CN203283375U

CN203283375U - Aircraft wing layout structure

Info

Publication number: CN203283375U
Application number: CN2013201900319U
Authority: CN
Inventors: 赵嘉珩
Original assignee: Individual
Current assignee: Individual
Priority date: 2013-04-16
Filing date: 2013-04-16
Publication date: 2013-11-13
Anticipated expiration: 2023-04-16

Abstract

The utility model provides an aircraft wing layout structure. The technical scheme is that an aircraft comprises a aircraft body, a aircraft head, main wings and a vertical tail, and further comprises wingtip winglets, back wings and duck wings, wherein the wingtip winglets are arranged at the end parts of the main wings; the back wings and the main wings are connected through connection plates; the back wings and the vertical tail are linked with each other; the duck wings are coupled with the front end of the aircraft body. The aircraft wing layout structure has the benefits that wing-connected layout and front wing and back wing connection are adopted to remarkably improve the strength and rigidity of the wings; the back wings not only provide a part of lift force but also bear the bending torque of part of the wings, so that the size and the weight of the wings are reduced; the high-aspect-ratio design is adopted to improve the slope of the lifting line and the maximum lift coefficient, and under the condition of specified wingspan and weight, the inductive resistance can be lowered.

Description

A kind of wing configurations structure of aircraft

Technical field:

The utility model belongs to the Flight Vehicle Design field, particularly a kind of wing configurations structure that relates to all kinds of aircraft.

Background technology:

China's large transport airplane be subjected to always in can't production high thrust aero-engine and high strength composite (such as the T1000 carbon fiber), present China does not have the failure-free transport plane to carry out long-range search and rescue.As everyone knows, in morning April 1 calendar year 2001, EP-3 type scout of Chinese found America is flown to overhead, marine site, the southern Chinese island of Hainan southeast, and two F-8 fighter planes of China sent monitor.9: 7, Chinese aircraft was when the 104 km normal flight of the southeast, Hainan Island, and American aircraft turns to suddenly, and same Chinese plane collision of its head and left wing, cause Chinese air crash, the chaufeur Wang Wei rear sacrifice of parachuting.This time the major cause of event is not only because of China's fighter plane strength poor (than the Soviet Union), is done motor-driven the lacking experience of expulsion, but the most important thing is that China does not have the failure-free transport plane to carry out long-range search and rescue.

As far back as the twenties in 20th century, just someone has designed a kind of diamond " Lian Yi " layout that vertical series type wing is linked together.To the seventies, the companies such as Lockheed and Boeing have proposed respectively multiple " Lian Yi " and " boxlike aircraft " concept, and wish to use it for potential commercial haulage machine and the scheme of military fuel charger.But the military or large-sized civil transport plane of endlessly being on active service so far (major cause is due to limited fund, larger etc. without demand, technical risk temporarily).

Do not have the failure-free transport plane to carry out long-range search and rescue problem in order to solve China, we have planned several wing configurations modes: 1, Flying-wing, its advantage are that stealth, pneumatic efficiency are high, and shortcoming is that cost is high, complicated without too much innovating, fly control; 2, adjustable wing layout, its advantage be fit to friction speed, flight quality is good, shortcoming be too complicated, cost is too high; 3, joined wing, its advantage are the size of the moment of deflection of high wing strength and stiffness, front and back wing shared part wing, little wing and weight, high aspect ratio, high lift line slope, maximum lift coefficient, low induced drag, and shortcoming is that to fly control complicated.Considering on the imperfect basis of each scheme, we adopt joined wing, on the basis of existing manufacturing capacity, the structural strength of bringing due to joined wing high (comparing same aspect ratio aircraft), induced drag are little, can produce under existence conditions.

Summary of the invention:

The utility model, in order to overcome the deficiency of existing aircraft wing design, designs a kind of new wing configurations and has high wing intensity and height.

The technical solution adopted in the utility model provides a kind of wing configurations structure of aircraft, this aircraft comprises fuselage, head, main wing and vertical tail, described aircraft also comprises winglet, rear wing and canard, the end of wherein said main wing is provided with winglet, rear wing is connected by connecting panel with main wing, described rear wing connects with vertical tail, front fuselage coupling canard;

Further, outside damping panel is housed on described winglet, assists the inboard damping panel interlock of connecting panel when turning to;

Further, described rear wing sweepforward contains inverted diherdral and wing flap is housed, and the angle of described inverted diherdral is the 1-2 degree;

Further, the described connection location of described rear wing and main wing on main wing apart from 70% position of fuselage;

Further, described outside damping panel and outside damping panel consist of aerolite;

Further, described rear wing and vertical tail apart from fuselage at 1/3 empennage At The Height;

Further, anti-in described main wing sweepback, double breasted is housed opens wing flap, the adjustable slat of leading edge;

Further, the aspect ratio of described main wing is 8-12.

The beneficial effects of the utility model are that before and after adopting joined wing, the wing connects, and significantly improve the wing strength and stiffness, and its postmedian wing except a part of lift is provided, is also born the moment of deflection of a part of wing, can reduce size and the weight of wing; The utility model is designed to high aspect ratio, improves slope of lift curve and maximum lift coefficient, in the situation that the given span and weight can reduce induced drag.

Description of drawings:

Fig. 1 is overall construction drawing of the present utility model;

Fig. 2 is local structure enlarged diagram of the present utility model.

The specific embodiment:

Following content elaborates to the specific embodiment of the present utility model in conjunction with Figure of description:

Referring to accompanying drawing 1-2, aircraft comprises fuselage, head, main wing 1 and vertical tail 5, and wherein the end of main wing 1 is equiped with winglet 2, and outside damping panel 7 is housed on winglet 2, this outside damping panel 7 consists of aerolite, assists inboard damping panel 8 interlocks of connecting panel 4 when turning to; Rear wing 3 sweepforwards contain inverted diherdral, this angle is the 1-2 degree, wing flap (not marking in figure) is housed, with disembark on main wing 1 70% position of body of the connection location of main wing 1, rear wing 3 is connected by connecting panel 4 with main wing 1, wherein connecting panel 4 is equipped with

inboard damping panel

8,7 interlocks of during turning and outside damping panel, and outside damping panel also consists of aerolite.

Rear wing 3 connects with vertical tail 5, and junction and fuselage have certain distance,, about 1/3 empennage At The Height, has the effect of the interference in air flow of wing before and after can reducing.

Anti-in main wing 1 sweepback, double breasted is housed opens wing flap, the adjustable slat of leading edge, have than high aspect ratio, and aspect ratio is 8-12.

The coupling of front fuselage long distance Canard 6, take off and open when landing, regain during flight, its action radius for horizontal base line, to be+35 to-10 degree.

Connect because the utility model adopts the joined wing front and back wing, significantly improve the wing strength and stiffness, its postmedian wing except a part of lift is provided, is also born the moment of deflection of a part of wing, can reduce size and the weight of wing; The utility model is designed to high aspect ratio, improves slope of lift curve and maximum lift coefficient, in the situation that the given span and weight can reduce induced drag.

How many preceences the aircraft of the company's of the employing wing-canard layout does not have under the normal flight state, but when aircraft need do large intensity motor-driven as face upward, during the action such as tight spiral, all can produce powerful eddy current on the front wing of aircraft and main wing, intercoupling and strengthening between two strands of eddy current, produce the lift stronger than normal arrangement.

Under the At High Angle of Attack state, canard only need to reduce generation lift can produce nose-down pitching moment, thereby effectively guarantees under At High Angle of Attack to suppress the controllability that excessively comes back.Canard can effectively be strengthened manoevreability and the short field take-off landing data of aircraft., because controlled rudder face is more, be convenient to realize direct force control.

Above content is in conjunction with specific embodiment further detailed description of the utility model, can not assert that concrete enforcement of the present utility model is confined to these explanations.For the utility model person of an ordinary skill in the technical field, without departing from the concept of the premise utility, can also make some simple deduction or replace, all should be considered as belonging to protection domain of the present utility model.

Claims

1. the wing configurations structure of an aircraft, this aircraft comprises fuselage, head, main wing (1) and vertical tail (5), it is characterized in that, described aircraft also comprises winglet (2), rear wing (3) and canard (6), the end of wherein said main wing (1) is provided with winglet (2), rear wing (3) is connected by connecting panel (4) with main wing (1), and described rear wing (3) connects with vertical tail (5), front fuselage coupling canard (6).

2. layout structure according to claim 1, is characterized in that, outside damping panel (7) is housed on described winglet (2), assists inboard damping panel (8) interlock of connecting panel (4) when turning to.

3. layout structure according to claim 1, is characterized in that, described rear wing (3) sweepforward contains inverted diherdral and wing flap is housed, and the angle of described inverted diherdral is the 1-2 degree.

4. layout structure according to claim 1, is characterized in that, described rear wing (3) and the described connection location of main wing are in upper 70% position apart from fuselage of main wing (1).

5. layout structure according to claim 2, is characterized in that, described outside damping panel (7) and outside damping panel (8) consist of aerolite.

6. layout structure according to claim 1, is characterized in that, described rear wing (3) and vertical tail (5) apart from fuselage at 1/3 empennage At The Height.

7. layout structure according to claim 1, is characterized in that, and is anti-in described main wing (1) sweepback, double breasted is housed opens wing flap, the adjustable slat of leading edge.

8. layout structure according to claim 7, is characterized in that, the aspect ratio of described main wing (1) is 8-12.