CN106741899A - Kite aircraft and its implementation - Google Patents
Kite aircraft and its implementation Download PDFInfo
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- CN106741899A CN106741899A CN201710003253.8A CN201710003253A CN106741899A CN 106741899 A CN106741899 A CN 106741899A CN 201710003253 A CN201710003253 A CN 201710003253A CN 106741899 A CN106741899 A CN 106741899A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 35
- 238000000034 method Methods 0.000 claims abstract description 19
- 230000004888 barrier function Effects 0.000 claims description 15
- 238000012544 monitoring process Methods 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 4
- 230000009187 flying Effects 0.000 claims description 4
- 230000006399 behavior Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 230000009471 action Effects 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 7
- 230000008859 change Effects 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 229930185605 Bisphenol Natural products 0.000 description 2
- 101000606504 Drosophila melanogaster Tyrosine-protein kinase-like otk Proteins 0.000 description 2
- IISBACLAFKSPIT-UHFFFAOYSA-N bisphenol A Chemical compound C=1C=C(O)C=CC=1C(C)(C)C1=CC=C(O)C=C1 IISBACLAFKSPIT-UHFFFAOYSA-N 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229920001684 low density polyethylene Polymers 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 210000003739 neck Anatomy 0.000 description 2
- 239000004745 nonwoven fabric Substances 0.000 description 2
- 230000000644 propagated effect Effects 0.000 description 2
- 229920002379 silicone rubber Polymers 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000002604 ultrasonography Methods 0.000 description 2
- 239000004425 Makrolon Substances 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- BVKZGUZCCUSVTD-UHFFFAOYSA-N carbonic acid Chemical compound OC(O)=O BVKZGUZCCUSVTD-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 229920000515 polycarbonate Polymers 0.000 description 1
- 238000012545 processing Methods 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
- B64C19/00—Aircraft control not otherwise provided for
-
- 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
- B64U10/00—Type of UAV
- B64U10/50—Glider-type UAVs, e.g. with parachute, parasail or kite
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of kite aircraft and its corresponding implementation method, belong to unmanned air vehicle technique field.A kind of kite aircraft in the present invention, including aircraft body, aircraft body has the structure that reception wind-force raises up, aircraft body is provided with wind sensor, for detecting wind speed and direction, flight control units can adjust the flight attitude of aircraft according to wind speed and direction, and the structure for enabling reception wind-force to raise up receives wind-force, the flight thrust that acquisition raises up.The aircraft can adjust the flight attitude of aircraft according to wind speed and direction, enable the flight thrust for raising up that aircraft is obtained under the action of the forces of the wind, for the flight of aircraft provides power, the consumption of electric energy is reduced, substantially increase the cruising time of aircraft.
Description
Technical field
The invention belongs to unmanned air vehicle technique field.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and providing for oneself
The not manned aircraft that presetting apparatus is manipulated.Unmanned plane press application field, can be divided into it is military with it is civilian.Unmanned plane is in civilian neck
Domain is widely used, is mainly used in the industries such as police, city management, agricultural, geology, meteorology, electric power, rescue and relief work, video capture.
It is the common fault of existing unmanned plane that cruising time is short, causes it to complete time-consuming task more long, is greatly reduced
The use scope of unmanned plane, and, the charging interval is time-consuming more long after electric quantity consumption is complete, reduces the recreational of unmanned plane, and
To user with very big trouble.
The content of the invention
The invention provides a kind of kite aircraft, and its corresponding implementation method.A kind of kite in the present invention
Aircraft, including aircraft body, the aircraft body have the structure that reception wind-force raises up, and are set in the aircraft body
There is wind sensor, connect flight control units, for detecting wind speed and direction, the flight control units can be according to wind speed
With the flight attitude that wind direction adjusts aircraft, the reception structure that raises up of wind-force is set to receive wind-force, what acquisition raised up flies
Row thrust.
Further, the aircraft uses rotary wind type flight structure, or
The aircraft uses flapping wings type flight structure, or
The aircraft uses fixed-wing formula flight structure, or
The aircraft uses umbrella wing formula flight structure, or
The aircraft uses jet-propelled flight structure, or
The aircraft uses dirigible structure.
Further, the flight control units include
Gyroscope, for sensing flight attitude；
Memory module, for accessing default flight attitude information.
Main control module, connects gyroscope and memory module, for flight attitude to be entered with default flight attitude information
Row is compared, and is adjusted to default flight attitude.
Further, the default flight attitude information includes
Wind direction attitude information, is according to the corresponding flight attitude information of specific wind direction；
Wind speed attitude information, is according to the corresponding flight attitude information of specific wind speed.
Further, the flight attitude of the aircraft includes inclination angle and the anglec of rotation of heading and aircraft body.
Further, the structure that the reception wind-force raises up has the stress surface of wind-force, and the stress surface is configured to connect
The structure of power of calling prisoners in after letting them out for exercise.
Further, the flight thrust for raising up, including the raise up thrust or with heading identical relatively anti-with gravity
Thrust.
Further, also including monitoring unit, the monitoring unit connects wind sensor, is used to monitor the wind-force sensing
Wind direction and air speed data that device is detected, when the wind speed exceeds predetermined threshold value, output alarm signal；Or
When wind vector frequency exceeds predetermined threshold value, output alarm signal.
Further, also include
Collecting unit, the image information for gathering barrier；
Recognition unit, the location and shape for recognizing the barrier；
Demand identifying unit, connects flight control units, to determine whether according to the location and shape of the barrier
There is avoidance demand；
If, to there is avoidance demand, flight control units are by adjusting flying for aircraft for the result of determination of demand identifying unit
Row attitude is avoided to barrier.
Further, also including signal transmitting and receiving unit, the signal transmitting and receiving unit connects flight control units, is used to receive use
Family signal simultaneously passes to flight control units, and the flight attitude of aircraft is controlled by flight control units.
Further, the aircraft is multi-rotor aerocraft, is connected with each other by windward structure between each rotor.
Further, present invention additionally comprises a kind of implementation method of kite aircraft, the method includes：
According to wind behaviour, the flight attitude of aircraft is adjusted, the wherein aircraft is set to be carried out with reception wind-force
The structure for raising up；
Receive wind-force effect, the flight thrust that generation raises up.
Further, the flight attitude of the aircraft includes inclination angle and the anglec of rotation of heading and aircraft.
Further, also include before the flight attitude of regulation aircraft：Wind speed and direction, root are detected by wind sensor
Flight attitude is adjusted according to pre-set flight attitude information.
Further, the default flight attitude information includes
Wind direction attitude information, is according to the corresponding flight attitude information of specific wind direction；
Wind speed attitude information, is according to the corresponding flight attitude information of specific wind speed.
The advantage of the invention is that：Aircraft body in the present invention has the structure that reception wind-force raises up, being capable of basis
Wind speed and direction adjusts the flight attitude of aircraft so that the flight for raising up that aircraft can be obtained under the action of the forces of the wind is pushed away
Power, for the flight of aircraft provides power, reduces the consumption of electric energy, substantially increases the cruising time of aircraft, while increasing
The interest of aircraft is added.
Brief description of the drawings
Fig. 1 is a kind of structural representation of kite aircraft of the invention.
Fig. 2 is a kind of another structural representation of kite aircraft of the invention.
Fig. 3 is a kind of structured flowchart of kite aircraft of the invention.
Fig. 4 is a kind of flow chart of the implementation method of kite aircraft machine of the invention.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
It should be noted that in the case where not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Mutually combination.
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings, but not as limiting to the invention.
As shown in figure 1, Fig. 1 is a kind of structural representation of kite aircraft 100 of the invention.As preferred rather than limit
Fixed, the present embodiment uses quadrotor, and quadrotor stability in takeoff and landing is preferable, and has four above
Individual rotor 130, using the teaching of the invention it is possible to provide bigger power so that aircraft is sensitiveer.
Fig. 1 includes aircraft body, fuselage 120, rotor 130, and wherein aircraft body 110 has what reception wind-force raised up
Fuselage 120, as preferred and non-limiting, the structure that reception wind-force raises up, fuselage 120 is configured in the present embodiment by structure
Bottom surface is made using integrally formed mode, and the bottom surface of whole fuselage 120 does not have gap, can receive advertising for wind-force, is
Aircraft provides a flight thrust for raising up, as preferred and non-limiting, the bottom surface of fuselage 120 made using lightweight rubber and
Into for example can be using the material such as silicon rubber, makrolon (bisphenol A-type), high pressure (low-density) polyethylene.These quality of materials
Gently, good toughness, high temperature resistant, can reduce the weight of aircraft, the energy for making the flight consumption of aircraft less, while toughness
Good, high temperature resistant, enables aircraft to increase the service life, and even across repeatedly colliding with or falling, also aircraft will not be caused
Fatal harm.
Used as preferred and non-limiting, the aircraft in the present invention can be using rotary wind type flight structure, flapping wings type flight knot
Structure, fixed-wing formula flight structure, umbrella wing formula flight structure, jet-propelled flight structure or dirigible structure.
Used as preferred and non-limiting, the present embodiment preferentially uses rotary wind type flight structure, and rotary wind type flight structure is more steady
Gu, and it is easier to aircraft flight.
Used as preferred and non-limiting, the kite aircraft 100 in the present invention, aircraft body 110 is provided with wind-force biography
Sensor 140, used as preferred and non-limiting, wind sensor 140 is fixed on the surface of aircraft fuselage 120, for detect wind speed and
Wind direction, as preferred and non-limiting, uses ultrasonic wind speed sensor in this implementation, ultrasonic wind speed sensor is using ultrasound
Ripple time difference method realizes the measurement of wind speed.The aerial spread speed of sound, can be with the superposition of the air velocity on wind direction.If super
The direction of propagation of sound wave is identical with wind direction, and its speed can be accelerated；If if conversely, the direction of propagation of ultrasonic wave with wind direction conversely,
Its speed can be slack-off.Therefore, under fixed testing conditions, the speed that ultrasonic wave is propagated in atmosphere can and function of wind speed
Correspondence.Accurate wind speed and direction is can obtain by calculating.
As preferred and non-limiting, in the present invention, when wind speed and direction is detected using wind sensor 140, fly
Control unit 150 can adjust the flight attitude of aircraft, and the structure for enabling the reception wind-force to raise up receives wind-force, obtains
The flight thrust for raising up.As an example, when wind sensor 140 detects wind direction for east wind, and wind speed is when being 2m/s, flight
Control unit 150 adjusts aircraft flight attitude, aircraft is westwards inclined, so that aircraft bottom surface is towards east, so
Aircraft bottom surface can receive wind-force, obtain the flight thrust for raising up, and because wind speed now is 2m/s, wind-force is smaller, just
The angle of inclination of aircraft is correspondingly adjusted so that the increase of the effective lifting surface area in aircraft bottom surface, so as to increase flying of raising up
Row thrust；If detecting wind speed for 8m/s, because wind speed is larger, aircraft angle of inclination is excessive can not only to make aircraft smooth
Take off, also result in aircraft and gone by the place of wind to off-track, so now aircraft can reduce angle of inclination so that
Aircraft bottom surface reduces towards the effective area of wind direction, so that aircraft can smoothly take off on default track.
Used as preferred and non-limiting, in the present invention, flight control units 150 include,
Gyroscope 160, for sensing flight attitude；
Memory module 170, for accessing default flight attitude information.
Main control module 180, connects gyroscope 160 and memory module 170, for flight attitude and default flight appearance
State information is compared, and is adjusted to default flight attitude.
As preferred and non-limiting, the gyroscope 160 in the present invention, belong to a part for flight control units 150, can
Sensing flight attitude, the flight attitude of aircraft includes inclination angle and the anglec of rotation of heading and aircraft body 110.Gyro
The principle of instrument 160 is exactly that a direction for the rotary shaft meaning of rotating object will not change when not influenceed by external force.
According to this reason, direction is kept with it.Then the direction indicated by axle is read with various methods, and it is automatic by data-signal
Flight control units 150 are transmitted to so that the information of the aircraft flight attitude that flight control units 150 can be obtained, so that basis
Wind speed and direction is adjusted to the flight attitude that can receive wind-force, the flight thrust for raising up for obtaining.
As preferred and non-limiting, the memory module 170 in the present invention, for accessing default flight attitude information, in advance
If flight attitude information include wind direction attitude information and wind speed attitude information, wind direction attitude information is according to specific wind direction pair
The flight attitude information answered, wind speed attitude information is according to the corresponding flight attitude information of specific wind speed.As an example, preset
Flight attitude information can be：If wind direction is east wind, aircraft is westwards inclined；If wind direction is north wind, aircraft is to the south
Incline.The direction that aircraft bottom surface is come towards wind in a word, convenient to receive advertising for wind-force, the flight for raising up for obtaining is pushed away
Power.As an example, default flight attitude information can also be：Wind-force is dragged for 2m/s, then angle of inclination is 15 degree；If wind-force is
8m/s, then angle of inclination is 30 degree.So enable that aircraft adjusts angle of inclination according to wind-force, so as to control aircraft bottom
The effective lifting surface area in face, enables aircraft successfully to be taken off in the case where less electrical energy is consumed.
As preferred and non-limiting, there is wind as the structure that reception wind-force raises up with the bottom surface of fuselage 120 in the present embodiment
The stress surface of power, the stress surface is configured to receive the structure of wind-force.The bottom surface of fuselage 120 is made using integrally formed mode
Form, the bottom surface of whole fuselage 120 does not have gap, can receive advertising for wind-force, pushed away for aircraft provides the flight for raising up
Power, used as preferred and non-limiting, the bottom surface of fuselage 120 is made using lightweight rubber, for example, can use silicon rubber, poly- carbonic acid
The materials such as ester (bisphenol A-type), high pressure (low-density) polyethylene.These quality of materials are light, good toughness, high temperature resistant, can reduce winged
The weight of row device, the energy for making the flight consumption of aircraft less, while good toughness, high temperature resistant, aircraft is extended makes
With the life-span, even across repeatedly colliding with or falling, will not also fatal harm be caused to aircraft.
As preferred and non-limiting, in another embodiment, as shown in Fig. 2 the kite aircraft 100 in Fig. 2, bag
Include aircraft body 110, fuselage 120, rotor 130, also including windward structure 140, the windward structure 140 is located at each rotor
Between 130, the two ends of windward structure 140 connect the base of rotor 130 respectively, by setting windward structure 140, considerably increase kite
The lifting surface area of type aircraft 100 so that with bigger stress surface, obtain the bigger flight thrust that can be raised up.As
It is preferred that and it is non-limiting, the windward structure 140 is made using non-woven fabrics, during non-woven fabrics make kite good material, matter
Amount is light, good toughness, is the good material for making windward structure 140, certainly, using the material of other similarities also in the present invention
Protection domain within.
As preferred and non-limiting, the flight thrust raised up in the present invention, including it is relative with gravity it is anti-raise up thrust or
With heading identical thrust.
Used as preferred and non-limiting, present invention additionally comprises monitoring unit, the monitoring unit connects wind sensor 140,
It is used to monitor wind direction and air speed data that the wind sensor 140 is detected, when the wind speed exceeds predetermined threshold value, output
Alarm signal；Or when wind vector frequency exceeds predetermined threshold value, output alarm signal.
As preferred and non-limiting, wind speed threshold value and wind vector frequency threshold are provided with the detection unit in the present invention,
As an example, wind speed threshold value is set to 10m/s, when wind speed meets or exceeds 10m/s, it is possible to damages aircraft or causes
Aircraft cannot take off, this be will output alarm signal, as preferred and non-limiting, blown a whistle using loudspeaker in the present embodiment
Mode output alarm signal, it is of course also possible to use the mode output alarm signal such as luminous, output radio wave.In addition
In the case of one kind, used as preferred and non-limiting, when wind vector frequency exceedes twice, i.e., wind direction changed twice in one second,
With regard to output alarm signal, because wind speed frequency change is too fast, it is impossible to when aircraft receive what the structural plane that wind-force advertises came towards wind
Direction, so as to cause aircraft to receive advertising for wind-force, the flight thrust for raising up for obtaining.
Fig. 3 is a kind of structured flowchart of kite aircraft 100 of the invention.As shown in figure 3, kite aircraft 100 is wrapped
Aircraft body 110 and flight control units 150 are included, aircraft body 110 includes fuselage 120, wind sensor 140 and rotor
130；Flight control units 150 include gyroscope 160, memory module 170 and main control module 180.Can be clearly from Fig. 3
Find out the subordinate relation between aircraft all parts.
As preferred and non-limiting, in the present invention, also including collecting unit, recognition unit, demand identifying unit.Collection
Unit is used to gather the image information of barrier；Recognition unit is used to recognize the location and shape of the barrier；Demand judges
Unit connects flight control units 150, to determine whether there is avoidance demand according to the location and shape of the barrier.If needing
The result of determination of identifying unit is sought to there is avoidance demand, then flight control units 150 are by adjusting the flight attitude pair of aircraft
Barrier is avoided.In the present embodiment, as preferred and non-limiting, collecting unit is entered by the way of shooting to barrier
Row collection, it is of course also possible to use the mode of ultrasonic wave is acquired to barrier, needs when demand identifying unit is determined with avoidance
When asking, avoidance instruction is transferred to flight control units 150, flight attitude is controlled by flight control units 150, to barrier
Hidden.
As preferred and non-limiting, in the present invention, also including signal transmitting and receiving unit, the signal transmitting and receiving unit connection flight
Control unit 150, is used to receive subscriber signal and passes to flight control units 150, controls to fly by flight control units 150
The flight attitude of row device.Used as preferred and non-limiting, user can be remotely controlled using remote control to aircraft, such as by distant
Control device sends radio wave signal, after signal transmitting and receiving unit receives the radio wave signal of user, radio wave will be believed
Number be transferred to flight control units 150, by the flight attitude of the change of flight device of flight control units 150, as preferably rather than
Limit, the flight attitude of aircraft includes inclination angle and the anglec of rotation of heading and aircraft body 110.
Present invention additionally comprises a kind of implementation method of kite aircraft 100, as shown in figure 4, the method includes：
S110. according to wind behaviour, the flight attitude of aircraft is adjusted, the wherein aircraft is set to have and receives wind-force
The structure for being raised up；
S120. wind-force effect, the flight thrust that generation raises up are received.
As preferred and non-limiting, also include before the flight attitude that aircraft is adjusted in implementation method of the present invention：Pass through
Wind sensor 140 detects wind speed and direction, and flight attitude is adjusted according to pre-set flight attitude information.
Used as preferred and non-limiting, the aircraft in the present invention can be using rotary wind type flight structure, flapping wings type flight knot
Structure, fixed-wing formula flight structure, umbrella wing formula flight structure, jet-propelled flight structure or dirigible structure.
Used as preferred and non-limiting, the present embodiment preferentially uses rotary wind type flight structure, and rotary wind type flight structure is more steady
Gu, and it is easier to aircraft flight.
Used as preferred and non-limiting, the kite aircraft 100 in the present invention, aircraft body 110 is provided with wind-force biography
Sensor 140, used as preferred and non-limiting, wind sensor 140 is fixed on the surface of aircraft fuselage 120, for detect wind speed and
Wind direction, as preferred and non-limiting, uses ultrasonic wind speed sensor in this implementation, ultrasonic wind speed sensor is using ultrasound
Ripple time difference method realizes the measurement of wind speed.The aerial spread speed of sound, can be with the superposition of the air velocity on wind direction.If super
The direction of propagation of sound wave is identical with wind direction, and its speed can be accelerated；If if conversely, the direction of propagation of ultrasonic wave with wind direction conversely,
Its speed can be slack-off.Therefore, under fixed testing conditions, the speed that ultrasonic wave is propagated in atmosphere can and function of wind speed
Correspondence.Accurate wind speed and direction is can obtain by calculating.
As preferred and non-limiting, in the present invention, when wind speed and direction is detected using wind sensor 140, fly
Control unit 150 can adjust the flight attitude of aircraft, and the structure for enabling the reception wind-force to raise up receives wind-force, obtains
The flight thrust for raising up.As an example, when wind sensor 140 detects wind direction for east wind, and wind speed is when being 2m/s, flight
Control unit 150 adjusts aircraft flight attitude, aircraft is westwards inclined, so that aircraft bottom surface is towards east, so
Aircraft bottom surface can receive wind-force, obtain the flight thrust for raising up, and because wind speed now is 2m/s, wind-force is smaller, just
The angle of inclination of aircraft is correspondingly adjusted so that the increase of the effective lifting surface area in aircraft bottom surface, so as to increase flying of raising up
Row thrust；If detecting wind speed for 8m/s, because wind speed is larger, aircraft angle of inclination is excessive can not only to make aircraft smooth
Take off, also result in aircraft and gone by the place of wind to off-track, so now aircraft can reduce angle of inclination so that
Aircraft bottom surface reduces towards the effective area of wind direction, so that aircraft can smoothly take off on default track.
As preferred and non-limiting, in the present invention, the flight attitude of aircraft is controlled by flight control units 150, flown
Row control unit 150 can perceive flight attitude by gyroscope 160, so as to be adjusted to flight attitude, enable aircraft
Enough receive the effect of wind-force, the flight thrust that generation raises up.
In several embodiments provided by the present invention, it should be understood that disclosed relevant apparatus and method, Ke Yitong
Other modes are crossed to realize.For example, device embodiment described above is only schematical, for example, the module or list
The division of unit, only a kind of division of logic function can have other dividing mode when actually realizing, such as multiple units or
Component can be combined or be desirably integrated into another system, or some features can be ignored, or not performed.
The unit that is illustrated as separating component can be or may not be it is physically separate, it is aobvious as unit
The part for showing can be or may not be physical location, you can with positioned at a place, or can also be distributed to multiple
On NE.Some or all of unit therein can be according to the actual needs selected to realize the mesh of this embodiment scheme
's.
In addition, during each functional unit or module in each embodiment of the invention can be integrated in a processing unit,
Can also be that unit is individually physically present, it is also possible to which two or more units are integrated in a unit.Above-mentioned collection
Into unit can both be realized in the form of hardware, it would however also be possible to employ the form of SFU software functional unit is realized.
Embodiments of the invention are these are only, the scope of the claims of the invention is not thereby limited, it is every to be said using the present invention
Equivalent structure or equivalent flow conversion that bright book and accompanying drawing content are made, or directly or indirectly it is used in other related technology necks
Domain, is included within the scope of the present invention.
Claims (15)
1. a kind of kite aircraft, it is characterised in that：Including aircraft body, the aircraft body has on reception wind-force
The structure raised, the aircraft body is provided with wind sensor, connects flight control units, for detecting wind speed and direction,
The flight control units can adjust the flight attitude of aircraft according to wind speed and direction, the knot for making the reception wind-force raise up
Structure can receive wind-force, the flight thrust that acquisition raises up.
2. a kind of kite aircraft according to claim 1, it is characterised in that：
The aircraft uses rotary wind type flight structure, or
The aircraft uses flapping wings type flight structure, or
The aircraft uses fixed-wing formula flight structure, or
The aircraft uses umbrella wing formula flight structure, or
The aircraft uses jet-propelled flight structure, or
The aircraft uses dirigible structure.
3. a kind of kite aircraft according to claim 1, it is characterised in that：The flight control units include,
Gyroscope, for sensing flight attitude；
Memory module, for accessing default flight attitude information.
Main control module, connects gyroscope and memory module, for flight attitude to be compared with default flight attitude information
It is right, adjust to default flight attitude.
4. a kind of kite aircraft according to claim 3, it is characterised in that：The default flight attitude packet
Include,
Wind direction attitude information, is according to the corresponding flight attitude information of specific wind direction；
Wind speed attitude information, is according to the corresponding flight attitude information of specific wind speed.
5. a kind of kite aircraft according to claim 1, it is characterised in that：The flight attitude of the aircraft includes
The inclination angle and the anglec of rotation of heading and aircraft body.
6. a kind of kite aircraft according to claim 1, it is characterised in that：It is described to receive the structure tool that wind-force raises up
There is the stress surface of wind-force, the stress surface is configured to receive the structure of wind-force.
7. a kind of kite aircraft according to claim 1, it is characterised in that：The flight thrust for raising up, including
It is relative with gravity it is anti-raise up thrust or with heading identical thrust.
8. a kind of kite aircraft according to claim 1, it is characterised in that：Also include monitoring unit, the monitoring
Unit connects wind sensor, is used to monitor wind direction and air speed data that the wind sensor is detected, when the wind speed is super
When going out wind speed predetermined threshold value, output alarm signal；Or
When wind vector frequency exceeds wind direction predetermined threshold value, output alarm signal.
9. a kind of kite aircraft according to claim 1, it is characterised in that：The aircraft also includes,
Collecting unit, the image information for gathering barrier；
Recognition unit, the location and shape for recognizing the barrier；
Demand identifying unit, connects flight control units, is kept away to be determined whether there is according to the location and shape of the barrier
Allow demand；
If the result of determination of demand identifying unit is to there is an avoidance demand, flight control units are by adjusting the flight appearance of aircraft
State is avoided to barrier.
10. a kind of kite aircraft according to claim 1, it is characterised in that：The aircraft also includes signal transmitting and receiving
Unit, the signal transmitting and receiving unit connects flight control units, is used to receive subscriber signal and passes to flight control units, leads to
Cross the flight attitude that flight control units control aircraft.
A kind of 11. kite aircraft according to claim 1, it is characterised in that：The aircraft is many rotor flyings
Device, is connected with each other between each rotor by windward structure.
A kind of 12. implementation methods of kite aircraft, it is characterised in that：The method includes,
According to wind behaviour, the flight attitude of aircraft is adjusted, the wherein aircraft is set to that there is reception wind-force to be raised up
Structure；
Receive wind-force effect, the flight thrust that generation raises up.
A kind of 13. implementation methods of kite aircraft according to claim 12, it is characterised in that：The aircraft
Flight attitude includes inclination angle and the anglec of rotation of heading and aircraft.
A kind of 14. implementation methods of kite aircraft according to claim 12, it is characterised in that：Regulation aircraft
Also include before flight attitude, wind speed and direction is detected by wind sensor, adjusted according to pre-set flight attitude information and flown
Attitude.
A kind of 15. implementation methods of kite aircraft according to claim 14, it is characterised in that：It is described default winged
Row attitude information includes,
Wind direction attitude information, is according to the corresponding flight attitude information of specific wind direction；
Wind speed attitude information, is according to the corresponding flight attitude information of specific wind speed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| WO2021135823A1 (en) * | 2019-12-31 | 2021-07-08 | 深圳市道通智能航空技术股份有限公司 | Flight control method and device, and unmanned aerial vehicle |
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