Variable-area canard forward-swept wing morphing aircraft

Abstract

The invention discloses a variable-area canard forward-swept wing morphing aircraft which adopts a canard layout. The plane shape of an airfoil is quadrilateral, and when wings are completely retracted, the wings and a canard wing are connected to form a delta wing. The canard wing is arranged at the head of a fuselage. The wings on the two sides of the tail of the fuselage can be synchronously folded forwards towards the inner fuselage side around a wing body connecting rotating shaft or unfolded backwards towards the outer side. When the wings are folded forwards, the wings are gradually folded forwards to reduce the sweepforward angle, the wings are completely attached to the fuselage, and the whole aircraft is of a curved streamline aerodynamic configuration. When the wings are completely unfolded into forward-swept wings, the wing span of the aircraft is greatly increased, so that the aircraft can ensure large lift force. Double vertical tails are symmetrically arranged on the rear portion of the fuselage, lifting ailerons are installed at the rear end of the fuselage and located on the rear portions of the two vertical tails, and an air inlet channel is located below the fuselage. Through reasonable cooperation of the variable-area canard forward-swept wing variants, the aircraft has small flight resistance when the wings are in the unfolded state and the folded state, and the flight flexibility of the aircraft is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft design, in particular to a variable-area canard forward-swept wing variant aircraft. Background technique [0002] The morphing aircraft can effectively improve the comprehensive flight performance of existing aircraft by changing its shape during flight to adapt to different flight states, taking into account all aspects of performance, and has great development prospects. The overall deformation of the aircraft is still difficult to achieve, but within the acceptable range, it is entirely feasible to use local deformation to improve the performance of the aircraft. Such as the MiG-23 of the former Soviet Union, the F-14 of the United States, and the Tornado fighter jointly developed by Britain, Germany and Italy, etc., variable-sweep aircraft can take into account high and low speed performance. However, because the structural weight is greater than that of the same model at the same time, and...

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Problems solved by technology

[0003] In the literature "Simulation Research on Unsteady Aerodynamic Characteristics of Variable Airfoil of Variant Aircraft" ("Computer Simulation". 2015.10. Wang Xu), the unsteady aerodynamic characteristics of variable airfoil are studied, which can be used for the aerodynamic characteristics of variant aircraft. Layout design and dynamic analysis provide useful references, but lack of strength verificat

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