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A variant supersonic aircraft

A supersonic and aircraft technology, applied to supersonic aircraft, motor vehicles, aircraft, etc., to achieve the effects of increasing low-speed range, improving maneuverability, and reducing induced resistance

Active Publication Date: 2021-08-17
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The object of the present invention is to provide a variant supersonic aircraft to solve at least one problem existing in existing supersonic aircraft

Method used

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  • A variant supersonic aircraft
  • A variant supersonic aircraft
  • A variant supersonic aircraft

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Embodiment Construction

[0021] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft overall design, in particular to a variant supersonic aircraft. Comprising: fuselage, two wings (1) and landing gear. The modified supersonic aircraft of the present invention can realize the modal conversion from the low-speed flight state to the supersonic flight state through the variable forward-sweep mechanism (2), and when the low-speed flight and take-off and landing states, the large aspect ratio of the leading edge is adopted Wings reduce induced drag and increase range at low speeds; when flying at supersonic speeds, wings with sharp leading edges and small aspect ratios are used to reduce wave resistance and improve maneuverability. The aircraft can well meet the requirements of high-speed and low-speed use. The passenger compartment, cargo compartment, fuel tank and landing gear compartment are all arranged in the two wings (1), and there is no obvious fuselage, which reduces the weight of the aircraft to a certain extent.

Description

technical field [0001] The invention relates to the field of overall design of aircraft, in particular to a large variant supersonic aircraft. Background technique [0002] Now the demand for air transport is increasing year by year, especially in Asia, where the economy is developing rapidly, the increase in demand is more significant. Under this demand, the capacity of air transport is approaching the limit, and the countermeasure is to vigorously develop larger and higher-speed aircraft all over the world. [0003] The existing layout of supersonic transport aircraft can be divided into four categories. 1. Small aspect ratio wings are adopted, and the aircraft’s aerodynamic efficiency is low during subsonic flight and take-off and landing stages of this type of layout; 2. Variable rear (front) swept wings are adopted, and this type of layout has a large weight of the aircraft body, and the wings are swept back Angle changes bring about large changes in the focus of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C30/00B64C39/00B64C3/38
CPCB64C3/38B64C30/00B64C39/00
Inventor 梁欣杰王伟吕飞
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA