helicopter

Abstract

The invention relates to: a fuselage (2) exposed to an airstream; at least one wing (3) arranged on the fuselage (2) and extending outwardly from the fuselage (2) and enabling ammunition and similar payloads to be placed to the wing; a rotor (R) generating aerodynamic lift and / or thrust required for the take-off of the fuselage (2); a tail fin (4) arranged on the fuselage (2) and extending outwardly from the fuselage (2) and providing balance during the movement of the fuselage (2).

Description

Technical Field

[0001] This invention relates to wings mounted on armed helicopters. Background Technology

[0002] Attack helicopters carry munitions and similar payloads via wings with low aspect ratios extending from their relatively narrow fuselages. In conventional designs, the impact of these wings on overall aerodynamic characteristics is designed to be minimized, while the wingspan is determined to be the minimum required to ensure safe separation. One of the major components of the total aerodynamic drag of an attack helicopter is the munitions-laden wing section. In this case, the munitions-laden wing accounts for a significant share of the airframe drag breakdown of the attack helicopter.

[0003] Unlike the load-bearing columns used in civilian helicopters modified for military operations to support external loads, in attack helicopters, ammunition and payloads (such as external fuel tanks) are carried by the wings. Compared to the fuselage of a civilian helicopter, the fuselage of an attack helicopter is narrower, with ammunition placed along the wingspan on the outer portions of the wings to ensure safe separation of the ammunition from the aircraft.

[0004] The prior art includes U.S. Patent No. 5,542,625, which describes an angle of dihedral between the inner portion of each wing segment and the fuselage, and an angle of dihedral between the outer portion of each wing segment and the inner portion, or alternatively, an angle of dihedral between the inner portion of each wing segment and the fuselage, and an angle of dihedral between the outer portion of each wing segment and the inner portion.

[0005] In another published patent document, EP2690011A1, a compound helicopter is disclosed for high-speed operation while ensuring high efficiency in terms of architectural integration, structural weight, aerodynamic performance, and compliance with operational and safety requirements. The helicopter includes a fuselage, an engine, and a main rotor driven by the engine. At least one pair of fixed wings are mounted on the left and right sides of the fuselage in a substantially horizontal plane, and horizontally oriented propulsion devices are mounted to each fixed wing, each of which includes a drive shaft from the engine. Each fixed wing includes a lower main wing and an upper aileron connected to each other in an interconnecting region. The lower main wing extends beyond the interconnecting region with the outer wing. The propulsion devices are arranged at the interconnecting region, and the upper aileron houses the drive shaft from the engine. Summary of the Invention

[0006] The helicopter developed using this invention enhances the helicopter's forward flight speed capability.

[0007] Another objective of this invention is to provide helicopters with the ability to operate with higher weight at high-density altitudes under hovering flight conditions.

[0008] Another objective of this invention is to save fuel when helicopters are performing missions.

[0009] The helicopter implemented to achieve the objectives of this invention comprises: a rotorcraft-type fuselage; ammunition, arranged on the fuselage to extend beyond the fuselage; a fuel tank; and more than one wing, connected to an onboard gun bay and similar payloads. The helicopter includes a rotor located on the fuselage, which enables the fuselage to move and utilizes the aerodynamic lift and thrust required to keep the fuselage airborne to generate control torque. The helicopter includes a horizontal tail, which ensures longitudinal stability of the fuselage during forward flight.

[0010] In the helicopter of the present invention, regarding the wing extending outward from the fuselage, the angle formed between the root portion of the wing and the ground is determined by the geometric value generated by the dihedral angle formed by the root portion of the wing. A positive dihedral angle indicates that the wing rises vertically in the wingspan direction. The helicopter includes a root region of the wing that extends outward with a dihedral angle from the portion where the wing connects to the fuselage. The angle between the tip portion of the wing and the ground is determined by the geometric value of the dihedral angle formed by the tip portion of the wing. A positive dihedral angle indicates that the wing descends vertically in the wingspan direction. The helicopter includes a tip region that extends downward with a dihedral angle from the root region. The helicopter includes an inverted V-shaped curved region located on the wing and connecting the root region to the tip region. The profile sections of the root region, tip region, and curved region on the wing are different from each other. The helicopter's wing design provides control and enhanced stability against aerodynamic interference from munitions and the horizontal tail by reducing the low-pressure wake region formed behind the wing.

[0011] In one embodiment of the invention, in a helicopter, the line connecting all midpoints between the upper and lower asymmetric surfaces along the chord of the wing profile is called the hump curve, and the ratio between the maximum vertical deviation of this curve from the chord line and the chord length is called the hump ratio. The hump ratio in the root region is greater than that in the bend region. The hump ratio in the tip region is greater than that in the bend region. The hump ratio in the tip region is greater than that in the root region. Based on the different hump ratios in the root, tip, and bend regions, the wing has different forms.

[0012] In one embodiment of the invention, the length of the chord line between the leading and trailing edges of the helicopter wing narrows from the root region to the tip region. The leading edge is the first part of the wing that comes into contact with the air, and the trailing edge is the part where the air leaves the wing.

[0013] In one embodiment of the invention, the helicopter includes two wings, which are longitudinally aligned with the center of the rotor on the fuselage, symmetrically positioned relative to the fuselage in the lateral direction, and located below the rotor on the vertical axis.

[0014] In one embodiment of the invention, the helicopter includes at least one air inlet that receives air required to trigger engine operation of the rotor. The helicopter includes a root region whose lower surface facing the air inlet rises substantially parallel to the lower surface.

[0015] In one embodiment of the invention, the helicopter includes two wings, wherein a horizontal tail on a tail cone is positioned nearly aligned with the waterline, and the horizontal tail is symmetrically arranged relative to the fuselage on a lateral axis.

[0016] In one embodiment of the invention, in a helicopter, the ideal midpoint of the angle at the root region, which is approximately 25°-32°, is where the dihedral angle is between 20°-45°. The ideal midpoint of the angle at the end region, which is approximately 25°-29°, is where the dihedral angle is between 0°-30°.

[0017] In one embodiment of the invention, the section from the wing to the fuselage up to the curved region is relatively short. The helicopter includes a curved region located at approximately 42% of its wingspan.

[0018] In one embodiment of the invention, the helicopter includes a fuselage suitable for armed purposes, which is narrow and nearly capable of accommodating only one pilot. The helicopter includes a narrow fuselage design with a nearly constant width along the waterline from the base of the fuselage to the center of the rotor.

[0019] In one embodiment of the invention, the helicopter includes a wing, with the end regions of the wing connected to munitions and similar loads. Attached Figure Description

[0020] The accompanying drawings illustrate a helicopter implemented to achieve the objectives of the present invention, wherein, in these drawings;

[0021] Figure 1 It's a 3D image of a helicopter.

[0022] Figure 2 This is a front view of a helicopter.

[0023] Figure 3 This is a top view of the wing.

[0024] Figure 4 This is a front view of the wing.

[0025] Figure 5 This is a cross-sectional profile analysis diagram of the root region.

[0026] Figure 6 This is a cross-sectional profile analysis diagram of the curved region.

[0027] Figure 7 This is a cross-sectional profile analysis diagram of the end region.

[0028] The parts shown in the accompanying drawings are individually designated with reference numerals, and the corresponding terms for these numbers are listed below.

[0029] 1. Helicopter

[0030] 2. Body

[0031] 3. Wings

[0032] 301. Root region

[0033] 302. End region

[0034] 303. Curved area

[0035] 4. Tail wing

[0036] 5. Air Inlet

[0037] 6. Horizontal tail fin

[0038] R rotor

[0039] K Camel Hump Line

[0040] V-wing chord

[0041] E-rotor axis Detailed Implementation

[0042] The helicopter 1 includes: a fuselage 2 exposed to airflow; at least one wing 3 disposed on the fuselage 2, extending outward from the fuselage 2 and enabling the placement of munitions and similar payloads thereon; a rotor R that generates aerodynamic lift and / or thrust required for takeoff of the fuselage 2; and a tail 4 disposed on the fuselage 2, extending outward from the fuselage 2 and providing balance during movement of the fuselage 2.

[0043] The helicopter 1 of the present invention includes: a root region 301 on a wing 3 extending from a fuselage 2 to form an upward dihedral angle; an end region 302 on the wing 3 extending from the root region 301 to form a downward dihedral angle with the fuselage 2; and a curved region 303 on the wing 3 located between the root region 301 and the end region 302, connecting the root region 301 and the end region 302 to each other, wherein the wing 3 is manufactured such that each of the root region 301, the end region 302 and the curved region 303 has a different profile cross section.

[0044] The helicopter includes: a fuselage 2; at least one wing 3 on the fuselage 2, extending outward from the fuselage 2 and carrying munitions and similar payloads; and a rotor R on the fuselage 2, enabling the fuselage 2 to move. The helicopter includes a tail 4, which ensures the stability of the fuselage 2 throughout flight. Since the wing 3 extends laterally outward from the fuselage 2 of the rotorcraft, it carries munitions, fuel tanks, and similar payloads. The helicopter includes: a rotor R, generating the aerodynamic lift and thrust required for takeoff of the fuselage 2; and a tail 4 on a cone-shaped structure on the fuselage 2, extending outward from the fuselage 2 and providing stability to the flight characteristics of the fuselage 2.

[0045] The helicopter includes: a root region 301 on the wing 3, extending from the fuselage 2 to form an upward dihedral angle; and a tip region 302 on the wing 3, connected to the root region 301 and extending from the root region 301 by forming a downward dihedral angle. The helicopter includes a curved region 303 on the wing 3 located between the root region 301 and the tip region 302, thereby connecting these two regions to each other. The helicopter includes a wing 3 manufactured such that each of the root region 301, the tip region 302, and the curved region 303 has a different form. Due to the curved form of the wing 3, more efficient airflow is provided, while simultaneously ensuring better flight performance, fuel savings, and higher speeds in forward flight, and reducing aerodynamic interference between the rotor R and the wing 3 during hovering to provide the ability to hover at higher weights.

[0046] In one embodiment of the present invention, the helicopter 1 includes a wing 3 having a profile section along a hump line K on the wing 3, wherein the hump ratio of the root region 301 is greater than that of the curved region 303, and the hump ratio of the tip region 302 is greater than that of the curved region 303. Because the hump ratio of the root region 301 is higher than that of the curved region 303, and the hump ratio of the tip region 302 is higher than that of the curved region 303, the wing 3 has more efficient aerodynamic performance under airflow.

[0047] In one embodiment of the invention, the helicopter 1 includes a wing 3, wherein the length of the chord line V between the leading and trailing edges of the wing 3 profile narrows from the root region 301 toward the end region 302. The length of the chord line V decreases from the root region 301 toward the end region 302.

[0048] In one embodiment of the invention, the helicopter 1 includes a wing 3 located on the fuselage 2 below the rotor R and aligned with the rotor axis E. The helicopter includes two wings 3, which are located on the fuselage 2 along a vertical axis below the rotor R and aligned longitudinally with the rotor axis E, and are symmetrically positioned on the fuselage 2 along a lateral axis. The curved shape of the wing 3 (inverted V-shape) improves aerodynamic interference between the wing 3 and the rotor R wake and provides better hovering performance.

[0049] In one embodiment of the invention, the helicopter 1 includes: at least one air inlet 5 on the fuselage 2 for obtaining air required for rotor R operation; and a root region 301, the surface of which faces the lower surface of the air inlet 5 extending nearly parallel to the lower surface. The wing 3 extends nearly parallel to the air inlet 5, providing enhanced aerodynamic performance.

[0050] In one embodiment of the invention, the helicopter 1 includes: at least one horizontal tail 6 located on the tail 4, providing balance during movement; and a wing 3 on the fuselage 2, positioned nearly aligned with the horizontal tail 6. The helicopter includes: at least one horizontal tail 6 located on the tail 4, providing longitudinal stability throughout flight; and a wing 3 on the fuselage 2, positioned in a waterline position nearly similar to the waterline position of the horizontal tail 6. This provides better flight performance due to the improved aerodynamic interference between the wing 3 and the horizontal tail 6.

[0051] In one embodiment of the invention, the helicopter 1 includes a root region 301 having an anhedral angle between 20° and 45° and an end region 302 having an anhedral angle between 0° and 30°. The fact that the anhedral angle is 25°–32° and the anhedral angle is 25°–29° ensures better flight performance.

[0052] In one embodiment of the invention, the helicopter 1 includes a wing 3, wherein a root region 301 is shorter than a tip region 302. The helicopter also includes a curved region 303 of the wing 3 located approximately 42% of the wingspan from the root region 301. Furthermore, the length of the root region 301 on the wing 3 is longer than the length of the tip region 302.

[0053] In one embodiment of the invention, the helicopter 1 includes a narrow fuselage 2 suitable for armed purposes, which can accommodate only one pilot.

[0054] In one embodiment of the invention, the helicopter 1 includes a wing 3 having an end portion 302 where munitions and similar payloads are housed. This ensures that the munitions can be safely separated without interacting with the fuselage 2.

Claims

1. A helicopter (1), comprising: The body (2) is exposed to airflow; At least one wing (3) is provided on the fuselage (2) and extends outward from the fuselage (2); The rotor (R) generates the aerodynamic lift and / or thrust required for the takeoff of the aircraft (2); The tail fin (4) is mounted on the fuselage (2), extends outward from the fuselage (2), and provides balance during the movement of the fuselage (2); The root region (301) located on the wing (3) extends from the fuselage (2) to form an upward dihedral. Its features are, The helicopter further includes: an end region (302) on the wing (3) extending from the root region (301) to form a dihedral angle with the fuselage (2); A curved region (303) is located on the wing (3) between the root region (301) and the end region (302), the curved region connecting the root region (301) and the end region (302) to each other. The wing (3) is adapted to allow a payload to be placed on the wing and is manufactured such that each of the root region (301), the end region (302) and the curved region (303) has a different profile section. The wing (3) has a profile section along a hump curve (K) on the wing (3), the hump curve being a line connecting all midpoints between the upper and lower asymmetric surfaces along the chord of the wing profile. The hump ratio is the ratio between the maximum vertical deviation of the hump curve (K) and the chord line and the chord length. The hump ratio of the root region (301) is greater than that of the curved region (303), and the hump ratio of the end region (302) is greater than that of the curved region (303). The root region (301) has an upper concave angle between 20° and 45°, and the end region (302) has a lower concave angle between 0° and 30°.

2. The helicopter (1) according to claim 1, characterized in that, For the wing (3), the length of the chord line (V) between the leading edge and the trailing edge of the wing (3) profile narrows from the root region (301) toward the end region (302).

3. The helicopter (1) according to claim 1, characterized in that, The wing (3) is located on the fuselage (2) below the rotor (R) so as to be aligned with the rotor axis (E).

4. The helicopter (1) according to any one of claims 1 to 3, characterized in that, The helicopter includes at least one air inlet (5) on the fuselage (2) for obtaining air required for the operation of the rotor (R), wherein a surface of the root region (301) facing the lower surface of the air inlet (5) extends parallel to the lower surface.

5. The helicopter (1) according to any one of claims 1 to 3, characterized in that, The helicopter includes at least one horizontal tail (6) on the tail (4), the at least one horizontal tail providing balance during movement, wherein the wing (3) located on the fuselage (2) is aligned with the horizontal tail (6).

6. The helicopter (1) according to any one of claims 1 to 3, characterized in that, The root region (301) of the wing (3) is shorter than the tip region (302) of the wing.

7. The helicopter (1) according to any one of claims 1 to 3, characterized in that, The helicopter is suitable for armed purposes and has a narrow fuselage (2) that can only accommodate one pilot.

8. The helicopter (1) according to any one of claims 1 to 3, characterized in that, The wing (3) has an end region (302) suitable for placing a payload.

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