CN207141388U - Three-wing-surface unmanned vehicle - Google Patents
Three-wing-surface unmanned vehicle Download PDFInfo
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- CN207141388U CN207141388U CN201720816144.3U CN201720816144U CN207141388U CN 207141388 U CN207141388 U CN 207141388U CN 201720816144 U CN201720816144 U CN 201720816144U CN 207141388 U CN207141388 U CN 207141388U
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Abstract
The utility model 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
It the utility model is related 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.
Utility model content
The utility model provides a kind of Three-wing-surface unmanned vehicle, can reduce tilting wing aircraft and be verted in rotor
Difficulty is manipulated and controlled in transient, adds the resistance to overturning during verting.
The utility model 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 utility model, including：Body, be arranged on two of the body both sides it is solid
Determine main wing, and be arranged on the girder of two equal lengths below described two main wings；Two girders are along the body
Be arranged on longitudinally asymmetricly on the main wing of the body both sides；The front end of two girders passes through rotatable preposition
The canard that verts connects；The rear end of two girders is connected by empennage；One is symmetrically provided with the preposition canard that verts
To preposition propeller；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, added whole during verting
Body stability.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, drawings in the following description are
Some embodiments of the utility model, for those of ordinary skill in the art, do not paying the premise of creative labor
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation for Three-wing-surface unmanned vehicle that the utility model embodiment one provides；
Fig. 2 is the state under a kind of Three-wing-surface unmanned vehicle VTOL pattern that the utility model embodiment one provides
Schematic diagram；
Fig. 3 is a kind of state signal for Three-wing-surface unmanned vehicle transient process that the utility model embodiment one provides
Figure；
Fig. 4 is the state signal under the flat winged pattern of a kind of Three-wing-surface unmanned vehicle that the utility model embodiment one provides
Figure.
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
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the embodiment of the utility model is clearly and completely described, it is clear that is retouched
The embodiment stated is the utility model part of the embodiment, rather than whole embodiments.Based on the implementation in the utility model
Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, is belonged to
The scope of the utility model protection.
Fig. 1 is the structural representation for the Three-wing-surface unmanned vehicle that the utility model embodiment one provides, as shown in figure 1,
A kind of Three-wing-surface unmanned vehicle that the present embodiment provides includes：Body 1, main wing 2, the preposition canard 4 that verts, empennage 7, two root longs
Spend equal 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 state signal under a kind of Three-wing-surface unmanned vehicle VTOL pattern that the utility model embodiment one provides
Figure.
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 reality
A kind of view of the Three-wing-surface unmanned vehicle transient process provided with new embodiment one.
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 utility model embodiment 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 utility model embodiment one provides turns the transient process of vertical landing,
Its preposition canard 4 that verts, which verts to become to turn to take off vertically, turns the inverse process for equalling winged transient process, so as to complete hanging down for aircraft
Straight landing operation, here is omitted.
A kind of Three-wing-surface unmanned vehicle that the utility model embodiment one provides it is flat fly and VTOL state under, by
The Three-wing-surface aerodynamic configuration that the preposition canard 4 that verts, fixed main wing 2 and empennage 7 are formed is connected by girder 3, makes full machine structure strong
Degree and rigidity are 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；
Under transition state, due to the preposition preposition propeller 5 for verting canard 4 while connecting both ends, synchronizer can be played a part of, shown
Improve the sync rates of the preposition propeller 5 of bilateral with writing, add the resistance to overturning during verting；Three-surface configuration and spiral shell
The mutual cooperation of oar is revolved, 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 only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should
Understand：It can still modify to the technical scheme described in foregoing embodiments, either to which part or whole
Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly
The scope of each embodiment technical scheme of type.
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 master are quiet 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 |
|---|---|---|---|
| CN201720816144.3U CN207141388U (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720816144.3U CN207141388U (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
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| Publication Number | Publication Date |
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| CN207141388U true CN207141388U (en) | 2018-03-27 |
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| CN201720816144.3U Active CN207141388U (en) | 2017-07-07 | 2017-07-07 | Three-wing-surface unmanned vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499505A (en) * | 2017-07-07 | 2017-12-22 | 北京航空航天大学 | Three-wing-surface unmanned vehicle |
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2017
- 2017-07-07 CN CN201720816144.3U patent/CN207141388U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499505A (en) * | 2017-07-07 | 2017-12-22 | 北京航空航天大学 | Three-wing-surface unmanned vehicle |
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