CN105438464B - A kind of aircraft and its control method - Google Patents
A kind of aircraft and its control method Download PDFInfo
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- CN105438464B CN105438464B CN201410508883.7A CN201410508883A CN105438464B CN 105438464 B CN105438464 B CN 105438464B CN 201410508883 A CN201410508883 A CN 201410508883A CN 105438464 B CN105438464 B CN 105438464B
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Abstract
The invention belongs to field of flight vehicle design, and in particular to a kind of aircraft and control method.A kind of aircraft that the present invention is provided provides the design method of lift by sub- driver drives blade, and pneumatic efficiency is high.Blade, which can rotate around installation axle and can be realized along the hinge for being arranged on mid blade, to be folded, and the folding of many attitude can be realized after combination, and can be taken off in a folded configuration, can meet the requirement taken off vertically in small space.Control method proposed by the present invention can meet the control requirement to the flight attitude of aircraft proposed by the present invention.
Description
Technical field
The invention belongs to field of flight vehicle design, and in particular to a kind of aircraft and its control method.
Background technology
The current aircraft closest to the present invention includes two kinds：Autogyro and helicopter.Both aircraft are in height
It is different in terms of degree control, Heading control.
The rotor of autogyro is unpowered rotation, and rotor always influences autorotation rotating speed away from size variation, therefore according to
By always climbing or declining away from gyroplane can not be controlled to realize.The rotating speed of autorotating rotor is by disk angle of attack and with respect to speed of incoming flow
Obvious effect, therefore when height is controlled, variable rotor speed is changed by the rotor disk angle of attack is manipulated.Become in disk angle of attack
During change, fuselage attitude angle can also change, so as to cause the change of forward flight speed.In order to keep gyroplane it is stable climb or under
It is sliding, motor power is controlled while disk angle of attack is manipulated, influence of the forward flight speed change to rotor rotating speed is fallen in compensation.And navigate
To during control, autogyro also has the rudder similar with fixed-wing to manipulate, rotated certainly in addition to it can manipulate rotor
The wing realizes the steering of gyroplane jointly with the control of combining of rudder.
Helicopter be by manipulate rotor always away from height control is carried out, the always change away from size can cause rotor lift
Change, when increase rotor always away from when, lift increase, if the gravity phase of the component of lift in the vertical direction and depopulated helicopter
Deng then helicopter keeps present level or at the uniform velocity lifting, and otherwise helicopter accelerates or glided.With helicopter control rotor
Always away from realizing that it is different that height is controlled, the rotor of helicopter is engine driving constant revolution.
The content of the invention
The purpose of the present invention is：A kind of aircraft and its control method are provided, realize aircraft in the vertical of small space
Landing, the flexibility that increase aircraft is fought realizes that sub- driver drives blade provides the design method of lift, improves machinery and turns
Efficiency is changed, and realizes that arrangement solar panel causes aircraft cruising time to increase significantly on body, blade, adapts to modern
The requirement of war.
The technical scheme is that：A kind of aircraft, including body 1, blade mounting disc 2, blade 3, sub- driver 4,
Support meanss 5, main stabilization 6 and adjustment rudder face 7, the top of 2 fitting machine body of blade mounting disc 1 are co-axially mounted with body 1,
And can carry out gyration relative to body 1, blade 3 along blade mounting disc 2 it is circumferential it is uniform radially, while blade 3 can be around
Itself installation axle is rotated, each blade 3 can along the portion that is disposed therein hinge folding, support meanss 5 are installed on body lower end,
Main stabilization 6 is circumferentially distributed in along body on the downside of body, and adjustment rudder face 7 is fixed on each end of main stabilization 6, can be relative to master
Stabilization 6 enters horizontal deflection, and sub- driver 4 is opened up to being arranged in parallel on each blade along blade 3.
Further：Body 1, blade mounting disc 2, the surface of blade 3 are provided with solar panel, are that sub- driver 4 is carried
Energy supply amount.
A kind of flying vehicles control method, it is characterised in that：Comprise the steps of：
A：When aircraft is deposited in ground or surface ship, every group of blade 3 is folded according to unified direction, reduces it
Floor space；
B：When aircraft takes off with landing in limited place, blade 3 is kept to fold, by the established angle for adjusting blade 3
Degree, makes the driving force direction of every sub- driver 4 perpendicular to ground, provides lift by sub- driver, realization is taken off vertically and dropped
Fall；Aircraft blade 3 deploys after taking off, and makes the driving force direction and blade that every sub- driver 4 is produced with blade mounting disc 2
Plane of rotation is parallel, drives the rotation of blade 3 to obtain lift；
C：When aircraft takes off with dropping rudder in open area, deploy blade 3, by adjusting the setting angle of blade 3, make every
The driving force direction that individual sub- driver 4 is produced is parallel with the Plane of rotation of blade mounting disc 2 with blade 3；
D：When aircraft is in flat winged or hovering working condition, changes the deflection angle of adjustment rudder face 7, make body relative
Its rotating shaft is static；
E：When aircraft needs to change posture in the air, the angle of blade 3 is adjusted, sub- driver 4 is produced blade
The vertical component of the rotational plane of mounting disc 2, the posture that aircraft planning is turned over to each group changes the sub- driver 4 of plane, enters
Row is instantly increased the power for contributing to aircraft to deflect, and realizes the pose adjustment of aircraft.
Beneficial effect produced by the present invention：A kind of aircraft of the present invention and its control method, pass through sub- driver drives
Folding king bolt blade provides lift, is greatly improved mechanical switch efficiency.Blade is around the installation axle of its own simultaneously
Rotate so that aircraft can realize the VTOL in more narrow position, reduce requirement of the aircraft to operational environment,
It greatly strengthen the flexibility of aircraft operation.And heliotechnics, effective use of energy sources are used, and is not increased too much
Aircraft weight, on the basis of aircraft performance is not influenceed, realizes the long-time continuation of the journey of aircraft.
Brief description of the drawings
Fig. 1 is a kind of structure principle chart of aircraft of the invention；
Fig. 2 is a kind of a kind of folded state schematic diagram of aircraft of the invention；
Fig. 3 is that a kind of blade of aircraft of the invention folds takeoff condition schematic diagram；
Fig. 4 is a kind of blade deployed condition schematic diagram of aircraft of the invention；
Fig. 5 is verted view after a kind of blade expansion of aircraft of the invention；
Wherein, 1- bodies, 2- blade mounting discs, 3- blades, 4- drivers, 5- support meanss, the main stabilizations of 6- and
7- adjusts rudder face.
Embodiment
The present invention is described in further detail with reference to Figure of description, Fig. 1 and Fig. 5 is referred to.
A kind of scouting aircraft, including body 1, blade mounting disc 2, blade 3, sub- driver 4, support meanss 5, main peace
Determine face 6 and adjustment rudder face 7, body 1 is revolving body, and blade mounting disc 2 is arranged on the top of body 1, is co-axially mounted with body 1,
And can carry out gyration relative to body 1, blade 3 along blade mounting disc 2 it is circumferential it is uniform radially, while blade 3 can be around
Itself installation axle is rotated, each blade can along the portion that is disposed therein hinge folding, support meanss 5 are installed on body lower end,
Main stabilization 6 is circumferentially distributed in along body on the downside of body, and adjustment rudder face 7 is fixed on each end of main stabilization 6, can be relative to master
Stabilization 6 enters horizontal deflection, and sub- driver 4, on each blade 3, is arranged in parallel two-by-two along blade spanwise arrangement.Wherein blade 3 by
Power driving mechanism realizes that it is rotated around installation axle, and sub- driver 4 is that oar fans formula electric drive engine.
A kind of flying vehicles control method, it is characterised in that：Comprise the steps of：
A：When aircraft is deposited in ground or surface ship, by the way that every group of blade 3 is folded according to unified direction, subtract
Its small floor space, is shown in Fig. 2；
B：When aircraft takes off with landing in limited place, blade 3 is kept to fold, by adjusting wing setting angle degree,
Make the driving force direction of every sub- driver 4 perpendicular to ground, realization is taken off vertically and landed, and sees Fig. 3；After taking off, pass through control
The hinge of mid blade processed, deploys blade 3, sees Fig. 4；Blade expansion after, make blade 3 around its installation axle rotate so that blade by
Gradually vert and rotate, see Fig. 5, finally vert to state shown in Fig. 1.After the connection blade of blade 3 mounting disc 2 is rotated, sub- drive
The resistance that the function of dynamic device 4 is gradually become by the lift for providing full machine when overcoming the blade 3 to rotate, consumption power declines to a great extent；
C：When aircraft takes off with landing in open area, by controlling the hinge of mid blade, deploy blade 3, adjust
The whole setting angle of blade 3, makes the driving force direction and blade of every sub- generation of driver 4 with the Plane of rotation of blade mounting disc 2
It is substantially parallel, as shown in Figure 1；
D：When aircraft is in flat winged or hovering working condition, by rudder surface control system, change the inclined of adjustment rudder face 7
Gyration, makes body 1 static with respect to its rotating shaft；
E：When aircraft needs to change posture in the air, the angle of blade 3 is adjusted, sub- driver 4 is produced and oar
The thrust of the vertical component of the rotational plane of leaf mounting disc 2, the son drive of the posture transformation plane of aircraft planning is turned over to each group
Dynamic device 4 carries out being instantly increased the power for contributing to aircraft to deflect, and realizes pose adjustment (the similar gun shooting synchronization association of aircraft
Adjust device).
Claims (3)
1. a kind of aircraft, it is characterised in that：Including body [1], blade mounting disc [2], blade [3], sub- driver [4], branch
Support arrangement [5], main stabilization [6] and adjustment rudder face [7], blade mounting disc [2] is installed on body [1] top, with body [1]
It is co-axially mounted, and gyration can be carried out relative to body [1], blade [3] is circumferential uniform in radiation along blade mounting disc [2]
Shape, at the same blade [3] can around itself installation axle rotate, each blade [3] can along the portion that is disposed therein hinge folding, support
Device is installed on body [1] lower end, and main stabilization [6] is circumferentially distributed in along body on the downside of body [1], and adjustment rudder face [7] is fixed
In each main stabilization [6] end, horizontal deflection can be entered relative to main stabilization [6], sub- driver [4] is opened up to parallel cloth along blade
It is placed on each blade.
2. a kind of aircraft as required by claim 1, it is characterised in that：Body [1], blade mounting disc [2], blade [3] table
Face is provided with solar panel, is that sub- driver [4] provides energy.
3. a kind of flying vehicles control method, it is characterised in that：Comprise the steps of：
A：When aircraft is deposited in ground or surface ship, by the way that every group of blade [3] is folded according to unified direction, reduce
Aircraft floor space；
B：When aircraft takes off with landing in limited place, blade [3] is kept to fold, by adjusting blade [3] setting angle,
Make the driving force direction of every sub- driver [4] perpendicular to ground, realization is taken off vertically and landed, aircraft blade after taking off
[3] deploy, and rotated around blade [3] installation axle, driving force direction and blade that every sub- driver [4] produces is pacified with blade
The Plane of rotation of sabot [2] is parallel, and driving blade [3] rotates to obtain lift；
C：When aircraft takes off with landing in open area, deploy blade [3], adjust blade [3] setting angle, make every height
The driving force direction that driver [4] is produced is parallel with the Plane of rotation of blade mounting disc [2] with blade [3]；
D：When aircraft is in flat winged or hovering working condition, changes the deflection angle of adjustment rudder face [7], make body [1] phase
It is static to its rotating shaft；
E：When aircraft needs to change posture in the air, blade [3] angle is adjusted, sub- driver [4] is produced and oar
The vertical component of leaf mounting disc [2] rotational plane, the posture that aircraft planning is turned over to each group changes the sub- driver of plane
[4], carry out being instantly increased the power for contributing to aircraft to deflect, realize the pose adjustment of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508883.7A CN105438464B (en) | 2014-09-28 | 2014-09-28 | A kind of aircraft and its control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410508883.7A CN105438464B (en) | 2014-09-28 | 2014-09-28 | A kind of aircraft and its control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105438464A CN105438464A (en) | 2016-03-30 |
| CN105438464B true CN105438464B (en) | 2017-08-25 |
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ID=55549207
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410508883.7A Active CN105438464B (en) | 2014-09-28 | 2014-09-28 | A kind of aircraft and its control method |
Country Status (1)
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| CN (1) | CN105438464B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2967221C (en) * | 2016-05-13 | 2021-08-24 | Bell Helicopter Textron Inc. | Forward folding rotor blades |
| US10676183B2 (en) | 2016-05-13 | 2020-06-09 | Bell Helicopter Textron Inc. | Forward folding rotor blades |
| CN106444814B (en) * | 2016-10-28 | 2020-01-24 | 易瓦特科技股份公司 | Method and device for adjusting posture of unmanned aerial vehicle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4119810A1 (en) * | 1991-06-15 | 1992-12-17 | Stemme Gmbh & Co Kg | Aircraft propeller with foldable blades - has variable blade adjustment angle with link between outer linkage positions and propeller drive shaft |
| DE10209881A1 (en) * | 2002-03-06 | 2003-09-18 | Aloys Wobben | aircraft |
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| CA2888144C (en) * | 2012-10-19 | 2021-06-01 | Aeryon Labs Inc. | Hovering unmanned aerial vehicle |
| CN103863561B (en) * | 2014-02-19 | 2016-08-17 | 厦门大学 | A kind of wing folding VUAV |
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| Publication number | Publication date |
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| CN105438464A (en) | 2016-03-30 |
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