CN1276319A

CN1276319A - Wing-varying aircraft

Info

Publication number: CN1276319A
Application number: CN 00108531
Authority: CN
Inventors: 贾书翰
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-08-10
Filing date: 2000-08-10
Publication date: 2000-12-13

Abstract

A wing-varying aircraft features that its triangular wing is composed of three parallel flat wings with gap between adjacent flat wings and three gaps are filled by three flaps. The switch between triangular wing and flat wing is realized by opening or closing the flaps. Its advantages are low-speed short-distance taking off and landing, high-speed flying, and no variation of gravitational center.

Description

Variable wing plane

The present invention relates to a kind of aircraft by wing variation realization low speed short take-off and landing (STOL) and high-performance cruise and become swing device, this scheme not only is used for fighter plane, and can also be applied to passenger plane and transport plane.

The background technology of variable wing plane is a variable sweep aircraft.At present, there are Russia, the U.S., three countries of Britain in the country that has a variable sweep aircraft.Muscovite change back wing aircraft is Mi Ge-23, Mi Ge-27, Soviet Union-24, figure-22, figure-16 0.The variable swept back wing strategic bomber biggest lifting capacity reaches 275 tons.It is 216 tons that there are F-14, F-111 fighter plane, the B-1 variable swept back wing hyprsonic strategic bomber biggest lifting capacity in the U.S..The blast variable swept back wing fighter plane of Britain.General variable swept back wing is made up of fixing inner wing and movable outer wing two parts, the rotating shaft that runs through wing thickness is equipped with in the inner wing outside, outer wing is connected with inner wing by rotating shaft, and outer wing can be plunderred before and after rotating shaft under the heavy again hydraulic booster of complexity drives.Between common 20 °-75 ° of the sweep range of swing-wing, swing-wing advantage is the contradiction that has solved between the flight of supersonic plane high, low speed, has realized that just high low speed takes into account, and finishes that low speed rises and falls and this facility of high-speed flight.Swing-wing shortcoming is because interior outer wing can not become a fixing integral body, adds the rotation and the control mechanism of a cover more complicated, makes aircaft configuration become complicated more, and the weight of aircraft increases to some extent.With the F-14 fighter plane is example, nearly 18.2 tons of its bare weight, and contemporary isonomic other aircaft configuration weight is all little than it, nearly 13 tons of F-15, F-16 has only more than 8 tons, and F-14 is than its heavy several ton, even more than one times, this can bring adverse effect to the airworthiness of aircraft undoubtedly.The first half of the year in 1996, aviation accident, following the present of U.S. army side repeatedly take place and forbid the F-14 grounding 3 days in U.S. F-14 fighter plane.The F-111 fighter plane just the accident because of wing rotating shaft fracture fatal crass once occurred.Variable swept back wing can change the center of gravity of aircraft, and is unfavorable to aircraft safety.(the 10th page of wing eternal lasting of list of references " aviation knowledge " fifth phase)

The low speed that the objective of the invention is to the to improve aircraft performance of rising and falling shortens ground run distance, improves the supersonic performance of aircraft simultaneously again.

It is to adopt the blended wing-body technology that aircraft of the present invention becomes its scheme of swing device, and the division controlsurface, delta wing that the delta wing afterbody of being made up of the straight wing adopts U.S. B-2 stealth strategic bomber is made up of three straight wings that differ in size and slat.When slat was opened, wing was three straight wing attitudes and carries out short take-off and landing (STOL).When three wing flaps are closed, when aircraft is the delta wing state, can carry out high-speed flight.No matter taking off and land, what all must run stage and this process of high-performance cruise through low ski-running.Yet straight wing low-speed performance is good, and the delta wing high speed performance claims excellent.For high low performance is taken into account, so just adopt delta wing, the straight wing to become circulating technology, simple with the joystick manipulation slat.Because the area of slat is little, so load is also little, most of weight of aircraft is shared by three straight wings, and the manipulation of wing flap and conventional airplane principle are similar, so description of drawings not.

Owing to adopt blended wing-body, triangle, the straight wing to become circulation and anury (horizontal tail, vertical tail) control technology, make the great achievement of variable wing plane collection current technology, adding boards a plane becomes the feature of the wing.Its effect is conspicuous.Engineering staff of this area and audit crew reach generally has the people of aviation knowledge all can know, weight major part that becomes the sweepback fighter plane of the Russia and the U.S. all surpasses 10 tons, the bare weight of F-14 just has 18.2 tons, nearly 13 tons of F-15, and the total weight that becomes the sweepback strategic bomber is above hundred tons.The load of wing is so big, handles the sweepback and the reach not a duck soup of outer wing, and a cover complicated heavy again rotation and transmission device must be arranged, promptly---and hydraulic booster is.And variable wing plane of the present invention, chaufeur only uses an auxiliary operating rod just passable.Face is little because wing flap is subjected to air pressure, the center of gravity of airplane is changed because of the switch slat makes wing in the middle of changing again, so safe and reliable, its effect is self-evident.

The variable wing plane drawing is described as follows:

Fig. 1 is the birds-eye view of variable wing plane

Fig. 2 is the lateral plan of variable wing plane.Among the figure in order to show the opening and closing situation of slat, so do not paint strake wing.This figure is a slat place closed condition.

Fig. 3 shows slat place opening, and wing is straight wing attitude.Among the figure: 1: pitot 2: the triangle aerofoil 3 of aircraft forward: passenger cabin 4: ventral duct 5: the strake wing 6 that connects straight aerofoil: preceding slat 7: middle slat 8:

back slat

9,10,11 is respectively aerofoil fuel tank 12: division elevating rudder 13:

cleavage direction rudder

12,13 is M shape controlsurface 14: the compound engine freeing pipe.

When variable wing plane took off, chaufeur can push away auxiliary operating rod (maneuvering system is not drawn), made slat be in Fig. 3 state, and slat plays the effect of wing flap lift-rising, simultaneously before 9,10,11 in back three straight wings produce lifting forces.Because straight wing low-speed performance is good, aircraft ground run distance weak point can take off, and after the aircraft lift-off, the aviator draws auxiliary operating rod, and when making three slats close the position of getting back to Fig. 2, the wing of this moment resembles Fig. 1 fully becomes acute triangle, can high-performance cruise.During landing, the office staff also pushes away auxiliary operating rod opens slat, can continue to land.Because this programme is the blended wing-body technology, fuselage is surrounded by delta wing fully, and the designer has to draw this machine profile full figure, and empennage is to draw by the B-2 stealth bombers principle, and whole controlsurface is the M type, and other parts are only made setoff.

Claims

1, the variable wing plane taken into account of a kind of high low speed.It comprises the delta wing of a blended wing-body, three straight wings, slat, M type division formula controlsurface, ventral duct.

2, according to right one.In the middle of the delta wing three straight wings are arranged, it is characterized in that: three straight wings are parallel to each other.

3, according to claim two, leave space length between three straight wings.It is characterized in that: between the distance slat is installed.

4, dependent claims.According to the requirement of right two, three, be installed on slat between three straight wings.It is characterized in that: open or close slat, wing is changed, slat is opened, and is straight wing attitude, closes slat, is the delta wing state.