Aircraft high-lift apparatus

Abstract

The present invention relates to an aircraft high-lift apparatus, which increases the lift of an aircraft such that the time required for takeoff and a runway length can be reduced. In order to implement this, the present invention may comprise: an air supply unit for supplying, to wings on both sides of a fuselage, air drawn in through an intake port of an aircraft; and an air spray unit having a plurality of spray nozzles so that the air supplied from the air supply unit can be sprayed in the direction from a leading edge to a trailing edge on the upper surface of the wing.

Description

High-lift devices for aircraft

[0001] The present invention relates to a high-lift device for an aircraft capable of increasing the lift of the aircraft.

[0002] [Korean Acknowledgements] This result was produced with support from the 2025 Gyeongsangbuk-do Regional Innovation Center University Support System (RISE)-(MEGAversity Alliance University).

[0003] [English Acknowledgments] This research was supported by the Gyeongsangbuk-do RISE (Regional Innovation System & Education) project[MEGAversity unit]

[0004]

[0005] Generally, lift refers to the mechanical force generated at the surface of an object perpendicular to the flow of fluid when fluid flows around the object.

[0006] For example, aircraft require high lift at relatively low speeds during takeoff. Since lift is proportional to speed, sufficient lift necessary for takeoff may not be generated at low speeds. Accordingly, a long runway and takeoff time are required to generate sufficient lift.

[0007] Accordingly, technology capable of increasing lift during aircraft takeoff is required.

[0008]

[0009] The present invention aims to solve the aforementioned problems and provides a high-lift device for an aircraft that increases the lift of the aircraft, thereby reducing the time required for takeoff and the runway length.

[0010]

[0011] A high-lift device for an aircraft according to the present invention for realizing the purpose described above may include: an air supply unit that supplies air sucked in through the intake port of the aircraft to wings on both sides of the fuselage; and an air injection unit equipped with a plurality of injection nozzles to inject the air supplied from the air supply unit in the direction from the leading edge to the trailing edge of the upper surface of the wing.

[0012] In this case, the air sucked in through the intake port may be supplied to the air injection unit through a flow path formed along the longitudinal direction of the leading edge of the wing.

[0013] In addition, the above injection nozzles may include a plurality of spaced-apart nozzles arranged along the longitudinal direction of the flow path.

[0014] In addition, the above injection nozzle may include being disposed on an installation surface formed with a downward step from the leading edge to the trailing edge of the upper surface of the wing.

[0015] In addition, the outer surface of the above-mentioned installation surface may further include a streamlined cover installed to minimize air resistance.

[0016] In addition, the cover is installed such that one side is pivotally hinged to the installation surface and can be opened and closed by receiving power, thereby allowing the amount of air sprayed through the spray nozzle to be controlled according to the degree of opening and closing of the cover.

[0017] In addition, the above-mentioned Euro further includes a heater that heats the air supplied to the air injection unit, thereby preventing freezing of the leading surface.

[0018]

[0019] The high-lift device for an aircraft according to the present invention, configured as described above, can increase the lift of an aircraft by applying a structure that injects air from the leading edge to the trailing edge of the upper surface of the wing, and thereby reduce the time required for the aircraft's takeoff and the runway length.

[0020]

[0021] FIG. 1 is a front view of an aircraft equipped with a high-lift device for an aircraft according to the present invention.

[0022] FIG. 2 is a partial enlarged view of a wing equipped with an air injection unit according to the present invention.

[0023] FIG. 3 is a cross-sectional view along line I-I' of FIG. 1 and a partial detail view,

[0024] FIGS. 4 and FIGS. 5 are enlarged views and operating state views of a part with a cover applied to an air injection part according to the present invention.

[0025]

[0026] ※Explanation of symbols※

[0027] 10 : Aircraft 11 : Fuselage

[0028] 13 : Wing 13a : Leading edge

[0029] 13b : trailing edge 13c : mounting surface

[0030] 100: Aircraft high-lift device 110: Air supply unit

[0031] 111 : Intake 113 : Euro

[0032] 120: Air injection section 121: Injection nozzle

[0033] 123 : Cover 123a : Hinge

[0034] 125 : Heater

[0035]

[0036] The configuration and operation of a specific embodiment of the present invention will be described in detail below with reference to the attached drawings.

[0037] Here, it should be noted that when assigning reference numerals to the components of each drawing, identical components are denoted by the same numeral whenever possible, even if they are shown on different drawings.

[0038] FIG. 1 is a front view of an aircraft equipped with a high-lift device for an aircraft according to the present invention, and FIG. 2 is a partial enlarged view of a wing equipped with an air injection unit according to the present invention.

[0039] Referring to FIG. 1, a high-lift device (100) for an aircraft according to a preferred embodiment of the present invention may include an air supply unit (110) and an air injection unit (120).

[0040] The configuration of the present invention is described in detail as follows.

[0041]

[0042] First, the air supply unit (110) can supply air sucked in through the intake port (111) formed on the front of the aircraft (10) to the wings (13) on both sides of the fuselage (11).

[0043] In this case, the intake port (111) may be formed at a predetermined point on the fuselage (11) or wing (13). That is, the intake port (111) can be applied in various ways as long as it is in a location where external air can be smoothly drawn in, and accordingly, the present invention does not specifically limit the location where the intake port (111) is formed.

[0044] The air sucked in through the above intake port (111) can be supplied to the air injection unit (120) to be described later through the flow path (113) formed along the internal longitudinal direction of the leading edge (13a) of the wing (13).

[0045] In addition, the intake port (111) may be equipped with a fan that receives power and rotates to smoothly supply the inhaled air to the air injection unit (120) described later. The fan may also control the flow rate of the air injected through the air injection unit (120) described later.

[0046]

[0047] Referring to FIG. 2, the air injection unit (120) may be equipped with a plurality of injection nozzles (121) so as to inject air supplied through the air passage (113) of the air supply unit (110) from the leading edge (13a) to the trailing edge (13b) of the upper surface of the wing (13).

[0048] In this case, the above injection nozzles (121) may be spaced apart along the longitudinal direction of the flow path (113) provided at the leading edge (13a) of the wing.

[0049] The air injection unit (120) of this structure can inject air at a predetermined speed onto the upper surface of the wing (13) to increase the upper flow, thereby causing the pressure on the upper surface of the wing (13) to be lower than that on the lower surface of the wing (13). That is, the present invention can increase the lift force during the takeoff of the aircraft (10) by creating a greater pressure difference between the upper and lower surfaces of the wing (13) through the air injection unit (120).

[0050] Referring to FIG. 3, the air injection unit (120) can be positioned on an installation surface (13c) formed downwardly from the leading edge (13a) to the trailing edge (13b) on the upper surface of the wing (13) so that the injection nozzle (121) is not exposed on the surface of the wing (13).

[0051] That is, the above-mentioned mounting surface (13c) is positioned to face the trailing edge (13b), and as the injection nozzle (121) is installed on this mounting surface (13c), the structure of the injection nozzle (121) may not obstruct the flow of fluid during the operation of the aircraft (10).

[0052] Referring to FIG. 4, a streamlined cover (123) may be installed on the outer perimeter of the installation surface (13c) to cover and conceal the spray nozzle (121) and to minimize air resistance.

[0053] In this case, the cover (123) can be installed so that one side is rotatably connected to the installation surface (13c) by a hinge (123a) and can be opened and closed by receiving power from an actuator (not shown). Accordingly, the lift force can be controlled by adjusting the amount of air sprayed through the spray nozzle (121) according to the degree of opening (t) (see FIG. 5) of the cover (123).

[0054]

[0055] Referring again to FIG. 1, the air supply section (110) may be equipped with a heater (125) that heats the air supplied to the air injection section (120) after it is introduced through the intake port (111). Accordingly, it is possible to prevent ice formation on the leading edge (13a) surface during the operation of the aircraft (10).

[0056]

[0057] The high-lift device (100) for an aircraft according to the present invention, having the configuration as described above, can increase the lift of the aircraft by applying a structure that sprays air from the leading edge to the trailing edge of the upper surface of the wing, and accordingly, can reduce the time required for the aircraft's takeoff and the runway length.

[0058]

[0059] Although the present invention has been illustrated and described above with specific embodiments, the present invention is not limited to the embodiments described above, and it is understood that various changes and modifications are possible within the scope of the technical spirit of the present invention.

Claims

1. An air supply unit that supplies air sucked in through the aircraft's intake to the wings on both sides of the fuselage; and An aircraft high-lift device comprising: an air injection unit equipped with a plurality of injection nozzles to inject air supplied from the air supply unit in the direction from the leading edge to the trailing edge of the upper surface of the wing.

2. In Paragraph 1, The air sucked in through the above intake port is, A high-lift device for an aircraft comprising supplying air to the air injection unit through a channel formed along the longitudinal direction of the leading edge of the wing.

3. In Paragraph 2, The above-mentioned spray nozzle is, A high-lift device for an aircraft comprising a plurality of spaced-apart units arranged along the longitudinal direction of the above-mentioned Euro.

4. In Paragraph 1, The above-mentioned spray nozzle is, A high-lift device for an aircraft comprising a mounting surface formed with a downward step from the leading edge toward the trailing edge of the upper surface of the wing.

5. In Paragraph 4, On the outer perimeter of the above-mentioned installation surface, A high-lift device for an aircraft, further comprising a streamlined cover installed to minimize air resistance.

6. In Paragraph 5, The above cover is, Including one side of which is hinge-connected to the above-mentioned installation surface so as to be rotatable, and installed to be openable and closable by receiving power, An aircraft high-lift device capable of controlling the amount of air sprayed through the spray nozzle according to the degree of opening or closing of the above cover.

7. In Paragraph 2, In the above Euro, A heater for heating the air supplied to the air injection unit; further comprising A high-lift device for an aircraft that prevents icing on the leading edge surface.

Images