CN101028867A - Aircraft with changeable wing shape - Google Patents

Abstract

An aircraft capable of changing the shape of its wings relates to an aircraft. Aiming at the problems of complex wing motion mechanism, heavy weight, high development cost, difficult operation of the aircraft and low flight performance in the existing deformed wing aircraft. The invention consists of a fuselage (1) and two wings (2); each wing (2) consists of a fixed wing (3), a sliding wing (4), a shape memory alloy rod (5), a cylinder (6), pulley (7) is formed; One end of fixed wing (3) is affixed with fuselage (1), and cylinder (6) and solid with cylinder (6) are housed in the skeleton of fixed wing (3). connected shape memory alloy rod (5), the cylinder (6) is provided with a spiral groove (8), the sliding wing (4) is contained in the skeleton of the fixed wing (3), and the sliding wing (4) The first end of the pulley (7) is equipped with, and the pulley (7) is contained in the spiral groove (8). The invention uses the shape memory alloy rod as the driving source of the deformed wing, which has light weight, simple mechanism and convenient maintenance, and solves the contradiction between the high and low speed flight performance of the aircraft through the change of the shape of the wing.

Description

An aircraft that can change the shape of its wings

technical field

The invention relates to an aircraft.

Background technique

Wings are the main components of an aircraft that are reconfigurable in flight. Purposefully changing the shape of the wing during flight (such as wing sweep, changing the wingspan and camber, etc.) can effectively increase the flight performance of the wing. Among them, the effect of changing the wingspan and wing area is the most prominent. For example, an aircraft usually requires a high aspect ratio and a large wing area when cruising, and a low aspect ratio and a small wing area are required for an aircraft to fly at high speed. The small aspect ratio and large swept wings widely used in modern supersonic aircraft have small supersonic resistance, but the aerodynamic efficiency is low at low speeds, and the lift characteristics are not good. Wings would again degrade supersonic performance. The variable aspect ratio aircraft can solve the contradiction between high and low speed performance requirements through the change of wing aspect ratio. The aircraft uses a larger aspect ratio when taking off, landing and low-speed flight, so it has higher low-speed cruising efficiency and greater take-off and landing lift; when flying at a supersonic speed, a smaller aspect ratio is used to reduce the supersonic speed. The drag of flight is good. In addition, when supersonic bombers and attack aircraft fly at ultra-low altitude and high speed, in order to reduce the turbulence caused by unsteady airflow, the wings are also required to have a smaller aspect ratio.

However, in some of today's deformable wing aircraft, the wing needs to pass through a set of powerful driving devices to quickly change its shape in flight, which will inevitably lead to complex wing motion mechanisms, heavy weight, high development costs, and difficulty in aircraft operation. Large, low flight performance issues.

Contents of the invention

The object of the present invention is to provide an aircraft capable of changing the shape of the wing, which can solve the problems of complex wing motion mechanism, heavy weight, high development cost, difficult operation and low flight performance in the existing deformed wing aircraft.

The present invention consists of a fuselage and two wings; each wing is composed of a fixed wing, a sliding wing, a shape memory alloy rod, a cylinder, and a pulley; one end of the fixed wing is fixedly connected to the fuselage A cylinder and a shape memory alloy rod affixed to the cylinder are sequentially installed in the skeleton of the fixed wing along the direction from the tail end to the head end of the fixed wing, and the outer surface of the cylinder is arranged along the length direction of the cylinder A spiral groove, the sliding wing is installed in the skeleton of the fixed wing, and the head end of the sliding wing is equipped with a pulley, and the pulley is installed in the spiral groove.

The present invention has the following beneficial effects: In the present invention, the driver that drives the sliding wing to move linearly is a shape memory alloy rod, and a certain angle of rotation is applied to the shape memory alloy rod in advance, and the shape memory alloy rod is heated by means of resistance wire heating , when the shape memory alloy rod is heated, the thermal drive makes the shape memory alloy rod return to its original shape, so that the twisting of the shape memory alloy rod drives the cylinder to rotate, and drives the pulley on the sliding wing to rotate in the helical shape of the cylinder Sliding in the groove, thereby realizing the extension and retraction of the sliding wing. Therefore, compared with the large-scale pivot device widely used at present, the present invention has the advantages of light weight, simple mechanism, convenient maintenance, etc., which can not only greatly reduce the overall quality of the aircraft, but also improve the combat maneuverability and safety of the weapon system. It can reduce the risk of weapons in service and reduce maintenance costs. In the long run, the change in the wing shape of the aircraft can enable the aircraft to achieve higher speeds, and have high fuel efficiency, high flight quality, high safety performance, better maneuverability, and faster landing speeds. The take-off field adapts to various conditions. For example, fighter jets can use their larger aspect ratio and larger wings to help them take off on a short runway, or hover slowly over enemy targets, when it is necessary to drop bombs When , the wings can be brought together to shorten the wings and reduce the aspect ratio in order to prepare for a rapid attack. Similarly, some commercial airliners can also change the shape of their wings during flight to save fuel and reach their destinations more quickly. That is to say, the present invention can not only make the aircraft have a shorter take-off distance and longer time in the air, but also enable the aircraft to have a faster flying speed and higher flexibility when necessary. Therefore, the present invention can not only change the shape of the wing, but also can be used in military weapon structures such as variable-wing cruise missiles, ship submarine structures, etc., to provide security, intelligence, and self-adaptation for realizing weapon systems. A strong basic support greatly improves the combat performance and safety of weapon systems (especially unmanned aerial vehicles).

Description of drawings

Fig. 1 is a top view of the present invention (wing shape is constant), and Fig. 2 is a top view of the present invention (wing shape is changed).

Detailed ways

Specific embodiment one: this embodiment is described in conjunction with Fig. 1 and Fig. 2, and this embodiment is made up of fuselage 1 and two wings 2; Two wings 2 are symmetrically arranged on the left and right sides of fuselage 1, and each Each wing 2 is made up of fixed wing 3, sliding wing 4, shape memory alloy rod 5, cylinder 6, pulley 7; A cylinder 6 and a shape memory alloy rod 5 affixed to the cylinder 6 are sequentially installed along the direction from the tail end of the fixed wing 3 to the head end, and the outer surface of the cylinder 6 is provided with Spiral groove 8, described sliding wing 4 is contained in the skeleton of fixed wing 3, and the head end of sliding wing 4 is equipped with pulley 7, and described pulley 7 is contained in described spiral groove 8, fixed The material used for the wing 3 and the sliding wing 4 is the same as that of the existing wing; the heating method of the shape memory alloy rod 5 is direct electric heating or heating by resistance wire.

Specific embodiment two: This embodiment is described in conjunction with Fig. 1 and Fig. 2, the shape memory alloy rod 5 of this embodiment is a TiNi shape memory alloy rod, a Cu-Zn shape memory alloy rod, a Cu-Al-Ni shape memory alloy rod, One of Cu-Sn shape memory alloy rods, Mn-Cu shape memory alloy rods, Fe-Pt shape memory alloy rods or Fe-Mn-Si shape memory alloy rods. Under the action of external torsional force on the shape memory alloy rod (the ambient temperature is lower than the martensitic transformation temperature of the shape memory alloy), the shape memory alloy rod produces a certain torsional deformation (the torsional strain is lower than 10%), and then the shape memory alloy rod is heated , the shape memory alloy rod undergoes transformation from austenite to martensite, and the torsional deformation returns to the original shape. With such setting, the above shape memory alloy rod has the characteristics of large torque, large recoverable torsion angle, fast response speed, and high repeatability of thermo-mechanical cycle. In addition, if electric heating is adopted, the above shape memory alloy rods also have electric response characteristics, which is convenient for controlling the movement of the system. Other components and connections are the same as those in the first embodiment.

Claims (3)

1, a kind of aircraft of changeable wing shape, it is made up of fuselage (1) and two wings (2); It is characterized in that described each wing (2) is made up of fixed wing (3), slip wing (4), marmem rod (5), cylinder (6), pulley (7); One end of described fixed wing (3) and fuselage (1) are affixed, tail end along fixed wing (3) in the skeleton of fixed wing (3) is equipped with cylinder (6) and the marmem rod (5) affixed with cylinder (6) successively to the direction of head end, the length direction of the outside face upper edge cylinder (6) of cylinder (6) is provided with spiral groove (8), described slip wing (4) is contained in the skeleton of fixed wing (3), the head end of slip wing (4) is equipped with pulley (7), and described pulley (7) is contained in the described spiral groove (8).

2, the aircraft of a kind of changeable wing shape according to claim 1 is characterized in that marmem rod (5) is wherein a kind of of TiNi marmem rod, Cu-Zn marmem rod, Cu-Al-Ni marmem rod, Cu-Sn marmem rod, Mn-Cu marmem rod, Fe-Pt marmem rod or Fe-Mn-Si marmem rod.

3, the aircraft of a kind of changeable wing shape according to claim 1 and 2, the type of heating that it is characterized in that described marmem rod (5) are that directly energising is heated or heated by resistor wire.

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