perpendicular to each other.

Optionally, the battery is further provided with a fifth power transmission terminal; the device further comprises: a third power bank connected to the battery through the fifth power transmission terminal; the third motor is provided with a third mounting seat, a third driving shaft and a third input port, and the third motor is electrically connected with the third electricity through the third input port; a third blade connected to the third motor via the third drive shaft; one end of the third connecting arm is fixedly connected with the third side face, and the other end of the third connecting arm is connected with the third motor through the third mounting seat; wherein the third power divider is located between the fifth power transmission terminal and the third mounting base, and the third driving shaft is perpendicular to a rotation plane of the third blade.

Optionally, the battery is further provided with a sixth power transmission terminal; the device further comprises: a fourth power bank connected to the battery through the sixth power transmission terminal; the fourth motor is provided with a fourth mounting seat, a fourth driving shaft and a fourth input port, and the fourth motor is electrically connected with the fourth electric controller through the fourth input port; a fourth blade connected to the fourth motor via the fourth drive shaft; one end of the fourth connecting arm is fixedly connected with the third side face, the other end of the fourth connecting arm is connected with the fourth motor through the fourth mounting seat, and the fourth electricity adjuster is located between the sixth power transmission end and the fourth mounting seat; the fourth paddle and the third paddle are symmetrically distributed relative to the circle center, and the rotation planes of the fourth driving shaft and the fourth paddle are perpendicular to each other.

Optionally, the battery is further provided with a seventh power transmission terminal; the device further comprises: a fifth power bank connected to the battery through the seventh power transmission terminal; the fifth motor is provided with a fifth mounting seat, a fifth driving shaft and a fifth input port, and the fifth motor is electrically connected with the fifth electric controller through the fifth input port; a fifth blade connected to the fifth motor via the fifth drive shaft; one end of the fifth connecting arm is fixedly connected with the third side face, and the other end of the fifth connecting arm is connected with the fifth motor through the fifth mounting seat; wherein the fifth power divider is located between the seventh power transmission end and the fifth mount, and the fifth drive shaft is perpendicular to a rotation plane of the fifth blade.

Has the advantages that:

the invention provides novel flight equipment, wherein an oil tank is fixed in a hollow body of a machine body, a first fastening surface of a connecting seat is detachably connected with a second side surface of the machine body, and an internal combustion engine is respectively connected with a second fastening surface of the connecting seat, a battery and a generator and is mutually communicated with the oil tank, so that fuel in the oil tank flows into the internal combustion engine and is ignited and combusted through the battery to generate mechanical kinetic energy; the mechanical kinetic energy is then transmitted by the internal combustion engine to the generator and generates electrical energy; the battery with the generator is connected, in order to save the electric energy to finally do through the electric energy that saves unmanned aerial vehicle power supply to act as unmanned aerial vehicle's power energy source, thereby reached the technological effect who improves unmanned aerial vehicle's time of endurance.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic overall structural diagram of a novel flight device provided by an embodiment of the invention;

FIG. 2 is a schematic front view of a novel flying apparatus according to an embodiment of the present invention;

FIG. 3 is a schematic bottom view of the novel flying apparatus provided in the embodiment of the present invention;

FIG. 4 is a schematic view of a single-head clamping seal head and a single-head clamping seal groove of the novel flying apparatus according to the embodiment of the present invention;

FIG. 5 is a schematic view of a clamping seal head and a clamping seal groove of the novel flying apparatus according to the embodiment of the present invention;

FIG. 6 is a schematic view of a shock absorption system of a novel flying apparatus according to an embodiment of the present invention;

FIG. 7 is a schematic view of a concave groove of the novel flight device according to the embodiment of the invention;

wherein,

100-fuselage, 110-first side, 120-second side, 130-third side, 140-hollow body, 150-sealing cover, 160-silencer;

200-oil tank;

300-an engagement seat, 310-a first fastening surface, 320-a second fastening surface;

400-internal combustion engine, 410-first housing;

500-generator, 510-second housing;

600-a rectifier;

700-a controller;

800-a battery;

900-first blade, 910-second blade, 920-third blade, 930-fourth blade, 940-fifth blade, 950-sixth blade, 960-first support, 961-first balance foot, 970-second support, 980-guard bar;

1000-joint sealing head, 1100-joint sealing groove, 1200-damping spring, 1300-limiting block, 1400-protruding end and 1500-concave groove.

Detailed Description

The invention discloses novel flight equipment, wherein an oil tank is fixed in a hollow body of a machine body, a first fastening surface of a connecting seat is detachably connected with a second side surface of the machine body, and an internal combustion engine is respectively connected with a second fastening surface of the connecting seat, a battery and a generator and is mutually communicated with the oil tank, so that fuel in the oil tank flows into the internal combustion engine and is ignited and combusted through the battery to generate mechanical kinetic energy; the mechanical kinetic energy is then transmitted by the internal combustion engine to the generator and generates electrical energy; the battery with the generator is connected, in order to save the electric energy to finally do through the electric energy that saves unmanned aerial vehicle power supply to act as unmanned aerial vehicle's power energy source, thereby reached the technological effect who improves unmanned aerial vehicle's time of endurance.

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention belong to the protection scope of the present invention; the "and/or" keyword referred to in this embodiment represents sum or two cases, in other words, a and/or B mentioned in the embodiment of the present invention represents two cases of a and B, A or B, and describes three states where a and B exist, such as a and/or B, which represents: only A does not include B; only B does not include A; including A and B.

Also, in embodiments of the invention where an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used in the embodiments of the present invention are for illustrative purposes only and are not intended to limit the present invention.

Referring to fig. 1, fig. 1 is a schematic view of an overall structure of a novel flight device according to an embodiment of the present invention. The embodiment of the invention provides novel flight equipment, which comprises a fuselage 100, an oil tank 200, a joint base 300, an internal combustion engine 400, a generator 500, a rectifier 600, a controller 700 and a battery 800. The following detailed description will now be made of the body 100, the oil tank 200, the docking station 300, the internal combustion engine 400, the generator 500, the rectifier 600, the controller 700, and the battery 800, respectively:

for the fuselage 100:

the body 100 is provided with a first side 110, a second side 120, a third side 130 and a hollow body 140, and the third side 130 may be located between the first side 110 and the second side 120, and the third side 130 may be circular.

Specifically, the overall appearance of the fuselage 100 may be in the shape of a cylinder, the first side 110 and the second side 120 may be the upper and lower surfaces of the cylinder, respectively, and the third side 130 may be the side of the cylinder. I.e., the first side 110, the second side 120, and the third side 130 may surround to form the outer surface of the hollow body 140. The hollow body 140 is a space in which various electronic devices can be accommodated inside the body 100, and for example, the hollow body 140 has a space in which an oil tank 200 described below can be accommodated.

In order to facilitate the opening of the hollow body 140 and to add fuel into the fuel tank 200 located in the hollow body 140, the novel flying apparatus provided by the embodiment of the present invention may further include a sealing cover 150, and a through hole and a base may be provided on the first side 110. The sealing cover 150 may be hinged to the first side 110 through the base, and the fuel tank 200 may be positioned between the sealing cover 150 and the second side 120.

Referring to fig. 1 and fig. 2, fig. 2 is a schematic front view of a novel flight device according to an embodiment of the present invention. The first side 110 may be provided with the sealing cap 150 that is matched with the oil tank 200 as described above.

As an implementation manner of the sealing cover 150 in the embodiment of the present invention, the sealing cover 150 and the base are hinged to each other, for example, an edge of the sealing cover 150 and one end of the hinge may be fixedly connected, and the other end of the hinge and the first side 110 may be fixedly connected to each other; meanwhile, a clamping connector may be disposed at the other end of the edge of the sealing cover 150, and a clamping seat matched with the clamping connector may be disposed at a corresponding position on the first side 110. When fuel needs to be injected into the fuel tank 200, the sealing cover 150 can be opened; when the drone starts to work (e.g., starts to fly), the sealing cover 150 and the first side 110 may be fixedly attached to each other by snapping the snap-fit head and the snap-fit seat to each other. Then in unmanned aerial vehicle flight process, prevent that oil tank 200 from falling, also prevent rainwater, insolate the adverse effect to oil tank 200 security. Thereby achieving the technical effect of improving the safety of the oil tank 200.

As another implementation manner of the sealing cover in the embodiment of the present invention, the sealing cover 150 may be a flexible sealing cover made of rubber, and specifically, includes a clamping sealing head and a clamping sealing groove.

Referring to fig. 4, fig. 4 is a schematic diagram of a single-headed clamping seal head and a single-headed clamping seal groove of a novel flight device according to an embodiment of the present invention. The snap seal head 1000 and snap seal groove 1100 are both one (i.e., a single snap seal head 1000 and a single snap seal groove 1100). The edge of the sealing cover may be provided with a clamping sealing head 1000, the first side surface 110 contacting the edge of the sealing cover may be provided with a clamping sealing groove 1100, and the clamping sealing groove 1100 may be matched with the clamping sealing head 1000, that is, the clamping sealing head 1000 may be inserted into the clamping sealing groove 1100, or the clamping sealing head 1000 inserted into the clamping sealing groove 1100 may be separated from the clamping sealing groove 1100. When the sealed lid 150 of needs closure, can be through pressing sealed lid 150, make the sealed head 1000 of joint insert in the joint seal groove 1100, at this moment, the outside rainwater of sealed lid 150 will unable entering cavity internal owing to receive blockking of the sealed head 1000 of joint, reach then inside can preventing the rainwater entering fuselage, avoid damaging electrical components, improve the technological effect of unmanned aerial vehicle's security.

Referring to fig. 7, fig. 7 is a schematic view of a concave groove 1500 of a novel flight device according to an embodiment of the present invention. The seal cover 150 may further be provided with a concave groove 1500 matching with fingers, for example, an operator may put five fingers into the corresponding concave groove 1500, and when the operator lifts the seal cover upwards with force, the fingers may be completely contacted with the concave groove 1500, which not only increases the friction between the fingers and the seal cover 150, but also facilitates pulling the seal cover 150. For example when sealed lid 150 is opened to needs, can put into the concave groove 1500 that is located sealed lid 150 with the finger, through pressing sealed lid 150, make flexible sealed lid 150 take place deformation, then can make joint sealing head 1000 and joint seal groove 1100 can alternate segregation to reach and conveniently open sealed lid 150, add the technological effect of fuel in to oil tank 200.

Referring to fig. 5, fig. 5 is a schematic diagram of a clamping seal head and a clamping seal groove of a novel flying apparatus according to an embodiment of the present invention. The number of snap seal heads 1000 may be two, and the number of snap seal grooves 1100 may also be two. The two snap seal grooves 1100 mate with the two snap seal heads 1000. Since the structures and principles of the two snap seal grooves 1100 and the two snap seal heads 1000 are the same as those of the single snap seal head 1000 and the single snap seal groove 1100, the description thereof will not be repeated here. Because two joint seal grooves 1100 and two joint seal 1000 interconnect, when the rainwater infiltration is close to joint seal groove 1100 and the joint seal 1000 outside the sealed lid, then another joint seal groove 1100 and joint seal 1000 can block the rainwater, prevent inside the rainwater infiltration fuselage. Thereby reach the technological effect who improves the security in the unmanned aerial vehicle flight.

In order to prevent the internal combustion engine 400 and the generator 500 from hitting obstacles such as walls in flight; or when the unmanned aerial vehicle lands on the ground, the generator 500 collides with the ground, so that a serious accident occurs. The novel flight device provided by the embodiment of the invention further comprises a first balance foot 961, a first support frame 960, a second balance foot and a second support frame 970.

The first support frame may be provided with a first support end, a second support end and a first middle section, the first support end may be fixedly connected with the second side surface 120, the second support end may be fixedly connected with the first balance leg 961, and the second support end may be perpendicular to the first balance leg 961, and the first support end and the second support end are correspondingly disposed at two ends of the first middle section. The second supporting leg may be provided with a third supporting end, a fourth supporting end and a second middle section, the third supporting end may be fixedly connected to the second side surface 120, the fourth supporting end may be fixedly connected to the second balance leg, the fourth supporting end is perpendicular to the second balance leg, and the third supporting end and the fourth supporting end may be correspondingly disposed at two ends of the second middle section.

Thus, the first balance leg 961, the first support frame 960, the second balance leg and the second support frame 970 form a protection area of a box-shaped structure, and the internal combustion engine 400 and the generator 500 are located in the protection area. Meanwhile, at least two protective rods 980 are arranged on the protective area to prevent external obstacles from entering from the gap part of the protective area and impacting the internal combustion engine 400 and the generator 500. Specifically, the adapter 300 may be located between the first support end and the third support end, the internal combustion engine 400 may be located between the first intermediate section and the second intermediate section, and the generator 500 may be located between the first intermediate section and the second intermediate section.

Referring to fig. 1 and fig. 3, fig. 3 is a schematic bottom view of a novel flight device according to an embodiment of the present invention. In unmanned aerial vehicle, the above-mentioned can be installed respectively to the both sides of second side 120 first supporting legs and second supporting legs, first supporting legs and second supporting legs can constitute first half and be trapezoidal, and the latter half is rectangular shape, also forms the above-mentioned protection zone of box body column structure. A first balance foot 961 can be fixedly arranged at the second support end of the first support foot, and the first balance foot 961 can be in a rod shape which can be in good contact with the ground, so that when the unmanned aerial vehicle stops on the ground, the weight of the unmanned aerial vehicle can be supported through the contact between the first balance foot 961 and the ground; can fix at the fourth support end of second supporting legs and be provided with the balanced foot of second, the balanced foot of second can be can with the shaft-like of ground good contact to when unmanned aerial vehicle berths on the ground, through the contact on the balanced foot of first balanced foot, the balanced foot of second and ground, better support unmanned aerial vehicle self weight. Simultaneously, can set up internal-combustion engine 400, generator 500, rectifier 600, controller 700 and battery 800 between first interlude and second interlude, protect internal-combustion engine 400, generator 500, rectifier 600, controller 700 and battery 800 through first interlude and second interlude and avoid the collision of barrier to reach the technological effect that improves the security in the unmanned aerial vehicle flight.

Referring to fig. 6, fig. 6 is a schematic view of a damping system of a novel flight device according to an embodiment of the present invention. In order to reduce the damage of the weight of the unmanned aerial vehicle to the first balance foot 961, the first support frame 960, the second balance foot and the second support frame 970 in the landing process of the unmanned aerial vehicle, a damping spring 1200 (which may be a spring), a limit block 1300 and a protruding end 1400 may be disposed between the second support end and the first middle section in the first support frame 960.

In particular, the second support end may be a hollow structure within which the first intermediate section may be received, i.e. the first intermediate section may extend into the second support end. The inner wall of the second support end is provided with a protruding end 1400, and the first middle section is provided with a limiting block 1300 matched with the protruding end 1400. When unmanned aerial vehicle takes off, will make first interlude keep away from the second and support the end, at this moment, block stopper 1300 through protrusion end 1400, prevent that the second from supporting end and first interlude after the mutual separation, make the second support the end and fall, lead to the incident to take place.

The damping spring 1200 may be located inside the second support end, one end of the damping spring 1200 may be fixedly connected to the second support end, and the other end of the damping spring 1200 may be fixedly connected to the first middle section. When the unmanned aerial vehicle lands to ground, because unmanned aerial vehicle's self weight is great, under inertial effect, will take place great recoil between unmanned aerial vehicle's fuselage and first support frame 960. At this time, through the elastic deformation of the damping spring 1200, the recoil force between the body of the unmanned aerial vehicle and the first support frame 960 can be weakened, and then the body of the unmanned aerial vehicle and the first support frame 960 are prevented from being damaged. Thereby reach the technological effect who improves unmanned aerial vehicle security.

A damping spring 1200, a limiting block 1300 and a protruding end 1400 may also be disposed between the fourth supporting end and the second middle section in the second supporting frame 970. Since the damping spring 1200, the limiting block 1300 and the protruding end 1400 disposed between the fourth supporting end and the second middle section of the second supporting frame 970 are the same as the damping spring 1200, the limiting block 1300 and the protruding end 1400 disposed between the second supporting end and the first middle section of the first supporting frame 960 in terms of structure and principle, the description thereof will not be repeated. Since the fourth supporting end and the second middle section of the second supporting frame 970 are identical to the second supporting end and the first middle section of the first supporting frame 960 in structure and principle, the description will not be repeated here.

For the oil tank 200:

the oil tank 200 may be fixedly disposed inside the hollow body 140, and the oil tank 200 may be located between the first side 110 and the second side 120.

Please continue to refer to fig. 1 and 3. The oil tank 200 may be fixedly installed inside the hollow body 140, for example, the bottom of the oil tank 200 is adhered to the inside of the hollow body 140. The oil tank 200 may have an opening, which may be in the shape of a circle, and the area of the opening may be smaller than the area of the through-hole provided on the first side 110. The oil tank 200 may communicate with an oil inlet of an internal combustion engine 400, described below, through an oil conduit to deliver fuel in the oil tank 200 to the internal combustion engine 400. The volume of the fuel tank 200 may be 4L to 6L, and each liter of fuel may provide the energy required for the drone to fly for 1 hour. Thereby reach the technological effect who improves unmanned aerial vehicle's duration.

For the adapter 300:

the adapter 300 may be provided with a first fastening surface 310 and a second fastening surface 320, and the adapter 300 may be detachably coupled to each other by the first fastening surface 310 and the second side surface 120.

Please refer to fig. 1. The coupling seat 300 may be further provided with a shock-absorbing member and a connecting block. The shock-absorbing member may include a first stopper rod, a second stopper rod, a third stopper rod, and a fourth stopper rod, and a first elastic member (for example, the first elastic member may refer to a spring), a second elastic member, a third elastic member, and a fourth elastic member. The second side 120 may present a rectangle having a first included angle region, a second included angle region, a third included angle region, and a fourth included angle region. The first, second, third and fourth angled regions are the four corners of the second side 120.

Through the regional fixed connection with the one end and the first contained angle of first gag lever post, the other end and the second side 120 of unmanned aerial vehicle of first gag lever post can dismantle the connection to first elastic component can overlap the outside at first gag lever post. One end of the second limiting rod can be fixedly connected with the second included angle area, the other end of the second limiting rod can be detachably connected with the second side face 120 of the unmanned aerial vehicle, and the second elastic component can be sleeved outside the second limiting rod. One end of the third limiting rod can be fixedly connected with the third included angle area, the other end of the third limiting rod can be detachably connected with the second side face 120 of the unmanned aerial vehicle, and the third elastic component can be sleeved outside the third limiting rod. One end of the fourth limiting rod can be fixedly connected with the fourth included angle area, the other end of the fourth limiting rod can be detachably connected with the second side face 120 of the unmanned aerial vehicle, and the fourth elastic component can be sleeved outside the fourth limiting rod. Can eliminate with the produced vibrations of internal-combustion engine 400 during operation through first elastic component, second elastic component, third elastic component and fourth elastic component's deformation, avoid the produced vibrations of internal-combustion engine 400 to cause adverse effect to unmanned aerial vehicle's normal flight then. Thereby reach the technological effect of security, the stationarity of promoting unmanned aerial vehicle's flight. The connecting block may include four cylindrical blocks fixedly connecting the second fastening surface 320 of the docking station 300 and a first housing 410 of the internal combustion engine 400 described below to each other to fix the first housing 410 and the drone together; in the flying process of the unmanned aerial vehicle, the internal combustion engine 400 can also continuously provide energy for the flying unmanned aerial vehicle. Thereby reach the technological effect who has improved unmanned aerial vehicle's duration.

For the internal combustion engine 400:

the internal combustion engine 400 may be provided with a first housing 410, an oil inlet, a rotation shaft, a spark plug, and an exhaust pipe, the internal combustion engine 400 may be detachably connected to each other by the first housing 410 and the second fastening surface 320, the internal combustion engine 400 may communicate with each other through the oil inlet and the oil tank 200, and the rotation shaft may pass through the first housing 410, and the oil inlet may be located on the first housing 410.

In order to reduce the noise generated by the drone during flight, the device may further comprise a silencer 160, the silencer 160 being interconnectable with the exhaust pipe.

Please continue to refer to fig. 1. The internal combustion engine 400 is a heat engine that can directly convert heat energy released by burning fuel inside the machine into power. After the fuel in the fuel tank 200 is delivered to the internal combustion engine 400, the internal combustion engine 400 directly converts the thermal energy into mechanical energy for driving the rotating shaft to rotate. The outlet of the exhaust pipe of the engine 400 may be fitted with a muffler 160, which may be a noise reduction device such as a pipe lined with an acoustic liner, an elbow, or a pipe with a sudden change in cross-sectional area and other discontinuities in acoustic impedance, for a gas flow pipe with noise propagation, to attenuate or reflect the noise within the pipe. The muffler 160 may attenuate noise generated by the engine 400 to avoid noise damage to the surrounding environment.

For the generator 500:

the generator 500 may be provided with a second housing 510, a coil, and an output end, the generator 500 may be fixedly connected to each other by the second housing 510 and the second fastening surface 320, the generator 500 may be fixedly connected to each other by the coil and the rotation shaft, and the coil may be located inside the second housing 510.

Please continue to refer to fig. 1. The rotating shaft extending out of the internal combustion engine 400 may be fixedly connected to the coil of the generator 500, and when the rotating shaft rotates, the coil of the generator 500 may be driven to rotate together, so as to cut the magnetic induction lines through the coil, thereby generating a current. That is, the second housing 510 is provided therein with a coil and a magnet, the magnet is fixed on the inner wall of the second housing 510, and the coil can cut the magnetic induction line when rotating. The electrical energy generated by the generator 500 can be fed to the rectifier 600 via the output. Thereby achieving the technical effect of converting the mechanical energy generated by the internal combustion engine 400 into the electrical energy of the generator 500. The continuous output power of generator 500 may be 1.8KW and the maximum output power may be 2 KW.

For the rectifier 600:

the rectifier 600 may be provided with a first terminal, a second terminal and a third terminal, and the rectifier 600 may be connected to each other through the first terminal and the output terminal.

Please continue to refer to fig. 1. By connecting the first terminal of the rectifier 600 and the output terminal of the generator 500, the ac power generated by the generator 500 can be converted into dc power, and then the dc power is output to the outside by connecting the second terminal and the third terminal. For example, the rectifier 600 may convert ac power generated by the generator 500 into dc power that may be used to charge the battery 800 described below.

For the controller 700:

the controller 700 may be connected to each other through the second terminal and the rectifier 600.

Please continue to refer to fig. 1. By interconnecting the second terminal of the controller 700 and the rectifier 600, the controller 700 may control the state of charge of the battery 800 such that when the battery 800 is fully charged, the controller 700 may cause the battery 800 to no longer continue to be charged. Meanwhile, the controller 700 can detect the voltage of the current required by the unmanned aerial vehicle flight control system, so that normal electric energy is provided for the flight control system, and the flight control system is prevented from being damaged by overlarge voltage. The controller 700 may also control the throttle of the internal combustion engine 400 to adjust the amount of mechanical energy generated by the internal combustion engine 400, and then control the operation state of the drone, for example, when the drone needs to work, the throttle may be opened, so that the internal combustion engine 400 provides energy for the generator 500; when the drone is out of service, the throttle may be closed so that the internal combustion engine 400 is no longer providing energy to the generator 500.

For battery 800:

the battery 800 may be provided with a first power transmission terminal, a second power transmission terminal, a third power transmission terminal, a fourth power transmission terminal, a fifth power transmission terminal, a sixth power transmission terminal, a seventh power transmission terminal, and an eighth power transmission terminal, the battery 800 may be interconnected through the first power transmission terminal and the third terminal, and the battery 800 may be interconnected through the second power transmission terminal and the spark plug.

To power the drone, the capability generated by the internal combustion engine 400 is made available to the power plant of the drone. The apparatus may also include a first electronic trim, a first motor, a first blade 900, and a first connecting arm.

The first power conditioner may be connected to the battery 800 through the third power transmission terminal; the first motor can be provided with a first mounting seat, a first driving shaft and a first input port, and the first motor is connected with the first electric regulator through the first input port; the first blade 900 may be coupled to the first motor via the first drive shaft; one end of the first connecting arm may be fixedly connected to the third side 130, and the other end of the first connecting arm may be connected to the first motor through the first mounting seat; wherein the first power divider is located between the third power transmission terminal and the first mounting base, and the first driving shaft is perpendicular to a rotation plane of the first blade 900.

Please continue to refer to fig. 1. By connecting the second power transmission terminal of the battery 800 and the spark plug in the internal combustion engine 400 to each other, the spark plug can be supplied with electric power. When it is desired to start operation of the engine 400 (i.e., when the engine 400 is outputting mechanical energy), an electrical spark may be generated by the spark plug to ignite the combustible mixture to initiate combustion of the fuel entering the engine 400. The battery 800 may be a 12s lithium battery 800 with a total capacity of 5000 mA.

By connecting the third power transmission terminal of the battery 800 with the first power regulator, which is connected with the first motor, electric energy can be transmitted to the first motor to supply electric energy to the first motor, so that the first blade 900 rotates; meanwhile, the rotating speed of the first motor is controlled through the first electric regulation, so that the rotating speed of the first blade 900 is regulated. One end of the first connecting arm is fixedly connected to the third side 130, and the other end of the first connecting arm is connected to the first motor. Thereby by the rotation of first paddle 900, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

In order to provide more robust power to the drone on the basis of the above-described supply of energy to the first blade 900, the power generated by the internal combustion engine 400 is made available to the power plant of the drone. The apparatus may further include a second electronic tilt, a second motor, a second blade 910, and a second link arm.

The second power conditioner may be connected to the battery 800 through the fourth power transmission terminal; the second motor can be provided with a second mounting seat, a second driving shaft and a second input port, and the second motor is electrically connected with the second electric controller through the second input port; the second blade 910 may be coupled to the second motor via the second drive shaft; one end of the second connecting arm may be fixedly connected to the third side 130, the other end of the second connecting arm may be connected to the second motor through the second mounting base, and the second power tap is located between the fourth power transmission end and the second mounting base;

wherein, the second blade 910 and the first blade 900 are symmetrically distributed with respect to the center of the third side 130, and the rotation planes of the second driving shaft and the second blade 910 are perpendicular to each other.

Referring to fig. 3, by connecting the fourth power transmission terminal of the battery 800 with the second power regulator, which is connected with the second motor, the power can be transmitted to the second motor to supply power to the second motor, so as to rotate the second blade 910; meanwhile, the rotating speed of the second motor is controlled through the second electric regulator, so that the rotating speed of the second blade 910 is regulated. One end of the second connecting arm is fixedly connected with the third side 130, and the other end of the second connecting arm is connected with the second motor. Thereby by the rotation of second paddle 910, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

In order to provide more robust power to the drone on the basis of the above-described supply of energy to the first blade 900 and the second blade 910, the power generated by the internal combustion engine 400 is used by the power plant of the drone. The device may further include a third electronic trim, a third motor, a third paddle 920, and a third link arm.

The third power conditioner may be connected to the battery 800 through the fifth power transmission terminal; the third motor may be provided with a third mounting seat, a third driving shaft and a third input port, and the third motor is electrically connected with the third power regulator through the third input port; the third blade 920 may be connected to the third motor by the third driving shaft; one end of the third connecting arm may be fixedly connected to the third side 130, and the other end of the third connecting arm may be connected to the third motor through the third mounting seat;

wherein the third power divider is located between the fifth power transmission terminal and the third mounting seat, and the third driving shaft is perpendicular to a rotation plane of the third blade 920.

Referring to fig. 3, by connecting the fifth power transmission terminal of the battery 800 with the third power regulator, which is connected with the third motor, the electric energy can be transmitted to the third motor to supply the electric energy to the third motor, so as to rotate the third blade 920; meanwhile, the rotating speed of the third motor is controlled through the third electric controller, so that the rotating speed of the third paddle 920 is adjusted. One end of the third connecting arm is fixedly connected with the third side 130, and the other end of the third connecting arm is connected with the third motor. Thereby by the rotation of third paddle 920, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

In order to provide more powerful power to the drone on the basis of the above-mentioned energy supply to the first blade 900, the second blade 910 and the third blade 920, the power generated by the internal combustion engine 400 is used by the power plant of the drone. The apparatus may further include a fourth electronic trim, a fourth motor, a fourth blade 930, and a fourth link arm.

The fourth power conditioner may be connected to the battery 800 through the sixth power transmission terminal; the fourth motor is provided with a fourth mounting seat, a fourth driving shaft and a fourth input port, and the fourth motor can be electrically connected with the fourth electric controller through the fourth input port; the fourth blade 930 may be connected to the fourth motor via the fourth driving shaft; one end of the fourth connecting arm may be fixedly connected to the third side 130, the other end of the fourth connecting arm may be connected to the fourth motor through the fourth mounting seat, and the fourth power divider may be located between the sixth power transmission end and the fourth mounting seat.

Wherein, the fourth blade 930 and the third blade 920 are symmetrically distributed with respect to the circle center, and the rotation planes of the fourth driving shaft and the fourth blade 930 are perpendicular to each other.

Referring to fig. 3, by connecting the sixth power transmission terminal of the battery 800 to the fourth power terminal, which is connected to the fourth motor, the power can be transmitted to the fourth motor to supply the power to the fourth motor, so that the fourth blade 930 is rotated; meanwhile, the rotation speed of the fourth motor is controlled by the fourth electronic governor to adjust the rotation speed of the fourth paddle 930. One end of the fourth connecting arm is fixedly connected with the third side 130, and the other end of the fourth connecting arm is connected with the fourth motor. Thereby by the rotation of fourth paddle 930, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

In order to provide more abundant power to the drone on the basis of the above-mentioned energy supply to the first blade 900, the second blade 910, the third blade 920 and the fourth blade 930, the power generated by the internal combustion engine 400 is used by the power plant of the drone. The device may further include a fifth electric tilt, a fifth motor, a fifth paddle 940, and a fifth connecting arm.

The fifth power tap may be connected to the battery 800 through the seventh power transmission terminal; the fifth motor may be provided with a fifth mounting seat, a fifth driving shaft and a fifth input port, and the fifth motor is electrically connected with the fifth power regulator through the fifth input port; the fifth blade 940 may be connected to the fifth motor by the fifth driving shaft; one end of the fifth connecting arm may be fixedly connected to the third side 130, and the other end of the fifth connecting arm may be connected to the fifth motor through the fifth mounting seat;

wherein the fifth power divider is located between the seventh power transmission terminal and the fifth mount, and the fifth driving shaft is perpendicular to a rotation plane of the fifth blade 940.

Referring to fig. 3, by connecting the seventh power transmission terminal of the battery 800 with the fifth power regulator, which is connected with the fifth motor, the power can be transmitted to the fifth motor to supply the power to the fifth motor, so that the fifth blade 940 rotates; meanwhile, the rotation speed of the fifth motor is controlled through the fifth electric regulator to adjust the rotation speed of the fifth blade 940. One end of the fifth connecting arm is fixedly connected with the third side 130, and the other end of the fifth connecting arm is connected with the fifth motor. Thereby by the rotation of fifth paddle 940, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

In order to provide more abundant power to the drone on the basis of the above-mentioned energy supplied to first blade 900, second blade 910, third blade 920, fourth blade 930 and fifth blade 940, the capability generated by internal combustion engine 400 is made available to the power plant of the drone. The apparatus may further include a sixth electronic trim, a sixth motor, a sixth blade 950, and a sixth connecting arm.

The sixth power tap may be connected to the battery 800 through the eighth power transmission terminal; the sixth motor may be provided with a sixth mounting seat, a sixth driving shaft, and a sixth input port, and the sixth motor is electrically connected to the sixth input port through the sixth electric regulation; the sixth blade 950 may be connected to the sixth motor by the sixth drive shaft; one end of the sixth connecting arm may be fixedly connected to the third side surface 130, the other end of the sixth connecting arm may be connected to the sixth motor through the sixth mounting seat, and the sixth power tap is located between the eighth power transmission end and the sixth mounting seat;

wherein the sixth blade 950 and the fifth blade 940 are symmetrically distributed with respect to the center of the circle, and the rotation planes of the sixth driving shaft and the sixth blade 950 are perpendicular to each other.

Referring to fig. 3, by connecting the eighth power transmission terminal of the battery 800 with the sixth power terminal, which is connected with the sixth motor, the power can be transmitted to the sixth motor to supply the power to the sixth motor, so that the sixth blade 950 rotates; meanwhile, the rotation speed of the sixth motor is controlled through the sixth electronic governor to adjust the rotation speed of the sixth blade 950. One end of the sixth connecting arm is fixedly connected with the third side surface 130, and the other end of the sixth connecting arm is connected with the sixth motor. Thereby by the rotation of sixth paddle 950, pull unmanned aerial vehicle and rise or descend, provide the required power of flight for unmanned aerial vehicle.

It should be noted that in order to describe in detail the control of the drone by the oil tank 200, the internal combustion engine 400, the generator 500, the rectifier 600, the controller 700 and the battery 800 in the three phases of takeoff, flight and landing, the following three embodiments are now provided:

in the first embodiment, when the unmanned aerial vehicle takes off, the battery 800 may be controlled by the flight control system of the unmanned aerial vehicle to supply power to the spark plug located in the internal combustion engine 400, and the gas tank 200 is opened to deliver fuel to the internal combustion engine 400. The internal combustion engine 400 converts the heat energy into mechanical energy required by the generator 500, and then transmits the electric energy generated by the generator 500 to the first motor, the second motor, the third motor, the fourth motor, the fifth motor and the sixth motor, so as to drive the first blade 900, the second blade 910, the third blade 920, the fourth blade 930, the fifth blade 940 and the sixth blade 950 to start to rotate, and then pull the unmanned aerial vehicle to start to ascend to the air from the ground.

The second embodiment, unmanned aerial vehicle is in taking off, and at the in-process with electric energy transport to first motor, second motor, third motor, fourth motor, fifth motor and sixth motor, can change the rotational speed of motor through controlling corresponding electricity accent, adjusts the rotational speed of paddle then, makes unmanned aerial vehicle continue along original direction and high flight, perhaps changes unmanned direction of flight and height. For example, the first electric adjuster connected to the first motor is controlled to change the rotation speed of the first motor through the first electric adjuster, and then the rotation speed of the first blade 900 is adjusted to change the magnitude of the pulling force generated on the first connecting arm. Thereby reach and make unmanned aerial vehicle continue to fly along original direction and height, or change unmanned direction of flight and the technological effect of height.

In the third embodiment, during landing of the drone, the controller 700 may adjust the size of the throttle in the internal combustion engine 400 to change the speed of the coil cutting the magnetic induction line in the generator 500, so as to adjust the size of the output current of the generator 500. For example, the throttle is reduced, the electric energy output by the generator 500 is reduced, the electric energy provided by the first motor, the second motor, the third motor, the fourth motor, the fifth motor and the sixth motor is reduced, the rotation speeds of the first blade 900, the second blade 910, the third blade 920, the fourth blade 930, the fifth blade 940 and the sixth blade 950 are gradually reduced, and the pulling forces on the first connecting arm, the second connecting arm, the third connecting arm, the fourth connecting arm, the fifth connecting arm and the sixth connecting arm are reduced. When unmanned aerial vehicle self gravity is less than the total pulling force that produces on first linking arm, second linking arm, third linking arm, fourth linking arm, fifth linking arm and sixth linking arm, unmanned aerial vehicle will descend to ground from the air gradually.

The invention provides novel flight equipment, which is characterized in that an oil tank 200 is fixed in a hollow body 140 of a fuselage 100, a first fastening surface 310 of a connecting seat 300 is detachably connected with a second side surface 120 of the fuselage 100, a first shell 410 of an internal combustion engine 400 is detachably connected with a second fastening surface 320 of the connecting seat 300, an oil inlet of the internal combustion engine 400 is communicated with the oil tank 200, and a rotating shaft of the internal combustion engine 400 is fixedly connected with a coil of a generator 500. Meanwhile, the second housing 510 of the generator 500 is fixedly coupled to the second fastening surface 320 of the docking station 300, the output terminal of the generator 500 is coupled to the first terminal of the rectifier 600, the second terminal of the rectifier 600 is coupled to the controller 700, and the third terminal of the rectifier 600 is coupled to the first power transmission terminal of the battery 800. Since the second power transmission end of the battery 800 is connected to the spark plug of the internal combustion engine 400, after the internal energy of the fuel in the fuel tank 200 is converted into mechanical energy by the internal combustion engine 400, the mechanical energy is converted into electric energy by the generator 500 to serve as a power energy source of the unmanned aerial vehicle. Thereby reached the technological effect who improves unmanned aerial vehicle's duration.

Finally, it should be noted that the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to examples, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the claims of the present invention.

Claims

1. A novel flight device, its characterized in that, unmanned aerial vehicle includes:

the device comprises a machine body, a first side surface, a second side surface, a third side surface and a hollow body, wherein the third side surface is positioned between the first side surface and the second side surface;

the oil tank is fixedly arranged in the hollow body and is positioned between the first side surface and the second side surface;

the connecting seat is provided with a first fastening surface and a second fastening surface and is detachably connected with the second side surface through the first fastening surface;

the internal combustion engine is detachably connected with the joint seat through the second fastening surface and is communicated with the oil tank, so that fuel in the oil tank flows into the internal combustion engine to be combusted, and mechanical kinetic energy is generated;

the generator is fixedly connected with the connecting seat through the second fastening surface and is connected with the internal combustion engine, so that the mechanical kinetic energy is transmitted to the generator through the internal combustion engine to generate electric energy;

the battery is respectively connected with the internal combustion engine and the generator so as to store the electric energy to supply power to the unmanned aerial vehicle;

the device comprises a first balance foot, a first support frame, a second balance foot and a second support frame; the first support frame is provided with a first support end, a second support end and a first middle section, the first support end is fixedly connected with the second side face, the second support end is fixedly connected with the first balance foot, the second support end is perpendicular to the first balance foot, and the first support end and the second support end are correspondingly arranged at two ends of the first middle section; the second supporting leg is provided with a third supporting end, a fourth supporting end and a second middle section, the third supporting end is fixedly connected with the second side face, the fourth supporting end is fixedly connected with the second balance leg, the fourth supporting end is perpendicular to the second balance leg, and the third supporting end and the fourth supporting end are correspondingly arranged at two ends of the second middle section;

wherein the internal combustion engine further comprises an exhaust pipe;

the unmanned aerial vehicle still includes:

a muffler connected to the exhaust pipe;

the unmanned aerial vehicle still includes:

2. The novel flying apparatus of claim 1 wherein:

the internal combustion engine includes: the internal combustion engine is detachably connected with the second fastening surface through the first shell, the internal combustion engine is communicated with the oil tank through the oil inlet, the rotating shaft penetrates through the first shell, and the oil inlet is located in the first shell;

the generator includes: second casing, coil and output, just the generator passes through the second casing with second fastening face fixed connection, the generator passes through the coil with pivot fixed connection, just the coil is located in the second casing.

3. The novel flying apparatus of claim 2, wherein said drone further comprises:

a rectifier provided with a first terminal, a second terminal and a third terminal, the rectifier being connected with the output terminal through the first terminal;

a controller connected to the rectifier through the second terminal;

the battery includes: a first power transmission terminal and a second power transmission terminal, and the battery is connected through the first power transmission terminal and the third terminal, and the battery is connected through the second power transmission terminal and the spark plug.

4. A drone according to claim 3, characterised in that:

the first side surface is provided with a through hole and a base;

the device further comprises:

the sealing cover is hinged to the first side face through the base, and the oil tank is located between the sealing cover and the second side face.

5. A drone according to claim 3, characterised in that:

the battery is also provided with a third power transmission end;

the device further comprises:

a first power bank connected to the battery through the third power transmission terminal;

the first motor is provided with a first mounting seat, a first driving shaft and a first input port, and the first motor is connected with the first electric regulator through the first input port;

a first blade connected to the first motor by the first drive shaft;

one end of the first connecting arm is fixedly connected with the third side face, and the other end of the first connecting arm is connected with the first motor through the first mounting seat;

the third side surface is in a circular ring shape, the first electric regulator is located between the third power transmission end and the first mounting seat, and the first driving shaft is perpendicular to the rotating plane of the first blade.

6. A drone according to claim 3, characterised in that:

the battery is also provided with a fourth power transmission end;

the device further comprises:

a second power bank connected to the battery through the fourth power transmission terminal;

the second motor is provided with a second mounting seat, a second driving shaft and a second input port, and the second motor is electrically connected with the second electricity through the second input port;

a second blade connected to the second motor by the second drive shaft;

one end of the second connecting arm is fixedly connected with the third side face, the other end of the second connecting arm is connected with the second motor through the second mounting seat, and the second electricity adjuster is located between the fourth power transmission end and the second mounting seat;

the second blade and the first blade are symmetrically distributed relative to the circle center of the third side face, and the rotating planes of the second driving shaft and the second blade are perpendicular to each other.

7. A drone according to claim 3, characterised in that:

the battery is also provided with a fifth power transmission end;

the device further comprises:

a third power bank connected to the battery through the fifth power transmission terminal;

the third motor is provided with a third mounting seat, a third driving shaft and a third input port, and the third motor is electrically connected with the third electricity through the third input port;

a third blade connected to the third motor via the third drive shaft;

one end of the third connecting arm is fixedly connected with the third side face, and the other end of the third connecting arm is connected with the third motor through the third mounting seat;

wherein the third power divider is located between the fifth power transmission terminal and the third mounting base, and the third driving shaft is perpendicular to a rotation plane of the third blade.

8. A drone according to claim 3, characterised in that:

the battery is also provided with a sixth power transmission end;

the device further comprises:

a fourth power bank connected to the battery through the sixth power transmission terminal;

the fourth motor is provided with a fourth mounting seat, a fourth driving shaft and a fourth input port, and the fourth motor is electrically connected with the fourth electric controller through the fourth input port;

a fourth blade connected to the fourth motor via the fourth drive shaft;

one end of the fourth connecting arm is fixedly connected with the third side face, the other end of the fourth connecting arm is connected with the fourth motor through the fourth mounting seat, and the fourth electricity adjuster is located between the sixth power transmission end and the fourth mounting seat;

the fourth paddle and the third paddle are symmetrically distributed relative to the circle center, and the rotation planes of the fourth driving shaft and the fourth paddle are perpendicular to each other.

9. A drone according to claim 3, characterised in that:

the battery is also provided with a seventh power transmission end;

the device further comprises:

a fifth power bank connected to the battery through the seventh power transmission terminal;

the fifth motor is provided with a fifth mounting seat, a fifth driving shaft and a fifth input port, and the fifth motor is electrically connected with the fifth electric controller through the fifth input port;

a fifth blade connected to the fifth motor via the fifth drive shaft;

one end of the fifth connecting arm is fixedly connected with the third side face, and the other end of the fifth connecting arm is connected with the fifth motor through the fifth mounting seat;

wherein the fifth power divider is located between the seventh power transmission end and the fifth mount, and the fifth drive shaft is perpendicular to a rotation plane of the fifth blade.