CN108609168A - A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact - Google Patents
A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact Download PDFInfo
- Publication number
- CN108609168A CN108609168A CN201810565825.6A CN201810565825A CN108609168A CN 108609168 A CN108609168 A CN 108609168A CN 201810565825 A CN201810565825 A CN 201810565825A CN 108609168 A CN108609168 A CN 108609168A
- Authority
- CN
- China
- Prior art keywords
- holder
- unmanned plane
- fuselage
- fixed plate
- fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002828 fuel tank Substances 0.000 claims abstract description 35
- 239000003921 oil Substances 0.000 claims description 53
- 238000013016 damping Methods 0.000 claims description 42
- 230000005611 electricity Effects 0.000 claims description 36
- 239000011120 plywood Substances 0.000 claims description 25
- 229910052751 metal Inorganic materials 0.000 claims description 19
- 239000002184 metal Substances 0.000 claims description 19
- 230000035939 shock Effects 0.000 claims description 18
- 239000007788 liquid Substances 0.000 claims description 15
- 238000012806 monitoring device Methods 0.000 claims description 7
- 238000010079 rubber tapping Methods 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 5
- 150000002739 metals Chemical class 0.000 claims description 5
- 239000000295 fuel oil Substances 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 230000003111 delayed effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 28
- 230000003139 buffering effect Effects 0.000 description 10
- 230000006870 function Effects 0.000 description 10
- 239000007787 solid Substances 0.000 description 7
- 230000004888 barrier function Effects 0.000 description 6
- 230000005484 gravity Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000009423 ventilation Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000004080 punching Methods 0.000 description 3
- 239000011435 rock Substances 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 210000000349 chromosome Anatomy 0.000 description 2
- 239000012141 concentrate Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000011176 pooling Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000003351 stiffener Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact, including fuselage and the multiple rotors for being disposed in an evenly spaced relation in fuselage side, the bottom of the fuselage are equipped with engine module, generator module and head assembly, and the fuselage top is equipped with fuel tank；The fuselage interior is equipped with control system, the fuselage includes the first fixed plate and the second fixed plate, the engine module, generator module and head assembly are set to the first fixed plate lower end, the engine module is connect with generator, the engine module can drive generator operation, the generator and head assembly to be electrically connected respectively with control system；The rotor is hinged at the first fixed plate, and can realize the folding of rotor, and the rotor is proximal end close to fuselage one end, it is distal end far from fuselage one end, the distal end of the rotor be equipped with motor and rotation paddle, the motor be electrically connected connected control system and rotation paddle, and can drive rotation paddle rotation.
Description
Technical field
The present invention relates to the mixed dynamic air vehicle technique fields of oily electricity, and in particular to a kind of more rotor fuel-electrics of compact are mixed to move nobody
Machine.
Background technology
With the development of new and high technology, the progress of unmanned air vehicle technique constantly making a breakthrough property, unmanned plane will obtain rapidly
Development and widely application.In unmanned plane field, although a series of advanced skills such as vision positioning, high definition figure pass, perception obstacle
Art continues to develop, this root problem of continuing a journey is not solved effectively but always.
Multi-rotor unmanned aerial vehicle is the lift that is generated by multiple rotors to balance the gravity of aircraft, and aircraft can be flown
Get up, the steady and posture of aircraft is controlled by changing the rotating speed of each rotor.So multi-rotor aerocraft can hover,
It is flown with arbitrary speed in certain speed range, is basically the platform of an airflight, can add on platform
Fill the instrument of the devices such as sensor, the position indicator of oneself or even manipulator etc.It does not need runway can VTOL,
It can hover in the air after taking off.Its manipulating principle is simple, around four corresponding aircraft of remote sensing operation of control device,
Upper and lower and yaw direction movement.In terms of automatic pilot, more rotor autopilot control methods are simple, and controller parameter is adjusted
Also very simple.Integrated operation is simple, can be operated by simply training everybody, in addition, more rotors do not have movable part, it
Reliability be substantially dependent on the reliability of brushless motor, therefore reliability is higher.In comparison, fixed-wing and helicopter
There is movable mechanical connecting element, abrasion is will produce in flight course, leads to reliability decrease.And more rotors can hover,
Flight range is controlled, and it is safer to be relatively fixed the wing.
Common unmanned plane is in the majority with electronic unmanned plane in the market, followed by the dynamic unmanned plane of oil.Wherein electronic unmanned plane：With
Lithium battery provides power.Advantage is simple in structure, is easy maintaining；Relatively low to flying hand requirement, purchasing price is cheap；While because
To compare light and flexible, transport transition is more convenient quick.But a disadvantage is that under lithium battery technology limitation, load-carrying and continuation of the journey ratio
Smaller, outgoing flight needs to carry a large amount of batteries even generator.The dynamic unmanned plane of oil：There is provided power with fuel oil, have pure oil dynamic and
Oily electricity mixing two types.Among the unmanned plane of both types, but it is the most complicated with oily electricity mixing type.The dynamic unmanned plane of oil
Advantage is load-carrying and all bigger than electronic unmanned plane, technology content higher of continuing a journey.Disadvantage be also it will be apparent that due to complicated,
Maintaining difficulty is big, operates high to flying hand requirement；Purchasing price is more expensive；The vibrations of engine module are big, and the service life is not long etc..
Now unmanned plane market is gradually matured, and the intelligence degree of unmanned plane is continuously improved, and operation difficulty is increasingly
It is low.Even the complicated dynamic unmanned plane of oil, can realize the functions such as a key landing, autonomous flight, with little need for people
Work operates.Although unmanned plane operation is more convenient, the mixed dynamic unmanned plane of oil electricity in the prior art is due to devising oily electric energy
The conversion of amount, complicated integral structure, in design, each parts design is not compact enough so that unmanned plane overall volume is larger, nothing
By be carry or flight it is all not convenient enough.
Invention content
The present invention provides a kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact, mixed dynamic more for solving oil electricity in the prior art
Rotor wing unmanned aerial vehicle body volume is big, carries and place inconvenient problem
To solve the above-mentioned problems, the present invention provides a kind of more rotor fuel-electrics of compact mixed dynamic unmanned plane, including fuselage and uniformly
Multiple rotors of fuselage side are arranged at intervals on, the bottom of the fuselage is equipped with engine module, generator module and holder
Component, the fuselage top are equipped with fuel tank；The fuselage interior is equipped with control system, and the fuselage includes the first fixed plate and the
Two fixed plates, the engine module, generator module and head assembly are set to the first fixed plate lower end, the engine mould
Group is connect with generator, and the engine module can drive generator operation, the generator and head assembly respectively with control
System electrical connection processed；
The rotor is hinged at the first fixed plate, and can realize the folding of rotor, and the rotor is close to fuselage one end
It is distal end far from fuselage one end for proximal end, the distal end of the rotor is equipped with motor and rotation paddle, and the motor is electrically connected connected control system
With rotation paddle, and can drive rotation paddle rotation；
The control system is fixed between the first fixed plate and the second fixed plate, and the fuel tank is set in the second fixed plate, and
It is connect with engine module by oil circuit.
The mixed dynamic unmanned plane of oil electricity of the present invention is set there are six rotor, and six rotors are uniformly arranged on the side of fuselage,
It is symmetrically set so that fuselage is in Equilibrium state in natural conditions.Since engine module and generator are in work
As when will produce than stronger vibrations, therefore engine module and generator are set to the bottom of fuselage, simultaneously as starting
Machine module and generator weight are larger, and the center of gravity of entire fuselage can be made on the lower in fuselage bottom by being arranged so that flight is more flat
Surely.In order to enable camera to have most wide coverage, equally head assembly is arranged in the bottom of fuselage by the present invention, in order to protect
The shooting stability of head assembly is held, the present invention is equipped with holder bumper bracket in the junction of holder and fuselage so that shooting is more
Stablize, is shaken caused by reducing flight and engine module, the vibrations of engine module.
The fuel tank is set to the top of fuselage, since engine module and generator is arranged in fuselage bottom, in order to enable machine
Body is compact, while avoiding mutual interference, and keeps fuel tank to fix as possible and more stablize, and the present invention is by fuel tank and engine mould
Group, generator are spaced apart, and on the one hand do not influence the volume of whole device, are on the other hand whole while reaching compact-sized
Machine operation is more stablized.The fuel tank is connect by oil circuit with engine module so that the oil in fuel tank can be normally delivered to
Engine module is operated for engine module.
The control system is mainly used for controlling outputting and inputting for electric energy so that electric energy can be different according to being allocated to
Mechanism uses.
While in order to keep unmanned plane total compacter, each actuating unit of unmanned plane influences each other minimum,
The fuselage of unmanned plane is divided into several different levels by the present invention.And separated by the first fixed plate and the second fixed plate,
Reduce the interference between different institutions, overall structure is made more to stablize.
First fixed plate and the second fixed plate are arranged in parallel, wherein the setting of the first fixed plate is fixed in lower layer, second
Plate setting on upper layer, to the middle level that is divided under the first fixed plate that be between low layer, the first fixed plate and the second fixed plate be and
Second fixed plate, three different levels of upper top layer make unmanned plane integrally tie wherein in order to reduce the focus point of whole device
Structure is more stablized, and the engine module, generator and head assembly are arranged in low layer.
In order to enable the mixed dynamic unmanned plane structure of oil electricity is compacter, also the winged of unmanned plane stops more stablizing, and the present invention is by nothing
Man-machine rotor is arranged in the first fixed plate side, can reduce the center of gravity of unmanned plane entirety, in addition, the rotor and first is fixed
Plate is hinged at, and can realize the folding of rotor, and folding direction is fold-down, wherein distal end is equipped with motor and rotation paddle,
When not in use, rotation paddle can be removed.
Further, the unmanned plane is additionally provided with level Four shock-damping structure, includes first subtracting by the way that multigroup bolster connects
Shake component, the second dampening assembly, third dampening assembly and the 4th dampening assembly.
Since the operating of engine module and generator will produce prodigious vibration, in order to reduce vibration to unmanned plane during flying
Interference, and reduce damage of the vibration to unmanned plane inner components, the present invention is in engine module and generator and first
Fixed plate junction is provided with engine modular damping device.The damping has many levels, wherein the first dampening assembly,
Second dampening assembly, third dampening assembly and the 4th dampening assembly are sequentially connected from the bottom to top, form the effect of damping step by step.
The wherein described dampening assembly can be the elastic element for having cushioning effect, can also be flexible material be made,
Damping with cushioning effect is connected by bolster between the dampening assembly, the bolster can be have it is slow
The cushion rubber bumper or shock-absorbing ball or shock ring or damping spring etc. of punching effect, can realize better damping.
Further, first dampening assembly includes first for stationary engine component and generator assembly
Frame, and the second support by shock-absorbing ball connection first support；
Second dampening assembly includes third holder, and the third holder is rotatablely connected with second support by bolt part, and
It is equipped with elastomeric pad in junction；
The third dampening assembly includes the 4th holder and the 5th holder, and the 4th holder is fixedly connected with third holder, institute
It is connect by shock ring between the 5th holder between stating the 4th；
4th dampening assembly include the 6th holder being fixedly connected with the 5th holder and connect the 6th holder and first fix
The flexible carry component of plate.
The downside of the first support connects generator, and the engine connects generator, under first fixed plate
Side is additionally provided with accumulator, and the engine is that the oil in fuel tank burns in engine cylinder, pushes piston reciprocating,
The reciprocating motion of piston is become rotary motion by toggle again, as long as this rotary motion is exported by flywheel inertia energy storage
Sustainable supply fuel, this movement will continue.
Wherein start to remember to start to rely on storage battery power supply, engine rotation is driven after power supply.Work as normal working of engine
Afterwards, driven by engine generator starts to generate electricity, first, the electric elements to unmanned plane are powered, second is that charging a battery.
Since engine and generator weight are larger, it is arranged in the bottom of the first fixed plate, it is on the one hand so that main
Operation element weight on the other hand can be made to concentrate on the second fixed plate bottom far from focus, reduce vibration amplitude.
The first support is mainly used for stationary engine component and generator assembly, and the first support may be configured as two
The ventilative structure in face, heat dissipation caused by preventing engine and generator heat production excessive are uneven.The second support with first
Frame is connected by shock-absorbing ball, since there is liquid good cushioning effect, the present invention liquid damping ball is arranged, is realized more preferable
Damping effect.
The third holder, the third holder are rotatablely connected with second support by bolt part, due to second support and
Third holder is stiffener, therefore by the way that elastomeric pad is arranged in the junction of the two, and therefore, the second dampening assembly is on the one hand
Shake can be extended away from addition can also playing good buffering effect.
4th holder and the 5th holder are similarly rigid structure, and the two is connected by shock ring, form certain delay
Space is rushed, buffering effect is reached.
4th dampening assembly includes the 6th holder being fixedly connected with the 5th holder and connect the 6th holder and first
The flexible carry component of fixed plate.The fixed plate of 4th dampening assembly one end connection fuselage, the other end connect third damping
Component realizes the connection of total time, airframe, and engine, generator and dampening assembly, and therefore, the 4th dampening assembly should have one
Fixed elasticity realizes buffering, there is certain stress intensity again.Therefore the flexible carry component of present invention setting realizes flexible buffer
Function and carry function.
Therefore the present invention is by being arranged multilayer bracket so that certain cushion space, and each holder are formed between holder
Between connected by the damping ring of liquid damping ball or multi-layer annular with cushioning effect, extend shake away from while, reach
Buffering effect plays the role of multi-buffer.
Further, the first support is square set, and four angles protrude a join domain respectively, described each to connect
It connects region and is equipped with multiple first through hole；
The second support include two groups of bolsters, wherein every group of bolster include with first support buffer board disposed in parallel,
And it is vertical with buffer board, and set on two " n " type hanging pieces at buffer board both ends, the both ends of the buffer board are equipped with multiple second
Through-hole, and fixed with first through hole by multiple shock-absorbing balls；
The third holder includes multiple strip metal parts, and one end of wherein each two metalwork is correspondingly connected with " n " type hanging piece
Both sides, the other end are fixedly connected with the 4th holder；
4th holder includes multiple sheet metals equipped with third through-hole, is delayed wherein each sheet metal bottom surface is fixedly connected with one group
Stamping；
Described 5th is provided with multiple fourth holes, and is connect with third through-hole by shock ring.
Wherein first support is square set, is arranged on the region of square set main body connection generator a plurality of with ventilation
The ventilation slot of heat sinking function, in order to reduce weight support frame, the second support junction of the first support and buffer structure is prominent
The join domain gone out, the join domain may be alternatively provided as rectangular or round or other shapes, in order to preferably with
Two holders are fixed, and the first stable dampening assembly is formed.Preferably, the region is square region, each square region
If there are four first through hole, for connecting second support.
While in order to realize cushioning effect, reducing overall volume and weight, the buffer board of two pieces of strips is arranged in the present invention,
Wherein two block buffering plates are mutually parallel, and are separately connected corresponding two angles of two parallel edges of square set, and buffer board both ends
It is respectively equipped with multiple second through-holes, it is preferred that four the second through-holes corresponding with first through hole position in first support of setting, institute
It states and is connected by liquid damping ball between first through hole and the second through-hole, realize cushioning effect.
It is connected between second support and third holder to further realize, " n " type hanging piece is set in the second support,
Buffer board end positions are separately positioned on, and are fixedly connected, therefore, the setting of " n " type hanging piece primarily serves the effect of linking.
The third holder includes multiple strip metal parts, and wherein each two metalwork the same end is correspondingly connected with " n " type and hangs
The both sides of part, and junction is equipped with flexible gasket, forms the articulated structure with cushioning effect, the other end is fixedly connected with the 4th
Frame；4th holder is multiple sheet metals, and each sheet metal is correspondingly connected with one group of bolster, and connects the strip metal
Part, four angles of the sheet metal are equipped with multiple third through-holes, and the third through-hole of the 5th holder is connected by shock ring.
Therefore, the multilayer bracket structure that the present invention is arranged saves space, will not increase excessive weight to unmanned plane and increase
Add energy consumption, and mutual connection configuration is reasonable, realize the effect buffered step by step, the flight of unmanned plane is made more to stablize,
The service life of electric elements can be extended.
Further, the 6th holder is double-layer structure, including top plate, lower plywood and connecting rod, the connecting rod
Sequentially pass through top plate, lower plywood and the 5th holder so that the both ends of connecting rod are respectively fixedly connected with top plate and the 5th
Frame is connected between the lower plywood and top plate by shock ring.
The lower plywood is arranged between top plate and the 5th holder, but the bore dia of lower plywood setting is than connecting rod
Greatly, therefore connecting rod passes through lower plywood not connect with lower plywood.And the 6th holder top plate and lower plywood between have one
Fixed space, and the two is connected by shock ring, damping effect is realized, in addition to using shock ring, other flexible connecting members
The pooling feature of the present invention, such as liquid damping ball can be achieved.
Therefore double-deck damping space is formd between top plate, lower plywood and the 5th holder, plays better damping
Effect.
Further, the flexible carry component includes and fixed first fixed end of the first fixed plate, the 6th holder
Fixed second fixed end and both ends are equipped with the spring part of hook, and one end hook first fixed end of connection is another
End hook the second fixed end of connection.
The flexibility carry component is used to connect the first fixed plate of multilayer Buffer Unit and fuselage, it is therefore desirable to have soft
Property while, also have certain carry ability.
It is described flexibility carry component include and fixed first fixed end of the first fixed plate, the 6th holder fixed second
Fixed end and both ends are equipped with the spring part of hook, and first fixed end is consolidated with the first fixed plate by screw
Fixed, second fixed end is fixed again by screw and the 6th preparation, it is preferred that is fixed on the lower plywood of the 6th holder
Outer rim.In order to realize better fixation, the flexibility carry component is six, and is uniformly distributed so that fuselage weight distribution is equal
It is even.The both ends of the spring part are equipped with hook, are respectively used to catch on the first end and the second end, realize carry, have simultaneously
Good spring function, plays cushioning effect.
In order to further fix multilayer Buffer Unit, the present invention is additionally provided with vertical pendant, vertical pendant one end connection
The bottom of first fixed plate, the other end connect the medium position of lower plywood, in conjunction with six flexible carry components, form stable consolidate
Determine structure, avoids lower end Buffer Unit and engine, generator rocks so that airframe structure is more stablized, component
Connection is more closely.
Further, the fuel tank assembly includes fuel tank, level monitoring device and oil circuit for detecting Fuel Oil Remaining,
It is equipped with trepanning on the upside of the fuel tank, the level monitoring device is set to tapping, and according to liquid level difference dynamic detection oil mass information,
Described oil circuit one end connects the trepanning, and the other end connects engine.
The fuel tank is set in the second fixed plate, and is fixed by multiple tank support components, and rocking for fuel tank is avoided,
Influence the work of unmanned plane.The upside of the fuel tank be equipped with trepanning, the level monitoring device be set to the tapping, by
Tapping is laid with pipeline and measures liquid level difference, realizes that the dynamic of oil mass measures, and will not influence to survey because of the change of flight angle
Determine result.
Further, the mixed dynamic unmanned plane of the oil electricity further includes two symmetrically arranged tripods, described two tripod difference
The both sides of the first fixed plate bottom surface are fixed at, entire unmanned plane is used to support.
In order to enable unmanned plane to be smoothly parked in ground in startup and landing, the present invention is in the first fixed plate of unmanned plane
Bottom.It is reduced when making vibrations be transmitted to the first fixed plate by damping due to engine module and generator
It is enough.Therefore the tripod is arranged in the bottom of the first fixed plate, and the tripod struts certain angle to both sides, from front
See, be in splayed so that unmanned plane can gentle support in ground.Described two tripods are symmetrical arranged, solid with the first fixed plate
Fixed connection.
Further, the tripod includes main tripod and tripod supporting rod, and it is solid that described main tripod one end is fixedly connected with first
Fixed board, the other end are fixedly connected with tripod supporting rod, and the main tripod and tripod supporting rod are vertical.
The main tripod plays main support, and one end is fixedly connected with the first fixed plate, and other end connection support bar is described
Supporting rod is cylindric, is supported in ground, for held stationary, the main tripod and tripod supporting rod are vertical.
Further, the tripod supporting rod is equipped with multi-turn antiskid glue sleeve.
Due to unmanned plane takeoff and landing place may smoother, the present invention be provided with antiskid glue sleeve
It is arranged on supporting rod, can prevents from skidding, makes to park and more stablize.
Further, the unmanned plane is equipped with infrared obstacle avoidance system, the infrared obstacle avoidance system, the infrared obstacle avoidance system
Set on the front side of fuselage.
The infrared obstacle avoidance system includes the infrared sensor being arranged on front side of fuselage and control terminal, the infrared sensing
Device includes infrared transmitter and infrared remote receiver, and infrared transmitter emits infrared beam according to certain angle, after encountering object,
Light can reversely return, and after detecting reflected light, pass through the geometric triangulation relationship in structure, so that it may to calculate object distance.
In a certain range, if without barrier, the infrared ray launched gradually weakens, finally because propagation distance is remoter
It disappears.If there is barrier, infrared ray encounters barrier, is reflected to up to sensor and receives head.Sensor detects this letter
Motor number is controlled again realizes automatic obstacle-avoiding.Due to the present invention is directed medium-sized oil electricity is mixed to move unmanned plane, in flight
Speed will not be too fast, therefore only needs to ensure front avoidance.
Further, the unmanned plane is additionally provided with figure and passes antenna and GPS positioning antenna, and the figure passes antenna and GPS positioning
Antenna is set to the both sides of front fuselage, and the figure passes antenna and GPS positioning antenna is rotatably connected with fuselage.
The present invention is equipped with two chromosomes and passes antenna and two GPS positioning antennas, in order to make the unmanned plane structure of the present invention more
It is compact, volume can be reduced in storage, figure of the present invention passes antenna and GPS positioning antenna is rotatably connected with fuselage.
When it is desired to be used, antenna is rotated up vertical as fuselage, after use, is being rotated down, it being capable of maximum limit
The reduction of degree occupies volume.
Further, the figure passes the direction of rotation of antenna and GPS positioning antenna perpendicular to plane where fuselage.
It is hinged with fuselage that the figure passes antenna and GPS positioning antenna.
Further, the unmanned plane is additionally provided with the accumulator for storing electrical energy, and the accumulator is set to first and fixes
Board bottom portion, with power generation mechatronics.
Since unmanned plane is directly initiated by engine module, it cannot achieve stablizing for unmanned plane and start, therefore, the present invention exists
First fixed plate bottom is provided with accumulator, and after capable of being opened by one key unmanned plane, accumulator meeting priority task directly utilizes accumulator
The electricity of savings starts unmanned plane, on the one hand avoids the startup of each mechanism of vibration influence of engine module and generator, separately
Outside, the energy of oil is eventually converted into electric energy and is also required to the regular hour, therefore, booting operation can be accelerated using accumulator
Speed ensure that the stability of booting.In addition after start completion, the running of the engine module and generator is final to convert
Electric energy, wherein an electric energy part be used as accumulator charging, on the other hand be used as unmanned plane operation.
In order to mitigate the weight of entire unmanned plane, reduce the volume of unmanned plane, the accumulator that the present invention is arranged is used only as nothing
Man-machine startup is not used in and provides electricity to the flight of unmanned plane, can reduce the volume of battery, reduces occupied space, make
The structure of unmanned plane is compacter.
Beneficial effects of the present invention：
（1）The mixed dynamic unmanned plane of oil electricity that the present invention is arranged can realize that the energy of oil is converted to electric energy by unmanned plane, finally convert
At the kinetic energy of unmanned plane during flying, it can largely extend the flight time of multi-rotor unmanned aerial vehicle, the flight time is enable to reach
Three hours.
（2）The mixed dynamic unmanned plane of oil electricity of the present invention is compact-sized, and integral layout is reasonable, can overcome in the prior art, oil
The mixed dynamic unmanned plane volume of electricity is big, carrying, placement and problem inconvenient for operation.
（3）The fuselage of unmanned plane is divided into several different levels by the present invention.And it is solid by the first fixed plate and second
Fixed board separates, and reduces the interference between different institutions, and overall structure is made more to stablize.
（4）The oil electricity of the present invention mixes dynamic unmanned aerial vehicle design multigroup damping device, reduction that can be as much as possible and starts
The vibrations that machine module and generator are brought reduce the damage to each parts of unmanned plane, prolong the service life.
（5）The accumulator that the present invention is arranged is used only as the startup of unmanned plane, is not used in and provides electricity to the flight of unmanned plane
Amount can reduce the volume of battery, reduce occupied space, keep the structure of unmanned plane compacter.
Description of the drawings
Fig. 1 is the mixed dynamic unmanned plane complete machine figure of present invention oil electricity.
Fig. 2 is that unmanned plane removes shell figure.
Fig. 3 is unmanned plane partial exploded view of the present invention.
Fig. 4 is unmanned plane shock-damping structure partial exploded view of the present invention.
Fig. 5 is the another shock-damping structure partial exploded view of unmanned plane of the present invention.
Fig. 6 is the 4th dampening assembly schematic diagram of unmanned plane of the present invention.
Fig. 7 is unmanned plane entirety explosive view of the present invention.
Fig. 8 is stereogram after unmanned plane of the present invention folds.
Fig. 9 is another stereogram after unmanned plane of the present invention folds.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without making creative work, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
Embodiment
A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact, as shown in Figure 1, including fuselage 1 and being disposed in an evenly spaced relation in machine
The bottom of multiple rotors 2 of body side, the fuselage 1 is equipped with engine module 3, generator module 4 and head assembly 5, such as
Shown in Fig. 2,1 top of the fuselage is equipped with fuel tank 6；The fuselage 1 is internally provided with control system, and the fuselage 1 includes first solid
Fixed board 11 and the second fixed plate 12, the engine module 3, generator module 4 and head assembly 5 are set to the first fixed plate 11
Lower end, the engine module 3 are connect with generator module 4, and the engine module 3 can drive generator module 4 to operate,
The generator module 4 and head assembly 5 are electrically connected with control system respectively；
As shown in Fig. 2, the rotor 2 and the first fixed plate 11 are hinged at, and it can realize the folding of rotor 2, the rotation
The wing 2 is proximal end close to 1 one end of fuselage, is distal end far from 1 one end of fuselage, and the distal end of the rotor 2 is equipped with motor 22 and rotation paddle 21,
The motor be electrically connected connected control system and rotation paddle 21, and can drive rotation paddle 21 rotate；
As shown in Fig. 2, the control system is fixed between the first fixed plate 11 and the second fixed plate 12, the fuel tank 6 is set to
In second fixed plate 12, and pass through oil circuit（It is not indicated in figure）It is connect with engine module 3.
The mixed dynamic unmanned plane of oil electricity of the present invention is set there are six rotor 2, and six rotors 2 are uniformly arranged on the side of fuselage 1
Face is symmetrically set so that fuselage 1 is in Equilibrium state in natural conditions.Due to engine module 3 and generator
Module 4 is will produce at work than stronger vibrations, therefore engine module 3 and generator module 4 are set to the bottom of fuselage 1
Portion, simultaneously as engine module 3 and 4 weight of generator module are larger, entire fuselage 1 can be made in 1 bottom of fuselage by being arranged
Center of gravity is on the lower so that flight is more steady.In order to enable camera to have most wide coverage, the present invention is equally by head assembly
5 are arranged in the bottom of fuselage 1, and in order to keep the shooting stability of head assembly 5, the present invention is in the junction of holder and fuselage 1
Equipped with holder bumper bracket so that shooting is more stablized, and reduces flight and engine module 3, engine module 3 shake caused rolling
It is dynamic.
The fuel tank 6 is set to the top of fuselage 1, due to 1 bottom of fuselage setting engine module 3 and generator module 4, is
So that fuselage 1 is compact, while mutual interference is avoided, and keep fuel tank 6 to fix as possible and more stablize, the present invention is by fuel tank 6
It is spaced apart with engine module 3, generator module 4, does not on the one hand influence the volume of whole device, reach compact-sized same
When, on the other hand it is that complete machine operation is more stablized.The fuel tank 6 passes through oil circuit（It is not indicated in figure）Connect with engine module 3
It connects so that the oil in fuel tank 6 can normally be delivered to engine module 3, be operated for engine module 3.
The control system is mainly used for controlling outputting and inputting for electric energy so that electric energy can be different according to being allocated to
Mechanism uses.
While in order to keep unmanned plane total compacter, each actuating unit of unmanned plane influences each other minimum,
The fuselage 1 of unmanned plane is divided into several different levels by the present invention.And divided by the first fixed plate 11 and the second fixed plate 12
It cuts open, reduces the interference between different institutions, overall structure is made more to stablize.
First fixed plate, 11 and second fixed plate 12 is arranged in parallel, wherein the first fixed plate 11 is arranged in lower layer, the
The setting of two fixed plates 12 is on upper layer, to be divided into the first fixed plate 11 times for low layer, the first fixed plate 11 and the second fixed plate 12
Between be middle level and the second fixed plate 12 upper top layer, three different levels, wherein in order to reduce the center of gravity of whole device
Point makes unmanned plane overall structure more stablize, and the engine module 3, generator module 4 and head assembly 5 are arranged low
Layer.
In order to enable the mixed dynamic unmanned plane structure of oil electricity is compacter, also the winged of unmanned plane stops more stablizing, and the present invention is by nothing
Man-machine rotor 2 is arranged in 11 side of the first fixed plate, the center of gravity of unmanned plane entirety can be reduced, in addition, the rotor 2 and first
Fixed plate 11 is hinged at, and can realize the folding of rotor 2, and folding direction is fold-down, wherein distal end is equipped with motor
Rotation paddle 21 can be removed when not in use with rotation paddle 21.
Further, as shown in figure 3, the unmanned plane is additionally provided with level Four shock-damping structure, including connected by multigroup bolster
The first dampening assembly 100, the second dampening assembly 200, third dampening assembly 300 and the 4th dampening assembly 400 connect.
Since the operating of engine module 3 and generator module 4 will produce prodigious vibration, in order to reduce vibration to nobody
The interference of machine flight, and damage of the vibration to unmanned plane inner components is reduced, the present invention is in engine module 3 and generator
Module 4 and 11 junction of the first fixed plate are provided with 3 damping device of engine module.The damping has many levels,
In the first dampening assembly 100, the second dampening assembly 200, third dampening assembly 300 and the 4th dampening assembly 400 from the bottom to top
It is sequentially connected, forms the effect of damping step by step.
The wherein described dampening assembly can be the elastic element for having cushioning effect, can also be flexible material be made,
Damping with cushioning effect is connected by bolster between the dampening assembly, the bolster can be have it is slow
The cushion rubber bumper or shock-absorbing ball or shock ring or damping spring etc. of punching effect, can realize better damping.
Further, as shown in figure 4, first dampening assembly 100 includes being used for stationary engine component and generator
The first support 110 of module 4, and the second support 120 by the connection first support 110 of shock-absorbing ball 130；
Second dampening assembly 200 includes third holder 210, and the third holder 210 passes through bolt part with second support 120
Rotation connection, and it is equipped with elastomeric pad 220 in junction；
The third dampening assembly 300 includes the 4th holder 310 and the 5th holder 320, the 4th holder 310 and third holder
210 are fixedly connected, and are connected by shock ring 330 between the 4th holder 310 and the 5th holder 320；
4th dampening assembly 400 includes the 6th holder 410 being fixedly connected with the 5th holder 320 and connect the 6th holder
410 and first fixed plate 11 flexible carry component 420.
As shown in Fig. 3 ~ 4, the downside connection generator module 4 of the first support 110, the engine connects generator
The downside of module 4, first fixed plate 11 is additionally provided with accumulator 7, and the accumulator 7 is set to 11 bottom of the first fixed plate, with
Generator module 4 is electrically connected.
Since unmanned plane is directly initiated by engine module 3, it cannot achieve stablizing for unmanned plane and start, therefore, the present invention
First fixed plate, 11 bottom is provided with accumulator 7, after capable of being opened by one key unmanned plane, accumulator 7 can priority task, directly utilization
The electricity that accumulator 7 is saved starts unmanned plane, and the vibration influence on the one hand avoiding engine module 3 and generator module 4 is each
The startup of mechanism, in addition, the energy of oil, which is eventually converted into electric energy, is also required to the regular hour, it therefore, can using accumulator 7
The speed for accelerating booting operation, ensure that the stability of booting.In addition after start completion, the engine module 3 and generator
The running of module 4, the electric energy finally converted, wherein an electric energy part are used as the charging of accumulator 7, are on the other hand used as unmanned plane
Operation.
In order to mitigate the weight of entire unmanned plane, reduce the volume of unmanned plane, the accumulator 7 that the present invention is arranged is used only as nothing
Man-machine startup is not used in and provides electricity to the flight of unmanned plane, can reduce the volume of battery, reduces occupied space, make
The structure of unmanned plane is compacter.
The engine is that the oil in fuel tank 6 burns in engine cylinder, pushes piston reciprocating, crank connects
The reciprocating motion of piston is become rotary motion by linkage again, as long as this rotary motion is by the lasting confession of flywheel inertia energy storage output
To fuel, this movement will continue.
Wherein the startup of engine is powered by accumulator 7, and engine rotation is driven after power supply.Work as normal working of engine
Afterwards, driven by engine generator module 4 starts to generate electricity, first, the electric elements to unmanned plane are powered, second is that being filled to accumulator 7
Electricity.
Since engine and 4 weight of generator module are larger, it is arranged in the bottom of the first fixed plate 11, on the one hand makes
On the other hand obtaining main operation element can make weight concentrate on 12 bottom of the second fixed plate far from focus, reduce shake
Dynamic amplitude.
The first support 110 is mainly used for 4 component of stationary engine module 3 and generator module, the first support
110 may be configured as the ventilative structure in two sides, and heat dissipation caused by preventing engine and 4 heat production of generator module excessive is uneven.Institute
It states second support 120 to connect by shock-absorbing ball with first support 110, since liquid has good cushioning effect, this hair
Bright setting liquid damping ball, realizes better damping effect.
The third holder 210, the third holder 210 are rotatablely connected with second support 120 by bolt part, due to
Two holders 120 and third holder 210 are stiffener, therefore by the way that elastomeric pad 220 is arranged in the junction of the two, therefore,
Second dampening assembly, 200 one side can extend shake away from addition can also playing good buffering effect.
4th holder 310 and the 5th holder 320 are similarly rigid structure, and the two is connected by shock ring 330, are formed
Certain cushion space, reaches buffering effect.
4th dampening assembly 400 includes the 6th holder 410 being fixedly connected with the 5th holder 320 and connect the 6th
The flexible carry component 420 of frame 410 and the first fixed plate 11.The fixation of 4th dampening assembly, 400 one end connection fuselage 1
Plate, the other end connect third dampening assembly 300, realize the connection of fuselage 1 and engine, generator module 4 and dampening assembly,
Therefore, the 4th dampening assembly 400 should have certain elasticity to realize buffering, there is certain stress intensity again.Therefore originally
The flexible 420 realization flexible buffer function of carry component of invention setting and carry function.
Therefore the present invention is by being arranged multilayer bracket so that certain cushion space, and each holder are formed between holder
Between connected by the damping ring of liquid damping ball or multi-layer annular with cushioning effect, extend shake away from while, reach
Buffering effect plays the role of multi-buffer.
Further, as shown in figure 5, the first support 110 is square set, four angles protrude a bonding pad respectively
Domain 111, each join domain 111 are equipped with multiple first through hole 10；
As shown in figure 5, the second support 120 includes two groups of bolsters, wherein every group of bolster includes flat with first support 110
The buffer board 121 of row setting, and it is vertical with buffer board 121, and two " n " type hanging pieces 122 at 121 both ends of buffer board are set to,
The both ends of the buffer board 121 are equipped with multiple second through-holes 20, and are fixed by multiple shock-absorbing balls and first through hole 10；
As shown in Fig. 4 ~ 5, the third holder 210 includes multiple strip metal parts 211, wherein the one of each two metalwork 211
End is correspondingly connected with the both sides of " n " type hanging piece 122, and the other end is fixedly connected with the 4th holder 310；
4th holder 310 includes multiple sheet metals 321 equipped with third through-hole 30, wherein 321 bottom surface of each sheet metal is solid
Surely one group of bolster is connected；
5th holder 320 is equipped with multiple fourth holes 40, and is connect with third through-hole 30 by shock ring 330.
Wherein first support 110 is square set, is arranged on the region of square set main body connection generator module 4 a plurality of
Ventilation slot with ventilation and heat function, in order to reduce weight support frame, the second support of the first support 110 and buffer structure
120 junctions are join domain 111 outstanding, and the join domain 111 may be alternatively provided as rectangular or round or other shapes,
In order to preferably be fixed with second support 120, the first stable dampening assembly 100 is formed.Preferably, the region is side
Shape region, each square region is set there are four first through hole 10, for connecting second support 120.
While in order to realize cushioning effect, reduce overall volume and weight, the buffer board of two pieces of strips is arranged in the present invention
121, wherein two block buffering plates 121 are mutually parallel, corresponding two angles of two parallel edges of square set are separately connected, and buffer
121 both ends of plate are respectively equipped with multiple second through-holes 20, it is preferred that 10 position of first through hole in setting four and first support 110
Corresponding second through-hole 20 is connected between the first through hole 10 and the second through-hole 20 by liquid damping ball, realizes that damping is made
With.
It connects between second support 120 and third holder 210 to further realize, is arranged in the second support 120
" n " type hanging piece 122 is separately positioned on 121 end positions of buffer board, and is fixedly connected, therefore, the setting master of " n " type hanging piece 122
Play the role of linking.
The third holder 210 includes multiple strip metal parts 211, and wherein 211 the same end of each two metalwork, which corresponds to, connects
The both sides of " n " type hanging piece 122 are connect, and junction is equipped with flexible gasket, form the articulated structure with cushioning effect, the other end is solid
Surely the 4th holder 310 is connected；4th holder 310 is multiple sheet metals 321, and each sheet metal 321 is correspondingly connected with one group and delays
Stamping, and the strip metal part 211 is connected, four angles of the sheet metal 321 are equipped with multiple third through-holes 30, and by subtracting
Shake the third through-hole 30 that ring 330 connects the 5th holder 320.
Therefore, the multilayer bracket structure that the present invention is arranged saves space, will not increase excessive weight to unmanned plane and increase
Add energy consumption, and mutual connection configuration is reasonable, realize the effect buffered step by step, the flight of unmanned plane is made more to stablize,
The service life of electric elements can be extended.
Further, as shown in fig. 6, the 6th holder 410 is double-layer structure, including top plate 411, lower plywood 412
With connecting rod 413, the connecting rod 413 sequentially passes through top plate 411, lower plywood 412 and the 5th holder 320 so that connection
The both ends of bar 413 are respectively fixedly connected with the 5th holder 320 in of top plate 411, between the lower plywood 412 and top plate 411
It is connected by shock ring in Fig. 4 330.
The lower plywood 412 is arranged between top plate 411 and the 5th holder 320, but the Kong Zhi that lower plywood 412 is arranged
Diameter is bigger than connecting rod 413, therefore connecting rod 413 passes through lower plywood 412 not connect with lower plywood 412.And the 6th holder 410
Top plate 411 and lower plywood 412 between there is certain space, and the two is connected by shock ring 330, realizes damping effect
Fruit, in addition to using shock ring 330, other flexible connecting members that can also realize the pooling feature of the present invention, such as liquid damping ball.
Therefore double-deck damping space is formd between top plate 411, lower plywood 412 and the 5th holder 320, is played more
Good damping effect.
Further, as shown in fig. 7, the flexibility carry component 420 includes solid with the first fixed plate 11 fixed first
Fixed end head 421, the spring part 423 that hook is equipped with 410 fixed second fixed end 422 of the 6th holder and both ends, it is described
One end hook the first fixed end 421 of connection, other end hook the second fixed end 422 of connection.
First fixed plate 11 of the flexibility carry component 420 for connecting multilayer Buffer Unit and fuselage 1, it is therefore desirable to
While having flexibility, also there is certain carry ability.
The flexibility carry component 420 includes and 11 fixed first fixed end 421 of the first fixed plate, the 6th holder
410 fixed second fixed ends 422 and both ends are equipped with the spring part 423 of hook, first fixed end 421 and the
One fixed plate 11 is fixed by screw, and second fixed end 422 is fixed again by screw and the 6th holder 412,
Preferably, it is fixed on the outer rim of the lower plywood 412 of the 6th holder 410.In order to realize better fixation, the flexibility carry component
420 be six, and is uniformly distributed so that 1 distribution of weight of fuselage is uniform.The both ends of the spring part 423 are equipped with hook, use respectively
In catching on the first fixed end 421 and the second fixed end 422, realizes carry, while there is good spring function, play slow
Punching acts on.
As shown in fig. 7, in order to further fix multilayer Buffer Unit, the present invention is additionally provided with vertical pendant 500, described vertical
500 one end of pendant connects the bottom of the first fixed plate 11, and the other end connects the medium position of lower plywood 412, in conjunction with six flexibilities
Carry component 420 forms stable fixed structure, avoids lower end Buffer Unit and engine, generator module 4 rocks,
So that 1 structure of fuselage is more stablized, the connection of component is more closely.
Further, as shown in fig. 7,6 component of the fuel tank includes fuel tank 6, the level monitoring for detecting Fuel Oil Remaining
Device and oil circuit（It is not indicated in figure）, for 6 upside of the fuel tank equipped with trepanning, the level monitoring device is set to tapping,
And according to liquid level difference dynamic detection oil mass information, the oil circuit（It is not indicated in figure）One end connects the trepanning, and the other end connects
Sending and receiving motivation.
The fuel tank 6 is set in the second fixed plate 12, and is fixed by 6 bracket component of multiple fuel tanks, and fuel tank 6 is avoided
It rocks, influences the work of unmanned plane.The upside of the fuel tank 6 is equipped with trepanning, and the level monitoring device is set to the tapping,
By tapping be laid with pipeline measure liquid level difference, realize oil mass dynamic measure, and will not because of flight angle change and
Influence measurement result.
Further, as shown in figure 8, the mixed dynamic unmanned plane of the oil electricity further includes two symmetrically arranged tripods 8, described two
A tripod 8 is fixed at the both sides of 11 bottom surface of the first fixed plate respectively, is used to support entire unmanned plane.
In order to enable unmanned plane to be smoothly parked in ground in startup and landing, the present invention is in the first fixed plate of unmanned plane
11 bottom is equipped with tripod 8.Since engine module 3 and generator module 4 make vibrations be transmitted to first by damping
When fixed plate 11, reduced it is enough, therefore the tripod 8 is arranged in the bottom of the first fixed plate 11, the tripod 8 to two
Certain angle is opened in side stay, and from fuselage front view, tripod is in splayed so that unmanned plane can gentle support in ground.Institute
It states two tripods 8 to be symmetrical arranged, be fixedly connected with the first fixed plate 11.
Further, as shown in figure 8, the tripod 8 includes main tripod 81 and tripod supporting rod 82, the main tripod 81 1
End is fixedly connected with the first fixed plate 11, and the other end is fixedly connected with tripod supporting rod 82, the main tripod 81 and tripod supporting rod 82
Vertically.
The main tripod 81 plays main support, and one end is fixedly connected with the first fixed plate 11, other end connection support bar,
The supporting rod is cylindric, is supported in ground, and for held stationary, the main tripod 81 and tripod supporting rod 82 are vertical.
Further, the tripod supporting rod 82 is equipped with multi-turn antiskid glue sleeve 83.
Due to unmanned plane takeoff and landing place may smoother, the present invention be provided with antiskid glue sleeve
83 are arranged on supporting rod, can prevent from skidding, and make to park and more stablize.
Further, as shown in figure 9, the unmanned plane is equipped with infrared obstacle avoidance system, the infrared obstacle avoidance system is described red
Outer obstacle avoidance system is set to the front side of fuselage 1.
The infrared obstacle avoidance system includes the infrared sensor 9 and control terminal being arranged in 1 front side of fuselage, as shown in Figure 1,
The infrared sensor 9 includes infrared transmitter 91 and infrared remote receiver 92, and infrared transmitter 91 emits red according to certain angle
Outer light beam, after encountering object, light can reversely return, after detecting reflected light, by the geometric triangulation relationship in structure, just
Object distance can be calculated.In a certain range, if without barrier, the infrared ray launched, because of propagation distance
It is remoter and gradually weaken, finally disappear.If there is barrier, infrared ray encounters barrier, is reflected to up to sensor and receives head.
Sensor detects that this signal controls motor and realizes automatic obstacle-avoiding again.Due to the present invention is directed medium-sized oil electricity is mixed
Dynamic unmanned plane too soon, therefore will not only need to ensure front avoidance in speed per hour degree.
Further, as shown in Fig. 2, the unmanned plane, which is additionally provided with figure, passes antenna 50 and GPS positioning antenna 60, the figure passes
Antenna 50 and GPS positioning antenna 60 are set to the both sides of 1 front end of fuselage, and the figure passes antenna 50 and GPS positioning antenna 60 and fuselage 1
It is rotatably connected.
The present invention is equipped with two chromosomes and passes antenna 50 and two GPS positioning antennas 60, in order to make the unmanned plane structure of the present invention
It is compacter, volume can be reduced in storage, figure of the present invention passes antenna 50 and GPS positioning antenna 60 can with fuselage 1
Rotatable connection.When it is desired to be used, antenna is rotated up as fuselage 1 vertically, after use, is being rotated down,
Occupancy volume can be maximally reduced.
Further, the figure passes the direction of rotation of antenna 50 and GPS positioning antenna 60 perpendicular to 1 place plane of fuselage.
It is hinged with fuselage 1 that the figure passes antenna 50 and GPS positioning antenna 60.
Embodiment of above is merely illustrative of the technical solution of the present invention and unrestricted, although with reference to the above preferable embodiment party
Formula describes the invention in detail, it will be understood by those of ordinary skill in the art that, it can be to technical scheme of the present invention
It modifies or equivalent replacement should not all be detached from the spirit and scope of technical solution of the present invention.Those skilled in the art can also be at this
The design that other variations etc. are used in the present invention is done in spirit, without departing from the technique effect of the present invention.These
The variation that spirit is done according to the present invention all should include within scope of the present invention.
Claims (10)
1. a kind of mixed dynamic unmanned plane of more rotor fuel-electrics of compact, including fuselage and the multiple rotations for being disposed in an evenly spaced relation in fuselage side
The wing, the fuselage are equipped with shell, and the bottom of the fuselage is equipped with engine module, generator module and head assembly, described
Fuselage top is equipped with fuel tank；The fuselage interior be equipped with control system, which is characterized in that the fuselage include the first fixed plate and
Second fixed plate, the engine module, generator module and head assembly are set to the first fixed plate lower end, the engine
Module is connect with generator, and the engine module can drive generator operation, the generator and head assembly respectively with
Control system is electrically connected；
The rotor is hinged at the first fixed plate, and can realize the folding of rotor, and the rotor is close to fuselage one end
It is distal end far from fuselage one end for proximal end, the distal end of the rotor is equipped with motor and rotation paddle, and the motor is electrically connected connected control system
With rotation paddle, and can drive rotation paddle rotation；
The control system is fixed between the first fixed plate and the second fixed plate, and the fuel tank is set in the second fixed plate, and
It is connect with engine module by oil circuit.
2. the mixed dynamic unmanned plane of oil electricity according to claim 1, which is characterized in that the unmanned plane is additionally provided with level Four damping knot
Structure includes the first dampening assembly, the second dampening assembly, third dampening assembly and the 4th damping connected by multigroup bolster
Component.
3. the mixed dynamic unmanned plane of oil electricity according to claim 1, which is characterized in that
First dampening assembly includes the first support for stationary engine component and generator assembly, and passes through damping
Ball connects the second support of first support；
Second dampening assembly includes third holder, and the third holder is rotatablely connected with second support by bolt part, and
It is equipped with elastomeric pad in junction；
The third dampening assembly includes the 4th holder and the 5th holder, and the 4th holder is fixedly connected with third holder, institute
It is connect by shock ring between the 5th holder between stating the 4th；
4th dampening assembly include the 6th holder being fixedly connected with the 5th holder and connect the 6th holder and first fix
The flexible carry component of plate.
4. the mixed dynamic unmanned plane of oil electricity according to claim 3, which is characterized in that
The first support is square set, and four angles protrude a join domain respectively, and each join domain is equipped with more
A first through hole；
The second support include two groups of bolsters, wherein every group of bolster include with first support buffer board disposed in parallel,
And it is vertical with buffer board, and set on two " n " type hanging pieces at buffer board both ends, the both ends of the buffer board are equipped with multiple second
Through-hole, and fixed with first through hole by multiple shock-absorbing balls；
The third holder includes multiple strip metal parts, and one end of wherein each two metalwork is correspondingly connected with " n " type hanging piece
Both sides, the other end are fixedly connected with the 4th holder；
4th holder includes multiple sheet metals equipped with third through-hole, is delayed wherein each sheet metal bottom surface is fixedly connected with one group
Stamping；
Described 5th is provided with multiple fourth holes, and is connect with third through-hole by shock ring.
5. the mixed dynamic unmanned plane of oil electricity according to claim 2, which is characterized in that the 6th holder is double-layer structure, packet
Top plate, lower plywood and connecting rod are included,
The connecting rod sequentially passes through top plate, lower plywood and the 5th holder so that the both ends of connecting rod are respectively fixedly connected with
Top plate and the 5th holder,
It is connected by shock ring between the lower plywood and top plate.
6. the mixed dynamic unmanned plane of oil electricity according to claim 5, which is characterized in that the flexibility carry component includes and first
Fixed first fixed end of fixed plate, fixed second fixed end of the 6th holder and both ends are equipped with the spring part of hook,
One end hook first fixed end of connection, other end hook the second fixed end of connection.
7. the mixed dynamic unmanned plane of oil electricity according to claim 1, which is characterized in that the fuel tank assembly includes fuel tank, is used for
The level monitoring device and oil circuit of Fuel Oil Remaining are detected,
Trepanning is equipped on the upside of the fuel tank, the level monitoring device is set to tapping, and according to liquid level difference dynamic detection oil mass
Information, described oil circuit one end connect the trepanning, and the other end connects engine.
8. the mixed dynamic unmanned plane of oil electricity according to claim 1, which is characterized in that the mixed dynamic unmanned plane of oil electricity further includes two
A symmetrically arranged tripod, described two tripods are fixed at the both sides of the first fixed plate bottom surface, are used to support entire nothing respectively
It is man-machine.
9. the mixed dynamic unmanned plane of oil electricity according to claim 8, which is characterized in that the tripod includes main tripod and tripod branch
Strut, described main tripod one end are fixedly connected with the first fixed plate, and the other end is fixedly connected with tripod supporting rod, the main tripod and foot
Frame supporting rod is vertical.
10. the mixed dynamic unmanned plane of oil electricity according to claim 9, which is characterized in that the tripod supporting rod is equipped with multi-turn
Antiskid glue sleeve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810565825.6A CN108609168B (en) | 2018-06-04 | 2018-06-04 | Compact type multi-rotor-wing oil-electricity hybrid unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810565825.6A CN108609168B (en) | 2018-06-04 | 2018-06-04 | Compact type multi-rotor-wing oil-electricity hybrid unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108609168A true CN108609168A (en) | 2018-10-02 |
| CN108609168B CN108609168B (en) | 2024-02-13 |
Family
ID=63664761
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810565825.6A Active CN108609168B (en) | 2018-06-04 | 2018-06-04 | Compact type multi-rotor-wing oil-electricity hybrid unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108609168B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319132A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | The changeable aircraft of oily electricity |
| CN109573045A (en) * | 2018-11-30 | 2019-04-05 | 中交遥感农业科技江苏有限公司 | A kind of herbal sprinkling unmanned plane |
| CN109733622A (en) * | 2019-01-28 | 2019-05-10 | 河南正大航空工业股份有限公司 | A kind of mixed dynamic unmanned plane of oil electricity |
| CN110155329A (en) * | 2019-05-30 | 2019-08-23 | 吉林大学 | A kind of novel wing hybrid power search and rescue unmanned plane that verts |
| CN111071471A (en) * | 2018-10-18 | 2020-04-28 | 长春工业大学 | Combined type damping cloud platform with energy harvesting function |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
| CN208576721U (en) * | 2018-06-04 | 2019-03-05 | 广州市华科尔科技股份有限公司 | A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact |
-
2018
- 2018-06-04 CN CN201810565825.6A patent/CN108609168B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
| CN208576721U (en) * | 2018-06-04 | 2019-03-05 | 广州市华科尔科技股份有限公司 | A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319132A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | The changeable aircraft of oily electricity |
| CN111071471A (en) * | 2018-10-18 | 2020-04-28 | 长春工业大学 | Combined type damping cloud platform with energy harvesting function |
| CN109573045A (en) * | 2018-11-30 | 2019-04-05 | 中交遥感农业科技江苏有限公司 | A kind of herbal sprinkling unmanned plane |
| CN109573045B (en) * | 2018-11-30 | 2024-04-02 | 中交遥感载荷(江苏)科技有限公司 | Unmanned aerial vehicle is sprayed to medicine |
| CN109733622A (en) * | 2019-01-28 | 2019-05-10 | 河南正大航空工业股份有限公司 | A kind of mixed dynamic unmanned plane of oil electricity |
| CN109733622B (en) * | 2019-01-28 | 2023-09-08 | 河南正大航空工业股份有限公司 | Oil-electricity hybrid unmanned aerial vehicle |
| CN110155329A (en) * | 2019-05-30 | 2019-08-23 | 吉林大学 | A kind of novel wing hybrid power search and rescue unmanned plane that verts |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108609168B (en) | 2024-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108609168A (en) | A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact | |
| US9725158B2 (en) | Self-righting frame and aeronautical vehicle and method of use | |
| CN202071985U (en) | Novel plane symmetrical layout type multi-rotor unmanned air vehicle | |
| CN106114854B (en) | A kind of push-button aircraft | |
| CN104149982B (en) | Air quality detector based on quadcopter | |
| CN202345914U (en) | Intelligent helium-filled flapping wing air vehicle capable of tracking sound source | |
| US20190009876A1 (en) | Aircraft | |
| CN204473140U (en) | New vertical landing tilting rotor two axle aircraft | |
| CN209000276U (en) | Four-degree-of-freedom helicopter Dynamic Flight Simulator | |
| CN208576721U (en) | A kind of mixed dynamic unmanned plane of the more rotor fuel-electrics of compact | |
| RU2375253C1 (en) | Flight vehicle with flapping wings ("dragonfly") | |
| CN107856850A (en) | Multi-rotor unmanned aerial vehicle and its control method | |
| CN108583182A (en) | A kind of amphibious ball shape robot in sky land | |
| US20220001980A1 (en) | Group configurations for a modular drone system | |
| CN108423153A (en) | Modularized micro unmanned plane | |
| CN107097943A (en) | A kind of horn structure for being used to combine gyroplane | |
| CN208248488U (en) | Modularized micro unmanned plane | |
| CN211139645U (en) | Helium balloon unmanned aerial vehicle | |
| CN206021084U (en) | Manipulation device | |
| US20220001971A1 (en) | Modular flat-packable drone kit | |
| CN112373691A (en) | Use indoor unmanned aerial vehicle of helium gasbag | |
| CN208559733U (en) | A kind of mixed dynamic unmanned plane Multistage damping component of oil electricity | |
| CN206782066U (en) | A kind of horn structure for being used to combine gyroplane | |
| CN218955766U (en) | Mapping device for town planning | |
| CN206437216U (en) | A kind of amphibious unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |