CN107499505A - Three-wing-surface unmanned vehicle - Google Patents
Three-wing-surface unmanned vehicle Download PDFInfo
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- CN107499505A CN107499505A CN201710549390.1A CN201710549390A CN107499505A CN 107499505 A CN107499505 A CN 107499505A CN 201710549390 A CN201710549390 A CN 201710549390A CN 107499505 A CN107499505 A CN 107499505A
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- 230000003068 static effect Effects 0.000 claims abstract description 32
- 241000272517 Anseriformes Species 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 abstract description 13
- 230000008569 process Effects 0.000 abstract description 13
- 230000001052 transient effect Effects 0.000 abstract description 10
- 238000005516 engineering process Methods 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
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- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000011825 aerospace material Substances 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
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- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
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- 235000013399 edible fruits Nutrition 0.000 description 1
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- 230000002349 favourable effect Effects 0.000 description 1
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of Three-wing-surface unmanned vehicle.The aircraft includes：Body, two fixed main wings for being arranged on the body both sides, and it is arranged on the girder of two equal lengths below described two main wings；Two girders are arranged on the main wing of the body both sides along the longitudinally asymmetric of the body；The front end of two girders is connected by the rotatable preposition canard that verts；The rear end of two girders is connected by empennage；A pair of preposition propellers are symmetrically provided with the preposition canard that verts；Two girders, which are located on the part after the main wing, is symmetrically arranged with a pair of main static ribbon oars.Tilting wing aircraft can be reduced difficulty is manipulated and controlled in rotor verts transient process, add the resistance to overturning during verting.
Description
Technical field
The present embodiments relate to vehicle technology, more particularly to a kind of Three-wing-surface unmanned vehicle.
Background technology
Tilting wing aircraft is a kind of course of new aircraft that helicopter and fixed wing aircraft feature combine together, is both had
The ability of pure helicopter VTOL and the ability of hovering, the again high speed cruise flight with turboprop aircraft.
Tilting wing aircraft has three kinds of offline mode：Helicopter mode, fixed wing aircraft pattern and the transition mode that verts, its wing
Place is provided with the rotor that can carry out pitch motion, the state of flight of aircraft is adjusted by rotor deflection, when the axis of propeller
During in level, just one pulling force forward of aircraft is given；When propeller axis be in it is vertical when, then to aircraft provide one upwards
Lift；The process switched between the two state is the transition mode that verts.
But the existing wing of tilting wing aircraft has rotor again, aerodynamic characteristic is more multiple in rotor verts transient process
It is miscellaneous, there is dynamic analysis, the rotor/wing coupling technical barrier such as dynamic loading and stability, deposited in its airplane design structure
It is being short of, while there is also certain difficulty on manipulating and controlling.
The content of the invention
The present invention provides a kind of Three-wing-surface unmanned vehicle, can reduce tilting wing aircraft and was verted in rotor and be tided over
Difficulty is manipulated and controlled in journey, adds the resistance to overturning during verting.
The present invention provides a kind of Three-wing-surface unmanned vehicle, including：
Body, two fixed main wings for being arranged on the body both sides, and be arranged on below described two main wings two
The girder of root equal length；
Two girders are arranged on the main wing of the body both sides along the longitudinally asymmetric of the body；
The front end of two girders is connected by the rotatable preposition canard that verts；
The rear end of two girders is connected by empennage；
A pair of preposition propellers are symmetrically provided with the preposition canard that verts；
Two girders, which are located on the part after the main wing, is symmetrically arranged with a pair of main static ribbon oars.
Alternatively, a kind of Three-wing-surface unmanned vehicle, in addition to：
At least one pair of auxiliary static ribbon oar, at least one pair of described auxiliary static ribbon oar are arranged on two girders
On.
Alternatively, at least one pair of described static ribbon oar and the main static ribbon oar evenly spaced setting from front to back
On two girders.
Alternatively, the empennage is tailplane or vee tail.
Alternatively, the main wing is the straight wing, swept-back wing or dalta wing.
Three-wing-surface unmanned vehicle provided by the invention, including：Body, two fixed masters for being arranged on the body both sides
The wing, and it is arranged on the girder of two equal lengths below described two main wings；Two girders are indulged along the body
To being symmetrically disposed on the main wing of the body both sides；Preposition verted by rotatable the front end of two girders
Canard connects；The rear end of two girders is connected by empennage；Before a pair being symmetrically provided with the preposition canard that verts
Put propeller；Two girders, which are located on the part after the main wing, is symmetrically arranged with a pair of main static ribbon oars.Can
Reduce tilting wing aircraft and difficulty is manipulated and controlled in rotor verts transient process, add overall steady during verting
It is qualitative.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are this hairs
Some bright embodiments, for those of ordinary skill in the art, without having to pay creative labor, can be with
Other accompanying drawings are obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation for Three-wing-surface unmanned vehicle that the embodiment of the present invention one provides；
Fig. 2 is the state signal under a kind of Three-wing-surface unmanned vehicle VTOL pattern that the embodiment of the present invention one provides
Figure；
Fig. 3 is a kind of view for Three-wing-surface unmanned vehicle transient process that the embodiment of the present invention one provides；
Fig. 4 is the view under the flat winged pattern of a kind of Three-wing-surface unmanned vehicle that the embodiment of the present invention one provides.
Description of reference numerals：
1：Body；2：Main wing；3：Girder；4：The preposition canard that verts；5：Preposition propeller；6：Main static ribbon oar；7：Tail
The wing.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
Part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Fig. 1 is the structural representation for the Three-wing-surface unmanned vehicle that the embodiment of the present invention one provides, as shown in figure 1, this reality
Applying a kind of Three-wing-surface unmanned vehicle of example offer includes：Body 1, main wing 2, the preposition canard 4 that verts, empennage 7, two root long degree phases
Deng girder 3, a pair of preposition propellers 5 and a pair of main static ribbon oars 6.
Main wing 2 is arranged on the both sides of body 1, and two girders 3 are arranged on two lower sections of main wings 2, and two girders 3 are along the body
1 longitudinally asymmetric is arranged on the main wing 2 of the both sides of body 1, and the front ends of two girders 3 passes through rotatable preposition
The canard 4 that verts is connected, and the rear end of two girders 3 is connected by empennage 7, is symmetrically provided with the preposition canard 4 that verts rotatable
Preposition propeller 5, two girders 3, which are located on the part after the main wing 2, is symmetrically arranged with main static ribbon oar 6.
Alternatively, the framework of body 1 can be mainly made up of aluminum frame, aluminum reinforcing frame, aluminum stringer, and fuselage skin can use
Carbon fibre material, enhancing fuselage bears the ability of load while reducing weight.Control box, battery, motor are installed in body 1
Deng device.
Alternatively, the cross section of body 1 is circle, because in the case of the cross-sectional area identical of body 1, circular cross section
Girth it is minimum, in other words in the case of the volume identical of body 1, circular cross section has the surface area of minimum, thus selects
Cross section of the circular cross section as the present embodiment aircraft body so that body 1 has minimum frictional resistance.But such as
Fruit when not allowing the cross section for selecting circular cross section as body 1, can also select other shapes because some specific conditions
Section the shape of the cross section of body 1 is not defined as its cross section, the present embodiment.
Main wing 2 be used for aircraft is flat fly during for aircraft provides lift, main wing 2 is fixes master in the present embodiment
The wing, i.e. main wing 2 are non-rotatable, and main wing 2 is symmetrically disposed on body 1 along its longitudinal axis of body 1.Main wing 2 can be straight
The structure types such as the wing, swept-back wing, dalta wing, the present embodiment are not defined to the structure of main wing 2.
Alternatively, main wing 2 is hinged on the middle part of body 1, and rib can be bonded by high intensity aviation foam with carbon fiber board,
Appearance covering d type, covering can also be equally made of carbon fibre material.
The longitudinal axis of body 1 of the lower section of main wing 2 along aircraft is symmetrically arranged with the girder 3 of two equal lengths,
It can be attached between main wing 2 and girder 3 by modes such as bolt, welding or connectors.Girder 3 can use high-strength
Degree, lightweight aerospace material are made, such as aluminium alloy or titanium alloy.
The front end of two girders 3 is connected by the rotatable preposition canard 4 that verts, and the preposition canard 4 that verts is by servo driving
Longitudinal axis rotates, and verting for 0-90 degree can be achieved.Preposition propeller 5 be arranged on it is preposition vert on canard 4, in the preposition canard that verts
4 along its rotary shaft rotated when, rotary motion that preposition propeller 5 can also synchronize with the preposition canard 4 that verts.
Two girders 3 are located on the part after main wing 2 is symmetrically provided with a pair of main static spiral shells along the longitudinal axis of body 1
Revolve oar 6.Main static ribbon oar 6 is used for the more rotor configurations of the formation rule of preposition propeller 5 with plumbness, is hung down for aircraft
The lift enhancing of straight landing process and posture are kept.In the ideal case, main static ribbon oar 6 even can provide foot with the short time
Enough lift, it is ensured that preposition propeller 5 can be realized under non-power state to vert, so as to reduce the liter in transient process of verting
Fluctuation.
Alternatively, at least one pair of can also be symmetrically arranged on two girders 3 along the longitudinal axis of body 1 and aids in static spiral shell
Oar (not marked in figure) is revolved, auxiliary static ribbon oar is used to further increase lift of the aircraft when taking off vertically, this implementation
Example is not defined to auxiliary static ribbon oar quantity and position.For example, a pair of auxiliary static ribbon oars of increase are vertically rising
Depression of order section forms six rotor modes, increases by two pairs of auxiliary static ribbon oars and forms eight rotor modes in the VTOL stage.Six
During rotor mode, auxiliary static ribbon oar can be arranged on the preposition rear portion of propeller 5, the front portion of main wing 2, can also be arranged on master
The rear portion of the wing 2, the front portion of empennage 7.Or auxiliary static ribbon oar can also be arranged on the preposition rear portion of propeller 5, machine gravity
Front portion.In eight rotor modes, a pair of auxiliary static ribbon oars can be arranged on the preposition rear portion of propeller 5, before main wing 2
Portion, another pair auxiliary static ribbon oar can be arranged on the rear portion of main wing 2, the front portion of empennage 7.In the VTOL stage, even if
Preposition propeller 5 does not provide continuous driving force in transient process, can also be tieed up by main static ribbon oar and auxiliary static ribbon oar
Hold flight attitude.
Alternatively, empennage 7 is tailplane or vee tail.Tailplane is mainly used in keeping aircraft in-flight
The flight attitude of stability and control aircraft.Vee tail has the function of vertical fin and horizontal tail concurrently simultaneously, can play longitudinal direction and boat simultaneously
To stabilization, when both sides rudder face deflects to equidirectional, the effect of lifting rudder；Opposite, when being deflected to different directions,
Direction rudder action is then played, therefore V empennage big-elevation controllabilitys are more preferable.
When a kind of Three-wing-surface unmanned vehicle that embodiment one provides carries out VTOL operation, its state such as Fig. 2 institutes
Show, Fig. 2 is the view under a kind of Three-wing-surface unmanned vehicle VTOL pattern that the embodiment of the present invention one provides.
When a kind of Three-wing-surface unmanned vehicle that embodiment one provides carries out VTOL, the aerofoil of the preposition canard 4 that verts
Perpendicular to ground, be advantageous to reduce the vertical resistance of full machine.And preposition propeller 5 is parallel to the ground, the main static spiral shell with level
Rotation oar 6 provides lift vertically upward together, and driving aircraft completes VTOL action.After taking off, preposition inclined by controlling
Turn the rotating speed of canard 4 and main static ribbon oar 6, when the gravity of its caused lift and aircraft is reached balance, you can realize
Hovering.
In addition, when aircraft needs to be come back and bowed, by controlling preposition propeller 5 and main static ribbon oar 6
Rotating speed so that lift before and after body 1 is different, so as to produce nose-up pitching moment or nose-down pitching moment, realizes the pitching of aircraft
Motion.
When the aircraft that embodiment one provides carry out it is vertical turn it is flat fly over cross when, its state is as shown in figure 3, Fig. 3 is this hair
A kind of view for Three-wing-surface unmanned vehicle transient process that bright embodiment one provides.
Embodiment one provide a kind of Three-wing-surface unmanned vehicle complete take off vertically after, it is preposition vert canard 4 by
Servo driving longitudinal axis rotates, and verting for 0-90 degree is done step-by-step, and preposition propeller 5 provides upwardly and forwardly simultaneously during this
Pulling force, now preposition propeller 5 be in vector advanced state, it is possible to achieve thruster vector control, complete it is vertical turn it is flat fly or
The flat transient process for flying brake and turning vertical landing of person, it is ensured that make low speed, big angle of attack maneuvering flight and control vane in aircraft
The additional manipulation torque that is there is provided during a few near failures in face using thrust vectoring controls aircraft motor-driven.Due to the preposition canard 4 that verts
The preposition propeller 5 at both ends is connected simultaneously, can be played a part of synchronizer, be considerably enhanced the preposition propeller 5 of bilateral
Sync rates, add the resistance to overturning during verting.
When a kind of Three-wing-surface unmanned vehicle that embodiment one provides enters flat winged pattern, its state is as shown in figure 4, figure
4 be the view under the flat winged pattern of a kind of Three-wing-surface unmanned vehicle that the embodiment of the present invention one provides.
When the preposition canard 4 that verts completes 90 degree after verting, the aerofoil of the preposition canard 4 that verts is parallel with the aerofoil of empennage 7.
Under this state, preposition propeller 5 flies pulling force before only providing, under flat winged state, when aircraft reaches certain flying speed
When, main static ribbon oar 6 can be closed, only relies on the lift of main wing 2 to maintain the flight attitude of aircraft.Now, it is preposition to incline
Turn canard 4 and form favourable Coupled with Flow with main wing 2, be advantageous to reduce full machine resistance.
In addition, when aircraft is needed to the left or during flight to the right, can be by controlling preposition 4 liang of the canard that verts of aircraft
The rotating speed of the preposition propeller 5 of side so that two propellers produce different size of pulling force, form deflection torque, so as to
Realize the yawing rotation of control aircraft.
Similarly, in the flat winged state of aircraft that the embodiment of the present invention one provides turns the transient process of vertical landing, before it
Put the canard 4 that verts and vert to become to turn to take off vertically and turn the inverse process for equalling winged transient process, so as to complete the vertical of aircraft
Land acts, and here is omitted.
A kind of Three-wing-surface unmanned vehicle that the embodiment of the present invention one provides is under flat winged and VTOL state, by preposition
The Three-wing-surface aerodynamic configuration that canard 4, fixed main wing 2 and empennage 7 are formed that verts is connected by girder 3, make full machine structural strength and
Rigidity is more preferable；It is preposition to vert canard 4 and empennage 7 coordinates, it can preferably improve full machine longitudinal direction and horizontal lateral aerodynamic stability；Transition
Under state, due to the preposition preposition propeller 5 for verting canard 4 while connecting both ends, synchronizer can be played a part of, significantly
The sync rates of the preposition propeller 5 of bilateral are improved, add the resistance to overturning during verting；Three-surface configuration and propeller
Mutual cooperation, can effectively take into account the pneumatic requirement of long endurance horizontal flight and VTOL.
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 (5)
- A kind of 1. Three-wing-surface unmanned vehicle, it is characterised in that including：Body, two fixations for being arranged on the body both sides Main wing, and it is arranged on the girder of two equal lengths below described two main wings；Two girders are arranged on the main wing of the body both sides along the longitudinally asymmetric of the body；The front end of two girders is connected by the rotatable preposition canard that verts；The rear end of two girders is connected by empennage；A pair of preposition propellers are symmetrically provided with the preposition canard that verts；Two girders, which are located on the part after the main wing, is symmetrically arranged with a pair of main static ribbon oars.
- 2. aircraft according to claim 1, it is characterised in that also include：At least one pair of auxiliary static ribbon oar, it is described At least one pair of auxiliary static ribbon oar is arranged on two girders.
- 3. aircraft according to claim 2, it is characterised in that at least one pair of described main auxiliary propeller and the main static state Propeller is evenly spaced from front to back to be arranged on two girders.
- 4. according to the aircraft described in claim any one of 1-3, it is characterised in that the empennage is tailplane or V-type tail The wing.
- 5. according to the aircraft described in claim any one of 1-3, it is characterised in that the main wing be the straight wing, swept-back wing or Dalta wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710549390.1A CN107499505A (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710549390.1A CN107499505A (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107499505A true CN107499505A (en) | 2017-12-22 |
Family
ID=60679550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710549390.1A Pending CN107499505A (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107499505A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750113A (en) * | 2018-06-29 | 2018-11-06 | 西安航空学院 | A kind of annular wing unmanned vehicle |
| WO2023225819A1 (en) * | 2022-05-23 | 2023-11-30 | 深圳市闪至科技有限公司 | Aircraft, aircraft control method and device, and computer-readable storage medium |
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| WO2023225819A1 (en) * | 2022-05-23 | 2023-11-30 | 深圳市闪至科技有限公司 | Aircraft, aircraft control method and device, and computer-readable storage medium |
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