CN109319144A - Aircraft with closed type fuselage - Google Patents
Aircraft with closed type fuselage Download PDFInfo
- Publication number
- CN109319144A CN109319144A CN201810996999.8A CN201810996999A CN109319144A CN 109319144 A CN109319144 A CN 109319144A CN 201810996999 A CN201810996999 A CN 201810996999A CN 109319144 A CN109319144 A CN 109319144A
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- Prior art keywords
- aircraft
- internal combustion
- combustion engine
- motor
- fuel tank
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 81
- 239000002828 fuel tank Substances 0.000 claims abstract description 51
- 238000007789 sealing Methods 0.000 claims abstract description 40
- 239000000446 fuel Substances 0.000 claims description 13
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 7
- 230000000694 effects Effects 0.000 abstract description 16
- 230000005611 electricity Effects 0.000 description 65
- 238000010586 diagram Methods 0.000 description 14
- 238000013016 damping Methods 0.000 description 11
- 239000003921 oil Substances 0.000 description 9
- 230000008859 change Effects 0.000 description 6
- 230000033228 biological regulation Effects 0.000 description 4
- 230000006378 damage Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 230000006698 induction Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000037237 body shape Effects 0.000 description 2
- 235000013399 edible fruits Nutrition 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 230000000116 mitigating effect Effects 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000010892 electric spark Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 244000045947 parasite Species 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 230000003584 silencer Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B64D27/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/04—Arrangement thereof in or on aircraft
Abstract
The invention discloses a kind of aircrafts with closed type fuselage, belong to aircraft technical 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 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；Sealing cover, edge are provided with clamping seal head, with clamping seal groove is provided in the first side of sealing cover EDGE CONTACT, the clamping seal groove and the clamping seal head are mutually matched.Invention achieves the technical effects in the cruise duration for improving aircraft.
Description
Technical field
The invention belongs to aircraft technical field, in particular to a kind of aircraft with closed type fuselage.
Background technique
Push-button aircraft referred to as " aircraft ", is grasped using radio robot and the presetting apparatus provided for oneself
Vertical not man-carrying aircraft.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 generic aircraft under wireless remotecontrol or be launched with booster rocket, it can also be by machine tool
Aerial launch is taken to fly.
For more rotary wing aircrafts, more rotary wing aircraft fuselages in the prior art use 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 aircraft can awing consume largely
Electric energy, and the electricity of battery is extremely limited, when the electricity of battery exhausts, aircraft can be forced to stop flight, leads in this way
Cause the cruise duration of aircraft short.
In conclusion there is the technical problems that the cruise duration of aircraft is short in existing aircraft technology.
Summary of the invention
The technical problem to be solved by the present invention is in the course of work of aircraft, there is the cruise duration of aircraft
Short technical problem.
In order to solve the above technical problems, the present invention provides a kind of aircraft with closed type fuselage, the aircraft
It include: fuselage, the fuselage is provided with first side, second side, third side and ducted body, and the third side is located at
Between the first side and the second side；Fuel tank, the fuel tank are fixed in the ducted body, and the fuel tank
Between the first side and the second side；Connecting base, the connecting base are provided with the first fastening face and second tightly
Gu face, the connecting base is detachably connected by first fastening face and the second side；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 aircraft power supply.The aircraft further include: sealing cover, wherein at the edge of the sealing cover
Be provided with clamping seal head, be provided with clamping seal groove in the first side of the sealing cover EDGE CONTACT, it is described
Clamping seal groove and the clamping seal head are mutually matched, so that the clamping seal groove can be inserted in the clamping seal head
It is interior.
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 aircraft further include: the rectifier is connected by first terminals with the output end；
Controller, the controller are connected by second terminals with the rectifier；The battery include: the first sending end and
Second sending end, and the battery is connected by first sending end with the third terminals, the battery passes through described
Second sending end is connected with the spark plug.
Optionally, the first side is provided with through-hole and pedestal；Described device further include: sealing cover, the sealing cover
It is hinged by the pedestal and the first side, and the fuel tank is between the sealing cover and the second side.
Optionally, the internal combustion engine further includes exhaust pipe；Described device further include: muffler, the muffler and described
Exhaust pipe connection.
Optionally, the battery is additionally provided with third sending end；Described device further include: the first electricity is adjusted, first electricity
Tune is connected by the third sending end with the battery；First motor, the first motor are provided with the first mounting base, first
Drive shaft and the first input port, the first motor adjust connection by first input port and first electricity；First blade,
First blade is connected by first drive shaft with the first motor；First linking arm, first linking arm
One end is fixedly connected with the third side, and 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 first peace
It fills between seat, the rotational plane of first drive shaft and first blade is perpendicular.
Optionally, the battery is additionally provided with the 4th sending end；Described device further include: the second electricity is adjusted, second electricity
It adjusts and is connected by the 4th sending end with the battery；Second motor, second motor are provided with the second mounting base, second
Drive shaft and the second input port, second motor adjust connection by second input port and second electricity；Second blade,
Second blade is connected by second drive shaft with second motor；Second linking arm, second linking arm
One end is fixedly connected with the third side, and the other end of second linking arm passes through second mounting base and described second
Motor connection, and the second electricity positioning is between the 4th sending end and second mounting base；Wherein, second paddle
Leaf and first blade are symmetrical relative to the center of circle of the third side, second drive shaft and second blade
Rotational plane it is perpendicular.
Optionally, the battery is additionally provided with the 5th sending end；Described device further include: third electricity tune, the third electricity
It adjusts and is 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 are connected by the third input port with the third electricity tune；Third blade,
The third blade is connected by the third drive shaft with the third motor；Third linking arm, the third linking arm
One end is fixedly connected with the third side, and the other end of the third linking arm passes through the third mounting base and the third
Motor connection；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 is perpendicular.
Optionally, the battery is additionally provided with the 6th sending end；Described device further include: the 4th electricity is adjusted, the 4th electricity
It adjusts and is 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 adjust connection by the 4th input port and the 4th electricity；4th blade,
4th blade is connected by the 4th drive shaft with the 4th motor；4th linking arm, the 4th linking arm
One end is fixedly connected with the third side, and the other end of the 4th linking arm passes through the 4th mounting base and the described 4th
Motor connection, and the 4th electricity positioning is between the 6th sending end and the 4th mounting base；Wherein, the 4th paddle
Leaf and the third blade are symmetrical relative to the center of circle, the rotational plane of the 4th drive shaft and the 4th blade
It is perpendicular.
Optionally, the battery is additionally provided with the 7th sending end；Described device further include: the 5th electricity is adjusted, the 5th electricity
It adjusts and is 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 adjust connection by the 5th input port and the 5th electricity；5th blade,
5th blade is connected by the 5th drive shaft with the 5th motor；5th linking arm, the 5th linking arm
One end is fixedly connected with the third side, and the other end of the 5th linking arm passes through the 5th mounting base and the described 5th
Motor connection；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 is perpendicular.
The utility model has the advantages that
The present invention provides a kind of aircraft with closed type fuselage, by the way that fuel tank is fixed in the ducted body of fuselage,
The second side of the first fastening face of connecting base and fuselage is detachably connected again, internal combustion engine respectively with connecting base second
Fastening face, battery and generator are attached, and are interconnected with fuel tank, so that fuel flowing in fuel tank is to internal combustion engine
In, and burnt by the battery ignition, to generate mechanical kinetic energy；
Then the mechanical kinetic energy is transmitted to the generator by the internal combustion engine and produces electricl energy；The battery and institute
Generator connection is stated, to store the electric energy, and is aircraft power supply eventually by the electric energy stored, to serve as aviation
The power capacity source of device, to reach the technical effect for improving the cruise duration of aircraft.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is a kind of overall structure diagram of the aircraft with closed type fuselage provided in an embodiment of the present invention；
Fig. 2 provides a kind of front view schematic diagram of aircraft with closed type fuselage for the embodiment of the present invention；
Fig. 3 provides a kind of bottom view schematic diagram of aircraft with closed type fuselage for the embodiment of the present invention；
Fig. 4 is clamped seal head and single head for the single head that the embodiment of the present invention provides a kind of aircraft with closed type fuselage
It is clamped the schematic diagram of seal groove；
Fig. 5 provides clamping seal head and the clamping sealing of a kind of aircraft with closed type fuselage for the embodiment of the present invention
The schematic diagram of slot；
Fig. 6 provides a kind of schematic diagram of the shock mitigation system of aircraft with closed type fuselage for the embodiment of the present invention；
Fig. 7 provides a kind of schematic diagram of the concave groove of aircraft with closed type fuselage for the embodiment of the present invention；
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 invention discloses a kind of aircrafts with closed type fuselage, by the ducted body that fuel tank is fixed on to fuselage
It is interior, then the second side of the first fastening face of connecting base and fuselage is detachably connected, internal combustion engine respectively with connecting base
Second fastening face, battery and generator are attached, and are interconnected with fuel tank, so that fuel flowing in fuel tank is to internal combustion
It in machine, and is burnt by the battery ignition, to generate mechanical kinetic energy；Then the mechanical kinetic energy is transmitted by the internal combustion engine
To the generator and produce electricl energy；The battery is connect with the generator, to store the electric energy, and eventually by being deposited
The electric energy of storage is aircraft power supply, to serve as the power capacity source of aircraft, improves the continuous of aircraft to reach
The technical effect of ETS estimated time of sailing.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art's every other embodiment obtained belong to what the present invention protected
Range；Wherein "and/or" keyword involved in this implementation, indicate and or two kinds of situations, in other words, the present invention implement
A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, 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 embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another
On component or there may also be components placed in the middle.When a component is considered as " connection " another component, it be can be directly
It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being set to " another group
Part, it, which can be, is set up directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention
Term "vertical", "horizontal", "left" and "right" and similar statement are merely for purposes of illustration, and are not intended to
The limitation present invention.
Referring to Figure 1, Fig. 1 is a kind of overall structure of aircraft with closed type fuselage provided in an embodiment of the present invention
Schematic diagram.The embodiment of the present invention provides a kind of aircraft with closed type fuselage, the aircraft with closed type fuselage
Including fuselage 100, fuel tank 200, connecting base 300, internal combustion engine 400, generator 500, rectifier 600, controller 700 and battery
800.Now respectively to fuselage 100, fuel tank 200, connecting base 300, internal combustion engine 400, generator 500, rectifier 600, controller 700
Following detailed description is carried out with battery 800:
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 is added into the fuel tank 200 being located in ducted body 140, the present invention is implemented
A kind of aircraft with closed type fuselage that example provides can also include sealing cover 150, and can be in first side 110
It is provided with through-hole and pedestal.The sealing cover 150 can be hinged by the pedestal and the first side 110, and institute
Stating 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 embodiment of the present invention provides a kind of facing for aircraft with closed type fuselage
Diagram is intended to.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 embodiment of the present invention, sealing cover 150 and pedestal are hinged, example
The edge of sealing cover 150 can be such as fixedly connected with one end of hinge, it can be with 110 phase of first side by the other end of hinge
Mutually it is fixedly connected；Meanwhile clamping joint has can be set in the other end at 150 edge of sealing cover, it is corresponding in first side 110
The clamping seat being mutually matched with clamping joint can be set in position.When needing to inject fuel into fuel tank 200, can open close
Capping 150；It, can be by the way that clamping joint and clamping seat be mutually clamped, to make when aircraft starts to work (such as starting to fly)
Sealing cover 150 and first side 110 are mutually permanently connected.Then during aircraft, prevent fuel tank 200 from falling,
Pre- rainwater-proof, the adverse effect being exposed to the sun to 200 safety of fuel tank.To reach the technology effect that 200 safety of fuel tank can be improved
Fruit.
As another implementation of sealing cover in the embodiment of the present invention, sealing cover 150 be can be by rubber material system
Flexible sealing lid made of work, specifically, including clamping seal head and clamping seal groove.
If Fig. 4, Fig. 4 are that the embodiment of the present invention provides a kind of single head clamping seal head of aircraft with closed type fuselage
With the schematic diagram of single head clamping seal groove.Clamping seal head 1000 and clamping seal groove 1100 all (are individually clamped close for one
End socket 1000 and single clamping seal groove 1100).The edge of sealing cover can be set clamping seal head 1000, with sealing
Clamping seal groove 1100 can be set in the first side 110 of lid EDGE CONTACT, clamping seal groove 1100 can be close with clamping
End socket 1000 is mutually matched, i.e., clamping seal head 1000 can be inserted in clamping seal groove 1100, or insertion clamping seal groove
Clamping seal head 1000 in 1100 can be separated from each other with clamping seal groove 1100.It, can be with when needing closing seam lid 150
By pressing sealing cover 150, make to be clamped in the insertion clamping seal groove 1100 of seal head 1000, at this point, the rain outside sealing cover 150
Water due to by clamping seal head 1000 blocking, will be unable to enter ducted body in, then reach can pre- rainwater-proof enter machine
Inside body, damage electric elements are avoided, the technical effect of the safety of aircraft is improved.
Fig. 7 is referred to, Fig. 7 is that the embodiment of the present invention provides a kind of concave groove 1500 of aircraft with closed type fuselage
Schematic diagram.The concave groove 1500 to match with finger is also provided on sealing cover 150, such as operator can incite somebody to action
Five fingers are put into corresponding concave groove 1500, and when being firmly lifted up, finger and concave groove 1500 can be completely attached to,
Both the frictional force between finger and sealing cover 150 had been increased, pull-up sealing cover 150 is also facilitated.Such as when needing to open sealing cover
It when 150, can place a digit into the concave groove 1500 of sealing cover 150, by pressing sealing cover 150, make flexible close
Deformation occurs for capping 150, can then enable clamping seal head 1000 and clamping seal groove 1100 to be separated from each other, to reach
It is 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 embodiment of the present invention provides the clamping seal head and card of a kind of aircraft with closed type fuselage
Connect the schematic diagram of seal groove.The quantity of clamping seal head 1000 can be two, and the quantity of clamping seal groove 1100 is also possible to
Two.Two clamping seal grooves 1100 and two clamping seal heads 1000 are mutually matched.Due to two clamping 1100 Hes of seal groove
Structure, the principle of two clamping seal heads 1000 with above-mentioned single clamping seal head 1000 and are individually clamped seal groove 1100
Structure, principle are all identical, so be not repeated herein.Due to two clamping seal grooves 1100 and two clamping 1000 phases of seal head
It connects, when rainwater penetrates into clamping seal groove 1100 and clamping seal head 1000 on the outside of sealing cover, then another blocks
Rainwater can be stopped by connecing seal groove 1100 and clamping seal head 1000, prevent rainwater from penetrating into fuselage interior.To reach raising boat
The technical effect of the safety of pocket in-flight.
In order to make aircraft that following internal combustion engines 400, generator 500 awing be avoided to encounter the barrier such as wall
When；Or drop in ground in aircraft, generator 500 strikes ground, and major accident occurs.The embodiment of the present invention mentions
A kind of aircraft with closed type fuselage supplied can also include the first balancing leg 961, the first support frame 960, second balance
Foot 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 embodiment of the present invention provides a kind of looking up for aircraft with closed type fuselage
Diagram is intended to.In an aircraft, the two sides of second side 120 can be separately installed with the first support leg and second described above
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,
Form the zone of protection of box body shape structure described above.Can be fixedly installed in the second support end of the first support leg
One balancing leg 961, the first balancing leg 961 can be rendered as can be good accessible rod-shaped with ground, in order to aircraft stop
At ground, contact by the first balancing leg 961 with ground can support the weight of aircraft itself；In the second support leg
The 4th support end can be fixedly installed the second balancing leg, the second balancing leg can be can be with the good accessible bar in ground
Shape, when resting in ground in order to aircraft, contact by the first balancing leg, the second balancing leg with ground is preferably supported
The weight of aircraft itself.Meanwhile can 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 400, hair is protected by the first interlude and the second interlude
Motor 500, rectifier 600, controller 700 and battery 800 improve in aircraft from the collision of barrier to reach
Safety technical effect.
Fig. 6 is referred to, Fig. 6 is that the embodiment of the present invention provides a kind of shock mitigation system of aircraft with closed type fuselage
Schematic diagram.In order in aircraft descent, reduce the weight of aircraft to the first balancing leg 961, the first support frame 960,
The damage of second balancing leg and the second support frame 970, can be between second support end and the first interlude in the first support frame 960
It is provided with damping spring 1200 (can be thrum spring), limited block 1300 and protruding end 1400.
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 aircraft takeoff, 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 aircraft lands
When to ground, since the own wt of aircraft is larger, under the action of inertia, the fuselage of aircraft 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 aircraft can be weakened
And the first recoil strength between support frame 960, then avoid the fuselage of aircraft and the first support frame 960 from being damaged.To
Reach the technical effect for improving aircraft 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 aircraft.To reach the cruise duration for improving aircraft
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 aviation
The second side 120 of device 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 aircraft
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 aircraft,
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 aircraft, 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 aircraft.To reach promoted aircraft 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 aircraft are fixed on one
It rises；So that aircraft is awing, internal combustion engine 400 also can endlessly provide energy, and supply is in aviation in-flight
Device uses.To reach the technical effect for improving the cruise duration of aircraft.
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 aircraft 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 supplying aircraft flight control system needed for electric current voltage, ensure for 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 aircraft operating status, such as when
When aircraft needs work, throttle can be opened, so that internal combustion engine 400 is that generator 500 provides energy；When aircraft 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 aircraft, use ability caused by internal combustion engine 400 for the power-equipment of aircraft.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.To be navigated to pull by the rotation of the first blade 900
Pocket is risen or is declined, power needed for providing flight for aircraft.
In order to which more abundant power can be provided to aircraft 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 aircraft.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, to pull aircraft to be risen or be declined, power needed for providing flight for aircraft.
In order to be provided more to aircraft 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 aircraft.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, to pull aircraft to be risen or be declined, power needed for providing flight for aircraft.
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
Aircraft provides more abundant power, uses ability caused by internal combustion engine 400 for the power-equipment of aircraft.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
Connection, can be such that the 4th blade 930 is rotated electrical energy transportation to the 4th motor to provide electric energy for the 4th motor；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, to pull aircraft to be risen or be declined, power needed for providing flight for aircraft.
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 aircraft, set ability caused by internal combustion engine 400 for the power of aircraft
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
Connection, can be such that the 5th blade 940 is rotated electrical energy transportation to the 5th motor to provide electric energy for the 5th motor；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, to pull aircraft to be risen or be declined, power needed for providing flight for aircraft.
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 aircraft, make ability caused by internal combustion engine 400 for boat
The power-equipment of pocket 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
Connection, can be such that the 6th blade 950 is rotated electrical energy transportation to the 6th motor to provide electric energy for the 6th motor；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, to pull aircraft to be risen or be declined, power needed for providing flight for aircraft.
It should be noted that in order to take off, in-flight and in landing three phases to aircraft, fuel tank 200, internal combustion engine
400, the control of aircraft 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, aircraft when taking off, can be controlled by the flight control system of aircraft 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 aircraft
It begins to ramp up from ground to aerial.
Second of embodiment, aircraft 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 aircraft 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
Aircraft continues on original direction and height is flown, or change nobody heading and height technology effect
Fruit.
The third embodiment, aircraft 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 aircraft 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, aircraft will be from gradually droping to ground in the air.
The present invention provides a kind of aircraft with closed type fuselage, by the way that fuel tank 200 is fixed on the hollow of fuselage 100
In body 140, then the second side 120 of the first fastening face 310 of connecting base 300 and fuselage 100 is detachably connected, internal combustion
The first shell 410 of machine 400 and the second fastening face 320 of connecting base 300 are detachably connected, the oil inlet of internal combustion engine 400
It is interconnected with fuel tank 200, 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 of generator 500 and rectifier 600
The connection of first terminals, the second terminals and controller 700 connection of rectifier 600, the third terminals and electricity of rectifier 600
First sending end in pond 800 connects.Since the second sending end of battery 800 is connected with the spark plug of internal combustion engine 400, can including
Combustion engine 400 by fuel tank 200 fuel it is interior can be converted into mechanical energy after, then electric energy converted for mechanical energy by generator 500,
To serve as the power capacity source of aircraft.To reach the technical effect in the cruise duration for improving aircraft.
It should be noted last that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it,
Although being described the invention in detail referring to example, those skilled in the art should understand that, it can be to the present invention
Technical solution be modified or replaced equivalently, without departing from the spirit and scope of the technical solution of the present invention, should all cover
In the scope of the claims of the present invention.
Claims (4)
1. a kind of aircraft with closed type fuselage, which is characterized in that the aircraft includes:
Fuselage, the fuselage is provided with first side, second side, third side and ducted body, and the third side is located at
Between the first side and the second side；
Fuel tank, the fuel tank are fixed in the ducted body, and the fuel tank is located at the first side and described second
Between side；
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 second side 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；
The aircraft further include:
Sealing cover, wherein the edge of the sealing cover is provided with clamping seal head, in the institute with the sealing cover EDGE CONTACT
It states and is provided with clamping seal groove in first side, the clamping seal groove and the clamping seal head are mutually matched, so that described
Clamping seal head can be inserted in the clamping seal groove.
2. as described in claim 1 with the aircraft of closed type fuselage, 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. as claimed in claim 2 with the aircraft of closed type fuselage, which is characterized in that the aircraft 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.
4. aircraft as claimed in claim 3, it is characterised in that:
The first side is provided with through-hole and pedestal；
Described device further include:
Sealing cover, the sealing cover are hinged by the pedestal and the first side, and the fuel tank is located at the sealing
Between lid and the second side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810996999.8A CN109319144A (en) | 2018-08-29 | 2018-08-29 | Aircraft with closed type fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810996999.8A CN109319144A (en) | 2018-08-29 | 2018-08-29 | Aircraft with closed type fuselage |
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| CN109319144A true CN109319144A (en) | 2019-02-12 |
Family
ID=65263862
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| CN201810996999.8A Withdrawn CN109319144A (en) | 2018-08-29 | 2018-08-29 | Aircraft with closed type fuselage |
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Application publication date: 20190212 |