Deflection control device based on head of aircraft

Abstract

The invention discloses a deflection control device based on the head of an aircraft. The deflection control device is composed of a deflection mechanism, the head of the aircraft, an intelligent skin, an intelligent framework and an aircraft body; the deflection mechanism is installed between the head of the aircraft and the aircraft body; two ends of the intelligent framework are connected with the aircraft body and the head of the aircraft, respectively; and the intelligent skin is fixed on the intelligent framework. The deflection control device is used for controlling by taking the head of the aircraft as a control plane of the aircraft, a conventional canard is replaced, and negative aerodynamics and thermo-mechanical effects caused by the fact that the head is interfered with the airflow of the canard can be avoided; because the pressure increment of the front end is generated due to mutual deflection of the head and the canard, non-uniform change is generated in local circumstances along the range of the canard; simultaneously, the control plane is at the front part of the aircraft, so that the operation efficiency is higher; the head of the aircraft directly pulls shock wave under supersonic velocity so as to obtain higher aerodynamic force; and the deflection control device is simple in aerodynamic arrangement structure and better in aerodynamic characteristics and the aircraft resistance is low.

Description

technical field [0001] The invention relates to the field of supersonic aircraft control, in particular to an aircraft head-based deflection control device. Background technique [0002] The aircraft responds to maneuvers according to its own mission needs. Aerodynamic control surfaces are often used to achieve attitude and state changes. On aircraft, the commonly used aerodynamic control surfaces include vertical tail, horizontal tail, aileron and canard. The aerodynamic control surface changes the attitude Or the shape is used to change the air flow to generate aerodynamic force and aerodynamic moment, wherein the vertical tail, horizontal tail and aileron are placed behind the center of pressure of the aircraft, and the canard is placed in front of the center of pressure of the aircraft. But for canard control, when the aircraft is in supersonic flight, the canard may have negative aerodynamic and thermodynamic effects in the expansion region along the nose of the aircraf...

AI Technical Summary

Problems solved by technology

This kind of aircraft with duck rudder as the control surface has certain shortcomings

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