CN205469774U - Aircraft with fin - Google Patents

Abstract

The utility model discloses an aircraft with fin, the reciprocating impact tunnel drilling machine comprises a machine body, the both sides of fuselage all are provided with the wing, the aspect ratio of aircraft between 3 to 20, two keep away from on the wing the one end of fuselage all is provided with the fin, the fin deviates from the side of fuselage with the contained angle of wing is the acute angle. The utility model provides an aircraft is provided with the fin on the wing, and the fin is towards the slope of the direction of wing wing tip, so the air current of aircraft wing below rolled to wing top when lasting through the wing tip, and the fin has sheltered from the air current messenger, and it can't form the vortex at the wing tip, reduces the negative effects of tip vortex to aircraft lift from this.

Description

Has tail on aircraft

Technical field

This utility model relates to flight machinery, is specifically related to the tail on aircraft of a kind of tool.

Background technology

In aviation aircraft design, lift is one of major parameter needing consideration, bigger in order to obtain Lift, have many aircrafts to have employed all-wing aircraft design, the namely length of fuselage and the width phase of wing When design, such as B2, global hawk unmanned plane etc., so, roomy wing has the advantage of lift. Synchronize, the lift caused due to the large area of wing so that the pitching stability of wing is poor.

Fig. 1 is the ascending air schematic diagram of aircraft in prior art, as it is shown in figure 1, the wing of aircraft During 2 ' produce lift, the generation draught head between the above and below of wing 2 ', the gas of lower section Pressure height, and the air pressure of top is little, this pressure differential is formed for lift.Many studies have shown that at present simultaneously, The experiment of such as NASA, owing to the air pressure of wing 2 ' lower section is big, air-flow is just at wing tip 2 ' place the most up Upset, forms wing tip air-flow, and the rolling of wing tip air-flow forms tip vortex 5 ', the shape of this tip vortex Become, reduce the lift of wing 2 '.The way of some existing minimizing tip vortexes is at wing tip at present Add winglet, to reduce tip vortex 5 ', increase lift, but, winglet cannot be used for control and flies Row state.

Utility model content

The purpose of this utility model is to provide the tail on aircraft of a kind of tool, to reduce prior art airfoil point The eddy current negative effect to airplane ascensional force.

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

A kind of have tail on aircraft, and including fuselage, the both sides of described fuselage are provided with wing, institute State the aspect ratio of aircraft between 3 to 20, equal away from one end of described fuselage on two described wings Being provided with empennage, the angle of side and described wing that described empennage deviates from described fuselage is acute angle.

Above-mentioned aircraft, the angle of sweep of described wing is between 10～80 degree.

Above-mentioned aircraft, one end that described empennage deviates from head is provided with tail vane.

Above-mentioned aircraft, on described wing, the one end towards tail is provided with aileron.

Above-mentioned aircraft, described empennage deviate from the side of described fuselage and the angle of described wing between Between 20～80 degree.

Above-mentioned aircraft, the angle of side and described wing that described empennage deviates from described fuselage is 45 degree Or 60 degree.

Above-mentioned aircraft,

2≤L/l≤20；

In above formula, L is the root distance to described fuselage of described empennage, and l is the root of described empennage Distance to the wing tip of described wing.

In technique scheme, the aircraft that this utility model provides, wing is provided with empennage, and tail The wing tilts towards the direction of wing tip, and the air-flow below such aircraft wing rolls to machine by wing tip Time above the wing above, empennage has blocked air-flow makes it cannot form eddy current at wing tip, thus reduce wingtip vortex The stream negative effect to airplane ascensional force.

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 enforcement In example, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only Some embodiments described in this utility model, for those of ordinary skill in the art, it is also possible to according to These accompanying drawings obtain other accompanying drawing.

Fig. 1 is the ascending air schematic diagram of aircraft in prior art；

The structural representation of the aircraft that Fig. 2 provides for this utility model embodiment；

The ascending air schematic diagram of the aircraft that Fig. 3 provides for this utility model embodiment；

The rising stress schematic diagram of the aircraft that Fig. 4 provides for this utility model embodiment；

The decomposing schematic representation of the aircraft that Fig. 5 provides for one embodiment of this utility model；

The front view of the aircraft that Fig. 6 provides for one embodiment of this utility model；

Body that Fig. 7 provides for another embodiment of this utility model and the decomposing schematic representation of fuselage；

The front view of the aircraft that Fig. 8 provides for another embodiment of this utility model.

Description of reference numerals:

Prior art:

1 ', fuselage；2 ', wing；3 ', higher-pressure region；4 ', low-pressure area；5 ', tip vortex.

This utility model:

1, fuselage；2, wing；3, higher-pressure region；4, low-pressure area；5, tip vortex；6, empennage；7、 Tail vane；8, aileron；9, right outside centre of lift；10, left-external side centre of lift；11, wing liter Power center；12, center of gravity；F1, gravity；F2, airfoil lift；F3, right outside lift；F3, a left side Outside lift；L1, front praise the arm of force；L2, after praise the arm of force；L3, the rolling arm of force.

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 This utility model is further detailed by accompanying drawing.

As Figure 1-3, the one that this utility model embodiment provides has tail on aircraft, including machine Body 1, the both sides of fuselage 1 are provided with wing 2, the aspect ratio of aircraft between 3 to 20, two On individual wing 2, the one end away from fuselage 1 is provided with empennage 6, and empennage 6 deviates from the side of fuselage 1 It is acute angle with the angle of wing 2.

Concrete, aircraft includes fuselage 1 and wing 2, wherein, aspect ratio be wing 2 the span with The ratio of mean geometric chord, aspect ratio makes the span of aircraft relatively greatly more than or equal to 3 less than or equal to 20, So that the induced drag of aircraft is in reduced levels, thus improve the mobility of aircraft, for reducing The negative effect of the tip vortex that wing 2 brings greatly, on wing 2, the one end away from fuselage 1 arranges tail The wing 6, and the angle of wing 2 side and wing 2 that deviate from fuselage 1 is acute angle, i.e. two empennages 6 V-shaped layout, so, as it is shown on figure 3, from 2 higher-pressure regions of wing toward low-pressure area on wing 2 Wing tip air-flow, continuing after being blocked by empennage 6 supports or opposes, and the disembark direction of the wing 2 is overflowed, without at the wing Point region forms eddy current.The left-right balance thus facilitating aircraft keeps, and the left and right of opposing aircraft rolls, and carries Stability for left and right rolling.And now the lift of wing tip air-flow is obliquely, too increases aircraft Lift.

Meanwhile, as shown in Figure 4, flying when aircraft is flat, wing 2 is in level, due to outside wing 2 do not provide or provide minimum lift, total centre of lift of full wing 2 to be mainly to fall at machine The centre of lift of the wing 2.And when aircraft comes back, wing 2 forms certain angle of attack, left right lateral V empennage 6 adds lift faster, owing to the arm of force is bigger, thus provides for rear and lifts moment, The total life center back making full wing 2 offsets so that aircraft reaches new stable equilibrium again, Pitching stability is provided.So, the wing 2 that the present embodiment provides achieves centre of lift according to flight The performance that attitude automatic dynamic adjusts, and possess the stability of convergence, such beat all effect Really.

The aircraft with empennage 6 that the present embodiment provides is applicable to toy airplane, model plane, unmanned plane And other existing type of airplane.

The aircraft that the present embodiment provides, wing 2 is provided with empennage 6, and empennage 6 is towards wing 2 The direction of wing tip tilts, and the air-flow below such aircraft wing 2 is rolled to above wing 2 by wing tip Time upper, empennage 6 has blocked air-flow makes it cannot form eddy current at wing tip, thus reduces tip vortex pair The negative effect of airplane ascensional force.

In the present embodiment, it is preferred that the angle of sweep of wing 2 is between 10～80 degree, it is preferred that Angle of sweep is 30 degree, is arranged by the angle of sweep of possible angle, steady when promoting aircraft rolling further Qualitative energy.

In the present embodiment, further, one end empennage 6 deviating from head is provided with tail vane 7, tail The swing of rudder 7 can control the flow direction of air-flow, thus plays the left and right controlling flight attitude.When left tail Rudder 7, right tail vane 7 swing identical angle, airplane tail group downward bias together simultaneously to fuselage 1 direction Turning, aircraft comes back.When left tail vane 7, right tail vane 7 swing out identical angle the most simultaneously, fly Drive end unit upward deflects, and aircraft is bowed, and so plays the effect controlling aircraft pitch.When left tail vane 7 Swinging larger angle inside, right tail vane 7 swings less angle inside, and aircraft rolls to the left, Turn to the left on one side；When left tail vane 7 swings smaller angle inside, and right tail vane 7 swings bigger inside Angle, aircraft rolls to the right, while bending to right, so plays the left and right controlling heading.

In the present embodiment, further, on wing 2, the one end towards tail is provided with aileron 8, By stirring up and down of aileron 8, control the flow direction of air-flow, thus the flight for aircraft provide auxiliary, As being swung up when starboard aileron 8, port aileron 8 swung downward, the left and right rolling etc. of aircraft can be controlled.

In the present embodiment, it is preferred that empennage 6 deviate from the side of fuselage 1 and the angle of wing 2 between Between 20～80 degree, such as 45 degree or 60 degree, this angle too small is more weak to the occlusion effect of air-flow, The excessive then air-flow of angle is less to the lift power-assisted of aircraft, and 20～80 degree can preferably neutralize the two, Wherein, with 45 degree and 60 degree for more typical angle.

In the present embodiment, it is preferred that 2≤L/l≤20；

In above formula, L is the root distance to fuselage 1 of empennage 6, and l is that the root of empennage 6 is to wing The distance of the wing tip of 2.I.e. empennage 6 is close to wing tip, disembark body 1 farther out, be so easy to block the wing Tumble flows at Jian.

The aircraft with empennage 6 that the present embodiment provides, is applicable to all kinds of existing flight machinery, as Shown in Fig. 5 and 6, for throwing model plane on the other hand, produce one by sheet material (such as panel beating or cystosepiment) The fuselage 1 of body formula and the profile of wing 2, then on wing 2, cut out aileron 8, use adhesive plaster to post, Aileron 8 can conveniently be adjusted.It addition, cut out two empennages 6 and tail vane 7 again on sheet material, Between empennage 6 and tail vane 7, post with adhesive plaster, in order to V tail vane 7 can conveniently adjust, rear cutout Go out a rectangular plate to be additionally affixed on body as fuselage 1.So sheet material is made a hands to throw All-wing aircraft, the most easily starts, and flight stability, can change by adjusting tail vane 7 and aileron 8 Flight attitude, is suitable as children's teaching aid, it is also possible to make toy.

The aircraft with empennage 6 that the present embodiment provides, as shown in FIG. 7 and 8, is an electric remote control Aircraft, wing 2 has sweepback, 30 degree of angle of sweep, makes one and has the diagram fuselage 1 of profile, wing 2, empennage 6, tail vane 7 and aileron 8, meanwhile, the afterbody at fuselage 1 is installed motor and is driven propeller Propeller, at the internally installed battery of fuselage 1 to provide electric power, center of gravity is arranged on inboard wing 2 Centre of pressure position after a while.When motor drives screw propeller to promote aircraft flight forward when, Aircraft has fabulous stability, and is having fabulous manipulation using tail vane 7 to handle flight when Property.Owing to fuselage 1 full weight is relatively lighter, uneasy can fill undercarriage, land in meadow.Can also Install undercarriage additional, land on level land.

The model machine finally worked it out, in the case of using about cystosepiment and chord 40cm, weight is general At 100 grams, now, flight speed just can steadily fly by Horizon 8 meters per second when, easily grasps Control, is suitable to the airplane hobbyist's flight just got started, is suitable as exerciser and uses.

The aircraft with empennage 6 that the present embodiment provides, applies also on small-sized manned passenger plane, or On person's loading transporter, at the span 11.2 meters, wing 2 area about 32 square metres, it is assumed that transport The wing load of machine is 0.15 ton every square metre, and maximum take-off weight reaches 4.5 tons, has well delivery Ability, and the application of the present embodiment makes flying wing type fuselage 1 have good stability, thus have There is good application prospect.

Only by the way of explanation, describe some one exemplary embodiment of the present utility model above, need not put Doubt, for those of ordinary skill in the art, in the case of without departing from spirit and scope of the present utility model, By various different modes, described embodiment can be modified.Therefore, above-mentioned accompanying drawing and being described in It is substantially illustrative, should not be construed as the restriction to this utility model claims.

Claims (7)

1. having a tail on aircraft, including fuselage, the both sides of described fuselage are provided with wing, It is characterized in that, the aspect ratio of described aircraft is between 3 to 20, away from institute on two described wings The one end stating fuselage is provided with empennage, and described empennage deviates from the side of described fuselage and described wing Angle is acute angle.

Aircraft the most according to claim 1, it is characterised in that the angle of sweep of described wing between Between 10～80 degree.

Aircraft the most according to claim 2, it is characterised in that deviate from head on described empennage One end is provided with tail vane.

Aircraft the most according to claim 2, it is characterised in that towards tail on described wing One end is provided with aileron.

Aircraft the most according to claim 1, it is characterised in that described empennage deviates from described fuselage Side and the angle of described wing between 20～80 degree.

Aircraft the most according to claim 5, it is characterised in that described empennage deviates from described fuselage The angle of side and described wing be 45 degree or 60 degree.

Aircraft the most according to claim 1, it is characterised in that

2≤L/l≤20；

In above formula, L is the root distance to described fuselage of described empennage, and l is the root of described empennage Distance to the wing tip of described wing.