LT6788B - Aircraft wing with a double hinge - Google Patents

Abstract

The invention relates to reducing the aerodynamic drag of the flight planes of small aircraft when changing the direction of flight. The use of a wing with an additional hinge in the steering plane maintains the same torque about the center of gravity of the aircraft as with a single-hinged steering structure. The additional degree of freedom in the wing allows the wing to extend more evenly, thus creating a more even flow of airflow, avoiding unevenness of airflow at the wing plane. The proposed construction allows to reduce the aerodynamic drag of the aircraft by up to 10 percent.

Description

FIELD OF THE INVENTION

The invention relates to aviation, in particular to small aircraft with pilot planes for reducing their aerodynamic drag.

BACKGROUND OF THE INVENTION

Small unmanned aerial vehicles performing various missions in densely populated areas are increasingly in use. However, when they fly, they often have to change direction of flight, react to strong gusts of wind between buildings, and in order to maintain the flight course, the autopilot or flight operator often has to make adjustments to the flight of the aircraft. As a result, the speed and altitude of the aircraft fall, which requires the use of additional energy to maintain. Because small aircraft, due to their design characteristics, cannot carry large amounts of required energy in the form of fuel, batteries, or other energy, this limits their use for practical tasks.

Aerodynamic performance enhancers are widely used in large aviation to eliminate or at least reduce the listed functional deficiencies of aircraft and to ensure maximum aircraft performance at various stages of flight. Modern aircraft have a variety of devices that change the shape of the aircraft wing depending on the flight conditions. The wing of an airplane is one of the most important parts of an airplane. It creates the lifting force needed to get the plane off the ground and take off into the air. In addition, rudders (ailerons) and wing mechanization devices (flaps, fenders, spoilers, interceptors) are attached to the wing.

One of the first wings of an airplane is described in U.S. Pat. Re19412, issued in 1935. January 1 The solutions implemented in this wing of the aircraft have made it possible to increase the lifting efficiency of the aircraft at reduced take-off and landing speeds.

In another U.S. patent no. US7891611 describes systems and methods for controlling and controlling aircraft rudders. The rudders of the aircraft described in the present invention comprise integral ailerons.

Both of these analogues are characterized in that the wing rudder is realized as a single element, the change of wing shape is realized by applying many additional thrusts and hinges, and such kinematic schemes require an additional or servo mechanism or motor for kinematic movement. In small aircraft, such kinematic mechanisms are difficult to adapt because additional servo mechanisms or engines significantly increase the weight of the aircraft. Another disadvantage is that some kinematic elements become too small, difficult to manufacture, install, operate to ensure their synchronous operation, especially when used in flaps or ailerons requires high accuracy of all structural elements.

SUMMARY OF THE INVENTION

The object of the present invention is to provide an aircraft wing kinematic scheme that reduces the aerodynamic drag during aircraft evolution by generating lower torque than conventional rudder attachment schemes, with minimal increase in structural weight and number of elements required. This is realized through a double aircraft wing rudder structure with two hinges.

BRIEF DESCRIPTION OF THE DRAWINGS AND FIG. are schematic views of a double-hinged wing of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

As shown in Figs. and 5 stiffness is achieved by using a composite kevlar material and selecting its thickness. In practice, aramid twill fabric with a weight of 110 g / m ² , placed at an angle of 45 ', was best.

The rudder 3 of an aircraft type aircraft can be made of balsa wood, plastic or polymethacrylamide (PMI) foam known as Rohacel®, or other materials. The use of aramid fabric in the hinges 4, 5 has the property of returning the steering wheel 3 to the neutral position in the absence of an external load. When the steering rod 2 pushes the steering wheel 3 from the neutral position in the direction of the arrow A or B, both planes of the steering wheel 3 bend through the two hinges 4, 5 in the steering wheel 3 at an angle α, ensuring an even change of shape from the wing tip to the steering wheel end. With conventional steering design, when the steering wheel has only one hinge, with the steering wheel tilted by more than 10 °, the air flow around the outer steering surface starts to tear off the steering surface, which slightly increases the steering efficiency but significantly increases its resistance. With a double rudder 3 with two hinges 4, 5, the deflection of the flow around the rudder 3 starts at an approximately 2 times larger rudder angle of the rudder 3, which allows the aircraft-type aircraft to make flight changes with less energy loss than a typical rudder. This dual-hinge aircraft steering wheel design reduces the aerodynamic drag of the aircraft by approximately 10%.

Claims (2)

DEFINITION OF THE INVENTION An aircraft-type aircraft wing mechanism having a wing and a rudder pivotally connected to the wing by a hinge, characterized in that the aircraft has a double rudder (3) connected to the wing (1) by two hinges (4, 5). 2. An aircraft-type aircraft wing mechanism according to claim 1, characterized in that the hinges (4, 5) of the rudder (3) are made of aramid fabric and have the property of returning the structural elements to the initial neutral position without exerting an external load.