CN105438464A - Aircraft and control method thereof - Google Patents
Aircraft and control method thereof Download PDFInfo
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- CN105438464A CN105438464A CN201410508883.7A CN201410508883A CN105438464A CN 105438464 A CN105438464 A CN 105438464A CN 201410508883 A CN201410508883 A CN 201410508883A CN 105438464 A CN105438464 A CN 105438464A
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Abstract
Belonging to the field of aircraft design, the invention in particular relates to an aircraft and a control method. According to the design mode of the aircraft provided by the invention, sub-drivers drive blades to provide lift force, and the aerodynamic efficiency is high. The blades can rotate around an installation shaft and can realize folding along hinges arranged at the middle parts of the blades, after combination, folding in various attitudes can be realized, and the aircraft can take off under a folding state, thus meeting the requirement of vertical takeoff in a narrow and small space. The control method put forward by the method can meet the control requirements for the flight attitude of the aircraft provided by the invention.
Description
Technical field
The invention belongs to field of flight vehicle design, be specifically related to a kind of aircraft and control method thereof.
Background technology
Current closest aircraft of the present invention comprises two kinds: autogyro and helicopter.These two kinds of aircraft are at Altitude control, and the aspects such as Heading control are different.
The rotor of autogyro is unpowered rotation, and rotor is total affects autorotation rotating speed apart from size variation, therefore relies on total distance can not control cyclogyro and realizes climbing or declining.The rotating speed of autorotating rotor is subject to the obvious effect of disk angle of attack and relative speed of incoming flow, therefore when Altitude control, relies on the manipulation rotor disk angle of attack to change gyroplane rotate speed.In disk angle of attack change procedure, fuselage attitude angle also can change, thus causes the change of forward flight speed.In order to keep, cyclogyro is stable to climb or glides, while manipulation disk angle of attack, control engine thrust, compensates the impact of forward flight speed change on gyroplane rotate speed.And during Heading control, autogyro, except handling except rotor, also has the yaw rudder similar with fixed-wing to handle, the combination of autorotating rotor and yaw rudder controls jointly to achieve turning to of cyclogyro.
Helicopter is that the total distance by handling rotor carries out Altitude control, total change apart from size can cause the change of rotor lift, when the total distance of increasing rotor, lift increases, if the component of lift in the vertical direction is equal with the gravity of depopulated helicopter, then helicopter keeps present level or is at the uniform velocity elevated, otherwise helicopter accelerates to rise or glide.Total different apart from realizing Altitude control from helicopter control rotor, the rotor of helicopter is engine drive constant revolution.
Summary of the invention
The object of the invention is: a kind of aircraft and control method thereof are provided, realize the vertical takeoff and landing of aircraft at small space, increase the alerting ability that aircraft is fought, realize the design that sub-driver drives blade provides lift, improve mechanical switch efficiency, and realize on body, blade, arrange that solar panel makes aircraft greatly increase cruise duration, adapt to the requirement of modern war.
Technical scheme of the present invention is: a kind of aircraft, comprise body 1, blade subpanel 2, blade 3, sub-actuator 4, bracing or strutting arrangement 5, main stabilator 6 and adjustment rudder face 7, blade subpanel 2 fitting machine body 1 top, coaxially install with body 1, and gyroscopic movement can be carried out relative to body 1, blade 3 is radially uniform along blade subpanel 2 circumference, blade 3 can rotate around the installation shaft of self simultaneously, each blade 3 can along the hinge folding in portion disposed therein, bracing or strutting arrangement 5 is installed on body lower end, main stabilator 6 is distributed on the downside of body along body circumference, adjustment rudder face 7 is fixed on each main stabilator 6 end, can deflect relative to main stabilator 6, sub-actuator 4 is opened up to being arranged in parallel on each blade along blade 3.
Further: body 1, blade subpanel 2, blade 3 surface are provided with solar panel, for sub-actuator 4 provides energy.
A kind of flying vehicles control method, is characterized in that: comprise following steps:
A: when aircraft is deposited in ground or surface craft, folds often organizing blade 3 according to unified direction, reduces it and takes up an area space;
B: when aircraft takes off with when landing in limited place, keeps blade 3 to fold, and by adjusting the setting angle of blade 3, making the propulsive effort direction of every sub-actuator 4 perpendicular to ground, providing lift by sub-actuator, realize taking off vertically and landing; After taking off, aircraft blade 3 launches, and the propulsive effort direction that every sub-actuator 4 is produced is parallel with the plane of rotation of blade subpanel 2 with blade, drives the rotation of blade 3 to obtain lift;
C: when aircraft takes off with when falling rudder in open area, launches blade 3, and by adjustment blade 3 setting angle, the propulsive effort direction that every sub-actuator 4 is produced is parallel with the plane of rotation of blade subpanel 2 with blade 3;
D: when aircraft be in flat fly or hover mode time, change the deflection angle of adjustment rudder face 7, make body static relative to its rotating shaft;
E: when aircraft needs to change attitude aloft, adjustment blade 3 angle, make sub-actuator 4 can produce the vertical component of blade subpanel 2 rotational plane, each group is turned over to the sub-actuator 4 of the attitude transformation plane of aircraft planning, carry out the power that instantaneous increase contributes to aircraft deflection, realize the pose adjustment of aircraft.
The beneficial effect that the present invention produces: a kind of aircraft of the present invention and control method thereof, provide lift by the folding king bolt blade of sub-driver drives, can greatly improve mechanical switch efficiency.Blade rotates around the installation shaft of himself simultaneously, makes aircraft can be implemented in the vertical takeoff and landing of comparatively narrow position, reduces the requirement of aircraft to operational environment, greatly strengthen the alerting ability that aircraft is fought.And adopt heliotechnics, effective use of energy sources, and increase aircraft weight with exceeding, do not affecting on the basis of aircraft performance, achieve the long-time continuation of the journey of aircraft.
Accompanying drawing explanation
Fig. 1 is the structure principle chart of a kind of aircraft of the present invention;
Fig. 2 is a kind of folded state schematic diagram of a kind of aircraft of the present invention;
Fig. 3 is that the blade of a kind of aircraft of the present invention folds takeoff condition schematic diagram;
Fig. 4 is the blade deployed condition schematic diagram of a kind of aircraft of the present invention;
Fig. 5 is view of verting after the blade of a kind of aircraft of the present invention launches;
Wherein, 1-body, the subpanel of 2-blade, 3-blade, 4-actuator, 5-bracing or strutting arrangement, the main stabilator of 6-and 7-adjust rudder face.
Detailed description of the invention
Below in conjunction with Figure of description, the present invention is described in further detail, refers to Fig. 1 and Fig. 5.
A kind of scouting aircraft, comprise body 1, blade subpanel 2, blade 3, sub-actuator 4, bracing or strutting arrangement 5, main stabilator 6 and adjustment rudder face 7, body 1 is gyro-rotor, blade subpanel 2 is arranged on body 1 top, coaxially install with body 1, and gyroscopic movement can be carried out relative to body 1, blade 3 is radially uniform along blade subpanel 2 circumference, blade 3 can rotate around the installation shaft of self simultaneously, each blade can along the hinge folding in portion disposed therein, bracing or strutting arrangement 5 is installed on body lower end, main stabilator 6 is distributed on the downside of body along body circumference, adjustment rudder face 7 is fixed on each main stabilator 6 end, can deflect relative to main stabilator 6, sub-actuator 4 along blade spanwise arrangement on each blade 3, be arranged in parallel between two.Wherein blade 3 realizes it by power driving mechanism and rotates around installation shaft, and sub-actuator 4 is oar fan formula electric drive driving engine.
A kind of flying vehicles control method, is characterized in that: comprise following steps:
A: when aircraft is deposited in ground or surface craft, by folding often organizing blade 3 according to unified direction, reducing it and taking up an area space, seeing Fig. 2;
B: when aircraft takes off with when landing in limited place, keeps blade 3 to fold, and by adjustment blade angle degree, makes the propulsive effort direction of every sub-actuator 4 perpendicular to ground, realizes taking off vertically and landing, see Fig. 3; After taking off, by controlling the hinge of mid blade, launching blade 3, seeing Fig. 4; Blade makes blade 3 rotate around its installation shaft, makes blade vert gradually and rotate, see Fig. 5, finally vert to state shown in Fig. 1 after launching.Blade 3 is communicated with after blade subpanel 2 rotates, and the function of sub-actuator 4 is by the resistance providing the lift of full machine to gradually become to overcome when blade 3 rotates, and consumed power declines to a great extent;
C: when aircraft takes off with when landing in open area, by controlling the hinge of mid blade, launch blade 3, adjustment blade 3 setting angle, the propulsive effort direction that every sub-actuator 4 is produced and blade substantially parallel with the plane of rotation of blade subpanel 2, as shown in Figure 1;
D: when aircraft be in flat fly or hover mode time, by rudder surface control system, change the deflection angle of adjustment rudder face 7, make body 1 its rotating shaft relative static;
E: when aircraft needs to change attitude aloft, adjustment blade 3 angle, make sub-actuator 4 can produce the thrust of the component vertical with blade subpanel 2 rotational plane, the attitude turning over aircraft planning to each group changes the sub-actuator 4 of plane and carries out the power that instantaneous increase contributes to aircraft deflection, realizes the pose adjustment (similar gun shooting synchronization coordinator) of aircraft.
Claims (3)
1. an aircraft, it is characterized in that: comprise body [1], blade subpanel [2], blade [3], sub-actuator [4], bracing or strutting arrangement [5], main stabilator [6] and adjustment rudder face [7], blade subpanel [2] is installed on body [1] top, coaxially install with body [1], and gyroscopic movement can be carried out relative to body [1], blade [3] is radially uniform along blade subpanel [2] circumference, blade [3] can rotate around the installation shaft of self simultaneously, each blade [3] can along the hinge folding in portion disposed therein, bracing or strutting arrangement is installed on body [1] lower end, main stabilator [6] is distributed in body [1] downside along body circumference, each main stabilator [6] end is fixed in adjustment rudder face [7], can deflect relative to main stabilator [6], sub-actuator [4] is along blade exhibition to being arranged in parallel on each blade.
2. a kind of aircraft required by claim 1, is characterized in that: body [1], blade subpanel [2], blade [3] surface are provided with solar panel, for sub-actuator [4] provides energy.
3. a flying vehicles control method, is characterized in that: comprise following steps:
A: when aircraft is deposited in ground or surface craft, folds according to unified direction by often organizing blade [3], reduces it and take up an area space;
B: when aircraft takes off with when landing in limited place, blade [3] is kept to fold, by adjustment blade [3] setting angle, make the propulsive effort direction of every sub-actuator [4] perpendicular to ground, realization is taken off vertically and landing, after taking off, aircraft blade [3] launches, and rotate around blade [3] installation shaft, the propulsive effort direction that every sub-actuator [4] is produced is parallel with the plane of rotation of blade subpanel [2] with blade, drives blade [3] to rotate and obtains lift;
C: when aircraft takes off with when falling rudder in open area, launches blade [3], adjustment blade [3] setting angle, and the propulsive effort direction that every sub-actuator [4] is produced is parallel with the plane of rotation of blade subpanel [2] with blade [3];
D: when aircraft be in flat fly or hover mode time, change the deflection angle of adjustment rudder face [7], its rotating shaft is static relatively to make body [1];
E: when aircraft needs to change attitude aloft, adjustment blade [3] angle, make sub-actuator [4] that the component vertical with blade subpanel [2] rotational plane can be produced, each group is turned over to the sub-actuator [4] of the attitude transformation plane of aircraft planning, carry out the power that instantaneous increase contributes to aircraft deflection, 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 |
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| 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 |
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| CN105438464A true CN105438464A (en) | 2016-03-30 |
| CN105438464B CN105438464B (en) | 2017-08-25 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106444814A (en) * | 2016-10-28 | 2017-02-22 | 易瓦特科技股份公司 | A method and apparatus for adjusting attitudes of an unmanned aerial vehicle (UAV) |
| EP3243745A1 (en) * | 2016-05-13 | 2017-11-15 | Bell Helicopter Textron Inc. | Forward folding rotor blades |
| US10556680B2 (en) | 2016-05-13 | 2020-02-11 | Bell Helicopter Textron Inc. | Distributed propulsion system |
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| 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 |
| CN1639500A (en) * | 2002-03-06 | 2005-07-13 | 艾劳埃斯·乌本 | 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 |
| WO2014059549A1 (en) * | 2012-10-19 | 2014-04-24 | Aeryon Labs Inc | Hovering unmanned aerial vehicle |
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
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2014
- 2014-09-28 CN CN201410508883.7A patent/CN105438464B/en active Active
Patent Citations (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 |
| CN1639500A (en) * | 2002-03-06 | 2005-07-13 | 艾劳埃斯·乌本 | 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 |
| WO2014059549A1 (en) * | 2012-10-19 | 2014-04-24 | Aeryon Labs Inc | Hovering unmanned aerial vehicle |
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3243745A1 (en) * | 2016-05-13 | 2017-11-15 | Bell Helicopter Textron Inc. | Forward folding rotor blades |
| US10556680B2 (en) | 2016-05-13 | 2020-02-11 | Bell Helicopter Textron Inc. | Distributed propulsion system |
| US10676183B2 (en) | 2016-05-13 | 2020-06-09 | Bell Helicopter Textron Inc. | Forward folding rotor blades |
| US10730624B2 (en) | 2016-05-13 | 2020-08-04 | Bell Helicopter Textron Inc. | Modular fuselage sections for vertical take off and landing distributed airframe aircraft |
| US10737786B2 (en) | 2016-05-13 | 2020-08-11 | Bell Helicopter Textron Inc. | Distributed propulsion system for vertical take off and landing closed wing aircraft |
| US10960978B2 (en) | 2016-05-13 | 2021-03-30 | Textron Innovations Inc. | Vertical take off and landing closed wing aircraft |
| US11603203B2 (en) | 2016-05-13 | 2023-03-14 | Textron Innovations Inc. | Distributed propulsion system |
| US11613355B2 (en) | 2016-05-13 | 2023-03-28 | Textron Innovations Inc. | Distributed propulsion system for vertical take off and landing closed wing aircraft |
| US11679877B2 (en) | 2016-05-13 | 2023-06-20 | Textron Innovations Inc. | Vertical take off and landing closed wing aircraft |
| CN106444814A (en) * | 2016-10-28 | 2017-02-22 | 易瓦特科技股份公司 | A method and apparatus for adjusting attitudes of an unmanned aerial vehicle (UAV) |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN105438464B (en) | 2017-08-25 |
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