Waverider integration design method for hypersonic aircraft forebody, air inlet and wing

A hypersonic and air inlet technology, which is applied in the combustion, transportation and packaging of aircraft parts and air inlets of power plants. And other issues

Active Publication Date: 2016-06-15
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this conventional waverider-inlet integrated design method, only the waverider is used as the aircraft front body, and the waverider integrated design of other parts of the aircraft (such as wings) is not considered, so the waverider cannot be fully utilized. High lift-to-drag ratio characteristics of the wave body

Method used

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  • Waverider integration design method for hypersonic aircraft forebody, air inlet and wing
  • Waverider integration design method for hypersonic aircraft forebody, air inlet and wing
  • Waverider integration design method for hypersonic aircraft forebody, air inlet and wing

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Embodiment Construction

[0084] A method for the integrated design of a hypersonic vehicle precursor, air intake and wing waveriders provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0085] Step S1. Using the characteristic line theory, design a supersonic axisymmetric flow field with inner and outer cone mixed compression, as the reference flow field for generating the integrated configuration of the precursor of the hypersonic vehicle and the inlet, and call this reference flow field a hypersonic vehicle The axisymmetric reference flow field of the precursor-inlet integration.

[0086] S1.1, if image 3 As shown, given the busbar 10-11 of the pointed rotary body, the rotation axis of the pointed rotary body is the X axis, the starting point of the pointed rotary body bus is point 10, and the end point of the pointed rotary body bus is point 11, select the intake air The cross-section 12 where the road lip is located and the cross-se...

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Abstract

The invention provides a waverider integration design method for a hypersonic aircraft forebody, an air inlet and a wing. On the basis of waverider forebody/air inlet integration design, the theory of characteristic lines is applied for establishing a hypersonic aircraft forebody-air inlet integration axial symmetrical benchmark flow field and a wing symmetrical benchmark flow field, and a hypersonic aircraft forebody-air inlet integration configuration and a wing configuration are generated by applying the streamline-tracing technique in the two benchmark flow fields correspondingly. The two configurations together form a hypersonic aircraft forebody-air inlet-wing waverider integration configuration. In the design state, a whole hypersonic aircraft external flow field has waverider-like characteristics, the waverider forebody is used as a precompression face of the air inlet, and precompressed airflow is efficiently captured and provided for the air inlet, so that the waverider wing provides a high lift-drag ratio for the aircraft.

Description

technical field [0001] The invention relates to the technical field of aerodynamic shape design of an air-breathing hypersonic vehicle, in particular to an integrated design method for a hypersonic vehicle precursor, an air inlet and a wing waverider. Background technique [0002] An air-breathing hypersonic vehicle refers to an aircraft with a flight Mach number greater than 5, powered by an air-breathing engine or a combined engine, and capable of long-distance flight in the atmosphere and across the atmosphere. Its application forms include hypersonic cruise missiles, hypersonic Manned / unmanned aircraft and aerospace aircraft and other aircraft. [0003] A large number of studies since the 1960s have fully demonstrated that the integrated design of the propulsion system and the airframe is the key to the realization of hypersonic flight, and it is one of the key technologies to be solved urgently in hypersonic vehicle technology, and the core of airframe / propulsion system...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02B64F5/00
CPCB64D33/02B64F5/00
Inventor 丁峰柳军沈赤兵刘珍黄伟王庆文姚雷雷
Owner NAT UNIV OF DEFENSE TECH
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