CN209684008U - The changeable power source of oily electricity - Google Patents

Abstract

The utility model discloses a kind of power sources that oil electricity is changeable, belong to air vehicle technique field, including fuel tank, the fuel tank is fixed in fuselage；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 fuselage；Internal combustion engine, the internal combustion engine is by second fastening face and the connecting base detachable connection, and the internal combustion engine is connected to the fuel tank；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, are powered using storing electric energy as unmanned plane.The utility model has reached the technical effect for improving the cruise duration of unmanned plane.

Description

The changeable power source of oily electricity

Technical field

The utility model belongs to air vehicle technique field, in particular to a kind of power source that oil electricity is changeable.

Background technique

Unmanned unmanned plane referred to as " unmanned plane ", is grasped using radio robot and the presetting apparatus provided for oneself Vertical not manned unmanned plane.Without cockpit on machine, but automatic pilot, presetting apparatus, information collecting device are installed etc. Equipment.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar, it is tracked, is positioned, is remotely controlled, telemetering and Digital Transmission.It can take off as common unmanned plane under wireless remotecontrol or be launched with booster rocket, it can also be by machine tool Aerial launch is taken to fly.

For multi-rotor unmanned aerial vehicle, multi-rotor unmanned aerial vehicle fuselage in the prior art uses integrally formed structure system It forms.Usually from the operator that has received professional training and with take off in the case where parasite power, the liter of flight Power is by airborne battery, to provide power for motor and propeller.But since unmanned plane can awing consume largely Electric energy, and the electricity of battery is extremely limited, when the electricity of battery exhausts, unmanned plane can be forced to stop flight, leads in this way Cause the cruise duration of unmanned plane short.

In conclusion there is the technical problems that the cruise duration of unmanned plane is short in existing unmanned air vehicle technique.

Utility model content

Technical problem to be solved in the utility model is in the course of work of unmanned plane, and there is the continuations of the journey of unmanned plane Time short technical problem.

In order to solve the above technical problems, the utility model provides a kind of power source that oil electricity is changeable, the nothing Man-machine includes: fuel tank, and the fuel tank is fixed in fuselage；Connecting base, the connecting base are provided with the first fastening face and Two fastening faces, the connecting base are detachably connected by first fastening face and the fuselage；Internal combustion engine, the internal combustion engine are logical Second fastening face and the connecting base detachable connection are crossed, and the internal combustion engine is connected to the fuel tank, so that described Fuel flowing in fuel tank is burnt into the internal combustion engine, generates mechanical kinetic energy；Generator, the generator pass through described second Fastening face is fixedly connected with the connecting base, and is connect with the internal combustion engine, so that the mechanical kinetic energy passes through the internal combustion engine After being transmitted to the generator, produce electricl energy；Battery, the battery are connect with the internal combustion engine and the generator respectively, with The electric energy is stored as unmanned plane power supply.

Optionally, the internal combustion engine includes: first shell, oil inlet, shaft and spark plug, and the internal combustion engine passes through institute It states first shell and second fastening face is detachably connected, the internal combustion engine is communicated by the oil inlet and the fuel tank, And the shaft passes through the first shell, the oil inlet is located in the first shell；The generator includes: second shell Body, coil and output end, and the generator is fixedly connected by the second shell with second fastening face, the power generation Machine is fixedly connected by the coil with the shaft, and the coil is located in the second shell.

Optionally, the unmanned plane further include: rectifier, the rectifier are provided with the first terminals, the second terminals With third terminals, the rectifier is connected by first terminals with the output end；Controller, the controller are logical Second terminals are crossed to connect with the rectifier；The battery includes: the first sending end and the second sending end, and the electricity Pond is connected by first sending end with the third terminals, and the battery passes through second sending end and the spark Plug connection.

Optionally, the internal combustion engine further includes exhaust pipe；The unmanned plane further include: muffler, the muffler and institute State exhaust pipe connection.

Optionally, the battery is additionally provided with third sending end；The unmanned plane further include: the first electricity is adjusted, and described first Electricity is adjusted and is connected by the third sending end with the battery；First motor, the first motor are provided with the first mounting base, One drive shaft and the first input port, the first motor adjust connection by first input port and first electricity；First paddle Leaf, first blade are connected by first drive shaft with the first motor；First linking arm, first linking arm One end be fixedly connected with the side of the fuselage, the other end of first linking arm passes through first mounting base and described First motor connection；Wherein, the third side is in circular ring shape, and the first electricity positioning is in the third sending end and described the Between one mounting base, the rotational plane of first drive shaft and first blade is perpendicular.

Optionally, the battery is additionally provided with the 4th sending end；The unmanned plane further include: the second electricity is adjusted, and described second Electricity, which is adjusted, to be connected by the 4th sending end with the battery；Second motor, second motor are provided with the second mounting base, Two drive shafts and the second input port, second motor adjust connection by second input port and second electricity；Second paddle Leaf, second blade are connected by second drive shaft with second motor；Second linking arm, second linking arm One end be fixedly connected with the side of the fuselage, the other end of second linking arm passes through second mounting base and described The connection of second motor, and the second electricity positioning is between the 4th sending end and second mounting base；Wherein, described Two blades and first blade are symmetrical relative to the center of circle of the third side, second drive shaft and described second The rotational plane of blade is perpendicular.

Optionally, the battery is additionally provided with the 5th sending end；The unmanned plane further include: third electricity tune, the third Electricity, which is adjusted, to be connected by the 5th sending end with the battery；Third motor, the third motor are provided with third mounting base, Three drive shafts and third input port, the third motor are connected by the third input port with the third electricity tune；Third paddle Leaf, the third blade are connected by the third drive shaft with the third motor；Third linking arm, the third linking arm One end be fixedly connected with the side of the fuselage, the other end of the third linking arm passes through the third mounting base and described The connection of third motor；Wherein, the third electricity positioning is between the 5th sending end and the third mounting base, the third The rotational plane of drive shaft and the third blade is perpendicular.

Optionally, the battery is additionally provided with the 6th sending end；The unmanned plane further include: the 4th electricity is adjusted, and the described 4th Electricity, which is adjusted, to be connected by the 6th sending end with the battery；4th motor, the 4th motor are provided with the 4th mounting base, Four drive shafts and the 4th input port, the 4th motor adjust connection by the 4th input port and the 4th electricity；4th paddle Leaf, the 4th blade are connected by the 4th drive shaft with the 4th motor；4th linking arm, the 4th linking arm One end be fixedly connected with the third side, the other end of the 4th linking arm passes through the 4th mounting base and described The connection of four motors, and the 4th electricity positioning is between the 6th sending end and the 4th mounting base；Wherein, the described 4th Blade and the third blade are symmetrical relative to the center of circle, and the rotation of the 4th drive shaft and the 4th blade is flat Face is perpendicular.

The utility model has the advantages that

The utility model provides a kind of power source that oil electricity is changeable, by the way that fuel tank is fixed in fuselage, then will The first fastening face and fuselage of connecting base are detachably connected, internal combustion engine respectively with the second fastening face, battery and the hair of connecting base Motor is attached, and is interconnected with fuel tank, so that the fuel flowing in fuel tank is into internal combustion engine, and passes through the battery point Fire burning, to generate mechanical kinetic energy；Then the mechanical kinetic energy is transmitted to the generator by the internal combustion engine and generates electricity Energy；The battery is connect with the generator, to store the electric energy, and is the unmanned plane eventually by the electric energy stored Power supply, to serve as the power capacity source of unmanned plane, to reach the technical effect for improving the cruise duration of unmanned plane.

Detailed description of the invention

In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model Some embodiments for those of ordinary skill in the art without creative efforts, can also be according to this A little attached drawings obtain other attached drawings.

Fig. 1 be it is provided by the embodiment of the utility model it is a kind of include the changeable power source of oily electricity unmanned plane it is whole Body structural schematic diagram；

Fig. 2 is providing a kind of unmanned plane for including the changeable power source of oily electricity just for the utility model embodiment View schematic diagram；

It includes that the unmanned plane of oily electricity changeable power source is faced upward that Fig. 3 is provided a kind of for the utility model embodiment View schematic diagram；

Fig. 4 provides a kind of list of unmanned plane for including the changeable power source of oily electricity for the utility model embodiment The schematic diagram of head clamping seal head and single head clamping seal groove；

Fig. 5 provides a kind of card of unmanned plane for including the changeable power source of oily electricity for the utility model embodiment It connects seal head and is clamped the schematic diagram of seal groove；

It includes that the unmanned plane of oily electricity changeable power source subtracts that Fig. 6 is provided a kind of for the utility model embodiment The schematic diagram of shake system；

Fig. 7 for the utility model embodiment provide it is a kind of include the changeable power source of oily electricity unmanned plane it is recessed The schematic diagram of type groove；

Wherein,

100-fuselages, 110-first sides, 120-second sides, 130-third sides, 140-ducted bodies, 150- Sealing cover, 160-mufflers；

200-fuel tanks；

300-connecting bases, the 310-the first fastening face, the 320-the second fastening face；

400-internal combustion engines, 410-first shells；

500-generators, 510-second shells；

600-rectifiers；

700-controllers；

800-batteries；

900-the first blade, the 910-the second blade, 920-third blades, the 930-the four blade, the 940-the five paddle Leaf, the 950-the six blade, the 960-the first support frame, the 961-the first balancing leg, the 970-the second support frame, 980-fender rods；

1000-clamping seal heads, 1100-clamping seal grooves, 1200-damping springs, 1300-limited blocks, 1400- Protruding end, 1500-concave grooves.

Specific embodiment

The utility model discloses a kind of power sources that oil electricity is changeable, by the way that fuel tank is fixed on the hollow of fuselage In vivo, then by the second side of the first fastening face of connecting base and fuselage it is detachably connected, internal combustion engine is respectively and connecting base The second fastening face, battery and generator be attached, and be interconnected with fuel tank, so that fuel flowing in fuel tank is to interior It in combustion engine, and is burnt by the battery ignition, to generate mechanical kinetic energy；Then the mechanical kinetic energy is passed by the internal combustion engine It transports to the generator and produces electricl energy；The battery is connect with the generator, to store the electric energy, and eventually by institute The electric energy of storage is unmanned plane power supply, to serve as the power capacity source of unmanned plane, improves unmanned plane to reach The technical effect in cruise duration.

The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art's every other embodiment obtained, all belongs to In the range of the utility model protection；Wherein "and/or" keyword involved in this implementation, indicate and or two kinds of situations, change Sentence is talked about, and A mentioned by the utility model embodiment and/or B illustrate two kinds of A and B, A or B situations, describe A and B and deposited Three kinds of states, such as A and/or B, indicate: only including A does not include B；Only including B does not include A；Including A and B.

Meanwhile in the utility model embodiment, when component is referred to as " being fixed on " another component, it can be directly another On one component or there may also be components placed in the middle.When a component is considered as " connection " another component, it be can be It is directly connected to another component or may be simultaneously present component placed in the middle.When a component be considered as " being set to " another Component, it, which can be, is set up directly on another component or may be simultaneously present component placed in the middle.The utility model embodiment Used in term "vertical", "horizontal", "left" and "right" and similar statement be merely for purposes of illustration, not It is intended to limit the utility model.

Referring to Figure 1, Fig. 1 is a kind of entirety of power source that oil electricity is changeable provided by the embodiment of the utility model Structural schematic diagram.The utility model embodiment provides a kind of electric changeable power source of oil, and the oil electricity is changeable to be moved Power source device includes fuselage 100, fuel tank 200, connecting base 300, internal combustion engine 400, generator 500, rectifier 600, controller 700 With battery 800.Now respectively to fuselage 100, fuel tank 200, connecting base 300, internal combustion engine 400, generator 500, rectifier 600, control Device 700 and battery 800 processed carry out following detailed description:

For fuselage 100:

Fuselage 100 is provided with first side 110, second side 120, third side 130 and ducted body 140, and described Third side 130 can be between the first side 110 and the second side 120, and the third side 130 can be annulus Shape.

Specifically, the overall appearance of fuselage 100 can be rendered as cylindrical shape, first side 110 and second side 120 can be respectively the above and below of cylindrical body, and third side 130 can be the side of cylindrical body.It can be by first side 110, the outer surface to form ducted body 140 is surrounded in second side 120 and third side 130.Ducted body 140 is inside fuselage 100 Can accommodate has the space that can accommodate following fuel tanks 200 in the space of various electronic devices, such as ducted body 140.

In order to facilitate ducted body 140 is opened, fuel, the utility model is added into the fuel tank 200 being located in ducted body 140 A kind of power source that oil electricity is changeable that embodiment provides can also include sealing cover 150, and in first side 110 Through-hole and pedestal can be set.The sealing cover 150 can be hinged by the pedestal and the first side 110, and And the fuel tank 200 can be between the sealing cover 150 and the second side 120.

Referring to Figure 1 and Fig. 2, Fig. 2 are that the utility model embodiment provides a kind of power source that oil electricity is changeable Front view schematic diagram.The sealing cover 150 described above to match with fuel tank 200 can be set in first side 110.

As a kind of implementation of sealing cover 150 in the utility model embodiment, sealing cover 150 and pedestal are mutually cut with scissors Connect, such as the edge of sealing cover 150 can be fixedly connected with one end of hinge, by the other end of hinge can and first side 110 are mutually permanently connected；Meanwhile clamping joint has can be set in the other end at 150 edge of sealing cover, in first side 110 Corresponding position the clamping seat being mutually matched with clamping joint can be set.It, can be with when needing to inject fuel into fuel tank 200 Open sealing cover 150；It, can be by the way that clamping joint and clamping seat be mutually blocked when unmanned plane starts to work (such as starting to fly) It connects, to make sealing cover 150 and first side 110 be mutually permanently connected.Then during unmanned plane during flying, fuel tank 200 is prevented It falls, also pre- rainwater-proof, the adverse effect being exposed to the sun to 200 safety of fuel tank.200 safety of fuel tank can be improved to reach Technical effect.

As another implementation of sealing cover in the utility model embodiment, sealing cover 150 be can be by rubber material The flexible sealing lid that matter is made, specifically, including clamping seal head and clamping seal groove.

As Fig. 4, Fig. 4 be the utility model embodiment provide a kind of power source that oil electricity is changeable single head clamping it is close The schematic diagram of end socket and single head clamping seal groove.Being clamped seal head 1000 and clamping seal groove 1100 all is (i.e. single a card Connect seal head 1000 and single clamping seal groove 1100).The edge of sealing cover can be set clamping seal head 1000, with Clamping seal groove 1100 can be set in the first side 110 of sealing cover EDGE CONTACT, clamping seal groove 1100 can and block It connects seal head 1000 to be mutually matched, i.e., clamping seal head 1000 can be inserted in clamping seal groove 1100, or insertion clamping is close Clamping seal head 1000 in sealing groove 1100 can be separated from each other with clamping seal groove 1100.When needing closing seam lid 150, It can make to be clamped in the insertion clamping seal groove 1100 of seal head 1000, at this point, outside sealing cover 150 by pressing sealing cover 150 Rainwater due to by clamping seal head 1000 blocking, will be unable to enter ducted body in, then reach can pre- rainwater-proof into Enter fuselage interior, avoids damage electric elements, improve the technical effect of the safety of unmanned plane.

Fig. 7 is referred to, Fig. 7 is that the utility model embodiment provides a kind of concave groove of power source that oil electricity is changeable 1500 schematic diagram.The concave groove 1500 to match with finger is also provided on sealing cover 150, such as operator can Five fingers to be put into corresponding concave groove 1500, when being firmly lifted up, finger and concave groove 1500 can be complete Contact, had both increased the frictional force between finger and sealing cover 150, and had also facilitated pull-up sealing cover 150.Such as it is close when needing to open It when covering 150, can place a digit into the concave groove 1500 of sealing cover 150, by pressing sealing cover 150, make flexibility Sealing cover 150 deformation occurs, can then enable clamping seal head 1000 and clamping seal groove 1100 be separated from each other, thus Reach and be easy to open sealing cover 150, the technical effect of fuel is added into fuel tank 200.

If Fig. 5, Fig. 5 are that the utility model embodiment provides a kind of clamping seal head of power source that oil electricity is changeable With the schematic diagram of clamping seal groove.The quantity of clamping seal head 1000 can be two, and the quantity of clamping seal groove 1100 can also To be two.Two clamping seal grooves 1100 and two clamping seal heads 1000 are mutually matched.Due to two clamping seal grooves 1100 and two clamping seal head 1000 structure, principle, with above-mentioned single clamping seal head 1000 and individually be clamped seal groove 1100 structure, principle are all identical, so be not repeated herein.Due to two clamping seal grooves 1100 and two clamping seal heads 1000 are connected with each other, when rainwater penetrates into clamping seal groove 1100 and clamping seal head 1000 on the outside of sealing cover, then separately One clamping seal groove 1100 and clamping seal head 1000 can stop rainwater, prevent rainwater from penetrating into fuselage interior.To reach Improve the technical effect of the safety in unmanned plane during flying.

In order to make unmanned plane that following internal combustion engines 400, generator 500 awing be avoided to encounter the barrier such as wall When；Or drop in ground in unmanned plane, generator 500 strikes ground, and major accident occurs.The utility model is implemented A kind of power source that oil electricity is changeable that example provides can also include the first balancing leg 961, the first support frame 960, second Balancing leg and the second support frame 970.

The first support end, the second support end and the first interlude, first support end has can be set in first support frame It can be fixedly connected with the second side 120, second support end can be fixedly connected with first balancing leg 961, And second support end can be perpendicular with first balancing leg 961, first support end and second support End is correspondingly arranged at the both ends of first interlude.Second support leg can be set third support end, the 4th support end and Second interlude, the third support end can be fixedly connected with the second side 120, the 4th support end can and institute It states the second balancing leg to be fixedly connected, and the 4th support end and second balancing leg are perpendicular, the third support end The both ends of second interlude can be correspondingly arranged at the 4th support end.

With this, first balancing leg 961, the first support frame 960, the second balancing leg and the second support frame 970 constitute box The zone of protection of body shape structure, the internal combustion engine 400, generator 500 are respectively positioned in the zone of protection.Meanwhile the guard plot It is additionally provided at least two fender rods 980 on domain, is entered to avoid extraneous barrier by zone of protection gap position, and hit Hit the internal combustion engine 400, generator 500.Specifically, the connecting base 300 can be located at the first support end of institute and described the Between three support ends, the internal combustion engine 400 can be located between institute the first interlude and second interlude, the generator 500 can be located between institute the first interlude and second interlude.

Referring to Figure 1 and Fig. 3, Fig. 3 are that the utility model embodiment provides a kind of power source that oil electricity is changeable Bottom view schematic diagram.In unmanned plane, the two sides of second side 120 can be separately installed with the first support leg described above and Second support leg, the first support leg and the second support leg may be constructed top half be it is trapezoidal, lower half portion be rectangular shape Shape, namely form the zone of protection of box body shape structure described above.It can fix and set in the second support end of the first support leg It is equipped with the first balancing leg 961, the first balancing leg 961 can be rendered as can be good accessible rod-shaped with ground, in order to nobody When machine rests in ground, contact by the first balancing leg 961 with ground can support the weight of unmanned plane itself；Second 4th support end of support leg can be fixedly installed the second balancing leg, and the second balancing leg, which can be, well to be contacted with ground It is rod-shaped, when resting in ground in order to unmanned plane, contact by the first balancing leg, the second balancing leg with ground, preferably Support the weight of unmanned plane itself.Meanwhile it can be by internal combustion engine 400, generator 500, rectifier 600, controller 700 and battery 800, it is arranged between the first interlude and the second interlude, internal combustion engine is protected by the first interlude and the second interlude 400, generator 500, rectifier 600, controller 700 and battery 800 from barrier collision, to reach raising unmanned plane The technical effect of safety in-flight.

Fig. 6 is referred to, Fig. 6 is that the utility model embodiment provides a kind of damping system of power source that oil electricity is changeable The schematic diagram of system.In order in unmanned plane descent, reduce the weight of unmanned plane to the first balancing leg 961, the first support frame 960, the damage of the second balancing leg and the second support frame 970, in the first support frame 960 between second support end and the first interlude Damping spring 1200 (can be thrum spring), limited block 1300 and protruding end 1400 can be set.

Specifically, the second support end can be hollow structure, the first interlude can be accommodated in the hollow structure, i.e., One interlude can protrude into the second support end.Protruding end 1400, the first interlude are provided on the inner wall of the second support end On be provided with the limited block 1300 to match with protruding end 1400.When unmanned plane takes off, it will make the first interlude far from Two support ends prevent the second support end and the first interlude from mutually dividing at this point, blocking limited block 1300 by protruding end 1400 From rear, the second support end is made to fall, leads to that safety accident occurs.

Damping spring 1200 can be located at the inside of the second support end, and one end of damping spring 1200 can be with the second support End is mutually permanently connected, and the other end of damping spring 1200 can be mutually permanently connected with the first interlude.When unmanned plane lands When to ground, since the own wt of unmanned plane is larger, under the action of inertia, the fuselage of unmanned plane and the first support frame 960 Between biggish recoil strength will occur.At this point, passing through the elastic deformation of damping spring 1200, the fuselage of unmanned plane can be weakened And the first recoil strength between support frame 960, then avoid the fuselage of unmanned plane and the first support frame 960 from being damaged.To Reach the technical effect for improving unmanned plane safety.

Also can be set between the 4th support end and the second interlude in the second support frame 970 damping spring 1200, Limited block 1300 and protruding end 1400.Due to being arranged in the second support frame 970 between the 4th support end and the second interlude Damping spring 1200, limited block 1300 and protruding end 1400, with above-mentioned setting in the first support frame 960 second support end and Damping spring 1200, limited block 1300 and protruding end 1400 between one interlude is all identical in structure, principle, so herein It is not repeated.Due in the second support frame 970 second in the 4th support end and the second interlude, with above-mentioned first support frame 960 Support end and the first interlude are all identical in structure, principle, so being also not repeated at this time.

For fuel tank 200:

Fuel tank 200 can be fixed at the inside of the ducted body 140, and the fuel tank 200 can be positioned at described Between first side 110 and the second side 120.

Continuing with referring to Fig. 1 and Fig. 3.Fuel tank 200 can be fixedly mounted on to the inside of ducted body 140, such as by fuel tank 200 bottoms are sticked to the inside of ducted body 140.Fuel tank 200 can have opening, which can be rendered as circle, the face of opening Product can be less than the above-mentioned via area being arranged in first side 110.Fuel tank 200 can pass through oil guide pipe and following internal combustion engines 400 oil inlet is connected, and the fuel in fuel tank 200 is delivered in internal combustion engine 400.The volume of fuel tank 200 can be 4L To 6L, every liter of fuel oil can provide energy needed for flight 1 hour for unmanned plane.To reach the cruise duration for improving unmanned plane Technical effect.

For connecting base 300:

The first fastening face 310 and the second fastening face 320 has can be set in connecting base 300, and the connecting base 300 can pass through First fastening face 310 and the second side 120 are mutually detachably connected.

Referring to Figure 1.Damping part and link block are also provided on connecting base 300.Damping part may include One gag lever post, the second gag lever post, third gag lever post and the 4th gag lever post and the first elastic parts (such as the first elastic parts Can be thrum spring), the second elastic parts, third elastic parts and the 4th elastic parts.Second side 120 can be rendered as growing Rectangular, which has the first angle region, the second angle region, third angle region and the 4th angle region.First folder Angular zone, the second angle region, third angle region and the 4th angle region are four angles of second side 120.

By the way that one end of the first gag lever post is fixedly connected with the first angle region, the other end of the first gag lever post and nobody The second side 120 of machine is detachably connected, and the first elastic parts can be set in the outside of the first gag lever post.Second limit One end of bar can be fixedly connected with the second angle region, and the other end of the second gag lever post can be with the second side of unmanned plane 120 are detachably connected, and the second elastic parts can be set in the outside of the second gag lever post.One end of third gag lever post can be with It being fixedly connected with third angle region, the other end of third gag lever post can be detachably connected with the second side 120 of unmanned plane, And third elastic parts can be set in the outside of third gag lever post.It one end of 4th gag lever post can be with the 4th angle region It is fixedly connected, the other end of the 4th gag lever post can be detachably connected with the second side 120 of unmanned plane, and the 4th elastic group Part can be set in the outside of the 4th gag lever post.Generated vibration passes through the first elasticity in internal combustion engine 400 being worked The deformation of component, the second elastic parts, third elastic parts and the 4th elastic parts is eliminated, and 400 institute of internal combustion engine is then avoided The vibration of generation adversely affects the normal flight of unmanned plane.To reach promoted unmanned plane flight safety, The technical effect of stationarity.Link block may include that four columns are fast, and four columns are fastly by the second fastening face of connecting base 300 320 and the first shells 410 of following internal combustion engines 400 be mutually permanently connected, first shell 410 and unmanned plane are fixed on one It rises；So that unmanned plane is awing, internal combustion engine 400 also can endlessly provide energy, and supply is in in-flight nobody Machine uses.To reach the technical effect for improving the cruise duration of unmanned plane.

For internal combustion engine 400:

First shell 410, oil inlet, shaft, spark plug and exhaust pipe, the internal combustion engine has can be set in internal combustion engine 400 400 can be mutually detachably connected by the first shell 410 and second fastening face 320, and the internal combustion engine 400 can be with It is interconnected by the oil inlet and the fuel tank 200, and the shaft can pass through the first shell 410, it is described Oil inlet can be located in the first shell 410.

In order to reduce unmanned plane generated noise awing, described device can also include muffler 160, described to disappear Sound device 160 can be connected with each other with the exhaust pipe.

Continuing with referring to Fig. 1.Internal combustion engine 400 refers to can be by making fuel in machine internal-combustion, the heat released The Thermal Motor of power can be converted directly into.It, will be hot by internal combustion engine 400 after fuel in fuel tank 200 is delivered to internal combustion engine 400 The mechanical energy for pushing shaft rotation can be converted directly into.The outlet of exhaust pipe can be equipped with muffler 160 in internal combustion engine 400, Silencer can refer to for the airflow line with noise transmission, can use pipeline, the elbow with sound absorption lining, or utilize The noise reductions device such as sectional area sudden change and the discontinuous pipeline of other acoustic impedances can make in pipeline noise be decayed or instead It is emitted back towards.Muffler 160 can noise caused by weaker internal combustion engine 400, the destruction to avoid noise to ambient enviroment.

For generator 500:

Second shell 510, coil and output end has can be set in generator 500, and the generator 500 can be by described Second shell 510 and second fastening face 320 are mutually permanently connected, and the generator 500 can pass through the coil and institute It states shaft to be mutually permanently connected, and the coil can be located in the second shell 510.

Continuing with referring to Fig. 1.The shaft for stretching out internal combustion engine 400 can be fixedly connected with the coil in generator 500, turned When axis rotates, the coil in generator 500 can be driven to rotate together, electric current is then generated come cutting magnetic induction line by coil. Coil and magnet are provided in second shell 510, magnet is fixed on the inner wall of second shell 510, and coil can be with when rotating Cutting magnetic induction line.Electric energy caused by generator 500 can be delivered in rectifier 600 by output end.It will be interior to reach The mechanical energy that combustion engine 400 generates is converted into the technical effect of the electric energy of generator 500.The continuous output of generator 500 can To be 1.8KW, peak power output can be 2KW.

For rectifier 600:

The first terminals, the second terminals and third terminals have can be set in rectifier 600, and the rectifier 600 can To be connected with each other by first terminals and the output end.

Continuing with referring to Fig. 1.By the way that the output end of the first terminals of rectifier 600 and generator 500 is connected with each other, Just it can be direct current by AC conversion caused by generator 500, then pass through the company of the second terminals and third terminals It connects, direct current is externally exported.Such as rectifier 600 can be by alternating current caused by generator 500, being converted to can be with The direct current to charge for following batteries 800.

For controller 700:

Controller 700 can be connected with each other by second terminals and the rectifier 600.

Continuing with referring to Fig. 1.By being connected with each other the second terminals of controller 700 and rectifier 600, so that control Device 700 can control the charged state of following batteries 800, i.e., when battery 800 is fully charged, controller 700 can make battery 800 not It is further continued for charging.Meanwhile controller 700 can detecte the voltage of electric current needed for supplying system for flight control computer, ensure to fly control System provides normal electric energy, and excessive voltage is avoided to damage flight control system.And controller 700 can also control internal combustion engine 400 throttle, to adjust the size of mechanical energy caused by internal combustion engine 400, then control unmanned plane operating status, such as when When unmanned plane needs work, throttle can be opened, so that internal combustion engine 400 is that generator 500 provides energy；When unmanned plane stops work When making, throttle can be closed, so that internal combustion engine 400 no longer provides energy for generator 500.

For battery 800:

The first sending end, the second sending end, third sending end, the 4th sending end, the 5th transmission of electricity has can be set in battery 800 End, the 6th sending end, the 7th sending end and the 8th sending end, the battery 800 can be by first sending ends and described Third terminals are connected with each other, and the battery 800 can be connected with each other by second sending end and the spark plug.

In order to provide power to unmanned plane, use ability caused by internal combustion engine 400 for the power-equipment of unmanned plane.Institute Stating device can also include the first electric tune, first motor, the first blade 900 and the first linking arm.

First electricity is adjusted and can be connected by the third sending end and the battery 800；The first motor can be with It is provided with the first mounting base, the first drive shaft and the first input port, the first motor passes through first input port and described First electricity adjusts connection；First blade 900 can be connected by first drive shaft with the first motor；Described first One end of linking arm can be fixedly connected with the third side 130, and the other end of first linking arm can be by described First mounting base is connected with the first motor；Wherein, the first electricity positioning is in the third sending end and first peace It fills between seat, the rotational plane of first drive shaft and first blade 900 is perpendicular.

Continuing with referring to Fig. 1.It is connected with each other by the spark plug in the second sending end and internal combustion engine 400 by battery 800, Electric energy can be provided for spark plug.It, can be with when needing internal combustion engine 400 to start to work (i.e. when 400 output mechanical energy of internal combustion engine) Electric spark is generated by spark plug, to light burning mixture, the fuel entered in internal combustion engine 400 is made to start to burn.Battery 800 can use the lithium battery 800 of 12s, total capacity 5000mA.

By by the third sending end of battery 800 and first electricity adjust connection, first electricity reconcile first motor connection, can will Electrical energy transportation rotates the first blade 900 to first motor to provide electric energy for first motor；Meanwhile passing through the first electricity Regulate and control the revolving speed of first motor processed, to adjust the revolving speed of the first blade 900.Again by one end of the first linking arm and third side 130 are fixedly connected, and the other end of the first linking arm is connected with first motor.Thus by the rotation of the first blade 900, to pull nothing It is man-machine to be risen or declined, power needed for providing flight for unmanned plane.

In order to which more abundant power can be provided to unmanned plane on the basis of above-mentioned 900 energy of the first blade of supply, Use ability caused by internal combustion engine 400 for the power-equipment of unmanned plane.Described device can also include the second electricity tune, second Motor, the second blade 910 and the second linking arm.

Second electricity is adjusted and can be connected by the 4th sending end and the battery 800；Second motor can be with It is provided with the second mounting base, the second drive shaft and the second input port, second motor passes through second input port and described Second electricity adjusts connection；Second blade 910 can be connected by second drive shaft with second motor；Described second One end of linking arm can be fixedly connected with the third side 130, and the other end of second linking arm can be by described Second mounting base is connected with second motor, and the second electricity positioning is in the 4th sending end and second installation Between seat；

Wherein, second blade 910 and first blade 900 are symmetrical relative to the center of circle of the third side 130 The rotational plane of distribution, second drive shaft and second blade 910 is perpendicular.

Fig. 3 is referred to, by the way that the 4th sending end of battery 800 and the second electricity are adjusted connection, second electricity the second motor of reconciliation Connection, to provide electric energy for the second motor, can be such that the second blade 910 is rotated electrical energy transportation to the second motor；Together When, by the revolving speed of second electricity regulation the second motor of system, to adjust the revolving speed of the second blade 910.Again by the one of the second linking arm End is fixedly connected with third side 130, the other end of the second linking arm and the connection of the second motor.To by the second blade 910 Rotation, Lai Ladong unmanned plane are risen or are declined, power needed for providing flight for unmanned plane.

In order to be provided more to unmanned plane on the basis of above-mentioned supply the first blade 900 and the second 910 energy of blade For abundant power, use ability caused by internal combustion engine 400 for the power-equipment of unmanned plane.Described device can also include Third electricity tune, third motor, third blade 920 and third linking arm.

The third electricity tune can be connected by the 5th sending end and the battery 800；The third motor can be with It is provided with third mounting base, third drive shaft and third input port, the third motor passes through the third input port and described The connection of third electricity tune；The third blade 920 can be connected by the third drive shaft with the third motor；The third One end of linking arm can be fixedly connected with the third side 130, and the other end of the third linking arm can be by described Third mounting base is connected with the third motor；

Wherein, the third electricity positioning is between the 5th sending end and the third mounting base, the third driving The rotational plane of axis and the third blade 920 is perpendicular.

Fig. 3 is referred to, by the way that the 5th sending end of battery 800 is connected with third electricity tune, third electricity reconciliation third motor Connection, can be such that third blade 920 is rotated electrical energy transportation to third motor to provide electric energy for third motor；Together When, regulate and control the revolving speed of third motor processed, by third electricity to adjust the revolving speed of third blade 920.Again by the one of third linking arm End is fixedly connected with third side 130, and the other end of third linking arm is connected with third motor.To by third blade 920 Rotation, Lai Ladong unmanned plane are risen or are declined, power needed for providing flight for unmanned plane.

In order to give on the basis of above-mentioned supply the first blade 900, the second blade 910 and third 920 energy of blade Unmanned plane provides more abundant power, uses ability caused by internal combustion engine 400 for the power-equipment of unmanned plane.The dress Setting can also include the 4th electric tune, the 4th motor, the 4th blade 930 and the 4th linking arm.

4th electricity is adjusted and can be connected by the 6th sending end and the battery 800；The 4th motor setting There are the 4th mounting base, the 4th drive shaft and the 4th input port, the 4th motor can be by the 4th input port and described 4th electricity adjusts connection；4th blade 930 can be connected by the 4th drive shaft with the 4th motor；Described 4th One end of linking arm can be fixedly connected with the third side 130, and the other end of the 4th linking arm can be by described 4th mounting base is connected with the 4th motor, and the 4th electricity positioning is in the 6th sending end and the 4th installation Between seat.

Wherein, the 4th blade 930 and the third blade 920 are symmetrical relative to the center of circle, and the described 4th The rotational plane of drive shaft and the 4th blade 930 is perpendicular.

Fig. 3 is referred to, by the way that the 6th sending end of battery 800 and the 4th electricity are adjusted connection, the 4th electricity the 4th motor of reconciliation Electrical energy transportation to the 4th motor, tetra- motor of Lai Wei can be provided electric energy, rotate the 4th blade 930 by connection；Together When, by the revolving speed of the 4th electricity regulation the 4th motor of system, to adjust the revolving speed of the 4th blade 930.Again by the one of the 4th linking arm End is fixedly connected with third side 130, the other end of the 4th linking arm and the connection of the 4th motor.To by the 4th blade 930 Rotation, Lai Ladong unmanned plane are risen or are declined, power needed for providing flight for unmanned plane.

In order in above-mentioned supply the first blade 900, the second blade 910,930 energy of third blade 920 and the 4th blade On the basis of, more abundant power can be provided to unmanned plane, set ability caused by internal combustion engine 400 for the power of unmanned plane It is standby to use.Described device can also include the 5th electric tune, the 5th motor, the 5th blade 940 and the 5th linking arm.

5th electricity is adjusted and can be connected by the 7th sending end and the battery 800；5th motor can be with It is provided with the 5th mounting base, the 5th drive shaft and the 5th input port, the 5th motor passes through the 5th input port and described 5th electricity adjusts connection；5th blade 940 can be connected by the 5th drive shaft with the 5th motor；Described 5th One end of linking arm can be fixedly connected with the third side 130, and the other end of the 5th linking arm can be by described 5th mounting base is connected with the 5th motor；

Wherein, the 5th electricity positioning is between the 7th sending end and the 5th mounting base, the 5th driving The rotational plane of axis and the 5th blade 940 is perpendicular.

Fig. 3 is referred to, by the way that the 7th sending end of battery 800 and the 5th electricity are adjusted connection, the 5th electricity the 5th motor of reconciliation Electrical energy transportation to the 5th motor, five motor of Lai Wei can be provided electric energy, rotate the 5th blade 940 by connection；Together When, by the revolving speed of the 5th electricity regulation the 5th motor of system, to adjust the revolving speed of the 5th blade 940.Again by the one of the 5th linking arm End is fixedly connected with third side 130, the other end of the 5th linking arm and the connection of the 5th motor.To by the 5th blade 940 Rotation, Lai Ladong unmanned plane are risen or are declined, power needed for providing flight for unmanned plane.

In order in above-mentioned supply the first blade 900, the second blade 910, third blade 920, the 4th blade 930 and the 5th paddle On the basis of 940 energy of leaf, more abundant power can be provided to unmanned plane, make ability caused by internal combustion engine 400 for nothing Man-machine power-equipment uses.Described device can also include the 6th electric tune, the 6th motor, the 6th blade 950 and the 6th connection Arm.

6th electricity is adjusted and can be connected by the 8th sending end and the battery 800；6th motor can be with It is provided with the 6th mounting base, the 6th drive shaft and the 6th input port, the 6th motor passes through the 6th input port and described 6th electricity adjusts connection；6th blade 950 can be connected by the 6th drive shaft with the 6th motor；Described 6th One end of linking arm can be fixedly connected with the third side 130, and the other end of the 6th linking arm can be by described 6th mounting base is connected with the 6th motor, and the 6th electricity positioning is in the 8th sending end and the 6th installation Between seat；

Wherein, the 6th blade 950 and symmetrical relative to the center of circle with the 5th blade 940, described The rotational plane of six drive shafts and the 6th blade 950 is perpendicular.

Fig. 3 is referred to, by the way that the 8th sending end of battery 800 and the 6th electricity are adjusted connection, the 6th electricity the 6th motor of reconciliation Electrical energy transportation to the 6th motor, six motor of Lai Wei can be provided electric energy, rotate the 6th blade 950 by connection；Together When, by the revolving speed of the 6th electricity regulation the 6th motor of system, to adjust the revolving speed of the 6th blade 950.Again by the one of the 6th linking arm End is fixedly connected with third side 130, the other end of the 6th linking arm and the connection of the 6th motor.To by the 6th blade 950 Rotation, Lai Ladong unmanned plane are risen or are declined, power needed for providing flight for unmanned plane.

It should be noted that in order to take off, in-flight and in landing three phases to unmanned plane, fuel tank 200, internal combustion engine 400, the control of unmanned plane is described in detail in generator 500, rectifier 600, controller 700 and battery 800, now provide with Lower three kinds of embodiments:

The first embodiment, unmanned plane when taking off, can be controlled by the flight control system of unmanned plane battery 800 to Spark plug power supply in internal combustion engine 400, opening simultaneously throttle makes fuel tank 200 convey fuel into internal combustion engine 400.Internal combustion engine 400 convert heat into generator 500 needed for mechanical energy, then by electrical energy transportation caused by generator 500 to above-mentioned first In motor, the second motor, third motor, the 4th motor, the 5th motor and the 6th motor, to drive the first blade 900, the second paddle Leaf 910, third blade 920, the 4th blade 930, the 5th blade 940 and the 6th blade 950 start turning, and then pull unmanned plane It begins to ramp up from ground to aerial.

Second of embodiment, unmanned plane is in taking off, electrical energy transportation to first motor, the second motor, third is electric During machine, the 4th motor, the 5th motor and the 6th motor, it can be adjusted by controlling corresponding electricity, to change turning for motor Speed then adjusts the revolving speed of blade, comes so that unmanned plane continues on original direction and altitude, or changes nobody Heading and height.Such as the first electricity that control is connected with first motor is adjusted, and transfers to change first motor by the first electricity Revolving speed then adjusts the revolving speed of the first blade 900, to change generated pulling force size on the first linking arm.Make to reach Unmanned plane continues on original direction and height is flown, or change nobody heading and height technology effect Fruit.

The third embodiment, unmanned plane can adjust internal combustion engine 400 during landing by controller 700 The size of middle throttle exports electric current to change the speed of 500 coil cutting magnetic induction line of generator with regulator generator 500 Size.Such as reduce throttle, reduce the electric energy that is exported of generator 500, make be first motor, the second motor, third motor, Electric energy provided in 4th motor, the 5th motor and the 6th motor reduces, and gradually decreases the first blade 900, the second blade 910, the revolving speed of third blade 920, the 4th blade 930, the 5th blade 940 and the 6th blade 950, reduce the first linking arm, Pulling force on second linking arm, third linking arm, the 4th linking arm, the 5th linking arm and the 6th linking arm.When unmanned plane itself Gravity is less than in the first linking arm, the second linking arm, third linking arm, the 4th linking arm, the 5th linking arm and the 6th linking arm When total pulling force caused by upper, unmanned plane will be from gradually droping to ground in the air.

The utility model provides a kind of power source that oil electricity is changeable, by the way that fuel tank 200 is fixed on fuselage 100 In ducted body 140, then the second side 120 of the first fastening face 310 of connecting base 300 and fuselage 100 is detachably connected, The first shell 410 of internal combustion engine 400 and the second fastening face 320 of connecting base 300 are detachably connected, internal combustion engine 400 into Hydraulic fluid port and fuel tank 200 are interconnected, and the shaft of internal combustion engine 400 is fixedly connected with the coil of generator 500.Meanwhile by generator 500 second shell 510 is fixedly connected with the second fastening face 320 of connecting base 300, the output end and rectifier of generator 500 600 the first terminals connection, the second terminals and controller 700 connection of rectifier 600, the third wiring of rectifier 600 End is connected with the first sending end of battery 800.It, can since the second sending end of battery 800 is connected with the spark plug of internal combustion engine 400 With internal combustion engine 400 by fuel tank 200 fuel it is interior can be converted into mechanical energy after, then by generator 500 mechanical energy is converted For electric energy, to serve as the power capacity source of unmanned plane.To reach the technical effect in the cruise duration for improving unmanned plane.

It should be noted last that the above specific embodiment is only to illustrate the technical solution of the utility model rather than limits System, although the utility model is described in detail referring to example, those skilled in the art should understand that, it can be right The technical solution of the utility model is modified or replaced equivalently, without departing from the spirit and model of technical solutions of the utility model It encloses, should all cover in the scope of the claims of the utility model.

Claims (8)

1. a kind of power source that oil electricity is changeable, which is characterized in that the changeable power source of the oil electricity includes:

Fuel tank, the fuel tank are fixed in fuselage；

Connecting base, the connecting base are provided with the first fastening face and the second fastening face, and the connecting base is fastened by described first Face and the fuselage are detachably connected；

Internal combustion engine, the internal combustion engine is by second fastening face and the connecting base detachable connection, and the internal combustion engine It is connected to the fuel tank, so that the fuel flowing in the fuel tank is burnt into the internal combustion engine, generates mechanical kinetic energy；

Generator, the generator are fixedly connected by second fastening face with the connecting base, and are connected with the internal combustion engine It connects, so that being produced electricl energy after the mechanical kinetic energy is transmitted to the generator by the internal combustion engine；

Battery, the battery are connect with the internal combustion engine and the generator respectively, are powered using storing the electric energy as unmanned plane.

2. the changeable power source of oil electricity as described in claim 1, it is characterised in that:

The internal combustion engine includes: first shell, oil inlet, shaft and spark plug, and the internal combustion engine passes through the first shell It is detachably connected with second fastening face, the internal combustion engine is communicated by the oil inlet and the fuel tank, and the shaft Across the first shell, the oil inlet is located in the first shell；

The generator includes: second shell, coil and output end, and the generator passes through the second shell and described Two fastening faces are fixedly connected, and the generator is fixedly connected by the coil with the shaft, and the coil is positioned at described In second shell.

3. the changeable power source of oil electricity as claimed in claim 2, which is characterized in that the unmanned plane further include:

Rectifier, the rectifier are provided with the first terminals, the second terminals and third terminals, and the rectifier passes through institute The first terminals are stated to connect with the output end；

Controller, the controller are connected by second terminals with the rectifier；

The battery includes: the first sending end and the second sending end, and the battery passes through first sending end and described the The connection of three terminals, the battery are connected by second sending end with the spark plug.

4. the changeable power source of oil electricity as claimed in claim 3, it is characterised in that:

The battery is additionally provided with third sending end；

The changeable power source of the oil electricity further include:

First electricity is adjusted, and first electricity, which is adjusted, to be connected by the third sending end with the battery；

First motor, the first motor are provided with the first mounting base, the first drive shaft and the first input port, the first motor Connection is adjusted by first input port and first electricity；

First blade, first blade are connected by first drive shaft with the first motor；

One end of first linking arm, first linking arm is fixedly connected with the side of the fuselage, first linking arm The other end is connected by first mounting base with the first motor；

Wherein, the third side is in circular ring shape, and the first electricity positioning is in the third sending end and first mounting base Between, the rotational plane of first drive shaft and first blade is perpendicular.

5. the changeable power source of oil electricity as claimed in claim 4, it is characterised in that:

The battery is additionally provided with the 4th sending end；

The changeable power source of the oil electricity further include:

Second electricity is adjusted, and second electricity, which is adjusted, to be connected by the 4th sending end with the battery；

Second motor, second motor are provided with the second mounting base, the second drive shaft and the second input port, second motor Connection is adjusted by second input port and second electricity；

Second blade, second blade are connected by second drive shaft with second motor；

One end of second linking arm, second linking arm is fixedly connected with the side of the fuselage, second linking arm The other end is connected by second mounting base with second motor, and the second electricity positioning in the 4th sending end and Between second mounting base；

Wherein, second blade and first blade are symmetrical relative to the center of circle of the third side, and described second The rotational plane of drive shaft and second blade is perpendicular.

6. the changeable power source of oil electricity as claimed in claim 5, it is characterised in that:

The battery is additionally provided with the 5th sending end；

The changeable power source of the oil electricity further include:

Third electricity tune, the third electricity tune are connected by the 5th sending end with the battery；

Third motor, the third motor are provided with third mounting base, third drive shaft and third input port, the third motor It is connected by the third input port with the third electricity tune；

Third blade, the third blade are connected by the third drive shaft with the third motor；

One end of third linking arm, the third linking arm is fixedly connected with the side of the fuselage, the third linking arm The other end is connected by the third mounting base with the third motor；

Wherein, third electricity positioning is between the 5th sending end and the third mounting base, the third drive shaft and The rotational plane of the third blade is perpendicular.

7. the changeable power source of oil electricity as claimed in claim 6, it is characterised in that:

The battery is additionally provided with the 6th sending end；

The changeable power source of the oil electricity further include:

4th electricity is adjusted, and the 4th electricity, which is adjusted, to be connected by the 6th sending end with the battery；

4th motor, the 4th motor are provided with the 4th mounting base, the 4th drive shaft and the 4th input port, the 4th motor Connection is adjusted by the 4th input port and the 4th electricity；

4th blade, the 4th blade are connected by the 4th drive shaft with the 4th motor；

One end of 4th linking arm, the 4th linking arm is fixedly connected with the third side, the 4th linking arm it is another One end is connected by the 4th mounting base with the 4th motor, and the 4th electricity positioning is in the 6th sending end and institute It states between the 4th mounting base；

Wherein, the 4th blade and the third blade are symmetrical relative to the center of circle, the 4th drive shaft and institute The rotational plane for stating the 4th blade is perpendicular.

8. the changeable power source of oil electricity as claimed in claim 3, it is characterised in that:

The battery is additionally provided with the 7th sending end；

The changeable power source of the oil electricity further include:

5th electricity is adjusted, and the 5th electricity, which is adjusted, to be connected by the 7th sending end with the battery；

5th motor, the 5th motor are provided with the 5th mounting base, the 5th drive shaft and the 5th input port, the 5th motor Connection is adjusted by the 5th input port and the 5th electricity；

5th blade, the 5th blade are connected by the 5th drive shaft with the 5th motor；

One end of 5th linking arm, the 5th linking arm is fixedly connected with the third side, the 5th linking arm it is another One end is connected by the 5th mounting base with the 5th motor；

Wherein, it is described 5th electricity positioning between the 7th sending end and the 5th mounting base, the 5th drive shaft and The rotational plane of 5th blade is perpendicular.