High-speed aircraft with pitching-adjustable high-pressure capture wings and adjusting method

Abstract

The embodiment of the invention discloses a high-speed aircraft with pitching adjustable high-pressure capture wings and an adjusting method. The high-speed aircraft comprises an aircraft body and a capture wing body arranged above the aircraft body, and the aircraft body and the capture wing body are connected through a pitching adjusting device. The pitching adjusting device is used for adjusting the pitching angle of the capturing wing body in the extending direction of the aircraft body. The change of the pitching angle of the capture wing body in the flight process is completed based on the arrangement of the pitching adjusting device, the angle between the capture wing body and the aircraft body is changed by applying direct force control of the lift force of the capture wing body in the pitching direction, the control ability of the whole aircraft is improved, and the flight speed is increased. An elevator originally used for improving the overall control capacity is reduced or even eliminated, and pneumatic losses caused by improvement of the control capacity are reduced. By adjusting the pitching angle of the capturing wing body, a shock wave reflection and interference structure in a flow field can be changed, and the aerodynamic stability characteristic of the capturing wing is further improved.

Description

technical field [0001] Embodiments of the present invention relate to the field of aircraft technology, and in particular to a high-speed aircraft with pitch-adjustable high-pressure capture wings and an adjustment method. Background technique [0002] The high-voltage capture wing layout is an aerodynamic layout that effectively utilizes shock wave interference to achieve high lift, high lift-to-drag ratio, and high volume ratio. However, its wave system structure and aerodynamic characteristics change significantly in a wide speed range, which greatly increases the difficulty of stability and control system design. In order to ensure the stability and maneuverability in a wide speed range, the control capability must be increased in the design, which brings the following two problems: [0003] a. The increase in the size of the rudder surface brings about an increase in frictional resistance and an increase in trim resistance when the rudder is yawed, resulting in aerodyn...

AI Technical Summary

Problems solved by technology

[0005] In this regard, in the current solution, the control capability can only be increased by increasing the rudder surface area at the rear of the fuselage

At the same time, with the change of incoming flow conditions, it also brings complex changes in aerodynamic force and stability, and the increased rudder surface area will increase the overall control difficulty

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