CN1660668A

CN1660668A - Attack angle changeable aircraft wing

Info

Publication number: CN1660668A
Application number: CN 200410005752
Authority: CN
Inventors: 陈启星
Original assignee: Individual
Current assignee: Individual
Priority date: 2004-02-24
Filing date: 2004-02-24
Publication date: 2005-08-31

Abstract

An incidence-variable wing of aircraft is disclosed, which can increase the lifting force of aircraft. Two additional wings are movably attached to top surfaces of original wings via the telescopic rod. When a large lifting force is required, the additional wings is raised up by said telescopic rods. Controlling the telescopic rods can change its incidence. When the aircraft is flying at high speed, the additional wing is close to origninal wing, so become a single wing.

Description

Can change the wing of the angle of attack

The invention relates to the invention of aircraft wing aspect.

It is very limited that aircraft improves the means of lift, to such an extent as to take off and very high speed is all arranged when landing, needs very long runway.

The objective of the invention is by improvement, make the angle of attack of wing to change, thereby improve lift wing.The base plate and the horizontal surface of this specification sheets definition wing (comprising additional fin) are the angle of attack (Fig. 6) at the angle α of heading.

Description of drawings: (the not repeat specification of label that preceding figure introduced)

Fig. 1---aircraft schematic diagram when additional fin is tightened up of band additional fin; The 1-main wing, the 2-additional fin, 3-connects the back of the body, 4-head, 5-cabin.

Fig. 2---aircraft schematic diagram when additional fin is launched of band additional fin; The 6-expansion link, the 23-valley line.

Fig. 3---the aircraft schematic diagram of rotatable main wing; The 7-substrate, the 8-active window, the 9-connecting strap, the 10-rotating shaft, 11-turns the wing.

Fig. 4---Fig. 3 is parallel to connecting strap direction schematic cross-section; 12-internal layer covering, the outer covering of 13-.

Fig. 5---Fig. 3 over against active window direction scheme drawing; The 14-guide rail, 15-actuator, 16-curb pins sheaf space, 17-potted line, 18-removable bottom, extension plate under the 19-, 20-wing base plate, the last extension plate of 21-, 22-wing upper board.

The wing of Fig. 6---Fig. 3 (width) prolongs scheme drawing.24-base plate hinge, 25-extension plate hinge.

Principle is introduced: the present invention proposes the whole angle of attack that changes of aircraft wing, make aircraft obtain the method for big lift.

The additional fin method is arranged, rotate wing method and prolong three kinds of wing methods.

The additional fin method: expansion link 6 is when aircraft need improve flying speed, additional fin 2 to be close to (Fig. 1) on the main wing 1 with additional fin 2 from the mechanism that main wing 1 ejects and regains; When needs strengthen lift, by the thrust of expansion link 6, additional fin 2 is stretched out (Fig. 2) from main wing 1 top, and control expansion link 6 as required, make additional fin form the various suitable stretching, extension height and the angle of attack.Connect the back of the body 3 additional fin and connect into an integral body, help to improve the intensity of additional fin both sides; If but the additional fin on both sides is made separation type, can regulate separately separately and stretch the height and the angle of attack, just can be used to adjust state of flight.When additional fin was close to main wing, the aircraft appearance requirement was smooth, so after additional fin stretches up, can form (Fig. 2) valley line 23 at some position.

Rotate wing method: rotate the wing 11 and be fixed on the substrate 7, with connecting strap 9 that the rotation wing and the substrate on both sides is fixing as a whole again, connecting strap 9 is between outer covering 13 of airframe and the internal layer covering 12 (Fig. 4), the top that actuator 15 can drive connecting strap 9 is that movement in a curve is done in the axle center along guide rail 14 (Fig. 5) with rotating shaft 10, so connecting strap 9 drives substrate 7 and rotates the wing 11 and rotate, because in substrate 7 is sandwiched in, between the outer covering, and by rotating shaft 10 definite axle center, so substrate 7 can only be the motion that seesaw type is made at the center with rotating shaft 10, rotate the wing 11 angles of attack thereby change.Active window 8 rotates formation in order to rotate the wing 11.Leak tightness for cabin in guaranteeing, substrate 7 and connecting strap 9 are sealed in nacelle exterior by internal layer covering 12, internal layer covering 12 is seen from Fig. 4 direction and is approximately semicircle (long lid), from Fig. 5 direction, inside and outside layer covering finished combination at potted line 17 places, realize the sealing in internal cabin, it is to guarantee the profile smoothness that outer covering mainly acts on.

Prolong wing method: wing 11 is the state (wing 11 that prolongs wing method can be to rotate the wing or fixed-wing) of Fig. 5 when contraction state, removable bottom 18, following extension plate 19 are close to wing base plate 20, and last extension plate 21 is retracted between wing upper board 22 and the wing base plate 20.When wing need launch, driver train will be gone up extension plate 21 and release outside (Fig. 6), last extension plate 21 will descend extension plate 19 to haul out, because last extension plate 21 is curved, so downward moving arranged in the time of lengthening, makes removable bottom 18 and the following extension plate 19 common new base plates that form that an angle of attack arranged.

Additional fin method embodiment

Additional fin 2 is made thin wing, and the main wing shape is unlikely to produce big adverse effect; Expansion link 6 is mechanisms of hydraulic jack formula, additional fin can be adjusted to the multiple height and the angle of attack, and be used to strengthen additional fin; Form recessedly at some position of fuselage and wing, make that when additional fin was close to main wing, the aircraft outward appearance was smooth.

The additional fin method can improve lift, makes the aircraft can be to flying soon and fly to make selection slowly, when fly slowly and lift big The time many advantages are arranged: 1, make and take off and shorten requirement to runway when landing; 2, improve the ceiling; 3, reduce to turn half Directly; Fuselage maintenance level when 4, climbing; 5, can improve safety coefficient during emergency; 6, reduce oil consumption.

Claims

1, the present invention a kind ofly improves the principle of lift with aircraft wing, and its principle is: with the whole angle of attack that changes of aircraft wing, make aircraft obtain big lift.

2, aircraft wing according to claim 1 improves the principle of lift, its further feature is: the method that adopts additional fin, expansion link 6 is can be with additional fin 2 from the mechanism that main wing 1 ejects and regains, and when aircraft during at normal flight, additional fin 2 is close to (Fig. 1) on the main wing 1; When needs strengthen lift, by the thrust of expansion link 6, additional fin 2 is stretched to come up (Fig. 2) from main wing 1, and control expansion link 6 as required, make additional fin form the various suitable stretching, extension height and the angle of attack.

3, according to the principle of claim 1 and the described aircraft wing raising of claim 2 lift, its further feature is: additional fin adopts the connection back of the body 3 additional fin with both sides to connect into an integral body, helps to improve the intensity of additional fin.

4, according to the principle of claim 1 and the described aircraft wing raising of claim 2 lift, its further feature is: the additional fin on both sides is made separation type, can regulate separately separately and stretch the height and the angle of attack, just can be used to adjust state of flight.

5, aircraft wing according to claim 1 improves the principle of lift, its further feature is: adopt the wing method of rotating, rotating the wing 11 is fixed on the substrate 7, with connecting strap 9 that the rotation wing and the substrate on both sides is fixing as a whole again, connecting strap 9 is between outer covering 13 of body and the internal layer covering 12 (Fig. 4), actuator 15 can drive the top of connecting strap 9 and do movement in a curve along guide rail 14 (Fig. 5), so connecting strap 9 drives substrate 7 and rotates the wing 11, because in substrate 7 is sandwiched in, between the outer covering, and by rotating shaft 10 definite axle center, so substrate 7 can only be the motion that seesaw type is made at the center with rotating shaft 10, rotate the wing 11 angles of attack thereby change.Active window 8 rotates formation in order to rotate the wing 11.

6, improve the principle of lift according to the described aircraft wing of claim 1 and claim 5, its further feature is: the leak free method that realizes internal cabin, leak tightness for cabin in guaranteeing, substrate 7 and connecting strap 9 are sealed in nacelle exterior by internal layer covering 12, internal layer covering 12 sees from Fig. 4 direction and is approximately semicircle (long lid) that from Fig. 5 direction, inside and outside layer covering finished combination at potted line 17 places, realize the sealing in internal cabin, it is to guarantee the profile smoothness that outer covering mainly acts on.

7, aircraft wing according to claim 1 improves the principle of lift, its further feature is: adopt to prolong wing method, wing 11 is when contraction state, removable bottom 18, following extension plate 19 are close to wing base plate 20, and last extension plate 21 is retracted between wing upper board 22 and the wing base plate 20.When wing need launch, driver train will be gone up extension plate 21 and release outside (Fig. 6), last extension plate 21 will descend extension plate 19 to haul out, because last extension plate 21 is curved, so downward moving arranged in the time of lengthening, makes removable bottom 18 and the following extension plate 19 common new base plates that form that an angle of attack arranged.

8, aircraft wing according to claim 1 improves the principle of lift, and its further feature is: prolonging wing method can be to rotate the wing or fixed-wing.