CN106114817A - A kind of aircraft and flight system - Google Patents
A kind of aircraft and flight system Download PDFInfo
- Publication number
- CN106114817A CN106114817A CN201610681969.9A CN201610681969A CN106114817A CN 106114817 A CN106114817 A CN 106114817A CN 201610681969 A CN201610681969 A CN 201610681969A CN 106114817 A CN106114817 A CN 106114817A
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- Prior art keywords
- aircraft
- wing
- master control
- rotor
- control borad
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides a kind of aircraft and flight system, this aircraft includes: fuselage main body and the wing of fuselage main body both sides, and the wing of aircraft both sides is symmetrically arranged with rotor；Rotor is configured with the motor providing power and the speed regulator being connected with motor, and speed regulator electrically connects with the master control borad of aircraft；The Plane of rotation of rotor is perpendicular to the plane at wing place.Aircraft provided by the present invention and flight system, on wing by aircraft both sides, symmetrically arranged rotor rotates in the plane being perpendicular to wing place, aircraft can be made to realize vertical rise and landing under rotor mode, reduce the aircraft requirement when takeoff and landing to ground environment, the vibration caused in the face of aircraft body when effectively prevent aircraft landing damages, and improves the safety of user operation and user uses the Experience Degree of aircraft.
Description
Technical field
The present invention relates to vehicle technology field, in particular to a kind of aircraft and flight system.
Background technology
At present, aircraft is because having that volume is little, lightweight and flexible operation and the high feature of safety, the most extensively
Be applied to take photo by plane, monitor, search and rescue, the technical field such as prospecting, in conventional art, use arranges fixed-wing in aircraft both sides more
Mode realizes advance and the acceleration of aircraft, this mode make aircraft when takeoff and landing to the requirement of ground environment relatively
Height, needs larger space and relatively flat area, and needs operator to have higher operation level, easily to flying during landing
Row device main body causes vibration to damage, and reduces the safety of user operation.And directly fixed-wing is made into the aircraft of rotor, though
So reduce the requirement to ground environment, but be greatly reduced its effect advanced and accelerate, reduce user and use flight
The Experience Degree of device.
For the aircraft in above-mentioned conventional art when takeoff and landing higher to ground environmental requirement, and landing time easy
Aircraft body causes vibration damage, reduces the safety of user operation, and then reduction user uses the Experience Degree of aircraft
Problem, the most not yet proposes effective solution.
Summary of the invention
In view of this, the purpose of the embodiment of the present invention is to provide a kind of aircraft and flight system, it is possible to reduce flight
Device requirement to ground environment when takeoff and landing, causes in the face of aircraft body when effectively prevent aircraft landing
Vibration damages, and also maintains aircraft small size and good advance and acceleration effect simultaneously.
First aspect, embodiments provides a kind of aircraft, including: fuselage main body and the machine of fuselage main body both sides
The wing, the wing of both sides is symmetrically arranged with rotor；Rotor is configured with the motor providing power and the speed regulator being connected with motor, adjusts
Speed device electrically connects with the master control borad of aircraft；The Plane of rotation of rotor is perpendicular to the plane at wing place.
In conjunction with first aspect, embodiments provide the first possible embodiment of first aspect, wherein, on
State rotor to fix seat by rotor and be arranged on wing on the side of head is stupefied.
In conjunction with first aspect, embodiments provide the embodiment that the second of first aspect is possible, wherein, on
Stating aircraft also to include: be symmetricly set in the wing tip foot rest of described wing both sides of the edge, wing tip foot rest is for being at aircraft
When resting on the state of ground, support aircraft.
In conjunction with first aspect, embodiments provide the third possible embodiment of first aspect, wherein, on
Stating aircraft also to include: be symmetricly set in the aileron of wing afterbody, aileron is electrically connected with master control borad by steering wheel.
In conjunction with first aspect, embodiments provide the 4th kind of possible embodiment of first aspect, wherein, often
Individual aileron is configured with independent steering wheel, and master control borad adjusts the attitude of corresponding aileron by controlling steering wheel, to control aircraft
Flight attitude.
In conjunction with the third and the 4th kind of possible embodiment of first aspect, embodiments provide first party
The 5th kind of possible embodiment in face, wherein, the number of above-mentioned rotor and above-mentioned aileron is two.
In conjunction with first aspect, embodiments provide the 6th kind of possible embodiment of first aspect, wherein, on
State aircraft also to include: the baroceptor electrically connected with master control borad respectively and GPS sensor；Wherein, baroceptor is used for
The atmospheric pressure value of sense aircraft current location, transmits atmospheric pressure value to master control borad；When GPS sensor is used for obtaining aircraft flight
Location information, and by location information transmit to master control borad；Master control borad receives and records atmospheric pressure value and location information, according to air pressure
Value obtains the flying height that aircraft is current.
In conjunction with the 6th kind of possible embodiment of first aspect, embodiments provide the 7th kind of first aspect
Possible embodiment, wherein, above-mentioned aircraft also includes: nine axle sensors, and this nine axle sensor includes: gyroscope, acceleration
Degree meter and magnetometer, the driving parameters of nine axle sensor sense aircraft, and driving parameters is transmitted to master control borad；Master control borad
The flight attitude of described aircraft is controlled according to flying height, location information and driving parameters.
In conjunction with first aspect, embodiments provide the 8th kind of possible embodiment of first aspect, wherein, on
Stating aircraft also to include: the sensor cluster being connected with master control borad, sensor cluster at least includes one below: light stream senses
Device, ultrasonic sensor and infrared sensor；Master control borad receives the collection information that sensor cluster is uploaded, and adjusts according to the information of collection
The flight attitude of whole aircraft.
Second aspect, the embodiment of the present invention also provides for a kind of flight system, and wherein, this flight system includes: above-mentioned first
The aircraft that aspect provides, and the controller of above-mentioned aircraft；Above-mentioned aircraft and controller radio communication；Wherein, control
Device is the remote controller of aircraft or is mobile terminal.
The aircraft of embodiment of the present invention offer and flight system, symmetrically arranged rotation on the wing by aircraft both sides
The wing rotates in the plane being perpendicular to wing place, it is possible to make aircraft realize vertical rise and landing under rotor mode,
Reduce the aircraft requirement when takeoff and landing to ground environment, when effectively prevent aircraft landing in the face of aircraft
The vibration that main body causes damages, and improves the safety of user operation.
Further, the aircraft of embodiment of the present invention offer and flight system, entered by the rotating speed of governor control motor
And regulate the rotary speed of aircraft rotor, it is possible to provide thrust when aircraft flight, it is achieved the VTOL mould of aircraft
The peaceful conversion flying pattern of formula, and transformation process stably smooths, and controllability is strong, also maintains good advance and acceleration simultaneously
Effect, improves user and uses the Experience Degree of aircraft.
For making the above-mentioned purpose of the present invention, feature and advantage to become apparent, preferred embodiment cited below particularly, and coordinate
Appended accompanying drawing, is described in detail below.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme of the embodiment of the present invention, below by embodiment required use attached
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, and it is right to be therefore not construed as
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to according to this
A little accompanying drawings obtain other relevant accompanying drawings.
Fig. 1 shows the perspective view of the rotor of a kind of aircraft that the embodiment of the present invention provided；
Fig. 2 shows the perspective view of a kind of aircraft that the embodiment of the present invention provided；
Fig. 3 shows the front view of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided；
Fig. 4 shows the rearview of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided；
Fig. 5 shows the side view of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided；
Fig. 6 shows the upward view of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided；
Fig. 7 shows the top view of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided；
Fig. 8 shows the explosive view of a kind of aircraft that the embodiment of the present invention provided；
Fig. 9 shows the circuit control principle block diagram of a kind of aircraft that the embodiment of the present invention provided.
Illustrate:
1-fuselage main body 2a-wing 2b-wing 3a-rotor 3b-rotor
4a-wing tip foot rest 4b-wing tip foot rest 5a-aileron 5b-aileron
6-electric machine support 7-motor fixing screw 8-motor 9-rotor fixes seat
10-rotor fixes seat screw 11-rotor fixed screw 12a-motor cover
12b-motor cover 13-battery 14-power panel 15-master control borad
16-master control borad is fixed seat 17a-aileron and is controlled assembly 17b-aileron control assembly
Detailed description of the invention
For making the purpose of the embodiment of the present invention, technical scheme and advantage clearer, below in conjunction with the embodiment of the present invention
Middle accompanying drawing, is clearly and completely described the technical scheme in the embodiment of the present invention, it is clear that described embodiment is only
It is a part of embodiment of the present invention rather than whole embodiments.Generally real with the present invention illustrated described in accompanying drawing herein
The assembly executing example can be arranged with various different configurations and design.Therefore, below to the present invention's provided in the accompanying drawings
The detailed description of embodiment is not intended to limit the scope of claimed invention, but is merely representative of the selected reality of the present invention
Execute example.Based on embodiments of the invention, the institute that those skilled in the art are obtained on the premise of not making creative work
There are other embodiments, broadly fall into the scope of protection of the invention.
In view of in conventional art, aircraft is higher to ground environmental requirement when takeoff and landing, and the most right during landing
Aircraft body causes vibration to damage, and reduces the safety of user operation, and then reduction user uses the Experience Degree of aircraft to ask
Topic, embodiments provides a kind of aircraft and flight system, is described below by embodiment.
Embodiment 1
The perspective view of the rotor of a kind of aircraft shown in Figure 1, this aircraft includes: fuselage main body 1
With wing 2a and 2b of fuselage main body 1 both sides, wing 2a and 2b of these aircraft both sides is symmetrically arranged with rotor 3a and 3b,
Rotor 3a and 3b is respectively configured and is provided with the motor (not shown in figure 1) of power and the speed regulator being connected with motor (does not shows in Fig. 1
Go out), speed regulator electrically connects with the master control borad (not shown in figure 1) of aircraft；The master control borad rotating speed by governor control motor,
Rotor 3a and 3b is driven to rotate, to control taking off vertically, land and hovering of aircraft.
The Plane of rotation of rotor 3a and 3b is perpendicular to wing 2a and the plane at 2b place, and rotor 3a and 3b is fixed by rotor
Seat (not shown in figure 1) is separately positioned on wing 2a and 2b on the side of head is stupefied, wherein, rotor 3a and 3b at wing 2a and
2b position is specifically set can arrange flexibly according to the structure of concrete aircraft on the side of head is stupefied, the present embodiment
This is not limited.
The aircraft that foregoing invention embodiment 1 provides, on the wing by aircraft both sides, symmetrically arranged rotor is hanging down
The straight plane in wing place rotates, it is possible to makes aircraft realize vertical rise and landing under rotor mode, reduces
Aircraft requirement to ground environment when takeoff and landing, makes in the face of aircraft body when effectively prevent aircraft landing
The vibration become damages, and improves the safety of user operation.
When implementing, above-mentioned aircraft also includes: be symmetricly set in the wing tip foot rest at wing 2a and 2b both sides of the edge,
Wing tip foot rest 4a and 4b in the perspective view of a kind of aircraft as shown in Figure 2, wing tip foot rest 4a and 4b are used for
Aircraft is in when resting on the state of ground, supports aircraft, it is possible to make aircraft realizes under rotor mode vertical rise with
Landing, it is not necessary to runway, the vibration damage caused in the face of aircraft body when effectively prevent aircraft landing, reduce flight
The device requirement to landing site.
When implementing, above-mentioned aircraft also includes: be symmetricly set in aircraft wing 2a and the aileron of 2b afterbody, such as figure
Shown in 2, aileron 5a and 5b is electrically connected with master control borad by steering wheel, and wherein, steering wheel is the most not shown with master control borad.Each pair
The wing 5a and 5b is configured with independent steering wheel, and master control borad adjusts the attitude of corresponding aileron by controlling steering wheel, to control aircraft
Flight attitude.Aileron 5a and 5b occurs differential deflection under the adjustment of steering wheel, including: ibid with lower deflection, the most partially
Turn, or make the pendulum angle of aileron 5a and 5b different, cause the lift at wing 2a and 2b two ends to change, produce pressure
Difference, i.e. produces rolling moment, and to control aircraft, to do roll motor-driven.
Aircraft takes off vertically after reaching specified altitude assignment under rotor flying pattern, and master control borad passes through governor control motor
Adjust the rotary speed of rotor 3a and 3b, simultaneously by the differential deflection of servos control aileron 5a and 5b, make aircraft adjust and fly
Row attitude, carries out horizontal flight, and now wing 2a and 2b plays a leading role, and rotor 3a and 3b and aileron 5a and 5b plays auxiliary and fly
The effect of row, i.e. fixed-wing offline mode.When aircraft needs to turn left, on aileron 5a partially, under aileron 5b partially, aircraft to
Roll left and turn, it is achieved turn left；Otherwise, when needing to turn right, on aileron 5b partially, under aileron 5a partially, aircraft rolling to the right, it is achieved
Turn right.
Fig. 3, Fig. 4 respectively illustrate the aircraft shown in Fig. 2 that foregoing invention embodiment is provided front view and after
View, by Fig. 3, Fig. 4 can be seen that aircraft be in rest on the state of ground time, by wing tip foot rest 4a and 4b support, it is achieved
The vertical and landing takeoff under rotor flying pattern of aircraft, the Plane of rotation of rotor 3a and 3b is perpendicular to wing 2a and 2b institute
Plane.
Fig. 5 shows the side view of the aircraft shown in Fig. 2 that foregoing invention embodiment is provided, as seen from Figure 5
Wing tip foot rest 4a and 4b is symmetricly set in the position of wing 2a and 2b (not shown in Fig. 5) both sides of the edge, and aircraft is risen support
Effect, enables aircraft to use in less place, reduces the aircraft requirement to landing site.
Fig. 6, Fig. 7 respectively illustrate upward view and the vertical view of the aircraft shown in Fig. 2 that the embodiment of the present invention is provided
Figure, can be seen that the simple in construction of aircraft by Fig. 6, Fig. 7, and optional equipment is less, it is not necessary to bigger takeoff and landing is empty
Between, make user more flexible to the operation of aircraft.
The rotor of above-mentioned aircraft and the number of aileron are two, it will be appreciated that the rotation of the aircraft of above-described embodiment
The number of the wing and aileron is the preferred embodiment that the embodiment of the present invention provides, and is therefore not construed as the restriction to scope.
On the basis of above-described embodiment 1, the embodiment of the present invention additionally provides the explosive view of above-mentioned aircraft, such as Fig. 8 institute
Show, it should be noted that the explosive view of the aircraft shown in Fig. 8, only include the main structural representation of aircraft rather than
The all of structure of aircraft.
As shown in Figure 8, rotor assemblies includes: rotor 3a and 3b, electric machine support 6, motor fixing screw 7, motor 8, rotor
Fixing seat 9, rotor fix seat screw 10, rotor fixed screw 11 and motor cover 12a and 12b, and rotor 3a and 3b passes through rotor
Fixing seat 9 is arranged on wing 2a and 2b on the side of head is stupefied；Wing tip foot rest 4a and 4b (is not shown in Fig. 8 by fixing device
Go out) it is arranged at the both sides of the edge of wing 2a and 2b；Aileron 5a and 5b controls assembly 17a by aileron respectively and 17b symmetry sets
It is placed in the afterbody of aircraft wing 2a and 2b；Battery 13, power panel 14 and master control borad 15 it is additionally provided with at aircraft top, its
Middle master control borad 15 is fixed seat 16 by master control borad and is arranged on aircraft top.
The aircraft that above-described embodiment provides is being perpendicular to machine by symmetrically arranged rotor on the wing of aircraft both sides
The plane at wing place rotates, it is possible to makes aircraft realize vertical rise and landing under rotor mode, reduces aircraft
The requirement to ground environment when takeoff and landing, in flight course, by the rotary speed of regulation aircraft rotor and
The differential upset of aileron, it is possible to provide thrust when aircraft flight, it is achieved the VTOL pattern of aircraft is peaceful flies pattern
Conversion, and complete relevant action, also maintain good advance and acceleration effect simultaneously, improve user and use aircraft
Experience Degree.
Embodiment 2
Aircraft for the ease of providing the embodiment of the present invention is further appreciated by, on the basis of embodiment 1, and the present invention
Additionally provide the circuit control principle block diagram of aircraft described in above-described embodiment 1, as it is shown in figure 9, concrete, this aircraft
Circuit control principle block diagram mainly includes following all parts: master control borad, baroceptor, GPS sensor, nine axle sensors,
Speed regulator, steering wheel, wireless transport module and sensor cluster, wherein, Fig. 9 only illustrates a speed regulator and steering wheel, specifically
When realizing, can arrange flexibly according to the structure of concrete aircraft, this is not limited by the present embodiment.
Wherein, baroceptor, GPS sensor and nine axle sensors electrically connect with master control borad.Baroceptor is used for
The atmospheric pressure value of current location during sense aircraft flight, and atmospheric pressure value is transmitted to master control borad；GPS sensor is used for obtaining flight
Location information during device flight, including: the longitude of aircraft current location and latitude, and location information is transmitted to master control borad；
Master control borad receives and records atmospheric pressure value and location information, obtains, according to atmospheric pressure value, the flying height that aircraft is current.
Nine axle sensors include: gyroscope, accelerometer and magnetometer, the traveling ginseng of nine axle sensor sense aircraft
Number, and driving parameters is transmitted to master control borad.When implementing, gyroscope judges currently to fly by measuring the rotation status of self
The kinestate of row device, including aircraft forward, back, up, downwards, to the left, to the right and aircraft accelerate, slow down
Deng；Accelerometer is by measuring aircraft acceleration and then calculating aircraft flight on this heading on heading
Distance；Magnetometer is by magnetic field intensity during measurement aircraft flight and direction, the heading that positioning aircraft is current.
Master control borad, according to the current flying height of aircraft, location information and driving parameters, controls the flight of aircraft
Posture, by the rotating speed of governor control motor and then the rotary speed of the rotor controlling aircraft and secondary by servos control
The differential upset of the wing, it is achieved control the flight attitude of aircraft, complete relevant action.
Further, above-mentioned aircraft also includes: the sensor cluster being connected with master control borad, sensor cluster at least include with
One of lower: light flow sensor, ultrasonic sensor and infrared sensor；Master control borad receives the collection letter that sensor cluster is uploaded
Breath, adjusts the flight attitude of aircraft according to the information of collection.Such as, aircraft can utilize light flow sensor to catch flight course
In image, and image is analyzed, with nine axle sensors or GPS sensor with the use of, obtain in real time aircraft from
The position of body and motion conditions；Aircraft can also be by the barrier on ultrasonic sensor and infrared sensor detection heading
Hinder thing, and obstacle information is sent to master control borad, and then adjust the flight attitude of aircraft, barrier is hidden, with
Reach more preferable state of flight.When implementing, kind of sensor that sensor cluster comprises and quantity, can be according to actual feelings
Condition is configured, and this is not limited by the present embodiment.
The aircraft that foregoing invention embodiment 2 provides, is controlled the flight of aircraft by master control borad, regulation aircraft rotation
The rotary speed of the wing and the differential upset of aileron, it is possible to make aircraft realize various flight attitude when flight and complete to be correlated with
Action, also maintains good advance and acceleration effect simultaneously, improves user and use the Experience Degree of aircraft.
Embodiment 3
On the basis of embodiment 1 with embodiment 2, the embodiment of the present invention additionally provides a kind of flight system, this flight system
System includes the aircraft in above-described embodiment, and the controller of aircraft, wherein, aircraft and controller radio communication.
The controller of above-mentioned aircraft includes: the remote controller of aircraft, or mobile terminal, such as: mobile phone, flat board electricity
Brain, PDA (Personal Digital Assistant, palm PC), pocket computer on knee, vehicle-mounted computer etc..
Aircraft communicates by being arranged at the wireless transport module foundation of master control borad with controller, and aircraft is by wireless biography
Defeated module, the real-time parameter received by master control borad sends to controller, and wherein real-time parameter includes: the flight height that aircraft is current
Degree, location information and driving parameters.
The real-time parameter that user can receive according to controller, is referred to by the operation control module input operation of controller
Show, aircraft is controlled, after aircraft receives the control command of controller by wireless transport module, according to controller
The control command given completes relevant action, such as, take off, land, hover, change of flight state, including: adjust flying height and
Heading and flight speed etc., or, according to the setting of user, aircraft can be automatically adjusted in flight course and fly
Row state, flies according to the setting of user.
The flight system that the embodiment of the present invention 3 is provided, its operation method and the technique effect of generation and previous embodiment
Identical, for briefly describing, the not mentioned part of the present embodiment part, refer to corresponding contents in previous embodiment.
The flight system that foregoing invention embodiment 3 is provided, is controlled the state of flight of aircraft, makes flight by controller
The operation of device is more flexible, it is possible to the operation instruction given according to user completes relevant action, it is achieved vertical rise and landing, carries
High user uses the Experience Degree of aircraft.
It should be noted that in describing the invention, term " " center ", " on ", D score, "left", "right", " vertically ",
Orientation or the position relationship of the instruction such as " level ", " interior ", " outward " they are based on orientation shown in the drawings or position relationship, merely to
Be easy to describe the present invention and simplifying describe rather than instruction or the hint device of indication or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.Additionally, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that indicate or hint relative importance.
It addition, in describing the invention, unless otherwise clearly defined and limited, term " install ", " being connected ", " even
Connect " should be interpreted broadly, connect for example, it may be fixing, it is also possible to be to removably connect, or be integrally connected；It can be machine
Tool connects, it is also possible to be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, can be two units
Connection within part.For the ordinary skill in the art, above-mentioned term can be understood in the present invention with concrete condition
Concrete meaning.
The above, the only detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto, and any
Those familiar with the art, in the technical scope that the invention discloses, can readily occur in change or replace, should contain
Cover within protection scope of the present invention.Therefore, protection scope of the present invention should described be as the criterion with scope of the claims.
Claims (10)
1. an aircraft, including: fuselage main body and the wing of described fuselage main body both sides, it is characterised in that described both sides
Rotor it is symmetrically arranged with on wing；
Described rotor is configured with the motor providing power and the speed regulator being connected with described motor, described speed regulator and described flight
The master control borad electrical connection of device；
The Plane of rotation of described rotor is perpendicular to the plane at described wing place.
Aircraft the most according to claim 1, it is characterised in that described rotor is fixed seat by rotor and is arranged on described machine
The wing is on the side of head is stupefied.
Aircraft the most according to claim 1, it is characterised in that described aircraft also includes: be symmetricly set in described machine
The wing tip foot rest of wing both sides of the edge, described wing tip foot rest, for when described aircraft is in and rests on the state of ground, supports institute
State aircraft.
Aircraft the most according to claim 1, it is characterised in that described aircraft also includes: be symmetricly set in described machine
The aileron of wing afterbody, described aileron is electrically connected with described master control borad by steering wheel.
Aircraft the most according to claim 1, it is characterised in that each described aileron is configured with independent steering wheel, described
Master control borad adjusts the attitude of corresponding aileron by controlling described steering wheel, to control the flight attitude of described aircraft.
6. according to the aircraft described in claim 4 or 5, it is characterised in that the number of described rotor and described aileron is two
Individual.
Aircraft the most according to claim 1, it is characterised in that described aircraft also includes: respectively with described master control borad
The baroceptor of electrical connection and GPS sensor；
Wherein, described atmospheric pressure value, for detecting the atmospheric pressure value of described aircraft current location, is transmitted extremely by described baroceptor
Described master control borad；
Location information when described GPS sensor is for obtaining described aircraft flight, and described location information is transmitted to institute
State master control borad；
Described master control borad receives and records described atmospheric pressure value and described location information, obtains described aircraft according to described atmospheric pressure value
Current flying height.
Aircraft the most according to claim 7, it is characterised in that described aircraft also includes: nine axle sensors, described nine
Axle sensor includes: gyroscope, accelerometer and magnetometer, and described nine axle sensors detect the traveling ginseng of described aircraft
Number, and by the transmission of described driving parameters to described master control borad；
Described master control borad controls flying of described aircraft according to described flying height, described location information and described driving parameters
Row posture.
Aircraft the most according to claim 1, it is characterised in that described aircraft also includes: be connected with described master control borad
Sensor cluster, described sensor cluster at least includes one below: light flow sensor, ultrasonic sensor and infrared sensing
Device；
Described master control borad receives the collection information that described sensor cluster is uploaded, and adjusts described aircraft according to described collection information
Flight attitude.
10. a flight system, it is characterised in that described flight system includes: flying described in claim 1～9 any one
Row device, and the controller of described aircraft；
Described aircraft and described controller radio communication；Described controller is the remote controller of described aircraft or is mobile whole
End.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610681969.9A CN106114817A (en) | 2016-08-17 | 2016-08-17 | A kind of aircraft and flight system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610681969.9A CN106114817A (en) | 2016-08-17 | 2016-08-17 | A kind of aircraft and flight system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107499513A (en) * | 2017-09-01 | 2017-12-22 | 无锡翼鸥科技有限公司 | Microminiature can hover Fixed Wing AirVehicle |
| CN108873916A (en) * | 2017-05-11 | 2018-11-23 | 圣速医疗器械江苏有限公司 | A kind of flight control method of intelligent balance aircraft |
| CN108860610A (en) * | 2018-04-03 | 2018-11-23 | 惠安县金建达电子科技有限公司 | A kind of microbubble plant protection helicopter |
| CN112678167A (en) * | 2020-12-28 | 2021-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated airplane |
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| CN112678167A (en) * | 2020-12-28 | 2021-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated airplane |
| CN112678167B (en) * | 2020-12-28 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated aircraft |
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Application publication date: 20161116 |