CN205524934U

CN205524934U - Aircraft

Info

Publication number: CN205524934U
Application number: CN201620221615.1U
Authority: CN
Inventors: 王; 王一
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-03-22
Filing date: 2016-03-22
Publication date: 2016-08-31
Anticipated expiration: 2026-03-22

Abstract

The utility model discloses an aircraft, including the fuselage, set up in the rotor device of fuselage front end, set up in the first wing of fuselage one side and the second wing of opposite side. Wherein, have first round hole on the first wing, have the second round hole on the second wing. Aircraft is still including setting up first screw in first round hole, setting up the second screw in the second round hole and control actuating mechanism first, the second screw.

Description

A kind of aircraft

Technical field

This utility model relates to aviation field, particularly relates to a kind of aircraft.

Background technology

UAV is called for short " unmanned plane ", is to utilize radio robot and the programme-control dress provided for oneself Put the most manned aircraft of manipulation.Without driving cabin on machine, but automatic pilot, presetting apparatus are installed Deng equipment.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar, it is tracked, Location, remote control, remote measurement and Digital Transmission.Generally, unmanned plane may be used for performing battlefield investigation, injuring The military missions such as assessment, target guide, and as carrier aircraft platform for taking photo by plane in the air, atmospheric sampling, The non-military task such as aerial mapping.

It is said that in general, existing unmanned plane can be divided into fixed-wing unmanned plane straight with unmanned according to flying method The machine of liter.Compared with depopulated helicopter, fixed-wing unmanned plane during flying speed is high and voyage is longer.But, Gu If determining wing unmanned plane to use VTOL or the mode of hovering, then exist and be difficult to control asking of fuselage attitude Topic.

Utility model content

To this end, this utility model provides a kind of new aircraft scheme, effectively solve above at least one Individual problem.

According to an aspect of the present utility model, it is provided that a kind of aircraft, including fuselage, it is arranged at fuselage The rotor driver of front end, it is arranged at the first wing of fuselage side and the second wing of opposite side.Wherein, There is on first wing the first circular hole, the second wing has the second circular hole.Aircraft also includes being arranged at The first propeller in first circular hole, the second propeller being arranged in the second circular hole and control first, the The drive mechanism of two propellers.

Alternatively, according in aircraft of the present utility model, drive mechanism is suitable to the flight at aircraft When speed is not up to threshold value, control the first propeller and the rotating speed of the second propeller and pitch.At aircraft Flight speed when reaching threshold value, drive mechanism closes the first propeller and the second propeller.

Alternatively, according in aircraft of the present utility model, the first circular hole is relative with described second circular hole Symmetrical in described fuselage.The trailing edge of the first wing is provided with the first flaperon, described second wing Trailing edge is provided with the second flaperon.Trousers it is provided with on rotor driver.Rotor driver has feathering Mechanism, in order to regulate the flight attitude of described aircraft.Fuselage is body of revolution.

Alternatively, according in aircraft of the present utility model, the first wing and the second wing are sweepback The wing.

Alternatively, also include being hingedly connected to fuselage and being symmetrical in fuselage according to aircraft of the present utility model First tail structure of plane of symmetry layout and the second tail structure.Wherein, at the first tail structure and second Tail structure is when closure state turns to reverse V-shaped open mode, and the first tail structure, the second afterbody are tied The wing tip of structure, the wing tip of the first wing and the second wing is in same plane.

Alternatively, according in aircraft of the present utility model, the first tail structure includes being articulated with fuselage The first rod member and the first coccygeal vertebra portion that is arranged on the first rod member.Second tail structure includes being articulated with machine Second rod member of body and the second coccygeal vertebra portion being arranged on the second rod member.At the first tail structure and the second tail When portion's structure is in closure state, first coccygeal vertebra portion and second coccygeal vertebra portion one caudal vertebra of composition.First afterbody Structure also includes the first vertical tail being arranged in described first coccygeal vertebra portion.Second tail structure also includes It is arranged on the second vertical tail in described second coccygeal vertebra portion.At the first tail structure and the second tail structure When being in closure state, the first vertical tail and the second vertical tail form upper and lower twin vertical fin configuration.

Alternatively, according in aircraft of the present utility model, the wing tip of the first wing is provided with the first Fall frame, and the wing tip of the second wing is provided with the second undercarriage.Caudal vertebra has cavity, and described fuselage afterbody is also It is provided with the 3rd undercarriage being placed in this cavity.

Aircraft of the present utility model is disposed with circular hole and the propeller being arranged in circular hole on double-vane.This Sample, aircraft of the present utility model can also be when VTOL or hovering, by arrange on wing Fuselage is done by the main rotor of propeller balance front fuselage by anti-twisted moment and the balance strong wind of fuselage Disturb, to keep stablizing of fuselage attitude.Further, when flight horizontal velocity is not up to threshold value, on wing The roll attitude of fuselage can be controlled, to avoid uncontrolled rolling to occur by the propeller arranged. It addition, the non-aircraft of this utility model is upper and lower by the first propeller and the second propeller are arranged on wing Circular hole between aerofoil (is i.e. embedded in wing), extra flight resistance will not be increased.Further, The first tail structure and the second afterbody being articulated with fuselage can also be included according to aircraft of the present utility model Structure.When aircraft horizontal flight, the first tail structure and the second tail structure are in closure state (class It is similar to the afterbody of usual fixed wing airplane).When aircraft needs VTOL, the first tail structure and Two tail structures rotate into reverse V-shaped open mode, jointly aircraft can be carried out ten with the wing tip of the two-shipper wing Word supports.So, aircraft of the present utility model can carry out VTOL, thus is not only restricted to flight Run, ejector and parachute.Further, aircraft of the present utility model can use Flying-wing's (phase Ying Di, the first tail structure and the second tail structure can form the one of caudal vertebra and vertical tail when Guan Bi Body structure) so that aircraft flight resistance of the present utility model is the lowest, and further increases oceangoing voyage Cheng Nengli.Further, flexible shock-damping structure can also be arranged (such as, according to aircraft of the present utility model It is arranged on the undercarriage in both sides wing tip and afterbody cavity) so that flight of the present utility model Device can also reduce impact by flexible shock-damping structure when vertical drop is on ground.

Accompanying drawing explanation

In order to realize above-mentioned and relevant purpose, describe some herein in conjunction with explained below and accompanying drawing and say Bright property aspect, these aspects indicate can be to put into practice the various modes of principles disclosed herein, and institute Aspect and equivalence aspect thereof is had to be intended to fall under in the range of theme required for protection.Read by combining accompanying drawing Reading detailed description below, above-mentioned and other purpose, feature and the advantage of the disclosure will become brighter Aobvious.Throughout the disclosure, identical reference generally refers to identical parts or element.

Fig. 1 shows the schematic diagram of the aircraft 100 according to one embodiment of this utility model；And

Fig. 2 shows the schematic diagram of the aircraft 200 according to another embodiment of this utility model.

Detailed description of the invention

It is more fully described the exemplary embodiment of the disclosure below with reference to accompanying drawings.Although accompanying drawing shows The exemplary embodiment of the disclosure, it being understood, however, that may be realized in various forms the disclosure and not Should be limited by embodiments set forth here.On the contrary, it is provided that these embodiments are able to more thoroughly Understand the disclosure, and complete for the scope of the present disclosure can be conveyed to those skilled in the art.

Fig. 1 shows the schematic diagram of the aircraft 100 according to one embodiment of this utility model.Such as Fig. 1 Shown in, aircraft 100 includes fuselage 110, the rotor driver 140 being arranged at fuselage 110 front end, arranges The first wing 120 in fuselage 110 side and the second wing 130 of opposite side.Fuselage 110 can use Various structures, for example, body of revolution, but it is not limited to this.First wing 120 and the second wing 130 are such as Can be Flying-wing, and there is high aspect ratio, to reduce the flight resistance of aircraft 100.But root Can also use the wing of other layouts according to embodiment of the present utility model, this is not limited by this utility model System.Wherein, the first wing 120 is provided with the first circular hole 121, the second wing 130 is provided with second Circular hole 131.Typically, the first circular hole 121 and the second circular hole 131 are symmetrical relative to fuselage 110, But it is not limited to this.Aircraft 100 is provided with the first propeller 150 in the first circular hole 121, at the second circle Hole 131 is provided with the second propeller 160.Aircraft 100 also includes controlling the first propeller 150 and The drive mechanism (not shown) of two propellers 160.Rotor driver 140 can not only pull flight Device 100 carries out horizontal flight, it is also possible to drive aircraft 100 to carry out vertically (front fuselage is straight up) Landing or hovering.The concrete structure of rotor driver 140 and lifting airscrew one well known in the art Cause.Alternatively, rotor driver 140 is additionally provided with trousers 141.Rotor driver 140 of the present utility model Also there is feathering mechanism (not shown), it is possible to regulate the flight side of aircraft 100 easily To and attitude.Here feathering mechanism can use multiple known concrete structure, repeats no more here. Such as, " Aeronautics " the 3rd phase in 2009 the 37-41 page discloses a kind of feathering mechanism Example, but be not limited to this.It should be noted that rotor driver 140 is typically configured as single shaft rotor structure. Single shaft rotor is configured, can be at aircraft 100 according to the first and second propellers of the present utility model When lifting or hovering, rotor driver 140 can be balanced and be applied to the torsion of fuselage, in order to fuselage keeps appearance Stablizing of state, thus avoid the uncontrolled rolling of fuselage.Or, it is in VTOL or hovering Aircraft 100 is when by airflow influence, and the first and second propellers can be used for reducing air-flow to flying The impact of row device attitude.Furthermore, it is upper and lower that the first propeller 150 and the second propeller 160 are arranged on wing Circular hole between aerofoil (is i.e. embedded in wing), extra flight resistance will not be increased.

Alternatively, when the flight speed of aircraft 100 is not up to threshold value, drive mechanism can be to first The rotational parameters of propeller 150 and the second propeller 160 is controlled, in order to two propellers can be adjusted The roll attitude of joint aircraft.Here, rotational parameters such as can include rotating speed and pitch etc..It addition, When the flight speed of aircraft 100 reaches threshold value, then show that aircraft 100 can be when horizontal flight Having stable roll angle, drive mechanism can select to close the first and second propellers.It addition, flight Device 100 can also include flaperon.Specifically, the trailing edge of the first wing 120 is provided with the first flap pair The trailing edge of the wing the 122, second wing 130 is provided with the second flaperon 132.So, need at aircraft 100 During lift to be increased, first, second flaperon can deflect below wing stabilization simultaneously.In flight When device 100 needs to regulate roll attitude (particularly first, second propeller close after), first, the Two flaperons regulate the roll angle of aircraft 100 by differential deflection.

Fig. 2 shows the schematic diagram of the aircraft 200 according to another embodiment of this utility model.Due to Aircraft 200 needs to carry out VTOL, and aircraft 200 is arranged to tail structure and can close and beat Open.As in figure 2 it is shown, aircraft 200 is on the basis of aircraft 100, it is further configured with respectively It is articulated with fuselage and is symmetrical in the first tail structure 170 and the second tail structure 180 of the fuselage plane of symmetry.This In, when the first tail structure 170 and the second tail structure 180 are in closure state, afterbody entirety is tied Structure can have multiple known selection.The afterbody overall structure of such as aircraft 200 includes that caudal vertebra is with vertical Empennage, the i.e. Flying-wing of aircraft 200 generally blended wing-body.So, fuselage 110 and afterbody are whole The global shape of body structure composition can be rendered as " water-drop-shaped ", can greatly reduce flight resistance.

It addition, the first tail structure 170 and the second tail structure 180 are different from conventional fixed-wing aircraft Afterbody, but reverse V-shaped open mode can be rotated into.More specifically, the first tail structure 170 He Second tail structure 180 can rotate in the vertical plane of wing (first, second wing) plane. First tail structure 170 and the second tail structure 180 respectively with fuselage 110 plane of symmetry formed by angle big Cause identical.When first tail structure 170 becomes reverse V-shaped open mode with the second tail structure 180, first The wing tip of tail structure the 170, second tail structure the 180, first wing 120 and the wing of the second wing 130 Point may be at same plane.The angle of the first tail structure 170 and the second tail structure 180 depends on The two length own and the tip location of the two-shipper wing.Here, the two-shipper wing for example, swept-back wing, but do not limit In this.Sum it up, the first tail structure 170 and the second tail structure 180 rotate into reverse V-shaped opening During state, jointly aircraft 200 can be carried out cross hang with the wing tip of double-vane.On this basis, According to aircraft 200 of the present utility model when carrying out aerial mission, can be not only restricted to airstrips, Ejector or parachute.

As it has been described above, according to the afterbody overall structure (i.e. first, of aircraft 200 of the present utility model Two tail structures) can there be multiple choices.Correspondingly, the first tail structure 170 and the second tail structure 180 also have multiple choices.Illustrative with the embodiment shown in Fig. 2 below.At the present embodiment In, the first tail structure 170 includes the first rod member 171 being articulated with fuselage and is arranged on the first rod member 171 On first coccygeal vertebra portion 172.Being similar to, the second tail structure 180 includes the second rod member 181 and is arranged at Second coccygeal vertebra portion 182 on second rod member 181.So, tie at the first tail structure 170 and the second afterbody Structure 180 is in closure state, and (the i.e. first rod member 171 and the second rod member 181 turn to and the fuselage plane of symmetry Parallel) time, first coccygeal vertebra portion 172 and second coccygeal vertebra portion 182 form a caudal vertebra.Alternatively, first The first vertical tail 173 can be provided with in caudal vertebra portion 172, and in second coccygeal vertebra portion 182, can be provided with Two vertical tails 183.First vertical tail 173 and the second vertical tail 183 can form upper and lower twin vertical fin Configuration.It addition, the first rod member 171 and 181, the second bar can be along being perpendicular to wing horizontal stabilizer Direction rotate into reverse V-shaped open mode, in order to the outer end in first coccygeal vertebra portion 172, second coccygeal vertebra portion 182 Outer end and the wing tip (4 strong points altogether) of double-vane whole aircraft 200 is carried out cross hang. Here, about the first rod member 171 and rotation control mode of the second rod member 181, multiple public affairs can be used The type of drive known, such as, be driven by motor and travelling gear, the most such as by motor and connecting rod The kind of drive, this is the most without limitation.

Alternatively, aircraft 200 there also is provided flexible shock-damping structure, such as undercarriage, but is not limited to this. Specifically, the first undercarriage 123, the wing of the second wing 130 it are provided with at the wing tip of the first wing 120 The second undercarriage 133 it is provided with at Jian.It addition, caudal vertebra (first coccygeal vertebra portion 172 and second coccygeal vertebra portion 182) There is cavity (not shown).And fuselage 110 rear portion is provided with the 3rd be placed in this cavity Fall frame 111.So, aircraft 200 vertically place (fuselage 110 front end is upward) lift ground time, Three undercarriages can support aircraft 200 together with first, second caudal vertebra portion it addition, the 3rd undercarriage 111 can play main supporting role, to reduce double-vane and the stress in two caudal vertebra portions.This utility model

In description mentioned herein, illustrate a large amount of detail.It is to be appreciated, however, that this The embodiment of utility model can be put into practice in the case of not having these details.In some instances, It is not shown specifically known method, structure and technology, in order to do not obscure the understanding of this description.

Similarly, it will be appreciated that in order to simplify the disclosure and help understand in each inventive aspect one Or multiple, in description to exemplary embodiment of the present utility model above, of the present utility model each Feature is grouped together in single embodiment, figure or descriptions thereof sometimes.But, should not Be construed to the method for the disclosure to reflect an intention that this utility model the most required for protection require than The feature more features being expressly recited in each claim.More precisely, as following right is wanted As asking book to be reflected, inventive aspect is all features less than single embodiment disclosed above. Therefore, it then follows claims of detailed description of the invention are thus expressly incorporated in this detailed description of the invention, its In each claim itself as independent embodiment of the present utility model.

Those skilled in the art are to be understood that module or the list of the equipment in example disclosed herein Unit or assembly can be arranged in equipment as depicted in this embodiment, or alternatively can position In the one or more equipment different from the equipment in this example.Module in aforementioned exemplary can combine It is a module or is segmented into multiple submodule in addition.

Those skilled in the art are appreciated that and can carry out the module in the equipment in embodiment certainly Change adaptively and they are arranged in one or more equipment different from this embodiment.Permissible Module in embodiment or unit or assembly are combined into a module or unit or assembly, and in addition may be used To put them into multiple submodule or subelement or sub-component.Except such feature and/or process or Outside at least some in unit excludes each other, can use any combination that (this specification is included companion With claim, summary and accompanying drawing) disclosed in all features and so disclosed any method or All processes of person's equipment or unit are combined.Unless expressly stated otherwise, this specification (includes companion With claim, summary and accompanying drawing) disclosed in each feature can by provide identical, equivalent or phase Replace like the alternative features of purpose.

Although additionally, it will be appreciated by those of skill in the art that embodiments more described herein include it Some feature included in its embodiment rather than further feature, but the group of the feature of different embodiment Close and mean to be within the scope of this utility model and form different embodiments.Such as, below Claims in, embodiment required for protection one of arbitrarily can mode in any combination Use.

Additionally, some in described embodiment be described as at this can by the processor of computer system or Person by perform described function other device implement method or the combination of method element.Therefore, there is use Processor in the necessary instruction implementing described method or method element is formed and is used for implementing the method or method The device of element.Additionally, the element described herein of device embodiment is the example of following device: this dress Put for implementing by the function performed by the element of the purpose in order to implement this invention.

As used in this, unless specifically stated so, use ordinal number " first ", " second ", " the Three " etc. describe plain objects and be merely representative of the different instances relating to similar object, and be not intended dark Show the object being so described must have the time upper, spatially, sequence aspect or with arbitrarily other side Formula to definite sequence.

Although the embodiment according to limited quantity describes this utility model, but benefits from above description, Those skilled in the art will appreciate that, in the range of this utility model thus described, Ke Yishe Think other embodiments.Additionally, it should be noted that the language used in this specification is primarily to readability With teaching purpose and select rather than select to explain or limit theme of the present utility model 's.Therefore, in the case of without departing from the scope of the appended claims and spirit, this technology is led For the those of ordinary skill in territory, many modifications and changes will be apparent from.For of the present utility model Scope, the disclosure being done this utility model is illustrative and not restrictive, of the present utility model Scope is defined by the appended claims.

Claims

1. an aircraft, it is characterised in that including:

Fuselage；

It is arranged at the rotor driver of front fuselage；

It is arranged at the first wing of fuselage side and the second wing of opposite side, wherein there is on the first wing the first circular hole, the second wing has the second circular hole；

The first propeller being arranged in the first circular hole and the second propeller being arranged in the second circular hole；And

Control the first propeller and the drive mechanism of the second propeller.

2. aircraft as claimed in claim 1, it is characterised in that described drive mechanism is suitable to, when the flight speed of described aircraft is not up to threshold value, control described first propeller and the rotating speed of the second propeller and pitch.

3. aircraft as claimed in claim 1, it is characterised in that the trailing edge of described first wing is provided with the first flaperon, and the trailing edge of described second wing is provided with the second flaperon.

4. aircraft as claimed in claim 1, it is characterised in that be provided with trousers on described rotor driver.

5. aircraft as claimed in claim 1, it is characterised in that described rotor driver has the feathering mechanism of the flight attitude regulating described aircraft.

6. aircraft as claimed in claim 1, it is characterised in that also include being hingedly connected to fuselage and being symmetrical in the first tail structure and the second tail structure that the fuselage plane of symmetry is arranged,

Wherein, when the first tail structure and the second tail structure turn to reverse V-shaped open mode from closure state, the wing tip of the first tail structure, the second tail structure, the wing tip of the first wing and the second wing is in same plane.

7. aircraft as claimed in claim 6, it is characterised in that

Described first tail structure includes the first rod member being articulated with fuselage and the first coccygeal vertebra portion being arranged on the first rod member；

Described second tail structure includes the second rod member being articulated with fuselage and the second coccygeal vertebra portion being arranged on the second rod member；

When described first tail structure and described second tail structure are in closure state, first coccygeal vertebra portion and second coccygeal vertebra portion one caudal vertebra of composition.

8. aircraft as claimed in claim 7, it is characterised in that

Described first tail structure also includes the first vertical tail being arranged in described first coccygeal vertebra portion；

Described second tail structure also includes the second vertical tail being arranged in described second coccygeal vertebra portion；

When described first tail structure and described second tail structure are in closure state, the first vertical tail and the second vertical tail form upper and lower twin vertical fin configuration.

9. aircraft as claimed in claim 7, it is characterised in that the wing tip of described first wing is provided with the first undercarriage, and the wing tip of described second wing is provided with the second undercarriage.

10. aircraft as claimed in claim 9, it is characterised in that described caudal vertebra has cavity, and described fuselage afterbody is additionally provided with the 3rd undercarriage being placed in this cavity.