RU2705503C1 - Aircraft wing - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering and can be used in aircraft, ships, structures of blades, building structures, etc. Aircraft wing comprises upper and lower panels. Panels are waffle and monolithic. Ribs of the transverse set of panels are oriented along the flow. They protrude above the longitudinal ribs with formation of a lap sufficient for placement on the transverse ribs of the upper panel of ledges included in the corresponding slots on the ribs of the lower panel. Due to this, upper panel has the possibility of displacement (shift) relative to lower panel. At shift at front edge of wing there formed is hole for inlet, and on rear edge hole for air flow output, formed by movement of aircraft. At air inlet, air flow exerts pressure on inner surface of wing panel. When exiting the wing, the flow exerts pressure on the inner surface of the wing, but with a different sign. Torque created by pressure forces is able to influence flight trajectory of aircraft.

EFFECT: invention is also aimed at simplification of mechanization system, reduction of wing area and weight.

1 cl, 2 dwg

Description

Aircraft wing (L.A.) refers to the field of aircraft and can be used in aircraft, ships, blade structures, etc.

Known RF patent 2436709 from 12.20.2011, where the wing L.A. has a leading edge, curvature of flat surfaces, a trailing edge, flaps and is divided longitudinally into two parts, the lower and the upper, which are fastened with jumpers, and a cavity is formed inside, and a through slit is made along the leading edge of the wing with the function of directing the air flow along the upper inner cavity of the high region pressure through the trailing edge, characterized in that the inlet slit is located at a certain angle to the upper wall so that the air flow passes through the cavity along the upper wall, pressing against it under centrifugal force with the possibility of overlapping it with a movable flap, and at the trailing edge there is an exit slit with flaps that can overlap the exit slit, and winglets are installed along the side walls, the function of which is to prevent air from flowing from the vertical wall to the bottom along the side walls, and the upper edge the winglet is installed at the lower boundary of the air flow passing through the cavity.

The disadvantage of this technical solution is the uncertainty of the location of the through gap with respect to the upper wall of the cavity ("at some angle".) Thus, the "function of the direction of flow along the upper inner cavity to the high-pressure region" is also not defined. The control of the flight path of L.A., is carried out mainly by means of mechanization of the wing, which interact with air currents washing the outer surfaces of the lower and upper panels.

Mechanization tools contain a large number of parts, occupy (30-40)% of the wing area and up to 30% of the wing mass. According to (1), mechanization means on a modern aircraft are the “most complicated system”.

In order to increase the efficiency of flight path management L.A. the wing structure of the aircraft contains two main parts: the upper and lower panels. The panels are made wafer and monolithic with ribs of the transverse set, oriented along the flow and protruding above the longitudinal ribs with the formation of overlap, sufficient for placement in the middle part of the wing on the transverse ribs of the upper panel of the protrusions included in the corresponding grooves on the edges of the lower panel and with the possibility of displacement of the upper panel relatively lower.

When the upper panel is displaced relative to the lower one, air is opened into the wing by its span in the area of the leading edge and outward in the area of the trailing edge. The flow enters the ducts. Ducts are obtained by connecting the panels after placing the protrusions on the edges of the upper panel in the grooves on the edges of the lower panel.

The stream is in contact with the inner surface of the panel with pressure exerted on it. The geometry of the surface is given by the drawing. At the exit of the wing outward, the air flow changes its direction. The angle of exit of the flow from the wing is set by the drawing and is close to a right angle.

Thus, there are active forces on the leading edge of the wing and reactive forces on the trailing edge of the wing. These forces of different signs create a torque that can be used as a means to change the trajectory of L.A. The magnitude of the torque depends on the magnitude of the shift of the upper panel relative to the lower. When the shift is zero, the wing functions like a regular wing.

Mechanical, electrical, pneumatic, hydraulic, and other sources for obtaining the movement of parts can be used as a shear drive for panels.

In order not to create additional resistance to the passage of the air flow inside the wing and at the exit, the ribs of the transverse set are oriented along the main flow (the upper and lower air flows washing the wing, as well as the air flow inside the wing through the air ducts, are obtained by dividing the main flow air and are its parts)

The wing works on bending and torsion, therefore, the choice of a wafer set of ribs to reinforce the skin is optimal.

The comparative simplicity of the proposed technical solution will reduce the number of parts included in the mechanization of the wing, simplify the mechanization system, reduce the area and weight of the wing.

As a result of the analysis of known technical solutions during patent research, the applicant did not find technical solutions with features similar to the distinguishing features of the proposed solution, and therefore, the totality of the mentioned essential features allows us to consider the proposed useful wing model as a popular part of the aircraft.

The technical solution is illustrated in figures 1 and 2 ..

In FIG. 1 a) Aircraft wing profile.

b) The upper panel that fits into the wing profile

c) Bottom panel that fits into the wing profile.

Arrow A indicates a wafer set of longitudinal (1) and transverse (2) stiffeners.

The dotted line is the center line for the groove and protrusion. N is the size of the lap.

The protrusion in the transverse rib of the upper panel, section. BB Groove in the transverse rib of the bottom panel, section. SS.

When connecting the panels, the protrusion enters the groove, which ensures a directing shift of the upper panel relative to the lower. On the next pair of transverse ribs, the protrusion and groove are mirrored relative to the first pair, etc.

The places of mating panels (groove and protrusion) are placed in the middle part of the wing to the neutral line, where the operating voltage is minimal. The number of ducts in this wing is equal to the number of transverse stiffeners minus one.

In FIG. 2a) shows the shift “K” of the upper panel relative to the lower one, (from left to right) As a result of the shift, openings in the wing open along the front and rear edges of the wing. The first hole includes air flow, then flowing through the duct. The reaction of the inner surface of the panel to the flow pressure is denoted by P1.

The air flow exits the wing air ducts to the outside. The flow exerts pressure on the inner surface of the panel with a force of P2. Thus, there are active forces on the leading edge of the wing P1 and reactive forces on the trailing edge of the wing P2. These forces of different signs create a torque that can be used as a means to change the trajectory of L.A.

» и Л.А. идет на снижение.The moment turns the wing at an angle "

"And L.A. goes down.

In FIG. 2 b) shows the shift "M" of the upper panel relative to the bottom.

The shift is directed in the opposite direction (from right to left)

As a result of the shift, openings in the wing open. The flow enters the first hole, the reaction of which from the wing side is the force P3. The stream exits the wing duct to the outside. The reaction from the wing to the flow is the force P4.

Thus, there are active forces on the leading edge of the wing P3 and reactive forces on the trailing edge of the wing P4. These forces of different signs create a torque that can be used as a means to change the trajectory of L.A. Torque rotates the wing angle “β”. L.A. is taking off.

Under certain conditions, when the panels are wafer and interconnected without intermediate parts, such wings turn out to be more technological and the most advantageous in terms of weight.

1) Literature.

G. Zhitomirsky “Aircraft construction.” Mechanical engineering 1995. Page 148

Claims (1)

The wing of the aircraft, containing the upper and lower panels, characterized in that in order to increase the efficiency of controlling the flight path, the panels are made wafer and monolithic with ribs of the transverse set, oriented along the flow and protruding above the longitudinal ribs with the formation of overlap, sufficient for placement in the middle part of the wing on the transverse ribs of the upper panel of the protrusions included in the corresponding grooves on the edges of the lower panel and with the possibility of shifting the upper panel relative to the bottom.

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