CN115649454A - Hot air anti-icing structure for front edge of wing - Google Patents

Abstract

The invention belongs to the technical field of structural design of aviation technology, and relates to a hot air anti-icing structure for a front edge of a wing. The method comprises the following steps: covering (1), wave plate (2), trabecula (3), first enhancement section bar (4), baffle (5), heat insulating board (6), wave plate (2) cross-section is the wave form, the trough position of wave plate (2) is fixed with covering (1), form the gas circuit along the course direction between crest and the covering, trabecula (3) are platelike bearing structure, trabecula (3) are arranged and perpendicular with the course along span direction, both ends all are connected with covering (1) about trabecula (3), trabecula (3) divide into preceding air chamber and back air chamber with the wing leading edge, baffle (5) are arranged along the course, both sides all are connected with covering (1) about baffle (5), baffle (5) rear end is connected with two first enhancement section bar (4) respectively, all laid heat insulating board (6) on preceding air chamber interior wave plate (2) and trabecula (3). Strong bird collision resistance and good anti-icing performance.

Description

Hot air anti-icing structure for front edge of wing

Technical Field

The invention belongs to the technical field of aviation technical structure design, and relates to a wing leading edge hot air anti-icing structure.

Background

The wings are main components for generating lift force of the airplane, the wing leading edges are also an aerodynamic area, the requirement on the shape deviation is very high, and the wing leading edges are easy to freeze under the high-altitude condition, so that the shape deviation can be caused, and the flying quality and the flying safety are influenced. In order to improve the safety and reliability of the airplane, the bird impact resistance of the front edge of the wing needs to be improved, but the anti-icing effect of the front edge cannot be reduced.

Disclosure of Invention

The purpose of the invention is as follows: the front edge structure has the advantages of strong bird impact resistance and good anti-icing performance.

The technical scheme is as follows:

a wing leading edge hot air anti-icing structure comprising: the corrugated plate comprises a covering 1, a corrugated plate 2, a trabecula 3, two first reinforcing section bars 4, a partition plate 5 and a heat insulation plate 6, wherein the section of the corrugated plate 2 is in a corrugated shape, the trough position of the corrugated plate 2 is fixed with the covering 1, an air path in the course direction is formed between the wave crest and the covering, the trabecula 3 is of a plate-shaped supporting structure, the trabecula 3 is arranged in the span direction and is perpendicular to the course direction, the upper end and the lower end of the trabecula 3 are connected with the covering 1, the front edge of the wing is divided into a front air chamber and a rear air chamber by the trabecula 3, the partition plate 5 is arranged in the course direction, the upper side and the lower side of the partition plate 5 are connected with the covering 1, the rear end of the partition plate 5 is connected with the two first reinforcing section bars 4 respectively, and the heat insulation plate 6 is laid on the corrugated plate 2 and the trabecula 3 in the front air chamber.

Further, a weight reduction groove is formed in one side of the small beam 3.

Furthermore, the corrugated plate 2 is formed by overlapping a plurality of sections along the spanwise direction, and each section is formed by butt joint of an upper section and a lower section at the end part of the front edge in a gap mode.

Further, the trabecula 3 is divided into a plurality of sections in the extending direction for butt joint.

Further, the partition 5 includes an end partition for splicing leading edge sections of the wings and a middle partition for supporting leading edge wing shapes.

Further, the heat insulation board 6 is segmented along the spreading direction, and the segments are bonded by glue X98-14.

Further, the gap between the butt seams of the upper corrugated plate and the lower corrugated plate is 10mm.

Further, the thickness of the corrugated plate 2 is 0.5mm, the corrugations of the aluminum plate are perpendicular to the course, a plurality of wave crests and wave troughs are arranged in the spanwise direction, the corrugations are variable in cross section in the chord direction, the corrugated plate 2 is connected with the front beam of the wing, the wave troughs of the corrugations are changed into tongue-shaped edges and are connected with two T-shaped first reinforcing section bars 4 of the front edge, the wave crests are opened to form hot air outlets, and therefore air flows to the rear air chamber.

Has the advantages that:

the invention provides a hot air anti-icing structure for a leading edge of a wing, which utilizes tail gas of an engine to heat inner and outer skins of the leading edge of the wing in the whole range through a proper leading edge structure form so as to achieve the aim of anti-icing; in addition, the thickness of the front edge trabecula is increased for strengthening, and the bird impact resistance of the front edge of the wing is improved.

Drawings

FIG. 1 is a theoretical front edge hot air anti-icing diagram;

FIG. 2 is a schematic view of a leading edge hot air anti-icing arrangement;

fig. 3 is a sectional view taken along line AA in fig. 2.

Wherein: 1. the composite plate comprises a covering, 2. A corrugated plate, 3. A small beam, 4. A first reinforcing section bar, 5. A clapboard, 6. A heat insulation plate and 7. A second reinforcing section bar.

Detailed Description

In order to ensure the safe flight of the airplane under various complex meteorological conditions, a hot air ice (ice) preventing system is arranged in the wing leading edge, so that the wing leading edge is required to be designed into a structural form which is favorable for preventing (removing) ice. Referring to fig. 1-3, the leading edge of the wing is mainly a riveted structure composed of an upper reinforcing section 4 and a lower reinforcing section 4 with a skin 1 and a T-shaped section, a corrugated plate 2, a trabecula 3, a rack, a clapboard 5, an inspection opening cover, a thermal insulation plate 6 (a coating layer) and the like. The front edge is divided into a front air chamber and a rear air chamber by the trabecula 3, hot air output by an engine from a heat source is introduced into the front air chamber, a heat insulation plate (coating layer) of the front air chamber is used for heat insulation, so that the temperature of the hot air in the front air chamber is kept basically unchanged from the wing root to the wing tip, the front air chamber is a main anti-icing area, the hot air flows to the rear air chamber from the front air chamber of the wing front edge through a wave crest gap formed by the front edge wave-shaped plate and the outer skin, and the outer skin of the wing front edge is heated, so that the anti-icing purpose is achieved. Due to the requirement of a battle mission, the airplane mostly flies at low altitude on the sea surface, the probability of being hit by flying birds is high, and the thickness of the small beam 3 is thickened.

As shown in FIG. 2, the wing leading edge hot air anti-icing structure comprises a leading edge outer skin 1, a corrugated plate 2, a trabecula 3, a reinforcing section bar 4, a supporting clapboard 5 and a heat insulation plate 6; the corrugated plate 2 is formed by overlapping a plurality of sections in the spanwise direction, and each section is formed by butting the upper and lower sections at the end part of the front edge; the small beam 3 is formed by bending aluminum plates with different thicknesses and is formed by butt joint of a plurality of sections along the unfolding direction; the reinforcing section bar 4 is arranged at the upper wing surface and the lower wing surface and is formed by butt joint of a plurality of sections along the spanwise direction; the supporting partitions 5 are arranged in number along the exhibit; the heat insulation plate 6 is arranged at the theoretical shape of the front air chamber and the plane of the small beam of the front air chamber, and is formed by bonding X98-14 glue solution at the subsection along the spanwise direction.

The skin 1 is an aluminum plate with the thickness of 1mm, maintains the theoretical shape of the wing, and is connected with the corrugated plate 2; the gap between the butt seams of the upper corrugated plate and the lower corrugated plate is 10mm, the corrugated plate 2 is an aluminum plate with the thickness of 0.5mm, the corrugations are perpendicular to the front beam, a plurality of wave crests and wave troughs are arranged along the spanwise direction, the corrugations are variable in section along the chord direction, and from the wave troughs to the front beam of the wing, the wave troughs of the corrugations are changed into tongue-shaped edges and are connected with T-shaped upper and lower reinforcing sectional materials of the front edge, the wave crests are opened, and hot air outlets are formed; a trabecula is arranged in the front edge, the trabecula is formed by bending a plurality of layers of aluminum plates with different thicknesses, the front edge is divided into a front air chamber and a rear air chamber, cushion blocks are arranged between the trabecula and the wave troughs of the wave-shaped plate, and the gap between the trabecula and the wave-shaped plate is blocked by glass cloth rolled with X98-14 acetal glue hydraulic pressure so as to prevent hot air leakage; the heat insulation plates made of glass cloth laminated plates with the thickness of 0.5mm are arranged in the front air chamber along the inner side of the corrugated plate and on the trabecula, certain gaps are formed between the heat insulation plates and the trabecula and between the heat insulation plates and the corrugated plate, and the heat insulation plates have the function of keeping the temperature of hot air in the front air chamber from wing roots to wing tips basically unchanged; the reinforcing section bar 4 and the supporting clapboard 5 are both made of aluminum alloy materials and are used for supporting the front edge.

When the front edge of the wing is frozen, hot air output by an engine is introduced into a front air chamber of the front edge (the temperature of the front air chamber is basically the same from the wing root to the wing tip under the action of a heat insulation plate of the front air chamber), the hot air enters a gap between the heat insulation plate and the corrugated plate from the front air chamber along the course direction, then enters a wave crest between the corrugated plate and the skin through a butt seam gap of the corrugated plate at the front edge, enters the nose end of the front edge, and finally flows into a rear air chamber through the wave crest between the skin and the corrugated plate; the hot air flows from the wing root to the wing tip along the exhibition, and is exhausted into the atmosphere from the wing tip through the front beam opening to the outer wing lower wall shutter, so that the outer skin of the front edge of the wing is heated, and the anti-icing purpose is achieved. In addition, the thickness of the front edge trabecula is increased for strengthening, and the bird impact resistance of the front edge of the wing is improved.

Claims (8)

1. A wing leading edge hot air anti-icing structure, comprising: the wing comprises a covering (1), a corrugated plate (2), a trabecula (3), two first reinforcing section bars (4), a partition plate (5) and a heat insulation plate (6), wherein the section of the corrugated plate (2) is corrugated, the trough position of the corrugated plate (2) is fixed with the covering (1), a gas circuit along the course direction is formed between a wave crest and the covering, the trabecula (3) is of a plate-shaped supporting structure, the trabecula (3) is arranged along the span direction and is vertical to the course, the upper end and the lower end of the trabecula (3) are both connected with the covering (1), the front edge of the wing is divided into a front air chamber and a rear air chamber by the trabecula (3), the partition plate (5) is arranged along the course, the upper side and the lower side of the partition plate (5) are both connected with the covering (1), the rear end of the partition plate (5) is respectively connected with the two first reinforcing section bars (4), and the heat insulation plate (6) is laid on the corrugated plate (2) and the trabecula (3) in the front air chamber.

2. The wing leading edge hot air anti-icing structure of claim 1, characterized in that the side of the trabecula (3) is provided with a lightening slot.

3. The wing leading edge hot air anti-icing structure of claim 1, characterized in that the corrugated plate (2) is divided into a plurality of overlapping sections along the spanwise direction, and each section is formed by butt joint of an upper piece and a lower piece at the end part of the leading edge in a gap.

4. The wing leading edge hot air anti-icing structure of claim 1, characterized in that the trabecula (3) is butt-jointed by being divided into several sections in the spanwise direction.

5. The leading edge hot air anti-icing structure of claim 1, wherein the bulkhead (5) comprises an end bulkhead for splicing leading edge segments of the respective airfoils and a mid-section bulkhead for supporting the leading edge airfoils.

6. The wing leading edge hot air anti-icing structure according to claim 1, characterized in that the insulation panels (6) are segmented spanwise and are bonded between the segments with an X98-14 glue.

7. The airfoil leading edge hot air anti-icing structure of claim 1, wherein the upper and lower corrugated plates have a butt-joint gap of 10mm.

8. The wing leading edge hot air anti-icing structure of claim 1, characterized in that the corrugated plate (2) is an aluminum plate with the thickness of 0.5mm, the corrugation is perpendicular to the course direction, a plurality of wave crests and wave troughs are arranged along the spanwise direction, the corrugation is of a variable cross section along the chordwise direction, the wave troughs of the corrugation are changed into tongue-shaped edges at the position of the wing front beam, the wave crests are connected with two T-shaped first reinforcing section bars 4 at the leading edge, the wave crests are opened, and an outlet for hot air is formed, so that the air flows to the rear air chamber.

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