Aircraft and aircraft control method thereof

Abstract

The invention relates to the field of aircraft manufacturing, in particular to an aircraft and an aircraft control method thereof. The aircraft comprises a fuselage body and wings which are symmetrically arranged, a control part is arranged at the position, close to a wing tip, of any wing, each control part is used for controlling rolling motion of the corresponding wing, each control part comprises a rolling restraining device, each rolling restraining device comprises a shell and a sliding block, and the sliding blocks are movably arranged in the shells. The aircraft further comprises a driving assembly and a control assembly. The driving assembly is arranged in the shell and drives the sliding blocks to move in the shells. The control assembly is used for controlling the driving assembly to work, the sliding blocks and the shells are correspondingly provided with a plurality of open holes respectively, and the open holes of the sliding blocks and the open holes of the shells are selectively communicated along with the movement of the sliding blocks. According to the aircraft, the original aerodynamic configuration and the overall structure of the wings are not damaged, the occurrence of tumbling in the flight process is effectively improved, and the stability and the flight quality of the aircraft are not influenced.

Description

technical field [0001] The invention relates to the field of aircraft manufacturing, in particular to an aircraft and an aircraft control method thereof. Background technique [0002] The problem of static aeroelasticity of aircraft, also known as the problem of aeroelastic statics, belongs to the research category of aeroelasticity. For aircraft, the static aeroelasticity problem studies the deformation of the aircraft under aerodynamic loads and the stability characteristics of the static deformation generated by aerodynamic forces, and considers that force and motion are independent of time. Static aeroelastic deformation has a non-negligible impact on the aerodynamic performance of the aircraft, such as load distribution, control efficiency, trim characteristics, static and dynamic stability, and the safety, comfort, and economy of the aircraft under steady flight conditions. [0003] The structural deformation caused by the static aeroelastic effect of the wing will ha...

AI Technical Summary

Problems solved by technology

[0006] The reason why the efficiency of conventional ailerons is reduced or reversed is that assuming that the ailerons deflect downward, an upward additional lift force and aerodynamic moment will be generated at the aileron aerodynamic center, and they will form a torque on the rigid center of the wing surface, making the wing surface A negative twist angle is generated, which causes the wing surface to generate negative additional lift, thereby reducing the effect of the aileron on increasing the lift, thus reducing the efficiency of the aileron or even counteracting it

Compared with the straight wing, the chord distance between the aileron and the wing root of the swept wing is relatively farther, so the torsional deformation of the wing caused by the aileron control moment is greater, and the aileron failure phenomenon is more serious

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