CN107444606A - Course of new aircraft and aerocraft system - Google Patents
Course of new aircraft and aerocraft system Download PDFInfo
- Publication number
- CN107444606A CN107444606A CN201710837646.9A CN201710837646A CN107444606A CN 107444606 A CN107444606 A CN 107444606A CN 201710837646 A CN201710837646 A CN 201710837646A CN 107444606 A CN107444606 A CN 107444606A
- Authority
- CN
- China
- Prior art keywords
- propeller
- longitudinal adjusting
- course
- adjusting mechanism
- motor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 48
- 230000033228 biological regulation Effects 0.000 claims abstract description 25
- 230000033001 locomotion Effects 0.000 claims description 28
- 230000003028 elevating effect Effects 0.000 claims description 7
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 4
- 230000000116 mitigating effect Effects 0.000 claims description 4
- 230000009194 climbing Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 230000003993 interaction Effects 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims 1
- 238000005096 rolling process Methods 0.000 description 19
- 230000001133 acceleration Effects 0.000 description 7
- 230000008901 benefit Effects 0.000 description 6
- 230000009467 reduction Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- 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
- 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
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention provides a kind of course of new aircraft and aerocraft system, is related to airmanship field, including：Fuselage, pitch-control motor, roll control motor, lateral adjustment and two longitudinal adjusting mechanisms, four propeller braced wing regulation Dual-output shaft motors；Two longitudinal adjusting mechanisms are symmetrically arranged on the fuselage both sides；The pitch-control motor is arranged on the longitudinal adjusting mechanism, controls the longitudinal adjusting mechanism to move；The roll control motor is arranged on the fuselage, the roll control motor is connected by the lateral adjustment with the longitudinal adjusting mechanism, the lateral adjustment controls to be moved on horizontal direction of the longitudinal adjusting mechanism along the aircraft, the double output shaft that four propeller braced wings adjust Dual-output shaft motors moves axially with four propeller braced wings drive connection control propeller braced wings respectively, solves the technical problem that air crash, full landform landing do not occur easily comprehensively, in complex space flight for photographed scene.
Description
Technical field
The present invention relates to airmanship field, more particularly, to a kind of course of new aircraft and aerocraft system.
Background technology
Multi-rotor unmanned aerial vehicle have VTOL, hovering, take off, landing does not need runway, maneuverability and ultralow
The features such as empty flight, the incomparable advantage of fixed-wing unmanned plane is made it have, tool has a broad prospect of the use.Unmanned plane is in the people
With aspect, agricultural plant protection can operate with, power-line patrolling, surrounding air detection, Vehicle Detection, water resource detection takes photo by plane and the disaster relief.
Military aspect, task scouting is can operate with, as target drone, aerial relaying, aerial/ground is hit and the neck such as interference, electronic countermeasure
Domain.
With continuous development of the unmanned plane in each field, the task that it is performed is more diversified, complicates.To meet each neck
The demand in domain, requirement to autonomous flight control precision also more and more higher.Therefore, unmanned plane will be greatly developed, make its
Every profession and trade is used widely, and design maneuverability, type vdiverse in function and flight system are crucial.
For example, nowadays four rotor wing unmanned aerial vehicles are widely used as a grade unmanned plane first choice of taking photo by plane.Present four rotor wing unmanned aerial vehicle
The flight theory of (X4 types) is：Sorted successively clockwise by No. 1 propeller, other propellers of the propeller of right front, when 1,
2nd, 3, No. 4 propellers rev up as throttle simultaneously, unmanned plane is increased；During pitching, 2, No. 3 propellers, which are accelerated or slowed down, to be turned
Speed, while 1, No. 4 airscrew reduction or acceleration；During rolling, 1, No. 2 propeller acceleration or deceleration, while 3, No. 4 airscrew reductions
Or accelerate；During driftage, 1, No. 3 propeller acceleration or deceleration, while 2, No. 4 airscrew reductions or acceleration.
Prior art be actually by the elevating movement of unmanned plane and move forward and backward, rolling movement and side-to-side movement are mixed as one
Talk, independence can not do pitching or rolling movement when locus is constant.Because regulation of the head to angle is that have a fixed limit
Spend, therefore the picture of whole sphere can not be also shot even if using three-axis stabilization head.
In addition, existing X4 types unmanned plane situation of the safeguard measure such as No Chute again after thering is propeller to break down
Under be bound to occur air crash accident cause damage；It is right and existing X4 types unmanned plane landing need to be carried out in the landform of relatively flat
Landing landform there are certain requirements.
The information for being disclosed in the background section is merely intended to deepen the understanding of the general background technology to the present invention, and
It is not construed as recognizing or implies information structure prior art known to those skilled in the art in any form.
The content of the invention
It is an object of the invention to provide course of new aircraft and aerocraft system, is clapped with alleviating present in prior art
Take the photograph the technical problem that air crash, full landform landing do not occur easily comprehensively, in complex space flight for scene.
In a first aspect, a kind of course of new aircraft provided by the invention, including：Fuselage, pitch-control motor, roll control motor, transverse direction
Governor motion and two longitudinal adjusting mechanisms, four propeller braced wing regulation Dual-output shaft motors；
Two longitudinal adjusting mechanisms are symmetrically arranged on the fuselage both sides；
The pitch-control motor is arranged on the longitudinal adjusting mechanism, controls the longitudinal adjusting mechanism to move；
The roll control motor is arranged on the fuselage, and the roll control motor is indulged by the lateral adjustment with described
Connected to governor motion, the lateral adjustment controls horizontal direction of the longitudinal adjusting mechanism along the aircraft to move up
It is dynamic；
Each propeller braced wing regulation Dual-output shaft motor is arranged at the both ends of the longitudinal adjusting mechanism.
Further, the lateral adjustment includes：First cingulum, two be respectively cooperating with first cingulum the
One driven gear and the first driving gear；
Two first driven gears are separately positioned on the longitudinal adjusting mechanism, and first cingulum is arranged on two
The outside of individual first driven gear and first driving gear, and first driving gear and the roll control motor
Output shaft is connected.
Further, the longitudinal adjusting mechanism is connected by connector with the fuselage, and the freedom of the connector
First driven gear is provided with end；
The other end of the connector is connected with the longitudinal adjusting mechanism.
Further, the longitudinal adjusting mechanism includes：Support frame, the second cingulum, it is respectively cooperating with second cingulum
Two the second driven gears and the second driving gear；
Two second driven gears are arranged on the both ends of support frame as described above, and second driving gear is arranged on described
The stage casing of support frame, second cingulum are arranged on the outside of two second driven gears and second driving gear；
And second driving gear is connected with the pitch-control motor output shaft.
Further, four propeller braced wing regulation Dual-output shaft motors, make the aircraft do pitching fortune
When dynamic, wobble shaft not with motor overlapping of axles；
Second driven gear is fixedly connected with propeller braced wing regulation Dual-output shaft motor.
Further, the aircraft includes：For connecting the propeller braced wing of propeller；
The double output shaft of the propeller braced wing regulation Dual-output shaft motor is connected with the propeller braced wing.
Further, the end of the propeller braced wing and the spiral for providing climbing power to the aircraft
Oar connects.
Further, the propeller includes：Motor and blade；
The blade is connected with the motor, and the motor rotates the blade, the paddle belt
The aircraft is moved to rise or fall.
Further, the lightening core for mitigating flight gravity and resistance is provided with the fuselage.
Second aspect, a kind of aerocraft system provided by the invention, including it is new winged described in first aspect any one
Row device, in addition to remote control equipment and/or earth station；
The remote control equipment is used to carry out flight control to the course of new aircraft；
The earth station is used to carry out data interaction with the course of new aircraft.
Had the advantages that using course of new aircraft provided by the invention and aerocraft system：
A kind of course of new aircraft provided by the invention, including：Fuselage, pitch-control motor, roll control motor, lateral adjustment,
Two longitudinal adjusting mechanisms and four propeller braced wing regulation Dual-output shaft motors；Two longitudinal adjusting mechanisms are symmetrically set
In fuselage both sides；Pitch-control motor is arranged on longitudinal adjusting mechanism, control longitudinal adjusting mechanism motion；Roll control motor is arranged on machine
With, roll control motor is connected by lateral adjustment with longitudinal adjusting mechanism, lateral adjustment control longitudinal adjusting mechanism
Moved along the horizontal direction of aircraft；The double output shaft of four propeller braced wings regulation Dual-output shaft motors respectively with
Four propeller braced wing drive connection control propeller braced wing axial movements.So design will can move forward and backward and pitching
Motion or side-to-side movement separate with rolling movement stands alone as 4 passages.Unmanned plane is set to be bowed when locus is static
Face upward and rolling movement.Advantages below can so be realized：
First, during pan-shot：By the regulation of unmanned plane pitch-control motor and roll control motor, when the head elevation angle reaches
When maximum, fuselage can make camera continue to raise up so as to reach the coverage at full visual angle by pitching or rolling.
2nd, failure is saved oneself：It can make failure propeller and its homonymy spiral when one propeller of unmanned plane breaks down
Oar stalls, and with two propellers holding of opposite side and horizontal plane, fuselage is sling, makes its safe falling, avoids the occurrence of
Air crash accident.
3rd, full landform landing：By to unmanned plane pitching, rolling adjust, make fuselage in unmanned plane geo-stationary pitching,
Rolling, to adapt to different terrain needs, so as to complete landing of the unmanned plane in landform such as different inclined-planes.
4th, flexibly flight：Due to fuselage posture can be changed to adapt to different spaces, unmanned plane can be made narrow by some
Narrowly area, and being verted by rotor can greatly promote flight flexibility and flying speed, so that application scenarios are big
Big increase.
Aerocraft system provided by the invention with above-mentioned course of new aircraft with all advantages, and convenient manipulate.
Brief description of the drawings
, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical scheme of the prior art
The required accompanying drawing used is briefly described in embodiment or description of the prior art, it should be apparent that, in describing below
Accompanying drawing is some embodiments of the present invention, for those of ordinary skill in the art, before creative work is not paid
Put, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of course of new aircraft provided in an embodiment of the present invention；
Fig. 2 is the explosive view of course of new aircraft provided in an embodiment of the present invention；
Fig. 3 is the schematic diagram of the braced wing of course of new aircraft provided in an embodiment of the present invention.
Icon：100- fuselages；110- lightening cores；200- pitch-control motors；300- roll control motors；400- lateral adjustments
Mechanism；The cingulums of 410- first；The driven gears of 420- first；The driving gears of 430- first；500- longitudinal adjusting mechanisms；
510- support frames；The cingulums of 520- second；The driven gears of 530- second；The driving gears of 540- second；600- connectors；
700- propellers braced wing adjusts Dual-output shaft motor；800- propeller braced wings；900- propellers；910- driving electricity
Machine；920- blades.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than instruction or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that instruction or hint relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, with concrete condition above-mentioned term can be understood at this
Concrete meaning in invention.
The embodiment of the present invention is described in detail below in conjunction with accompanying drawing.It should be appreciated that this place is retouched
The embodiment stated is merely to illustrate and explain the present invention, and is not intended to limit the invention.
Fig. 1, Fig. 2, Fig. 3 are refer to, below in conjunction with accompanying drawing to course of new aircraft provided in an embodiment of the present invention and flight
Device system elaborates.
In a first aspect, a kind of course of new aircraft provided by the invention, including：Including：Fuselage 100, pitch-control motor 200, rolling
Come about machine 300,400, two longitudinal adjusting mechanisms 500 of lateral adjustment and four propeller braced wings regulation double output shafts electricity
Machine 700；
Two longitudinal adjusting mechanisms 500 are symmetrically arranged on the both sides of fuselage 100；
Pitch-control motor 200 is arranged on longitudinal adjusting mechanism 500, and control longitudinal adjusting mechanism 500 moves；
Roll control motor 300 is arranged on fuselage 100, and roll control motor 300 passes through lateral adjustment 400 and longitudinally adjust machine
Structure 500 connects, and lateral adjustment 400 controls longitudinal adjusting mechanism 500 to be moved along the horizontal direction of aircraft；Described in four
The double output shaft of propeller braced wing regulation Dual-output shaft motor is controlled with four bottom of propeller braced wing 800 drive connections respectively
Propeller braced wing 800 processed moves axially；
Each propeller braced wing regulation Dual-output shaft motor 700 is arranged at the both ends of longitudinal adjusting mechanism 500.
It should be noted that so design will can move forward and backward and elevating movement or side-to-side movement and rolling movement separation
Open and stand alone as 4 passages.Unmanned plane is set to do pitching and yawing rotation when locus is static.It can so realize following
Advantage：
First, during pan-shot：By the regulation of unmanned plane pitch-control motor 200 and roll control motor 300, when head is faced upward
When angle reaches maximum, fuselage 100 can make camera continue to raise up so as to reach the coverage at full visual angle by pitching or rolling.
2nd, failure is saved oneself：It can make failure propeller and its homonymy spiral when one propeller of unmanned plane breaks down
Oar stalls, and with two propellers holding of opposite side and horizontal plane, fuselage 100 is sling, makes its safe falling, avoids out
Existing air crash accident.
3rd, full landform landing：By being adjusted to unmanned plane pitching, rolling, fuselage 100 is set to believe in unmanned plane geo-stationary
Face upward, rolling, to adapt to different terrain needs, so as to complete landing of the unmanned plane in landform such as different inclined-planes.
4th, flexibly flight：Due to the posture of fuselage 100 can be changed to adapt to different spaces, unmanned plane can be made by one
A little narrow areas, and being verted by rotor can greatly promote flight flexibility and flying speed, so that applied field
Scape greatly increases.
Specifically, in order to express easily, longitudinal direction mentioned here is the direction of advance of aircraft, and transverse direction mentioned here is
The vertical direction of the direction of advance of aircraft, as width.
The flight theory of present four rotor wing unmanned aerial vehicle (X4 types) is：Using the propeller of right front as No. 1 propeller, other spiral shells
Rotation oar sorts successively clockwise, when 1,2,3, No. 4 propeller while revs up as throttle, unmanned plane is increased；During pitching,
2nd, rotating speed, while 1, No. 4 airscrew reduction or acceleration are accelerated or slowed down to No. 3 propellers；During rolling, 1, No. 2 propeller accelerate or
Slow down, while 3, No. 4 airscrew reductions or acceleration；During driftage, 1, No. 3 propeller acceleration or deceleration, while 2, No. 4 propellers subtract
Speed accelerates.
Course of new aircraft can change original flying method.Lifting and driftage principle and now identical, and will rolling
Turn and pitching is independently set to two passages.To during front or rear flight, pitch-control motor 200 is first adjusted before or after propeller unmanned plane
Incline, slightly speed balances anti-twisted torque again for 2, No. 3 propellers or 1, No. 4 propeller, and aircraft is to front or rear flight.Unmanned plane is to the left
Or during flight to the right, propeller braced wing regulation Dual-output shaft motor 700 first adjusts propeller and inclined to the left or to the right, 1, No. 2 spiral shell
Revolving oar or 3, No. 4 propellers, slightly speed balances anti-twisted torque again, and aircraft flies to the left or to the right.2, No. 3 when doing elevating movement
Or 1, No. 4 propeller first accelerates to make propeller vertical with horizontal plane holding with pitch-control motor 200 again, fuselage 100 does elevating movement.
1, No. 2 or 3, No. 4 propellers first accelerate to make propeller vertical with horizontal plane holding with roll control motor 300 again when doing rolling movement,
Fuselage 100 does rolling movement.
So design will can move forward and backward with elevating movement or side-to-side movement separated with rolling movement stand alone as 4 it is logical
Road.Unmanned plane is set to do pitching and rolling movement when locus is static.
In addition, lateral adjustment 400 includes：First cingulum 410, two be respectively cooperating with first cingulum 410
First driven gear 420 and the first driving gear 430；
Two the first driven gears 420 are separately positioned on longitudinal adjusting mechanism 500, and the first cingulum 410 is arranged on two
The outside of first driven gear 420 and the first driving gear 430, and the output shaft of the first driving gear 430 and roll control motor 300
Drive connection.
The first cingulum 410 is driven to move it should be noted that being moved by roll control motor 300, the first cingulum 410 is transported here
Dynamic the first driven gear 420 for driving cingulum both ends moves, and the first driven gear 420 and longitudinal adjusting mechanism 500 here is logical
Cross connector 600 to be fixedly connected, rotated so as to drive longitudinal adjusting mechanism 500 to be rotated with the first driven gear 420.
In addition, longitudinal adjusting mechanism 500 is connected by connector 600 with fuselage 100, and the free end of connector 600
It is provided with the first driven gear 420；
The other end of connector 600 is connected with longitudinal adjusting mechanism 500.
Specifically, connector 600 here is the both sides for being spindle rotationally arranged in fuselage 100, and the first driven gear 420
Free end with connector 600 is is fixedly connected with, and the other end of connector 600 is fixedly connected with longitudinal adjusting mechanism 500, therefore
First cingulum 410 drives the first driven gear 420 to rotate, and the first driven gear 420 drives longitudinally adjust machine by connector 600
Structure 500 rotates.
In addition, longitudinal adjusting mechanism 500 includes：Support frame 510, the second cingulum 520, it is respectively cooperating with the second cingulum 520
Two the second driven gears 530 and the second driving gear 540；
Two the second driven gears 530 are arranged on the both ends of support frame 510, and the second driving gear 540 is arranged on support frame
510 stage casing, the second cingulum 520 are arranged on the outside of two the second driven gears 530 and the second driving gear 540；
And second driving gear 540 be connected with the output shaft of pitch-control motor 200.
It should be noted that pitch-control motor 200 is arranged on the centre position of support frame 510, the is driven by middle steering wheel
Two driving gears 540 rotate, the second cingulum 520 being at this moment arranged on outside the second driving gear 540 and the second driven gear 530
Rotate, drive the second driven gear 530 to rotate by the second cingulum 520, the second driven gear 530 is arranged on support frame 510
Both ends, the second driven gear 530 at the both ends of support frame 510 are solid with propeller braced wing regulation Dual-output shaft motor 700 respectively
Fixed connection, so as to drive axial direction of the propeller braced wing regulation Dual-output shaft motor 700 along its second driven gear 530 to turn
It is dynamic.
In addition, aircraft includes：Propeller braced wing adjusts Dual-output shaft motor 700, makes the aircraft by this structure
When doing elevating movement, wobble shaft not with motor overlapping of axles；
Second driven gear 530 is fixedly connected with propeller braced wing regulation Dual-output shaft motor 700 side.
Specifically, such four propeller braced wings regulation Dual-output shaft motor 700 then can flexibly by second from
Moving gear 530 drives its motion.
In addition, aircraft includes：For connecting the propeller braced wing 800 of propeller 900；
Two output shafts of propeller braced wing regulation Dual-output shaft motor 700 are connected with propeller braced wing 800.
It should be noted that two output shafts are connected with propeller braced wing 800, so as to be adjusted by propeller braced wing
Dual-output shaft motor 700 drives two output shaft rotations, so as to realize the edge of propeller braced wing 800 with two output shaft pivot joints
Its axial direction rotates.
In addition, the top of propeller braced wing 800 connects with the propeller 900 for providing climbing power to aircraft respectively
Connect.
It should be noted that propeller 900 is the power for providing course of new aircraft provided in an embodiment of the present invention power
Element, worked by propeller 900 and provide the lift risen for whole course of new aircraft.
In addition, propeller 900 includes：Motor 910 and blade 920；
Blade 920 is connected with motor 910, and motor 910 rotates blade 920, and blade 920 drives flight
Device rises or falls.
It should be noted that motor 910 here provides the power set of power for blade 920, by driving electricity
Machine 910 drives blade 920 to rotate, so as to complete a series of actions such as the rising of aircraft, decline, rotation, upset.
In addition, the lightening core 110 for mitigating flight gravity and resistance is provided with fuselage 100.
It should be noted that in order to improve flying speed and endurance, then by being provided with lightening core on fuselage 100
110, so as to realize the mitigation to aircraft weight so that flight resistance reduces, so that flying speed and follow-on mission time
Increase.
Second aspect, a kind of aerocraft system provided by the invention, including the course of new aircraft described in second aspect, are also wrapped
Include remote control equipment and/or earth station；
Remote control equipment is used to carry out flight control to course of new aircraft；
Earth station is used to carry out data interaction with course of new aircraft.
It should be noted that aerocraft system provided by the invention with above-mentioned course of new aircraft with all advantages,
It is and convenient to manipulate.And in order to ensure the stability of the flight of course of new aircraft, then 1, No. 3 propeller seat on board the aircraft
Gyroscope is arranged with, flight attitude can be fed back to remote control in time, orientation in-flight is detected at any time, so as to protect
Demonstrate,prove flight attitude so that keep propeller vertical when failure is saved oneself.
The course of new aircraft and aerocraft system of the present invention are illustrated above, still, the present invention is not limited to
Specific embodiment is stated, without departing from the scope of claim, various deformations or change can be carried out.The present invention
The various modifications being included within the scope of the claims and change.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, either which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
- A kind of 1. course of new aircraft, it is characterised in that including：Fuselage (100), pitch-control motor (200), roll control motor (300), horizontal stroke To governor motion (400) and two longitudinal adjusting mechanisms (500), four propeller braced wing regulation Dual-output shaft motors (700)；Two longitudinal adjusting mechanisms (500) are symmetrically arranged on the fuselage (100) both sides；The pitch-control motor (200) is arranged on the longitudinal adjusting mechanism (500), controls the longitudinal adjusting mechanism (500) Motion；The roll control motor (300) is arranged on the fuselage (100), and the roll control motor (300) passes through the lateral adjustments Mechanism (400) is connected with the longitudinal adjusting mechanism (500), and the lateral adjustment (400) controls the longitudinally adjust machine Structure (500) moves on the horizontal direction along the aircraft；Each propeller braced wing regulation Dual-output shaft motor (700) is arranged on the two of the longitudinal adjusting mechanism (500) At end.
- 2. course of new aircraft according to claim 1, it is characterised in that the lateral adjustment (400) includes：First Cingulum (410), two the first driven gears (420) being respectively cooperating with first cingulum (410) and the first driving gear (430)；Two first driven gears (420) are separately positioned on the longitudinal adjusting mechanism (500), first cingulum (410) outside of two first driven gears (420) and first driving gear (430), and described first are arranged on The output shaft of driving gear (430) and the roll control motor (300) is connected.
- 3. course of new aircraft according to claim 2, it is characterised in that the longitudinal adjusting mechanism (500) passes through connection Part (600) is connected with the fuselage (100), and the free end of the connector (600) is provided with first driven gear (420)；The other end of the connector (600) is connected with the longitudinal adjusting mechanism (500).
- 4. course of new aircraft according to claim 1, it is characterised in that the longitudinal adjusting mechanism (500) includes：Support Frame (510), the second cingulum (520), two the second driven gears (530) being respectively cooperating with second cingulum (520) and the Two driving gears (540)；Two second driven gears (530) are arranged on the both ends of support frame as described above (510), second driving gear (540) stage casing of support frame as described above (510) is arranged on, second cingulum (520) is arranged on two second driven gears (530) and second driving gear (540) outside；And second driving gear (540) is connected with the pitch-control motor (200) output shaft.
- 5. course of new aircraft according to claim 4, it is characterised in that four propeller braced wing regulation dual outputs Spindle motor (700), make the aircraft when doing elevating movement, wobble shaft not with motor overlapping of axles；Second driven gear (530) is fixedly connected with propeller braced wing regulation Dual-output shaft motor (700).
- 6. course of new aircraft according to claim 5, it is characterised in that the aircraft includes：For connecting propeller (900) propeller braced wing (800)；The double output shaft of the propeller braced wing regulation Dual-output shaft motor (700) passes with the propeller braced wing (800) Dynamic connection.
- 7. course of new aircraft according to claim 6, it is characterised in that the end of the propeller braced wing (800) with For providing the propeller (900) connection of climbing power to the aircraft.
- 8. course of new aircraft according to claim 7, it is characterised in that the propeller (900) includes：Motor And blade (920) (910)；The blade (920) is connected with the motor (910), and the motor (910) makes the blade (920) Rotate, the blade (920) drives the aircraft to rise or fall.
- 9. course of new aircraft according to claim 1, it is characterised in that be provided with the fuselage (100) for mitigating The lightening core of flight gravity and resistance (110).
- 10. a kind of aerocraft system, it is characterised in that including the course of new aircraft described in claim 1 to 9 any one, go back Including remote control equipment and/or earth station；The remote control equipment is used to carry out flight control to the course of new aircraft；The earth station is used to carry out data interaction with the course of new aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710837646.9A CN107444606B (en) | 2017-09-15 | 2017-09-15 | Novel aircraft and aircraft system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710837646.9A CN107444606B (en) | 2017-09-15 | 2017-09-15 | Novel aircraft and aircraft system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107444606A true CN107444606A (en) | 2017-12-08 |
| CN107444606B CN107444606B (en) | 2023-10-27 |
Family
ID=60496689
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710837646.9A Active CN107444606B (en) | 2017-09-15 | 2017-09-15 | Novel aircraft and aircraft system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107444606B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108706096A (en) * | 2018-04-02 | 2018-10-26 | 夏贵荣 | A kind of holder by adjusting the movement of rotor distance controlling quadrotor drone |
| WO2019119939A1 (en) * | 2017-12-22 | 2019-06-27 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN110077587A (en) * | 2019-04-30 | 2019-08-02 | 中北大学 | A kind of displacement aircraft and its control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010012285A2 (en) * | 2008-07-28 | 2010-02-04 | Fleck Fitness Concepts Gmbh | Combined air, water and road vehicle |
| US8376264B1 (en) * | 2009-08-24 | 2013-02-19 | Jianhui Hong | Rotor for a dual mode aircraft |
| CN106240790A (en) * | 2016-08-17 | 2016-12-21 | 深圳天鹰兄弟无人机创新有限公司 | A kind of multi-rotor aerocraft platform being easy to storage |
| CN207208450U (en) * | 2017-09-15 | 2018-04-10 | 汤新哲 | Course of new aircraft and aerocraft system |
-
2017
- 2017-09-15 CN CN201710837646.9A patent/CN107444606B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010012285A2 (en) * | 2008-07-28 | 2010-02-04 | Fleck Fitness Concepts Gmbh | Combined air, water and road vehicle |
| US8376264B1 (en) * | 2009-08-24 | 2013-02-19 | Jianhui Hong | Rotor for a dual mode aircraft |
| CN106240790A (en) * | 2016-08-17 | 2016-12-21 | 深圳天鹰兄弟无人机创新有限公司 | A kind of multi-rotor aerocraft platform being easy to storage |
| CN207208450U (en) * | 2017-09-15 | 2018-04-10 | 汤新哲 | Course of new aircraft and aerocraft system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019119939A1 (en) * | 2017-12-22 | 2019-06-27 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| CN108706096A (en) * | 2018-04-02 | 2018-10-26 | 夏贵荣 | A kind of holder by adjusting the movement of rotor distance controlling quadrotor drone |
| CN110077587A (en) * | 2019-04-30 | 2019-08-02 | 中北大学 | A kind of displacement aircraft and its control method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107444606B (en) | 2023-10-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| AU2018200729B2 (en) | Vertical takeoff and landing (VTOL) air vehicle | |
| US10144509B2 (en) | High performance VTOL aircraft | |
| CN106184739B (en) | Flying equipment capable of vertically taking off | |
| US10287011B2 (en) | Air vehicle | |
| US8733690B2 (en) | Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials | |
| US20190016459A1 (en) | Tri-Rotor Aircraft Capable of Vertical Takeoff and Landing and Transitioning to Forward Flight | |
| EP3087003B1 (en) | An unmanned aerial vehicle | |
| US20160244159A1 (en) | Controlled Take-Off And Flight System Using Thrust Differentials | |
| JP2019517412A (en) | Vertical take-off and landing winged aircraft with complementary angled rotors | |
| CN105711832B (en) | One kind is verted the long endurance combined type aircraft of three rotors | |
| CN106428548A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN104176247A (en) | Four-rotor unmanned aerial vehicle with engine for directly driving rotor | |
| US20180273168A1 (en) | Vertical takeoff and landing aircraft | |
| WO2016028358A2 (en) | High Performance VTOL Aircraft | |
| CN107444606A (en) | Course of new aircraft and aerocraft system | |
| JP2022059634A (en) | Drone with wings | |
| US6705905B1 (en) | Sea-land-sky craft | |
| CN207208450U (en) | Course of new aircraft and aerocraft system | |
| CN101525049B (en) | High-speed rotator type helicopter | |
| CN108639320A (en) | A kind of DCB Specimen unmanned helicopter | |
| CN205602092U (en) | Duct formula unmanned aerial vehicle | |
| CN208530839U (en) | A kind of DCB Specimen unmanned helicopter | |
| CN101590910B (en) | High-speed rotating helicopter | |
| CN218258694U (en) | Flying body | |
| WO2023152746A1 (en) | Aircraft and method of controlling aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |