Double-feather winglet device with variable inclination angle

Abstract

The invention discloses a double-feather winglet device with a variable inclination angle, and belongs to the technical field of aircraft devices. A winglet base is connected with the wing spanwise tail end of an aircraft through a wing transition section; a first winglet and a second winglet are arranged at the two sides of the winglet base respectively. The first winglet and the second winglet are connected with the wing transition section through a flexible connection section, and connected with a rigid connection section, and the rigid connection section is hinged to the winglet base; a servo transmission system is connected with a control system, and the servo transmission system is connected with the first winglet and the second winglet; and the control system is in communication connection with an aircraft control center. The double-feather winglet device does not generate extra additional force during attack-angle-free flight, is suitable for various wing layouts, can adjust the inclination angles of the first winglet and the second winglet in real time according to flight parameters of an aircraft, reduces the influence of wingtip vortexes, improves the flexibility and penetration performance of the aircraft, a and is suitable for executing maneuvering complex flight missions.

Description

technical field [0001] The invention belongs to the technical field of aircraft devices, in particular to a double-feather winglet device with a variable inclination angle. Background technique [0002] When the aircraft is in flight, the airflow in the high-pressure area on the lower surface of the wing will bypass the wingtip and flow to the upper surface, forming a strong vortex airflow, and extending a long distance from the wing to the rear edge. They take away energy and increase Induced drag, winglets are used to weaken this drag. [0003] During the cruising process of the aircraft, the wings provide the main lift, and at the same time due to the wing tip vortex effect, a large wing tip vortex is generated, thereby reducing the effective wing area and generating a large induced drag. In the process of penetration, it is often necessary to carry out large-scale maneuvers at large flight angles of attack. Since the generation of wing tip vortices will greatly reduce t...

AI Technical Summary

Problems solved by technology

In the process of penetration, it is often necessary to carry out large-scale maneuvers at large flight angles of attack. Since the generation of wing tip vortices will greatly reduce the rudder effect of the wing control rudder surface, it cannot meet the requirements of high maneuverability rudder effect. The sharp vortex has an adverse effect on high-speed maneuvering, greatly weakening the flexibility and penetration performance of the aircraft

For aircraft with different flight speeds, there are also differences in the optimal winglet inclination angles. The existing winglets are fixed inclination angle winglets, and the inclination angle of the winglets cannot be adjusted to adapt to various flight speeds and flight conditions

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