CN205022846U

CN205022846U - A vortex generator for aircraft vertical fin

Info

Publication number: CN205022846U
Application number: CN201520292105.9U
Authority: CN
Inventors: 温青山
Original assignee: Harbin Aircraft Industry Group Co Ltd
Current assignee: Harbin Aircraft Industry Group Co Ltd
Priority date: 2015-05-07
Filing date: 2015-05-07
Publication date: 2016-02-10
Anticipated expiration: 2025-05-07

Abstract

The utility model relates to a vortex generator for aircraft vertical fin, vortex generator are the structures that can postpone, control and prevent the boundary layer from the nappe separation. At present, external vortex generator windward side is mostly rectangle, trapezoidal and spade, and the manufacture process is complicated and weight is great, installs usually on wing surface and engine nacelle. The utility model discloses a vortex generator is to the aircraft optimization procedure in scientific research stage, and is less to the change volume of primary structure, implements simply, easy, quick and effectual, light in weight, with low costs.

Description

A kind of vortex generator for aircraft vertical fin

Technical field

The utility model, for improving the aerodynamic characteristic of aircraft, relates to a kind of vortex generator for aircraft vertical fin particularly.

Background technology

Air-flow is when flowing through aircraft surfaces, and the flowed energy of boundary 1ayer is lower, and aircraft can be caused like this to shift to an earlier date stall, and then affects minimum control speed and the flight quality of aircraft.Vortex generator is a kind of structure can postponing, control and prevent boundary 1ayer to be separated from surface.Replace low-energy air-flow in part boundary 1ayer thereafter by the higher mixing of the energy of the air-flow of vortex generator, delay burbling, and then prevent aircraft from shifting to an earlier date stall, improve flight quality.

At present, external vortex generator windward side mostly is rectangle, trapezoidal and spade, and complicate fabrication process and weight are comparatively large, and be usually arranged on aerofoil surface and engine nacelle, position is 12 ° ~ 15 ° relative to the angle of attack of local air flow.The joint face of vortex generator and main structure is normally realized by adhering method.

The aircraft of domestic independent development is before the utility model, and the design of vortex generator, manufacture and application are still in the blank phase.When the scientific research of YF aircraft is taken a flight test, the flow field at vertical fin place is separated serious, cause Aviatrix to be difficult to keep or control course and the gradient, and then cause the yaw rudder hinge moment nonlinear situation of aircraft serious, the too high Airworthiness Certification needs that cannot meet this type machine of minimum control speed.

Summary of the invention

For the hinge moment characteristic in the flow field and yaw rudder of effectively improving vertical fin place, and then reduce the minimum control speed of aircraft, YF aircraft is made to meet the requirement of seaworthiness clause, possesses excellent flight quality simultaneously, devise a kind of vortex generator for aircraft vertical fin, comprise the base plate of vortex generator and the driving surface of vortex generator, the right-angled triangle vortex generator of described vortex generator to be section shape be T-shaped, and be arranged on aircraft vertical fin by base plate, the driving surface of described vortex generator and the angle of formation plane are 42 °, wherein a square edge of right-angled triangle is towards vertical fin lagging dege.

This vortex generator is for the aircraft optimizing process in scientific research stage, less to the change amount of keystone configuration, implement simple, easy, quick and effective, lightweight, cost is low.

The vertical fin flow field that this utility model can be widely used in solving fixed wing machine is separated, yaw rudder hinge moment non-linear and the problem such as minimum control speed is excessive.

The triangle vortex generator being T-shaped from bottom to top by section shape by certain angle and status requirement is riveted on the surface of vertical fin covering.When air-flow arrives this vortex generator, high-octane eddy current will be produced at windward side place, thus improve the flow field at vertical fin place, postpone, control and prevent boundary 1ayer to be separated from surface, and then improve yaw rudder hinge moment characteristic and minimum control speed.

By carrying out Flight to the vortex generator be arranged on vertical fin, show that this structure meets produce stronger eddy current and then improve flow field, vertical fin place, postpone, control and prevent boundary 1ayer to be separated from surface, effectively improve the yaw rudder hinge moment characteristic at vertical fin rear portion and make the minimum control speed of aircraft meet Airworthiness Certification requirement.Effectively improve the flight quality of aircraft by carrying out less change, lower weight cost, less manufacturing expense and simple implementation process to airplane tail group structure, achieve gratifying effect.

Accompanying drawing explanation

Fig. 1 is the fundamental diagram of the utility model vortex generator;

Fig. 2 is the front view of the utility model vortex generator;

Fig. 3 is the birds-eye view of the utility model vortex generator;

Fig. 4 is the left view of the utility model vortex generator;

Fig. 5 is the mounting arrangement schematic diagram of the utility model vortex generator on vertical fin;

Fig. 6 is the partial enlarged drawing of Fig. 5;

Fig. 7 is the installation relation schematic diagram of vortex generator and vertical fin.

The driving surface 3-vertical fin of the base plate 2-vortex generator of 1-vortex generator

4-formation plane 5-vertical fin lagging dege

Detailed description of the invention

See Fig. 2-7, riveted by the connection side of width d=25mm on vortex generator base plate 1 and vertical fin 3, the rivet row of each connection side is single.The right-angled triangle vortex generator of vortex generator to be section shape be T-shaped, the angle of its driving surface and formation plane 4 is 42 °, wherein leg-of-mutton right angle towards fuselage afterbody vortex generator back apart from vertical fin lagging dege 5 be 240mm ~ 260mm.To ensure Joint strenght needs on the flange that the connection flange of vortex generator requires rib or the long purlin that 3 rivet interlacement at least will be had in vertical fin inside, connect the raised-head rivet that rivet used is Φ 3.2.

The long limit 2. a=130mm of vortex generator structure intermediate cam shape panel 1., minor face is b=65mm 3., and triangular panels is thickness δ=4mm 4., and part machine direction is the long side direction of triangular panels.The base plate 5. thickness δ of T-shaped section ₁=2mm, each connection side width d=25mm on base plate, 6. the transition region of triangular panels and T-shaped base plate locates R angle is R=3mm, and all the other fillets are R ₁=5mm.

Claims

1. the vortex generator for aircraft vertical fin, comprise the base plate (1) of vortex generator and the driving surface (2) of vortex generator, it is characterized in that: the right-angled triangle vortex generator of described vortex generator to be section shape be T-shaped, and be arranged on aircraft vertical fin (3) by base plate (1), the driving surface (2) of described vortex generator and the angle of formation plane (4) are 42 °, and wherein a square edge of right-angled triangle is towards the lagging dege (5) of vertical fin.