CN108516091A - A kind of novel changable aerodynamic arrangement aircraft - Google Patents
A kind of novel changable aerodynamic arrangement aircraft Download PDFInfo
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- CN108516091A CN108516091A CN201810308602.1A CN201810308602A CN108516091A CN 108516091 A CN108516091 A CN 108516091A CN 201810308602 A CN201810308602 A CN 201810308602A CN 108516091 A CN108516091 A CN 108516091A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
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Abstract
The present invention relates to a kind of novel changable aerodynamic arrangement aircrafts, belong to field of aerospace technology, including all-wing aircraft fuselage (5), canard (2), canard actuator (3), canard accommodating groove (1), canard jack stem (4) and sleeve (10), aileron (6), wing flap (7), storage channel opening radome fairing bottom sheet (8) and upper piece (9)；The fuselage main body is single all-wing aircraft, all-wing aircraft leading edge has one to be parallel to tangential canard accommodating groove (1), canard (2) can be accommodated in canard accommodating groove, canard (2) is connect by canard actuator (3) with canard jack stem (4) and sleeve (10), canard jack is connect in storage trench bottom with fuselage, and storing notch has the radome fairing bottom sheet (8) that can be opened and closed and upper piece (9).The present invention is the advantages that in conjunction with the advantages of Flying-wing and canard configuration, being provided simultaneously with stealthy radar, high subsonic speed lift resistance ratio and short take-off and landing, excellent low speed maneuverability on same type aircraft.
Description
Technical field
The present invention relates to a kind of novel changable aerodynamic arrangement aircrafts, belong to field of aerospace technology.
Background technology
Flying-wing's aircraft has stronger radar stealth ability, and since all-wing aircraft aspect ratio is high, space is big in machine, carries
Oil mass is big, has higher subsonic lift-drag ratio and voyage load performance.However due to lack on pitch channel control the arm of force compared with
Long control surface, maneuverability is poor on the aircraft pitch channel of Flying-wing, big angles-of-attack ability wretched insufficiency, agility compared with
Difference, landing rate request are higher.
And canard configuration airplane is exactly the opposite, the presence of canard is unfavorable for stealth and (destroys -20 fighter planes using canard configuration
In order to which stealth has to do some special designings), the voyage load performance of canard configuration airplane is compared under subsonic
Flying-wing does not have advantage.But canard layout have it is quiet it is unstable, manipulations is sensitive, the big angle of attack is functional, landing speed is low, cunning
Run apart from it is short the features such as.
Existing aircraft finally often has to due to just having determined that overall aerodynamic arrangement at the beginning of design
Choice is made between different, conflicting flight performance requirement.For example, the unmanned military aircraft of countries in the world today,
Often flying wing type is selected to be laid out to pursue longer subsonic flight time, voyage load performance and radar stealth ability, from
And it is forced to sacrifice mobility and landing range index.This, which becomes existing military unmanned air vehicle, can only execute reconnaissance mission or low-intensity
Air-to-ground attack task, and can not carry out antiaircraft compacting so control of the air contention task the reason of one of.In addition flying wing type unmanned plane
Longer landing distance is but also upper warship operates more difficult, existing unique Shipborne UAV using Flying-wing --- the U.S.
X-47B needs the huge ejector for relying on the super aircraft carrier in the U.S. that could realize and take off on warship that this is for not autonomous ejector skill
It obviously can not be achieved for other countries of art.
Contradiction between both aerodynamic arrangements is similar to the contradiction of the lower wing geometry of normal arrangement：Height exhibition string
The wing smaller than, angle of sweep better handling characteristic when can bring low-speed operations, and the big wing in low aspect ratio, angle of sweep is then
It is more suitable for prolonged supersonic flight.In six the seventies America and Soviet Union aerospace designs teacher of last century in order to solve wing geometric form
Shape design contradiction and use variable swept back wing technology, even wing is connect by moveable hinge with fuselage, pass through hydraulic device
The rotation that wing does low-angle using hinge as axis is manipulated, is realized after awing adjusting wing according to flying speed situation at any time
Sweep angle is to obtain the flying quality optimized under each speed interval.This is also a kind of form that geometry can be changed aerodynamic configuration, and
And this technology is very ripe at present and has been applied on the external famous aircraft model of more moneys, as F-14 fighter planes, B-1 are bombed
Machine, figure -22M bombers and Tu-160 bomber, etc..It can be seen that awing being changed by hydraulic pressure or other machinery device
The aerodynamic configuration for becoming aircraft has proven to feasible at present, has sufficient technical foundation.(reference《Flight mechanics》32nd
Rolled up for the 2nd phase《Swing-wing technology develops and prospect》)
By mechanically deform change aerodynamic configuration in terms of design can be found in CN201110320155.X,
The patents such as CN201510197632.6, CN201611123391.1, but these patented technologies are the change of wing geometry respectively
The deformation of rotor installation site and the mechanically deform of quadrotor drone, have been carried out or have carried at present in shape, helicopter
The geometry gone out can be changed Design of Aerodynamic Configuration, be an attempt to solve the other performance contradiction point in Aerodynamic Configuration of Aireraft scheme, and go back
It there are no and be directed to Flying-wing's variable aerodynamic arrangement's solution contradictory with canard configuration.
Invention content
It is an object of the invention to solve to use radar stealth, high subsonic speed liter caused by Flying-wing in the prior art
Hinder than the advantages of with using the contradiction that can not be got both the advantages of agility, good takeoff and landing performance caused by canard configuration, provide
A kind of aircraft of novel changable aerodynamic arrangement makes it have both the advantages of above two is laid out.
The present invention specifically uses following technical scheme to solve above-mentioned technical problem：
A kind of aircraft that can change aerodynamic arrangement by mechanically deform under state of flight is provided, it can be in landing state
Or the other occasions for improving mobility is needed to use canard configuration, it is tied for a long time, in the state of cruise over long distances by machinery
Structure is deformed into Flying-wing, to merge these conflicting flight characteristicses on same type aircraft.
A kind of novel changable aerodynamic arrangement aircraft, including all-wing aircraft fuselage (5), canard (2), canard actuator (3), canard are received
Receive slot (1), canard jack stem (4) and sleeve (10), aileron (6), wing flap (7), storage channel opening radome fairing bottom sheet (8)
With upper piece (9)；The fuselage main body is single all-wing aircraft, and all-wing aircraft leading edge has one to be parallel to tangential canard accommodating groove (1), and canard is received
Canard (2) can be accommodated in slot by receiving, and canard (2) passes through canard actuator (3) and canard jack stem (4) and sleeve (10) company
It connects, canard jack is connect in storage trench bottom with fuselage, and storing notch has the radome fairing bottom sheet (8) that can be opened and closed and upper
Piece (9).
As a preferred technical solution of the present invention：Novel changable aerodynamic arrangement aircraft is in landing state and needs
Under the flight progress for showing stronger mobility and agility, can by canard (2) stretch out canard accommodating groove (1), by canard (2),
Aileron (6), wing flap (7) collective effect adjust aspect, show as canard configuration.
As a preferred technical solution of the present invention：Novel changable aerodynamic arrangement aircraft, can under cruising condition
Canard (2) is recovered in canard accommodating groove (1), aspect is adjusted by aileron (2), wing flap (7) collective effect, shows as flying
The wing is laid out.
As a preferred technical solution of the present invention：Novel changable aerodynamic arrangement aircraft awing passes through machinery
Structure realizes rapid translating between canard configuration and Flying-wing, and uses movable radome fairing bottom sheet (8) and upper piece (9) holding
Aerodynamic configuration is smooth before and after conversion.
As a preferred technical solution of the present invention：The canard of its folding and unfolding canard (2) of variable aerodynamic arrangement's aircraft
Jack is made of stem (4), sleeve (10), spring (11), bracing wire (13), spool (14), servomotor (12)；Stem
(4) it is sleeved in sleeve (10), can be translated along length sleeve direction, spring (11) is located at sleeve (10) inner leg (4) bottom and set
Between cylinder (10) end, translation of the stem (4) in sleeve (10) will lead to the contraction or stretching, extension of spring (11)；Bracing wire (13) one
End is connected to stem (4) bottom, and the other end is wrapped on spool (14), and spool (14) is driven by servomotor (12) to be rotated；
Canard (2) is mounted on stem (4) front end by canard actuator (3).
As a preferred technical solution of the present invention：Canard (2) is being stretched out canard storage by the canard jack
When slot (1), servomotor (12) manipulates spool (14) and discharges bracing wire (13), releases stem (4) by spring (11) elastic force
Sleeve (10), to which canard (2) is released canard accommodating groove (1).
As a preferred technical solution of the present invention：Canard (2) is being recovered to canard receipts by the canard jack
When slot (1) of receiving is interior, servomotor (12) manipulates spool (14) and withdraws bracing wire (13), and spring (11) elastic force is overcome to retract stem
Sleeve (10), to which canard (2) is retracted canard accommodating groove (1).
As a preferred technical solution of the present invention：Described its movable radome fairing of variable aerodynamic arrangement's aircraft is divided into bottom sheet
(8) and upper piece (9) it, is opened up along all-wing aircraft to being divided into three sections, left wing's section and right flank section are opened in folding and unfolding canard so that canard (2) can be with
Without stopping by storing channel opening, closed in flight course so that all-wing aircraft leading edge keeps smooth；Stage casing is in canard configuration mould
It is kept it turning under formula so that canard jack is stretched out from accommodating groove open center.
As a preferred technical solution of the present invention：Described its movable radome fairing of variable aerodynamic arrangement's aircraft passes through light-duty
Hinge connect with storage channel opening, and when closure is locked by incoming air dynamic pressure, and when unlatching is made every effort to overcome using electromagnet generation magnetic
Take air hydrodynamic unlatching.
As a preferred technical solution of the present invention：Outside its all-wing aircraft fuselage (5) rear of variable aerodynamic arrangement's aircraft
Side is equipped with aileron (6), and inside is equipped with wing flap (7)；Wherein aileron (6) controllable institute under canard configuration and Flying-wing's pattern
The roll attitude for stating type aircraft, by causing left and right wing panel asymmetry resistance also to can control yaw-position；Wing flap (7) only exists
It is disposed under canard configuration pattern, for further decreasing the permitted minimum landing speed of aircraft, shortening landing distance.
The present invention generates following advantageous effect using above-mentioned technical proposal：
The advantages of combining Flying-wing and canard configuration on same type aircraft, it is provided simultaneously with radar stealth, high subsonic speed
The advantages that lift resistance ratio and short take-off and landing, excellent low speed maneuverability.Compared with existing aircraft, this type aircraft is due in each flight
All without apparent performance short slab under speed interval, there is radar stealth ability under all-wing aircraft cruise mode, therefore using more
Flexibly, viability higher；Originally it needs canard configuration is respectively adopted, the amphitypy aircraft of Flying-wing can make completing for task
It is completed using the aircraft of the invention technology with a type, reduces the model quantity for needing to equip, so as to reduce cost and subtract
Few logistic work amount.
Description of the drawings
Fig. 1 is structural schematic diagram of the embodiment under canard configuration pattern.
Fig. 2 is structural schematic diagram of the embodiment under Flying-wing's pattern.
Fig. 3 is structural schematic diagram of the embodiment canard jack under Flying-wing's pattern.
Fig. 4 is structural schematic diagram of the embodiment canard jack under canard configuration pattern.
Wherein Symbol explanation：1- canard accommodating grooves, 2- canards, 3- canard actuator, 4- canard jack stems, 5- fly
Wing fuselage, 6- ailerons, 7- wing flaps, 8- store channel opening radome fairing bottom sheet, and 9- stores channel opening radome fairing upper piece, and 10- canards are received
Laying mechanism sleeve, 11- springs, 12- servomotors, 13- bracing wires, 14- spools.
Specific implementation mode
As depicted in figs. 1 and 2, the present invention provides a kind of novel changable aerodynamic arrangement aircraft, including all-wing aircraft fuselage (5), duck
The wing (2), canard actuator (3), canard accommodating groove (1), canard jack stem (4) and sleeve (10), aileron (6), wing flap
(7), storage channel opening radome fairing bottom sheet (8) and upper piece (9)；The fuselage main body is single all-wing aircraft, and all-wing aircraft leading edge has one parallel
In that can accommodate canard (2) in tangential canard accommodating groove (1), canard accommodating groove, canard (2) passes through canard actuator (3) and duck
Wing jack stem (4) and sleeve (10) connection, canard jack are connect in storage trench bottom with fuselage, store notch
There are the radome fairing bottom sheet (8) that can be opened and closed and upper piece (9).
In landing state and under needing to show the flight progress of stronger mobility and agility, canard (2) can be stretched out
Canard accommodating groove (1) adjusts aspect by canard (2), aileron (6), wing flap (7) collective effect, shows as canard configuration.
Under cruising condition, canard (2) can be recovered in canard accommodating groove (1), aircraft is adjusted by aileron (2), wing flap (7) collective effect
Posture shows as Flying-wing.Rapid translating is awing realized between canard configuration and Flying-wing by mechanical structure,
And convert the smooth of front and back aerodynamic configuration using movable radome fairing bottom sheet (8) and upper piece (9) holding.The jack of canard is one
Scalable, length-adjustable mechanical cantilever beam has weight light enough and sufficiently small volume.
As shown in Figure 3 and Figure 4, a kind of technical solution of jack is piston structure, has stem 4 and sleeve 10.It is right
In light-duty unmanned aerial vehicle, spring 11 and 13 realization of bracing wire can be used to act --- in this scheme, sleeve 10 and all-wing aircraft
1 bottom of accommodating groove of 5 front of fuselage is connected, and stem 4 is sleeved in sleeve 10, the one end of stem 4 in sleeve 10 and 10 bottom of sleeve
It is provided with spring 11 between portion, while bracing wire 13 is drawn at this end of stem 4,13 other end of bracing wire is wrapped on spool 14, spool
14 connect with the servomotor 12 of control jack；If stem 4 and sleeve 10 are designed to simple circular section, need to add
Fill toggle；One end that stem 4 forward extends out sleeve 10 is hinged with canard 2, and canard actuator 3 can be set up directly at hinge,
It may also be arranged at all-wing aircraft fuselage 5, connect with canard 2 by additional bracing wire, before the center of gravity of airplane during Reducing distortion
It moves.Under canard form, the spring 11 in jack sleeve 10 is in relaxed state, since spring 11 occupies inside sleeve 10
Space, stem 4 forward extends out sleeve 10, and most of length is exposed outside, and the canard 2 for being located at 4 end of stem stretches out accommodating groove 1
Except can participate in the control of aircraft with free deflection；By canard Morphological Transitions be all-wing aircraft form when, the servo-electric of jack
Machine 12 starts, and driving spool 14 is tensioned the bracing wire 13 for being connected to 4 rear portion of stem, and the elastic force of spring 11 is overcome to be withdrawn into stem 4
Within sleeve 10, the canard 2 positioned at 4 forward terminal of stem is also just withdrawn within accommodating groove 1, so that aircraft is become classical and is flown
Wing configuration；By all-wing aircraft Morphological Transitions be canard form when, discharge the bracing wire 13 of tensioning, so that compressed spring 11 is released energy extensive
It is multiple that stem 4 and the canard installed thereon 2 are popped up into accommodating groove 1 together to former long, by canard 2 be exposed to again in front of incoming it
In.Above scheme is simple in structure, lighter in weight, cost are relatively low, but due to the restriction of spring guy structure, and control force is limited, can
It is limited by property, it is suitable for light-duty, ultra light aircraft.
For the heavier aircraft of bigger, the technical solution of hydraulic actuation device can be used.Canard 2 is mounted on a root
It is fixed in accommodating groove 1, on telescopic sliding rail, the movement of sliding rail is controlled by hydraulic actuator；Hydraulic pressure can also directly be used
Platform of the action barrel as installation canard 2, action barrel itself needs certain structural strength under this design, and need to install torsion
The arm of force.
The opening of accommodating groove 1 of canard 2 is awing directly facing incoming, destroys wingflying aircraft in the leading edge of all-wing aircraft fuselage 5
The slickness of 5 surface profile of body increases flight resistance.For the negative effect for avoiding accommodating groove 1 from being open, being installed in open edge can
With the radome fairing bottom sheet 8 of free-open-close and upper piece 9, it is mounted on respectively by light-duty hinge on the lower top edge that accommodating groove 1 is open；
It is opened up along all-wing aircraft to radome fairing is divided into three sections, i.e. left wing's section, stage casing and right flank section.Under all-wing aircraft pattern cruising condition, all sections
Radome fairing is turned off, and covers all the opening of accommodating groove 1 so that the leading edge of all-wing aircraft has the surface of smooth low-resistance；In canard
Pattern transition status between all-wing aircraft, all sections of radome fairing are opened so that canard 2 can unhinderedly come in and go out accommodating groove
1；Under canard pattern, left wing's section, the right flank section of radome fairing are closed, and stage casing keeps opening wide so that the mechanical cantilever of installation canard 2
Beam is able to stretch out and be maintained at except accommodating groove 1.
Kinds of schemes equally may be used in the radome fairing bottom sheet 8 and upper piece 9 flowing mode of making that accommodating groove 1 is open.For light
Small electrical is arranged in type, simple unmanned aerial vehicle at radome fairing bottom sheet 8, upper piece 9 hinges being connect with 1 open edge of accommodating groove
Magnet, radome fairing bottom sheet 8, upper piece 9 be closed when, since upper and lower two panels radome fairing respectively connects with other side in end
It touches, is substantially had a generally triangular shape on the sectional view of wing, therefore due to the effect of front incoming air dynamic pressure under state of flight, it can
To be locked in closed position naturally；When need to open radome fairing bottom sheet 8, upper piece 9 when, be the small-sized electromagnet at connects hinge
It is powered, the magnetic attraction of radome fairing bottom sheet 8, upper piece 9 upper cores is inhaled out by electromagnet and is fixed on open position；It needs
Close radome fairing bottom sheet 8, upper piece 9 when the small-sized electromagnet at hinge need to only power off, you can so that it is moved in front incoming air
It is voluntarily closed under the action of pressure.For heavy, complicated aircraft, compression can be used in radome fairing bottom sheet 8, upper piece 9 open-close ways
The technical solution of air start, servo motor start or hydraulic control.
In addition to retractable canard 2,5 rear of aircraft all-wing aircraft fuselage there also is provided wing flap 7 and aileron 6.Wherein 7, wing flap
On the inside of 5 rear of all-wing aircraft fuselage, the wing flap using simple-type wing flap or other forms can be selected according to the volume size of aircraft；By
It will produce a larger nose-down pitching moment when wing flap 7 is disposed, wing flap 7 can not be used under Flying-wing, only in canard configuration mould
2 corresponding deflection of canard overcomes the nose-down pitching moment that wing flap 7 generates, 7 side of wing flap that can dispose, permit for further decreasing aircraft under formula
Perhaps minimum landing speed, shortening landing distance.Aileron 6 is located on the outside of 5 rear of all-wing aircraft fuselage, in Flying-wing and canard configuration
It can be used under pattern, for controlling posture of the aircraft on wobble shaft；For heavier aircraft, using including upper and lower two
The divided ailerons of control surface, the deflection control rolling maneuver in the same direction simultaneously of upper and lower two control surface, while reverse deflection is used as and slows down
Plate uses, and individually side aileron is deflected as flap to generate the steering force on yaw axis, adjustment partially in arranged on left and right sides aileron
Navigation attitude state.
Therefore, in novel changable aerodynamic arrangement provided by the invention aircraft, all-wing aircraft cloth can be combined on same type aircraft
Office and the advantages of canard configuration is provided simultaneously with radar stealth, high subsonic speed lift resistance ratio and short take-off and landing, excellent low speed maneuverability etc.
Advantage.Compared with existing aircraft, this type aircraft due under each flying speed section all without apparent performance short slab,
There is radar stealth ability under all-wing aircraft cruise mode, therefore use more flexible, viability higher；Originally it needs that duck is respectively adopted
Formula is laid out, the amphitypy aircraft of Flying-wing can be completed using a type using the aircraft of the invention technology completing for task,
Reduce the model quantity for needing to equip, so as to reduce cost and reduce logistic work amount.
Claims (10)
1. a kind of novel changable aerodynamic arrangement aircraft, including the storage of all-wing aircraft fuselage (5), canard (2), canard actuator (3), canard
Slot (1), canard jack stem (4) and sleeve (10), aileron (6), wing flap (7), storage channel opening radome fairing bottom sheet (8) and
Upper piece (9)；The fuselage main body is single all-wing aircraft, and all-wing aircraft leading edge has one to be parallel to tangential canard accommodating groove (1), canard storage
Canard (2) can be accommodated in slot, canard (2) is connected by canard actuator (3) and canard jack stem (4) and sleeve (10)
It connects, canard jack is connect in storage trench bottom with fuselage, and storing notch has the radome fairing bottom sheet (8) that can be opened and closed and upper
Piece (9).
2. a kind of novel changable aerodynamic arrangement aircraft according to claim 1, it is characterised in that：The novel changable is pneumatic
Airplane can stretch out canard (2) in landing state and under needing to show the flight progress of stronger mobility and agility
Canard accommodating groove (1) adjusts aspect by canard (2), aileron (6), wing flap (7) collective effect, shows as canard configuration.
3. a kind of novel changable aerodynamic arrangement aircraft according to claim 1, it is characterised in that：The novel changable is pneumatic
Canard (2) can be recovered under cruising condition in canard accommodating groove (1) by airplane, be made jointly by aileron (2), wing flap (7)
With adjustment aspect, Flying-wing is shown as.
4. a kind of novel changable aerodynamic arrangement aircraft according to claim 1, it is characterised in that：The novel changable is pneumatic
Airplane awing realizes rapid translating by mechanical structure between canard configuration and Flying-wing, and using movable whole
It flows cover bottom sheet (8) and the smooth of front and back aerodynamic configuration is converted in upper piece (9) holding.
5. a kind of novel changable aerodynamic arrangement aircraft according to claim 1, it is characterised in that：The variable aerodynamic arrangement
The canard jack of its folding and unfolding canard (2) of aircraft by stem (4), sleeve (10), spring (11), bracing wire (13), spool (14),
Servomotor (12) forms；Stem (4) is sleeved in sleeve (10), can be translated along length sleeve direction, and spring (11) is located at set
Between cylinder (10) inner leg (4) bottom and sleeve (10) end, translation of the stem (4) in sleeve (10) will lead to spring (11)
Contraction or stretching, extension；Bracing wire (13) one end is connected to stem (4) bottom, and the other end is wrapped on spool (14), spool (14) by
Servomotor (12) driving rotation；Canard (2) is mounted on stem (4) front end by canard actuator (3).
6. canard jack according to claim 1, it is characterised in that：The canard jack is by canard (2)
When stretching out canard accommodating groove (1), servomotor (12) manipulates spool (14) and discharges bracing wire (13), will by spring (11) elastic force
Stem (4) releases sleeve (10), to which canard (2) is released canard accommodating groove (1).
7. canard jack according to claim 1, it is characterised in that：The canard jack is by canard (2)
Be recovered to canard accommodating groove (1) it is interior when, servomotor (12) manipulate spool (14) withdraw bracing wire (13), overcome spring (11) bullet
Stem is retracted sleeve (10) by power, to which canard (2) is retracted canard accommodating groove (1).
8. variable aerodynamic arrangement's aircraft according to claim 1, it is characterised in that：Variable aerodynamic arrangement's aircraft its can
Dynamic radome fairing is divided into bottom sheet (8) and upper piece (9), is opened up along all-wing aircraft to being divided into three sections, left wing's section and right flank section are opened in folding and unfolding canard
It opens so that canard (2) can be closed in flight course without stopping by storing channel opening so that all-wing aircraft leading edge keeps smooth；
Stage casing is kept it turning under canard configuration pattern so that canard jack is stretched out from accommodating groove open center.
9. variable aerodynamic arrangement's aircraft according to claim 1, it is characterised in that：Variable aerodynamic arrangement's aircraft its can
Dynamic radome fairing connect by light-duty hinge with storage channel opening, and when closure is locked by incoming air dynamic pressure, and when unlatching uses electric
Magnet generates magnetic attraction and air hydrodynamic is overcome to open.
10. variable aerodynamic arrangement's aircraft according to claim 1, it is characterised in that：Variable aerodynamic arrangement's aircraft its
Aileron (6) is equipped on the outside of all-wing aircraft fuselage (5) rear, inside is equipped with wing flap (7)；Wherein aileron (6) is in canard configuration and all-wing aircraft cloth
The roll attitude that can control the type aircraft under office's pattern, by causing left and right wing panel asymmetry resistance also to can control yaw
Posture；Wing flap (7) is only disposed under canard configuration pattern, for further decrease the permitted minimum landing speed of aircraft,
Shorten landing distance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810308602.1A CN108516091B (en) | 2018-04-02 | 2018-04-02 | Novel variable aerodynamic layout aircraft |
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|---|---|---|---|
| CN201810308602.1A CN108516091B (en) | 2018-04-02 | 2018-04-02 | Novel variable aerodynamic layout aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2758366A1 (en) * | 2018-11-02 | 2020-05-05 | Torres Martinez M | AIRCRAFT WITH ENERGY GENERATION AND ACCUMULATION (Machine-translation by Google Translate, not legally binding) |
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| CN102267557A (en) * | 2011-04-27 | 2011-12-07 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN202279235U (en) * | 2011-09-06 | 2012-06-20 | 成都飞机设计研究所 | Variant canard tailless aerodynamic configuration |
| CN203020540U (en) * | 2012-12-19 | 2013-06-26 | 天津全华时代航天科技发展有限公司 | Folding unmanned aerial vehicle |
| CN204937478U (en) * | 2015-08-13 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Supersonic Cruise Aircraft with scalable canard |
| CN205273837U (en) * | 2015-11-23 | 2016-06-01 | 南京航空航天大学 | Variable aerodynamic layout's aircraft |
| CN106193688A (en) * | 2016-08-27 | 2016-12-07 | 季虎 | A kind of animal husbandry open air stable breeding Automatic-rain device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2758366A1 (en) * | 2018-11-02 | 2020-05-05 | Torres Martinez M | AIRCRAFT WITH ENERGY GENERATION AND ACCUMULATION (Machine-translation by Google Translate, not legally binding) |
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