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A Hypersonic Vehicle and Its Ballistic Design

A hypersonic and aircraft technology, applied in aircraft, supersonic aircraft, aircraft stability, etc., can solve problems such as ablation, invasion, and high heat flux density of airflow, and achieve a compact structure, good stability, and high structural stability. Effect

Active Publication Date: 2022-04-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In addition, under hypersonic flight conditions, the heat flux density of the airflow is high, which can heat the surface of the aircraft. If the traditional folding structure is adopted, the shaft of the aircraft will withstand higher temperatures; in such a traditional folding structure, the shaft of the aircraft is generally Direct contact with the incoming flow, being attacked by hot air flow, causing the shaft to bear more ablation

Method used

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  • A Hypersonic Vehicle and Its Ballistic Design
  • A Hypersonic Vehicle and Its Ballistic Design
  • A Hypersonic Vehicle and Its Ballistic Design

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Embodiment Construction

[0040] The present invention as Figure 1-16 As shown, the lift-to-drag ratio of the hypersonic vehicle is studied under the conditions of an altitude of 40 kilometers above the ground, an angle of attack ranging from 0° to 15°, and a Mach number Ma greater than or equal to 6, among which the altitude above the ground is 40 km can minimize the chance of being attacked; the hypersonic vehicle includes a conical leading edge 1, a cylindrical cabin 2, a pair of wings 3 and a vertical tail rudder 4, and the conical leading edge 1 is fixedly connected to The front part of the cylindrical nacelle 2, the vertical tail rudder 4 is vertically arranged and fixedly connected to the rear part of the top surface of the cylindrical nacelle 2;

[0041] Described wing 3 comprises the fixed wing 31 of uniform thickness, folding wing 32 and empennage 33, and described fixed wing 31 is arranged horizontally, and the front portion of fixed wing 31 in a pair of wings 3 is fixedly connected symmetr...

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Abstract

A hypersonic vehicle and its ballistic design. Improvements related to hypersonic vehicles in near space. A compact structure, good stability and high reliability is proposed, which can not only be accommodated in a hood with a length of 3200mm and a diameter of 800mm, but also maintain a high lift-to-drag ratio, and also enable the folding structure to maintain a high structure Stable hypersonic vehicle and its ballistic design. It includes a conical leading edge, a cylindrical nacelle, a pair of wings and a vertical rudder. The conical leading edge is fixedly connected to the front of the cylindrical nacelle. The rear portion of the top surface of the shaped nacelle; the wing comprises a fixed wing, a folding wing and an empennage of uniform thickness. On the whole, it has the advantages of compact structure, good stability and high reliability.

Description

technical field [0001] The present invention relates to the improvement of hypersonic aircraft in adjacent space. Background technique [0002] Near space generally refers to an aircraft that is 20-100 kilometers from the ground and performs specific tasks in near space. It can provide more and more accurate information than satellites, and it can reduce the chance of being attacked by the ground than ordinary aircraft. Therefore, hypersonic speed in near space Aircraft is a research hotspot in the aerospace field. At present, in the adjacent space, the wave resistance and frictional resistance encountered by hypersonic vehicles during flight are relatively large, and in the case of limited booster thrust, matching thrust cannot be generated. Therefore, the improvement of the aerodynamic shape layout of hypersonic vehicles, Further improving the lift-to-drag ratio of a hypersonic vehicle has always been a difficult point in this field. [0003] At the same time, in order t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C30/00B64C3/56B64C5/04B64C5/06B64F1/04
CPCB64C30/00B64C3/56B64C5/04B64C5/06B64F1/04
Inventor 殷超张军张木
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS