CN107310747A - A kind of aircraft and its application - Google Patents
A kind of aircraft and its application Download PDFInfo
- Publication number
- CN107310747A CN107310747A CN201710705337.6A CN201710705337A CN107310747A CN 107310747 A CN107310747 A CN 107310747A CN 201710705337 A CN201710705337 A CN 201710705337A CN 107310747 A CN107310747 A CN 107310747A
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- CN
- China
- Prior art keywords
- aircraft
- wire
- power supply
- pulling force
- flight
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F3/00—Ground installations specially adapted for captive aircraft
- B64F3/02—Ground installations specially adapted for captive aircraft with means for supplying electricity to aircraft during flight
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64D47/00—Equipment not otherwise provided for
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
- B64U50/34—In-flight charging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Electric Cable Installation (AREA)
Abstract
The invention discloses it is a kind of can the big aircraft of flying for long time, loading capacity, the aircraft contains the higher wire of intensity, disclosure satisfy that the field such as fire-fighting, fire extinguishing, rescue, transport, amusement needs.
Description
Technical field
The invention belongs to flight domain, it is particularly a kind of being capable of the big aircraft of flying for long time, loading capacity.
Background technology
Risk that unmanned plane is widely used, cost is low, efficiency-cost ratio is good, no one was injured, survival ability are strong, mobility is good,
It is easy to use, there is extremely important effect in modern war.Ground mapping, geology are also widely used in civil area to survey
The fields such as survey, disaster monitoring, air traffic control, border patrol monitoring, communication relay, pesticide spraying.Therefore, in recent years, it is right
The research temperature of unmanned plane heats up again and again.
The A of Chinese invention patent CN 105460206 disclose a kind of unmanned plane, including battery, control circuit unit, multigroup oar group
Part and fuselage, the oar component are circumferentially disposed around the fuselage；The oar component include paddle arm, blade and with the control
The motor of circuit unit electrical connection, one end and the fuselage of each paddle arm are hinged；The unmanned plane also include with it is each described
Paddle arm opens up oar component correspondingly, and the oar component has folded state and deployed condition, and the exhibition oar component will be in folding
The oar component of overlapping state is expanded to deployed condition and the oar component is maintained at into deployed condition.Thus, reducing is used for
The packaging structure of transport and spatial volume shared during storage is reduced, while oar component is to drive to deploy by motor,
Without manually installed.
Chinese utility model patent CN205133085U discloses a kind of manned machine of fire-fighting, to solve to disappear in the prior art
The problem of anti-dangerous height of member's rescue, material, manpower transport inconvenience and delay attack time.The manned machine of the fire-fighting, including it is manned
Owner's body, manned owner's body includes dynamical system, manned mechanism and controller;The dynamical system is arranged on manned mechanism
On, the dynamical system enables whole manned machine to fly；The manned mechanism is provided with electric drill, and the electric drill can be bored
Wall so that manned owner's body can be fixed on exterior wall；Support is additionally provided with the manned mechanism, the support connection is organic
Tool arm, described mechanical arm one end is connected the other end with support and also is provided with electric drill;Lowering or hoisting gear is additionally provided with the manned mechanism;Institute
Dynamical system and electric drill are stated all by controller control.By above-mentioned technology, the problems of the prior art just can be solved well.
Unmanned plane can be largely classified into fixed-wing and many classes of rotor two.Many rotors are comparatively more flexibly, and can hang
Stop, but its maximum shortcoming is that its loading capacity is small, the flight time is not long.Because multi-rotor unmanned aerial vehicle is usually to be made using battery
It is driven for the energy, it is longer if necessary to the load-carrying bigger, flight time, then need to provide more battery packs, however, battery
After group increase, the load of aircraft is increased again so that the increase of payload is very limited.
Chinese invention patent CN104691766A discloses a kind of unmanned plane, including fuselage, mast and oar clamp pin axle,
Also include simultaneously：Engine, is fixed on the inside of the fuselage；The engine includes：At least one cylinder, one side is set
There are exhaust outlet, cylinder body, be connected with the air cylinder detachable type；Air intake valve, and the cylinder body detachable connection, air-flow is from entering
The angle that the direction that air valve is flowed into is constituted with tail gas from the direction that exhaust outlet is discharged is 0 °~90 °；Air cleaner, it is fixed
In the bottom of the fuselage；Rotor connector, the mast is flexibly connected with the oar clamp pin axle;Dynamic balancing part,
It is set in the mast, and is flexibly connected with the oar clamp pin axle；The present invention is solved or partly solved traditional
Engine because gas burns it is insufficient caused by the technological deficiency that is impacted to unmanned plane during flying operation.
The unmanned plane of the patent employs engine as power, so solves what battery was brought to a certain extent
Problem, but the problem of bring new again：Engine can greatly increase the weight of unmanned plane, and fuel oil is also ponderable.
These loading capacity for all limiting the unmanned plane and flight time, therefore the fields such as pesticide spraying are also typically only used at present,
More than ten kilograms of load-carrying.
In summary, current many rotor type unmanned planes are due to energy problem, and loading capacity is small（Typically below 20 kilograms, absolutely
It is most of below 10 kilograms）, the flight time it is short（Typically within one hour or even in half an hour）, this is seriously limited
Unmanned plane some key areas application, such as fire-fighting, rescue, transport, amusement, it is manned field.
The content of the invention：
Goal of the invention：The invention provides it is a kind of can be with heavy load, the aircraft of flying for long time.
It was noticed that in fields such as fire-fighting, rescue, amusement, transports, it is necessary to which the loading capacity of aircraft is larger, it is desirable to most
Well can be manned, i.e. loading capacity requires the time long enough of flight more than 30 ~ 100 kilograms, preferably more than 2 hours.
However, current many rotor type unmanned planes can not meet the requirement of this loading capacity and flight time.Fixed aerofoil profile aircraft by
In the function without hovering, this requirement can not be met.
The present invention provides a kind of aircraft, load easily can be brought up into more than 30 kilograms, can also bring up to 200 public
It is more than jin, even more than several tons.So, aircraft can meet requirement that is manned, carrying many people.
The present invention aircraft, can easily by the flight time from current half when within lifted it is small to tens, hundreds of
When more than, in theory（Do not consider to be out of order）It can fly always.So, aircraft can have time enough to carry out operation.
Technical scheme is as follows:
Aircraft uses many rotor types, including the wing installed on motor, motor（Blade）, frame and control unit.Flight
Device is connected to wire, and wire is connected to the power supply outside aircraft（External power supply）Aircraft is powered.The wire has larger
Intensity, the pulling force more than more than 100N can be born, this can be realized by multiple modes, for example with thicker copper cash/copper
Cable or in wire use reinforcement（Such as steel wire, steel wire）Etc..
Preferably, the cross-sectional area of the conductive part of wire is more than 10 square millimeters.
Preferably, the quality for the load that wire can be born is also bigger more than M kilograms than the quality of aircraft, M scope is
20 ~ 5000 kilograms.
The wire is electrically conductive linear object, including but not limited to electric wire or cable.Wire is outer for being connected to
Power supply is connect to be powered aircraft；Or power interface is provided with the frame of aircraft/aircraft, it can also so pass through
Wire is connected to external power supply.
Described external power supply is including but not limited to generator, civilian electricity（Line）Or commercial power（Line）, battery, traffic set
Standby upper power supply, architectural power supply, aerial power supply etc..As needed, external power supply can be directly connected to aircraft,
Or reused after transformer, progress transformation are installed on board the aircraft.
Preferably, power supply uses civilian or commercial power.
During work, wire is aloft connected with external power supply, for example roof, aerial platform etc. place.The two of wire
The fixation on mechanics is made in end connection except ensureing between power supply and aircraft in addition to the conducting of electricity, also to the two ends of wire, with
Ensure when aircraft hinders fall for some reason, can be held by wire.Described fixation includes but is not limited in wire or wire
Mechanics reinforcement using tying up, be, the mode such as prick and fix or be limited to aircraft/aircraft frame, the jail of power supply position
Gu, the place of wire tension can be born.Then, aircraft flies downwards from eminence, while constantly discharging wire, makes the length of wire
The position spent with aircraft matches.So, the weight of wire is mainly born by wire itself, and aircraft is solely subjected to seldom one
The length of intraphase conductor, simultaneously as the intensity of wire is high, moreover it is possible to play a part of preventing aircraft from falling.
Described eminence, refers to more than 3 meters from the ground of place.
It is, of course, also possible to wire is connected with power supply in lower, but wire passes through eminence, is connected to aircraft.
So wire remains able to play with wire to be fixed to aloft similar effect.Those skilled in that art are according to the present invention's
The similar conversion that scheme can be made, also within protection scope of the present invention.
Preferably, wire is also fixed in the frame of aircraft.
Winder folding and unfolding wire can be used, is mutually coordinated with the length of pilot and the position of aircraft, it is ensured that is flown
Row device can be held in time when falling, and being unlikely to fall too, decrease speed is too fast long afterwards.
Described Winder can be used and manually or mechanically controlled, it would however also be possible to employ remote control.
In order to further lift the security of aircraft, safety rope can be installed on board the aircraft, one of safety rope is solid
Determine on board the aircraft；Other end is fixed on outside aircraft, is typically mounted at eminence.Safety rope can use rigid material or bullet
Property material make, the pulling force that can be born is more than more than 100N, and specific intensity should be able to ensure when aircraft breaks down
When falling, safety rope can hold aircraft.It so can guarantee that the safety on aircraft and periphery.
As can be seen that position when its extreme lower position during the aircraft work of the present invention can set out less than it, or
Extreme lower position during its work can be less than the position of external power supply, or minimum altitude during aircraft flight is than wire or line
The peak of shape thing is low more than 2 meters.
Safety rope rope can have one or more.
Preferably, safety rope uses elastomeric material.
The control section of aircraft, it is possible to use external power supply is directly powered, will can also power after external power supply transformation,
Or be powered using battery.Stand-by power supply can be included in aircraft, such as battery pack can also not have.Stand-by power supply
For being in case of emergency powered to motor, but the power supply of the power section of aircraft primarily or entirely outside is supplied
Electricity.Powered under normal circumstances using external power supply, once because power supply is out of order, stand-by power supply can be rapidly switched to, to prevent
Only aircraft is fallen due to power failure.
Motor of the present invention can be direct current generator or alternating current generator.
It is mounted with aircraft interior for measuring the instrument that height changes with horizontal level, including but not limited to ultrasonic wave
Sensor, barometer, GPS etc..Aircraft interior is also provided with Inertial Measurement Unit, including gyroscope, acceierometer sensor
And other control units, for recognizing state of flight and the relative displacement of itself.To ensure still in the place of gps signal difference
The posture of enough stably control aircraft, it is ensured that safety.The environment such as between interior, mountain area, skyscraper.
, can be using one or both of both of which be directly manipulated on remote control, aircraft in operator scheme, this two
The pattern of kind can switch mutually, to learn from other's strong points to offset one's weaknesses, ensure flight safety.Directly manipulation refers to people in aircraft on the aircraft
On aircraft is directly manipulated according to operation button, handle or operation interface etc..For example in the case of having remote control mode may be deposited
The situation such as disturb, block in signal, at this moment using line traffic control or it is artificial directly manipulate on board the aircraft it is more efficient.
The aircraft of the present invention can install the monitoring device of camera etc, by straight on remote control, line traffic control or aircraft
Connect manipulation, can easily monitoring objective situation.The aircraft of the present invention can also include landing and buffering system, to reduce
Impulsive force when aircraft lands, the buffer system can be contact to earth position mounting bracket or the elastomeric element in aircraft,
Or air cushion etc..
The aircraft of the present invention can install manned or loading part, such as platform, nacelle or other forms.Moving load part
Part can be for article, food of carrying rescue etc..Other instruments or accessory can also be installed on aircraft, to meet
Application of the aircraft in terms of fire-fighting, fire extinguishing, rescue, transport, amusement.
Rescue passage can be set on aircraft, can be the forms such as staircase, bridge or passageway, for connect aircraft with
Indicator of trapped personnel position, personnel's landing vehicles are rescued to allow.Rescuing passage can be using detachable, folding or scalable
Device, used when to need.
In order to prevent wire, safety rope from being encountered by blade, blade can be covered using guard, so, on the one hand avoided
Blade encounters wire, safety rope, on the one hand can also protect blade.
Beneficial effect：
Aircraft can be without battery first, or only with seldom battery, significantly reduces the weight of aircraft, and when increasing
Plus during motor, the increased power of motor institute substantially may serve to increase pulling force；Second, due to external power supply, aircraft
Flight time can be with unrestricted；3rd, because without the puzzlement brought in terms of the energy, aircraft of the invention can select work(
The big motor of rate, so as to produce very big pulling force.For example, the motor that multi-rotor unmanned aerial vehicle is used at present typically can only pull-up
Less than 10 kilograms of load, the overwhelming majority is below 5 kilograms.When increasing the power of motor, required battery can it is more,
It is heavier, thus actually can increased loading capacity it is extremely limited.Therefore, even current load is used to spray agriculture than larger
The unmanned plane of medicine, general namely more than ten kilograms of its load, many rotor types of the global dead weight having been reported that now nobody
Machine namely can more than 30 kilograms of load-carrying.However, the aircraft of the present invention easily can lift the loading capacity of aircraft very much
To more than 40 kilograms.For example, being 80 kilograms of even more big motors from pulling force, the rotor type aircraft of eight axles is made,
Then can be with the load of more than 500 kilograms of pull-up.Using more high-power motor, the pulling force of generation can be bigger.Such load energy
Power make it that the aircraft of the present invention is competent at the field of the highly desirable solution of some current mankinds enough, such as skyscraper fire extinguishing,
Rescue etc..Also, these fields many times and do not need aircraft flight very remote distance, usually hundreds of meters or one
More than thousand meters of distance just can be with, is especially suitable for the aircraft using the present invention.4th, because wire can bear larger drawing
Power, and fix aloft, one, which is that of avoiding aircraft, directly drops into the consequence that ground is caused, and is a kind of safe equipment；Two
It is the position flight that aircraft can be more relatively low at than wire/power supply wiring, so, most of own wt of wire is led
Line itself is born, and aircraft only needs to bear the weight of few part wire, so has bigger load capacity to go work.The
Five, cost of the invention is low, in the case of identical loading capacity, and cost of the invention is well below other aircraft, for example directly
The machine of liter.
Conceptually, the present invention has two innovations：1. conventional aircraft is all that up flight is made in the mind of people
Industry, and the main target of the aircraft of the present invention is down flight operation, certainly, it still remains the energy of upward flight operation
Power；2. wire has typically been used by people to the effect of conduction, and the wire in the present invention, in addition to conduction, also for by
Power, maintenance safety.
For the ease of understanding the present invention, drawings and Examples, which are provided below, to be used to explain the present invention, but they are not constituted pair
The restriction of the present invention.
Brief description of the drawings
Fig. 1 is the structural representation of the aircraft of the present invention.The schematic diagram has only marked the basic of the aircraft of the present invention
Structure, also many appurtenances are not marked, and those skilled in that art can install according to prior art.
Description of reference numerals：
1- motors
2- frames
3- wings（Oar）
4- wires
Embodiment
Below by the flight device that the present invention is described in detail in conjunction with the embodiments.
Frame is manufactured first, motor is installed in frame, and blade is installed on motor.Install again electric tune, barometer,
The flight control systems such as GPS module, gyroscope, acceierometer sensor, shooting/monitoring system etc..Control system uses battery
Power supply, motor is powered using external power supply, and wire uses the copper cable of steel wire reinforcement, and the pulling force that can be born is 5000N.By wire
One end it is fixed in frame after, then with electric tune/motor connection；When aircraft works, the other end of wire is fixed to
Eminence simultaneously connects power supply.
Described above is only some examples of embodiment of the present invention, it should be pointed out that：For the technology people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of aircraft, it is characterised in that：The aircraft has the wire for the external power that may be coupled to aircraft, or flight
Power interface, the electricity in order to be wired to when aircraft works outside aircraft have been reserved in the frame of device/aircraft
Source, and described wire not only plays conduction, can also play a part of stress, avoid after aircraft falls and bring
Really.
2. a kind of frame that may make up aircraft as claimed in claim 1, it is characterised in that：Being connected in the frame to connect
It is connected on the wire of the external power of aircraft, or the frame and has reserved power interface, in order to can be used when aircraft works
Wire is connected to the power supply outside aircraft.
3. a kind of aircraft as claimed in claim 1, it is characterised in that：There are guard, the blade quilt of aircraft on the aircraft
Guard is covered.
4. a kind of wire as claimed in claim 1, it is characterised in that：The wire can bear more than 100N pulling force；Or lead
In the part of line in addition to current-carrying part, insulated part, also pulling force strengthening part, the pulling force strengthening part include but
It is not limited to steel wire, steel wire；Or the cross-sectional area of the conductive part of the wire is more than 10 square millimeters.
5. a kind of wire as claimed in claim 1, it is characterised in that：The quality for the load that the wire can be born compares aircraft
Quality also want big more than M kilograms, M scope is 20 ~ 5000.
6. a kind of wire as claimed in claim 1, it is characterised in that：The two ends of the wire except connection power supply and aircraft it
Outside, fixation has also been done so that when aircraft carries more than M kilograms of load and power-off, wire can hold aircraft, avoid flying
Row device Crater face, described fixation, which includes but is not limited to use the mechanics strengthening part in wire or wire, ties up, is, pricking
Etc. mode be fixed on aircraft/aircraft parking stand, power supply position place firm or that wire tension can be born, M model
Enclose is 20 ~ 5000.
7. a kind of aircraft as claimed in claim 1, it is characterised in that：The extreme lower position when aircraft works can be less than
Position when it sets out, when either extreme lower position during its work can be less than position or the aircraft flight of external power supply
Minimum altitude it is lower than the peak of wire or thread more than 2 meters.
8. a kind of aircraft as claimed in claim 1, it is characterised in that：Safety rope, the safety are connected with the aircraft
Restrict as banding, the pulling force more than 100N can be born.
9. a kind of application of aircraft as claimed in claim 1 in terms of fire-fighting, fire extinguishing, rescue, transport, amusement.
10. a kind of aircraft as claimed in claim 1, it is characterised in that：The aircraft install aloft or wire or
Eminence can be hung in by wire or safety rope when safety rope is by eminence or aircraft work, and described eminence refers to from the ground 3
It is more than rice aerial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710705337.6A CN107310747A (en) | 2017-08-17 | 2017-08-17 | A kind of aircraft and its application |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710705337.6A CN107310747A (en) | 2017-08-17 | 2017-08-17 | A kind of aircraft and its application |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107310747A true CN107310747A (en) | 2017-11-03 |
Family
ID=60177042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710705337.6A Pending CN107310747A (en) | 2017-08-17 | 2017-08-17 | A kind of aircraft and its application |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107310747A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101574565A (en) * | 2009-06-25 | 2009-11-11 | 北京大业嘉成科技有限公司 | Ducted fan flexible aerial ladder fire truck |
| CN102107734A (en) * | 2009-12-23 | 2011-06-29 | 纳耶夫·宾马姆杜·宾阿卜杜尔阿齐兹阿尔沙特 | Helicopter to which fire-fighting and rescue facility can be attached and connected |
| CN204606235U (en) * | 2015-05-04 | 2015-09-02 | 厦门大学 | Many rotor wing unmanned aerial vehicles device when navigating based on the length hanging mooring system |
| CN106379554A (en) * | 2016-12-08 | 2017-02-08 | 中国科学院长春光学精密机械与物理研究所 | Flight test protection device and method |
-
2017
- 2017-08-17 CN CN201710705337.6A patent/CN107310747A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101574565A (en) * | 2009-06-25 | 2009-11-11 | 北京大业嘉成科技有限公司 | Ducted fan flexible aerial ladder fire truck |
| CN102107734A (en) * | 2009-12-23 | 2011-06-29 | 纳耶夫·宾马姆杜·宾阿卜杜尔阿齐兹阿尔沙特 | Helicopter to which fire-fighting and rescue facility can be attached and connected |
| CN204606235U (en) * | 2015-05-04 | 2015-09-02 | 厦门大学 | Many rotor wing unmanned aerial vehicles device when navigating based on the length hanging mooring system |
| CN106379554A (en) * | 2016-12-08 | 2017-02-08 | 中国科学院长春光学精密机械与物理研究所 | Flight test protection device and method |
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Application publication date: 20171103 |
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