CN205661648U - All -wing aircraft subassembly of aircraft and aircraft - Google Patents

Abstract

The utility model discloses an all -wing aircraft subassembly of aircraft, be used for installing in the fuselage of aircraft, the all -wing aircraft subassembly includes: the symmetry set up in two inboard wings of fuselage both sides, set up in two respectively the one -to -one two outside wings in the inboard wing outside, two outside wing symmetric distribution in the both sides of fuselage, the equivalent angle of attack of outside wing is less than rather than corresponding the equivalent angle of attack of inboard wing. The utility model discloses still disclose an aircraft. The relatively poor problem of present aircraft flight in -process stability can be solved to above -mentioned scheme.

Description

A kind of all-wing aircraft assembly of aircraft and aircraft

Technical field

This utility model relates to technical field of aircraft design, particularly relates to the all-wing aircraft group of a kind of aircraft and aircraft Part.

Background technology

At present, in order to obtain bigger climbing power, increasing aircraft uses all-wing aircraft design, uses all-wing aircraft design The fuselage of aircraft is relatively short, and fuselage length is suitable with the width of all-wing aircraft i.e. wing chord.The aircraft of this kind of structure is due to wing Wider, therefore there is the advantage that lift is bigger.

But, use the aircraft of all-wing aircraft design owing to there is no fuselage and the empennage that conventional aircraft is longer, therefore, pitching Less stable.In order to promote the stability of aircraft, need to use posture computer to add gyroscope, by gyroscope ceaselessly Adjust the attitude of aircraft to keep stable.Nonetheless, the flight stability of current aircraft is the best, in flight During jolt, shake bigger, manipulation more difficulty, this affect on the contrary all-wing aircraft design application.

It addition, the training type that student uses at present is usually the front machine drawing of high mounted wing, owing to propeller is arranged on fuselage Front end, fall if there is accidentally error when student operates, be arranged on the propeller high speed rotating of front fuselage, to ground People and thing can cause bigger potential safety hazard.

Utility model content

The purpose of this utility model is to provide the all-wing aircraft assembly of a kind of aircraft, to solve current aircraft flight process The problem that middle pitching stability is poor.

To achieve these goals, the following technical scheme of this utility model offer:

The all-wing aircraft assembly of a kind of aircraft, for being installed on the fuselage of described aircraft；Described all-wing aircraft assembly includes:

It is symmetricly set in two inboard wings of described fuselage both sides；

It is arranged at two outside wings outside two described inboard wings, two described outside machines the most correspondingly The wing is symmetrically distributed in the both sides of described fuselage；The equivalent angle of attack of described outside wing is less than described inboard wing corresponding thereto The equivalent angle of attack.

Preferably, described inboard wing is identical with described outside wing structure, and described inboard wing is horizontal by One installs the angle of attack；Described outside wing installs the angle of attack horizontal by second, and described second installs the angle of attack less than described first peace The dress angle of attack.

Preferably, described inboard wing is that planoconvex is wing, and described outside wing is symmetrical wing.

Preferably, described outside wing is provided with aileron, and the initial settling angle of described aileron is negative value so that described outside The equivalent angle of attack of wing is less than the equivalent angle of attack of described inboard wing.

Preferably, the wing that described inboard wing and described outside wing are formed sets sweepback for being formed with described fuselage The swept-back wing at angle, so that the centre of lift of described outside wing is positioned on rear side of the centre of lift of described inboard wing.

A kind of aircraft, including fuselage and the all-wing aircraft assembly that is connected with described fuselage, described all-wing aircraft assembly is arbitrary All-wing aircraft assembly described in Xiang.

Preferably, described fuselage and two described inboard wings are integral type structure.

Preferably, the bottom surface of the afterbody of described fuselage is less than the bottom surface of described inboard wing；The top of the afterbody of described fuselage Face is provided with vertical tail；The propeller of described aircraft is arranged at the tail end of described fuselage；The radius of gyration of described propeller Distance less than its centre of gyration top away from described vertical tail；The radius of gyration of described propeller less than its centre of gyration away from The bottom surface distance of described afterbody.

Preferably, described aircraft is aircraft or model aircraft.

In technique scheme, this utility model provide the all-wing aircraft assembly of aircraft aircraft is flat fly when, by Bigger than the equivalent angle of attack of outside wing in inboard wing, therefore inboard wing has bigger lift, and outside airfoil lift is relatively Little, inboard wing plays the effect providing prevailing lift, and the center of lift is also based on inner side.Liter inside this time Power center fuselage center of gravity somewhat before place so that aircraft is flat to fly, and somewhat has the trend that aircraft comes back.But When aircraft comes back when, the outside wing equivalence angle of attack also can increase, and outside this time, the lift of wing increases More, and the place of (near the tail end of fuselage) to the rear of inboard wing it is positioned at due to outside wing, there is large force from center of gravity Square, therefore forms the moment lifting aircraft tail end, and the device that socks in continues to come back, and plays the effect of stabilized flight device. Visible, the all-wing aircraft assembly that this utility model provides can solve the problem that pitching stability during current aircraft flight is poor.

Accompanying drawing explanation

In order to be illustrated more clearly that the embodiment of the present application or technical scheme of the prior art, below will be to institute in embodiment The accompanying drawing used is needed to be briefly described, it should be apparent that, the accompanying drawing in describing below is only described in this utility model Some embodiments, for those of ordinary skill in the art, it is also possible to obtain other accompanying drawing according to these accompanying drawings.

The structural representation of a kind of aircraft that Fig. 1 provides for this utility model embodiment.

Fig. 2 is that in the all-wing aircraft assembly that this utility model embodiment provides, a kind of inboard wing is connected with the concrete of outside wing Schematic diagram；

Fig. 3 is specifically the connecting of another kind of inboard wing and outside wing in the all-wing aircraft assembly that this utility model embodiment provides Connect schematic diagram；

Fig. 4 is the structural representation of the another kind of aircraft that this utility model embodiment provides；

Fig. 5 is that outside wing is provided with aileron, and makes the schematic diagram that initial settling angle is negative value of aileron.

Detailed description of the invention

In order to make those skilled in the art be more fully understood that the technical solution of the utility model, below in conjunction with accompanying drawing pair This utility model is further detailed.

Refer to Fig. 1, this utility model embodiment provides the all-wing aircraft assembly of a kind of aircraft.The all-wing aircraft assembly bag provided Include two inboard wings 2 and two outside wings 3.

Wherein, two inboard wings 2 are symmetrically arranged at fuselage 1 both sides of aircraft；Two outside wings 3 are the most one by one It is arranged in accordingly outside two inboard wings 2.I.e. two outside wings 3 are also symmetrically arranged at the both sides of fuselage 1.Certainly, All-wing aircraft technology, the entirety that outside wing 3 can be formed with inboard wing 2 corresponding thereto is used to have certain angle of sweep, The wing that i.e. inboard wing 2 and outside wing 3 are formed is the swept-back wing being formed with fuselage 1 and setting angle of sweep, so that described The centre of lift of outside wing 3 is positioned on rear side of the centre of lift of inboard wing 2.

In the present embodiment, the equivalent angle of attack of each outside wing 3 is met less than the equivalence of inboard wing 2 corresponding thereto Angle.The equivalent angle of attack of outside wing 3 is less than the equivalent angle of attack of inboard wing 2 corresponding thereto, and then both are met in formation Angular difference.In actual design process, various ways can be used to realize above-mentioned angle of attack difference.

Obtaining lift to allow wing be easier to, wing is not a flat board.The wing of aircraft with reference to the wing of birds Wing, its cross section is can be an arc or arch.Study now announcement wing and had a variety of.One of which is normal Planoconvex wing, wing lower surface is plane, and upper surface is an arch, so according to the title of his cross section just image Wing for plano-convex, it is symmetrical wing that another kind is commonly used wing, and in terms of the cross section of wing, top half and the latter half are all arches Shape, or the mirror image of symmetry, so being called symmetrical wing.Symmetrical wing do not produce lift at 0 angle of attack, and plano-convex is wing meets 0 Angle still can produce lift, say, that plano-convex is wing when be arranged on 0 angle of attack, and actual effect is to have little just meeting Angle.

In the application, inboard wing 2 can be identical with the structure of outside wing 3, and inboard wing 2 is horizontal by the first peace The dress angle of attack；Outside wing 3 installs the angle of attack horizontal by second, and described second installs the angle of attack installs the angle of attack less than described first. Refer to Fig. 2, in a kind of detailed description of the invention, inboard wing 2 can be planoconvex wing 21, and outside wing 3 can also be Planoconvex wing 31, both bottom surfaces are flat face.The bottom surface of inboard wing 2 horizontal by set angle (being not zero), The bottom surface of outside wing 3 and plane-parallel, can form angle of attack difference mentioned above in such cases.

Certainly, inboard wing 2 can also differ with the structure of outside wing 3, refer to Fig. 3, specifically real at another kind Executing in mode, inboard wing 2 can be planoconvex wing 22, and outside wing 3 can be symmetrical wing 32, and outside wing 3 is along water Plane extends, and the most symmetrical axis of symmetry of wing 32 extends along the horizontal plane.The most also the angle of attack mentioned above can be formed Difference.

It addition, as it is shown in figure 5, outside wing 3 be also equipped with aileron 33, for adjusting the left and right rolling shape of aircraft State.Aileron 33 is except adjusting the left and right roll mode of aircraft, it is also possible to arranges initial settling angle a to aileron 33, initially pacifies Dress angle a can be arranged to a negative value, the namely extended line forward of the centrage of aileron 33 cross section, less than outside wing 3 The centrage of cross section, so that outside wing 3 is together with aileron 33, forms the effect that the equivalence angle of attack diminishes.So that The equivalent angle of attack of outside wing 3, less than the equivalent angle of attack of inboard wing 2.

By foregoing description, the all-wing aircraft assembly of the aircraft that the present embodiment provides aircraft is flat fly when, Owing to inboard wing 2 is bigger than the equivalent angle of attack of outside wing 3, therefore inboard wing 2 has bigger lift, and outside wing 2 Lift is less, and inboard wing 2 plays the effect providing prevailing lift, and the center of lift is also based on inner side.This time The centre of lift of inner side fuselage 1 center of gravity somewhat before place so that aircraft is flat to fly, and somewhat has aircraft to come back Trend.But when aircraft comes back when, the outside wing 3 equivalence angle of attack also can increase, wing 3 outside this time It is more that lift increases, and be positioned at the place of (near the tail end of fuselage 1) to the rear of inboard wing 2 due to outside wing 3, from Center of gravity has larger torque, therefore forms the moment lifting aircraft tail end, and the device that socks in continues to come back, and plays stable flying The effect of row device.Visible, the all-wing aircraft assembly that this utility model provides can solve pitching stability during current aircraft flight Poor problem.

If aircraft is disturbed by wind, the when that aircraft deflecting down, outside wing 3 becomes due to the equivalence angle of attack Little, allow the lift of inboard wing 2 have the trend lifting aircraft head end, the device that socks in continues to bow, and plays stabilized flight device The effect of flight.Outside wing 3 provides the moment lifting rear side.So can improve the pitching stability of aircraft.

When aircraft comes back too high, the when of close to stall, owing to the equivalent angle of attack of inboard wing 2 is than outside wing 3 The equivalence angle of attack is big, therefore the first stall of inboard wing 2, and outside wing 3 does not also have stall, it is provided that lift the moment of both sides, this Aircraft upset tenesmus avoided by sample, namely avoids stall spin.Therefore the aircraft that this utility model embodiment provides also has The standby good stable performance avoiding stall spin.

By said process, aircraft is put down when flying, and does not provide or provide minimum liter due to outside wing 3 Power, total centre of lift of full wing (the all-wing aircraft assembly that i.e. inboard wing 2 is formed with outside wing 3) is mainly to fall at inner side machine The centre of lift of the wing 2.And come back at aircraft, the when that full wing forming certain angle of attack, outside wing 3 adds liter faster Power, and owing to the arm of force is bigger, therefore outside wing 3 provides the moment that the tail end of aircraft is lifted so that full wing Total centre of lift offset backward so that aircraft reaches new stable equilibrium again.Therefore this wing design is actually Having reached centre of lift to adjust according to flight attitude automatic dynamic, and possessed the stability of convergence, stabilizing effect goes out People expects.

The all-wing aircraft assembly provided based on this utility model embodiment, this utility model also provides for a kind of aircraft, is provided Aircraft can be aircraft, it is also possible to be model aircraft.The aircraft provided includes fuselage 1 and as described in any one above All-wing aircraft assembly.

As shown in Figure 1, it is preferred that two inboard wings 2 are integral type structure with fuselage 1, in the process that aircraft assembles In, operator can direct wing 3 outside the position that two inboard wings 2 are corresponding is installed.

Refer to Fig. 4, this utility model embodiment also provides for a kind of aircraft.In the aircraft provided, fuselage 11 The bottom surface of afterbody is less than the bottom surface of described inboard wing 12；The end face of the afterbody of fuselage 11 is provided with vertical tail 13, concrete, Vertical tail 13 is two be distributed side by side.

The propeller of aircraft is arranged at the tail end of described fuselage 11；The radius of gyration of propeller less than its centre of gyration away from The distance on the top of vertical tail 13；The radius of gyration of propeller is less than its centre of gyration bottom surface distance away from fuselage 11 afterbody. The aircraft of this kind of structure so that propeller can be implemented omnibearing protection by fuselage 11 and vertical tail 13.Due to aircraft When falling, the overwhelming majority is all that the head end of fuselage 11 first lands, and therefore propeller is arranged at the tail end of fuselage 11 and is avoided that propeller First land caused destruction；Further, since fuselage 11 and vertical tail 13 can implement omnibearing protection for propeller, therefore Propeller can be made will not to get to people or the thing on ground after aircraft falls, be avoided that personnel's property loss.Visible, this practicality The aircraft that new embodiment provides has preferable safety.

The aircraft that this utility model provides makes full use of aerodynamic and mechanics lever principle carries out scientific design, Conceive careful and ingenious, coordinate between each position and extremely coordinate so that all-wing aircraft assembly has possessed pitching stability and anti-stall tail The stability of rotation.In actual applications, the stability of the very big flying wing type aircraft increased so that aircraft is easier to make With, improve use value.Being used on model plane, stable flight allows people leicht fallen D/A manipulation, it is easier to by the green grass or young crops of manipulator Look at.Being used on true aircraft (aircraft), stable flight can improve the comfortable experience of passenger, allows pilot be easier to drive flight Device.The aircraft that this utility model embodiment provides has great actual application value.

By the way of explanation, only describe some one exemplary embodiment of the present utility model above, undoubtedly, for Those of ordinary skill in the art, in the case of without departing from spirit and scope of the present utility model, can be with various different Described embodiment is modified by mode.Therefore, above-mentioned accompanying drawing and description are the most illustrative, should not be construed as Restriction to this utility model claims.

Claims (9)

1. an all-wing aircraft assembly for aircraft, for being installed on the fuselage of described aircraft；It is characterized in that, described all-wing aircraft assembly Including:

It is symmetricly set in two inboard wings of described fuselage both sides；

It is arranged at two outside wings outside two described inboard wings, two described outside wings pair the most correspondingly Claim the both sides being distributed in described fuselage；The equivalent angle of attack of described outside wing less than described inboard wing corresponding thereto etc. The effect angle of attack.

All-wing aircraft assembly the most according to claim 1, it is characterised in that described inboard wing and described outside wing structure phase With, and described inboard wing is horizontal by the first installation angle of attack；Described outside wing installs the angle of attack, institute horizontal by second State the second installation angle of attack, less than described first, the angle of attack is installed.

All-wing aircraft assembly the most according to claim 1, it is characterised in that described inboard wing is that planoconvex is wing, described outside Side wing is symmetrical wing.

All-wing aircraft assembly the most according to claim 1, it is characterised in that described outside wing is provided with aileron, described aileron Initial settling angle be negative value so that the equivalent angle of attack of described outside wing is less than the equivalent angle of attack of described inboard wing.

5. according to described all-wing aircraft assembly arbitrary in claim 1-4, it is characterised in that described inboard wing and described outside machine The wing that the wing is formed is the swept-back wing being formed with described fuselage and setting angle of sweep, so that the centre of lift of described outside wing It is positioned on rear side of the centre of lift of described inboard wing.

6. an aircraft, it is characterised in that including fuselage and the all-wing aircraft assembly being connected with described fuselage, described all-wing aircraft assembly is All-wing aircraft assembly according to any one of claim 1-5.

Aircraft the most according to claim 6, it is characterised in that described fuselage and two described inboard wings are integral type Structure.

Aircraft the most according to claim 6, it is characterised in that the bottom surface of the afterbody of described fuselage is less than described inner side machine The bottom surface of the wing；The end face of the afterbody of described fuselage is provided with vertical tail；The propeller of described aircraft is arranged at described fuselage Tail end；The radius of gyration of described propeller is less than the distance on its centre of gyration top away from described vertical tail；Described spiral The radius of gyration of oar is less than its centre of gyration bottom surface distance away from described afterbody.

9. according to the aircraft described in any one in claim 6-8, it is characterised in that described aircraft is aircraft or aircraft Model.