Eddy current array generator of light moving aircraft

Abstract

The utility model discloses an eddy current array generator of a light moving aircraft, which comprises an aircraft fuselage, two aircraft wings are symmetrically fixed on two sides of the aircraft fuselage, and four groups of eddy current generator components are fixedly mounted on two side surfaces of the aircraft fuselage and close to wing roots of the aircraft wings. The four vortex generator assemblies on the two sides of the aircraft fuselage are symmetrically arranged. According to the utility model, the triangular vortex generator a with the filleted corners, the rectangular vortex generator b with the filleted corners, the rectangular vortex generator c with the filleted corners and the rectangular vortex generator d with the filleted corners are arranged, so that the airflow flowing characteristic at the cross-linking part of the wings and the fuselage of the light moving aircraft is improved, and the airflow separation of the wings is delayed when the aircraft flies at a low speed; stall is delayed, and the stall speed is reduced; pilots and passengers can fly up and down conveniently, and efficiency is improved; the crosswind resistance of the aircraft during low-speed flight is improved, and the transverse course stability is improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a vortex array generator for a light sport aircraft. Background Technology

[0002] Light sport aircraft are two-seat, single-engine aircraft that are characterized by high cost-effectiveness, low entry barriers, easy maintenance, and flexible operation. They are used in popular scenarios such as air sports, private recreation, in-flight experiences, and private pilot training, and are an indispensable and important part of the general aviation industry.

[0003] Aircraft configurations include three wing-body layouts: high-wing, mid-wing, and low-wing. Considering factors such as overall aircraft layout, structural design, operation and maintenance, overall aesthetics, and flight performance, light sport aircraft primarily use high-wing and low-wing configurations. In low-wing configurations, the wing is positioned under the fuselage, and the airflow at the upper surface of the wing root is significantly affected by the fuselage sidewalls. During high angles of attack, combined with the influence of the fuselage sidewalls, turbulent airflow separation occurs at the wing root, causing premature loss of lift and increased drag. This directly impacts flight stability and safety, and exacerbates the problem at sideslip angles. Without altering the wing-body configuration, adding vortex generators is the best way to optimize airflow and delay airflow separation. This can improve the lift coefficient, reduce stall speed, and improve low-speed characteristics. The deployment of vortex generators on the surfaces of many aircraft wings is widely used.

[0004] Traditional vortex generators are structures mounted on the wings to optimize the airflow boundary layer characteristics of the wing surface. They work by introducing high-speed airflow from outside the wing's boundary layer into slower airflow inside, altering the airflow characteristics near the boundary layer and improving airflow resistance to separation. In low-wing monoplane light sport aircraft, the airflow at the wing root-fuselage junction is significantly affected by the fuselage's surrounding airflow. Even slight sideslip can exacerbate airflow separation at the leeward side of the wing root, affecting the aircraft's lateral characteristics. Furthermore, in low-wing monoplane light sport aircraft, pilots and passengers access the cockpit by stepping from the ground to the wing root, landing, and then stepping into the cockpit. The conventional approach of placing vortex generators at the wing root is problematic because they are easily damaged by footsteps or hinder the pilot's and passenger's boarding and disembarking, and also detracts from the aircraft's aesthetics. Utility Model Content

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing a vortex array generator for lightweight sport aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a vortex array generator for a light sport aircraft, comprising an aircraft fuselage, two aircraft wings symmetrically fixed on both sides of the aircraft fuselage, and four sets of vortex generator assemblies fixedly installed on both sides of the aircraft fuselage near the wing roots. The four sets of vortex generator assemblies on both sides of the aircraft fuselage are symmetrically arranged, and the four sets of vortex generator assemblies include a triangular vortex generator a with rounded corners, a rectangular vortex generator b with rounded corners, a rectangular vortex generator c with rounded corners, and a rectangular vortex generator d with rounded corners.

[0007] Furthermore, the triangular vortex generator a with rounded corners includes a first base and a body of the triangular vortex generator a with rounded corners. The body of the triangular vortex generator a with rounded corners is fixed to the surface of the first base. The first base is fixed to the surface of the aircraft fuselage and close to the leading edge of the wing root of the aircraft. The first base is located at the transition and fusion point between the side and bottom surfaces of the aircraft fuselage. The connection point between the first base and the body of the triangular vortex generator a with rounded corners is contoured to the transition and fusion point of the aircraft fuselage.

[0008] Furthermore, the rectangular vortex generator b with rounded corners includes a second base and a rectangular vortex generator b body with rounded corners, and the rectangular vortex generator b body with rounded corners is fixed to the surface of the second base. The rectangular vortex generator c with rounded corners includes a third base and a rectangular vortex generator c body with rounded corners, and the rectangular vortex generator c body with rounded corners is fixed to the surface of the third base. The second base and the third base are fixed at the bulge where the aircraft wing and the aircraft fuselage transition, and the second base and the third base span the boundary line between the bulge and the side wall of the aircraft fuselage. The boundary line between the second base and the third base and the bulge is contoured.

[0009] Furthermore, the rectangular vortex generator d with rounded corners includes a fourth base and a rectangular vortex generator d body with rounded corners, and the rectangular vortex generator d body with rounded corners is fixed to the surface of the fourth base. The fourth base is fixed to the rear end of the transition bulge between the aircraft wing and the aircraft fuselage and is located on the upper surface of the bulge. The shape of the fourth base is contoured to the boundary line between the bulge and the shape of the fourth base.

[0010] Furthermore, the height of the triangular vortex generator a with rounded corners is 127mm-134mm, and the heights of the rectangular vortex generators b, c, and d with rounded corners are 33mm-42mm.

[0011] Furthermore, the four sets of vortex generator components are at an angle α with the horizontal plane, the angle α being within the range of ±25 degrees, and the four sets of vortex generator components are perpendicular to the aircraft fuselage symmetry plane in their height direction.

[0012] Furthermore, the sweep angle of the leading edge of the body strip of the triangular vortex generator a with rounded corners is 150°-155°.

[0013] The beneficial effects of this utility model are:

[0014] In use, this utility model provides a vortex array generator for light sport aircraft, comprising a triangular vortex generator a with rounded corners, a rectangular vortex generator b with rounded corners, a rectangular vortex generator c with rounded corners, and a rectangular vortex generator d with rounded corners. This improves the airflow characteristics at the wing-fuselage interface of the light sport aircraft, delaying airflow separation at low speeds, thus delaying stall and reducing stall speed. It also facilitates takeoff and landing for pilots and passengers, improving efficiency, and enhances the aircraft's resistance to crosswinds and lateral stability during low-speed flight. Attached Figure Description

[0015] To more clearly illustrate the technical solution of this utility model, the drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 : Axial view of the mounting position of the eddy current generator array of this utility model;

[0017] Figure 2 : A top view of the installation position of the eddy current generator array of this utility model;

[0018] Figure 3 Axial side view of the triangular vortex generator with rounded corners of this utility model;

[0019] Figure 4 A side view of the rectangular eddy current generator with rounded corners of this utility model (b-axis view).

[0020] Figure 5 A c-axis side view of the rectangular eddy current generator with rounded corners of this utility model;

[0021] Figure 6 : A d-axis side view of the rectangular eddy current generator with rounded corners of this utility model.

[0022] The attached figures are labeled as follows:

[0023] 1. Triangular vortex generator a with rounded corners; 101. First base; 102. Body of triangular vortex generator a with rounded corners; 2. Rectangular vortex generator b with rounded corners; 201. Second base; 202. Body of rectangular vortex generator b with rounded corners; 3. Rectangular vortex generator c with rounded corners; 301. Third base; 302. Body of rectangular vortex generator c with rounded corners; 4. Rectangular vortex generator d with rounded corners; 401. Fourth base; 402. Body of rectangular vortex generator d with rounded corners; 5. Aircraft fuselage; 6. Aircraft wing. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0025] like Figures 1-6 As shown, a vortex array generator for a light sport aircraft is disclosed, comprising an aircraft fuselage 5, two aircraft wings 6 symmetrically fixed on both sides of the aircraft fuselage 5, and four sets of vortex generator assemblies fixedly installed on both sides of the aircraft fuselage 5 near the wing roots of the aircraft wings 6. The four sets of vortex generator assemblies on both sides of the aircraft fuselage 5 are symmetrically arranged, and the four sets of vortex generator assemblies include a triangular vortex generator a1 with rounded corners, a rectangular vortex generator b2 with rounded corners, a rectangular vortex generator c3 with rounded corners, and a rectangular vortex generator d4 with rounded corners.

[0026] The triangular vortex generator a1 with rounded corners includes a first base 101 and a triangular vortex generator a body 102 with rounded corners. The triangular vortex generator a body 102 with rounded corners is fixed to the surface of the first base 101. The first base 101 is fixed to the surface of the aircraft fuselage 5 and close to the leading edge of the wing root of the aircraft wing 6. The first base 101 is located at the transition and fusion point between the side and bottom surfaces of the aircraft fuselage 5. The connection point between the first base 101 and the triangular vortex generator a body 102 with rounded corners is contoured to the transition and fusion point of the aircraft fuselage 5.

[0027] The aircraft fuselage 5 is a conventional low-wing light sport aircraft configuration, meaning that the aircraft wing 6 is located below the aircraft fuselage 5. The front, middle, and rear sections of the aircraft fuselage 5 form a streamlined shape that gradually thickens and then tapers again. During high angle-of-attack flight, the upward airflow from the bottom of the front fuselage expands to the sides of the fuselage as the airflow flows from the nose towards the middle of the fuselage, generating lateral velocity. The bottom airflow and the airflow with lateral velocity merge with the airflow that accelerates towards the rear of the fuselage from the upper surface of the wing root. The three airflows converge at the roots of the aircraft fuselage 5 and the wing 6, making the airflow extremely prone to turbulence and separation. This phenomenon is exacerbated during sideslip, resulting in poor wing root lift efficiency and poor low-speed performance of the aircraft.

[0028] The rectangular vortex generator b2 with rounded corners includes a second base 201 and a rectangular vortex generator b body 202 with rounded corners, and the rectangular vortex generator b body 202 with rounded corners is fixed to the surface of the second base 201. The rectangular vortex generator c3 with rounded corners includes a third base 301 and a rectangular vortex generator c body 302 with rounded corners, and the rectangular vortex generator c body 302 with rounded corners is fixed to the surface of the third base 301. The second base 201 and the third base 301 are fixed at the bulge where the aircraft wing 6 and the aircraft fuselage 5 transition, and the second base 201 and the third base 301 span the boundary line between the bulge and the side wall of the aircraft fuselage 5, and the boundary line between the second base 201 and the third base 301 and the bulge is contoured.

[0029] The rectangular vortex generator d4 with rounded corners includes a fourth base 401 and a rectangular vortex generator d body 402 with rounded corners. The rectangular vortex generator d body 402 with rounded corners is fixed to the surface of the fourth base 401. The fourth base 401 is fixed to the rear end of the transition bulge between the aircraft wing 6 and the aircraft fuselage 5 and is located on the upper surface of the bulge. The shape of the fourth base 401 is contoured to the boundary line between the bulge and the wing 6.

[0030] In this embodiment, when the aircraft is flying at a high angle of attack, the nose is slightly tilted upwards. The airflow under the aircraft fuselage 5 and the airflow on both sides of the aircraft fuselage 5 converge at the triangular vortex generator a1 with rounded corners. Under the influence of the triangular vortex generator a1 with rounded corners, high-energy airflow is introduced into the airflow boundary layer behind it, increasing the airflow energy on the upper surface of the wing root, suppressing and delaying airflow separation. The airflow continues to flow to the rectangular vortex generator b2, rectangular vortex generator c3 and rectangular vortex generator d4 with rounded corners, thereby accelerating the boundary layer airflow, delaying airflow separation at the trailing edge of the wing, and affecting the downwash of the airflow at the rear of the aircraft wing 6. Ultimately, it delays the airflow separation at the wing root of the entire aircraft wing 6, which plays a role in delaying stall and improving lift efficiency, increasing the lift coefficient and stall angle of attack of the entire aircraft, and reducing the stall speed.

[0031] The triangular vortex generator a1 with rounded corners has a height of 127mm-134mm, while the rectangular vortex generators b2, c3, and d4 with rounded corners have a height of 33mm-42mm.

[0032] In this embodiment, the triangular vortex generator a1 with rounded corners has a height of 127mm, and the rectangular vortex generators b2, c3, and d4 with rounded corners have a height of 33mm.

[0033] The four vortex generator assemblies are at an angle α with the horizontal plane, with an angle α range of ±25 degrees. The four vortex generator assemblies are perpendicular to the 5-plane of symmetry of the aircraft fuselage in their height direction.

[0034] In this embodiment, the four sets of eddy current generator components are at an angle α of 25 degrees to the horizontal plane.

[0035] The sweep angle of the leading edge of the 102 side strip of the triangular vortex generator with rounded corners is 150°-155°.

[0036] In this embodiment, the sweep angle of the leading edge of the side strip of the triangular vortex generator a body 102 with rounded corners is 150°.

[0037] The base of the four eddy current generator components is fixedly connected to the eddy current generator body, and is not limited to common bonding, riveting, screwing or direct one-piece forming connection.

[0038] The triangular vortex generator a body 102 with rounded corners, the rectangular vortex generator b body 202 with rounded corners, the rectangular vortex generator c body 302 with rounded corners, and the rectangular vortex generator d body 402 with rounded corners are respectively composed of triangular and rectangular sheet-like structures with rounded corners.

[0039] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to any specific implementation. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A vortex array generator for a light sport aircraft, comprising an aircraft fuselage (5), characterized in that: Two aircraft wings (6) are symmetrically fixed on both sides of the aircraft fuselage (5). Four sets of vortex generator assemblies are fixedly installed on both sides of the aircraft fuselage (5) and near the wing root of the aircraft wings (6). The four sets of vortex generator assemblies on both sides of the aircraft fuselage (5) are symmetrically arranged. The four sets of vortex generator assemblies include a triangular vortex generator a (1) with rounded corners, a rectangular vortex generator b (2) with rounded corners, a rectangular vortex generator c (3) with rounded corners, and a rectangular vortex generator d (4) with rounded corners.

2. The vortex array generator for a light sport aircraft according to claim 1, characterized in that: The rounded-corner triangular vortex generator a (1) includes a first base (101) and a rounded-corner triangular vortex generator a body (102). The rounded-corner triangular vortex generator a body (102) is fixed to the surface of the first base (101). The first base (101) is fixed to the surface of the aircraft fuselage (5) and close to the leading edge of the wing root of the aircraft wing (6). The first base (101) is located at the transition and fusion point between the side and bottom surfaces of the aircraft fuselage (5). The connection point between the first base (101) and the rounded-corner triangular vortex generator a body (102) is contoured to the transition and fusion point of the aircraft fuselage (5).

3. The vortex array generator for a light sport aircraft according to claim 1, characterized in that: The rectangular vortex generator b (2) with rounded corners includes a second base (201) and a rectangular vortex generator b body (202) with rounded corners, and the rectangular vortex generator b body (202) with rounded corners is fixed to the surface of the second base (201). The rectangular vortex generator c (3) with rounded corners includes a third base (301) and a rectangular vortex generator c body (302) with rounded corners, and the rectangular vortex generator c body (302) with rounded corners is fixed to the surface of the third base (301). The second base (201) and the third base (301) are fixed at the bulge where the aircraft wing (6) and the aircraft fuselage (5) transition, and the second base (201) and the third base (301) span the boundary line between the bulge and the side wall of the aircraft fuselage (5). The second base (201) and the third base (301) are contoured at the boundary line between the bulge and the bulge.

4. The vortex array generator for a light sport aircraft according to claim 1, characterized in that: The rectangular vortex generator d (4) with rounded corners includes a fourth base (401) and a rectangular vortex generator d body (402) with rounded corners. The rectangular vortex generator d body (402) with rounded corners is fixed to the surface of the fourth base (401). The fourth base (401) is fixed to the rear end of the transition bulge between the aircraft wing (6) and the aircraft fuselage (5) and is located on the upper surface of the bulge. The shape of the fourth base (401) is similar to the boundary line between the bulge and the shape of the fourth base (401).

5. The vortex array generator for a light sport aircraft according to claim 1, characterized in that: The height of the triangular vortex generator a(1) with rounded corners is 127mm-134mm, and the height of the rectangular vortex generator b(2), rectangular vortex generator c(3), and rectangular vortex generator d(4) with rounded corners is 33mm-42mm.

6. The vortex array generator for a light sport aircraft according to claim 5, characterized in that: The four sets of vortex generator components are at an angle α with the horizontal plane, the angle α being ±25 degrees, and the four sets of vortex generator components are perpendicular to the symmetry plane of the aircraft fuselage (5) in their height direction.

7. The vortex array generator for a light sport aircraft according to claim 2, characterized in that: The sweep angle of the leading edge of the triangular vortex generator a body (102) with rounded corners is 150°-155°.

Images