Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft

A hypersonic, dual-inlet technology, which is applied to aircraft parts, aircraft control, and air flow that affects the surface of the aircraft. 3.8 and other problems, to achieve the effect of high lift resistance characteristics and broaden the range of working Mach number

Inactive Publication Date: 2015-12-30
厦门翔腾新材料科技有限公司
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Problems solved by technology

Mark Lewis, chief scientist of the U.S. Air Force's hypersonic program, pointed out in the literature (M.Lewis, AHypersonicPropulsionAirframeIntegrationOverview, 39thAIAA and ASME and SAE and ASEEJointPropulsionConferenceandExhibit, 2003), although a perfect waveriding theory can help us easily design a lift-t

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  • Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft
  • Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft
  • Method for designing double-air-inlet hypersonic-velocity wave-rider aircraft

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Embodiment Construction

[0018] The design method of dual-inlet hypersonic waverider aircraft is an inverse design method of aerodynamics, that is, its aerodynamic characteristics are specified first, and then a design scheme that satisfies the characteristics is deduced inversely.

[0019] The main implementation steps of the design method for the dual-inlet hypersonic waverider vehicle include:

[0020] 1) Specify the three-dimensional shock wave surface according to the design requirements, and obtain the outer band of the shock wave curve of the continuous dual-inlet hypersonic waverider aircraft. 1. The shock wave curve of the dual-inlet hypersonic waverider aircraft The inner band 2 and the middle band 3 of the shock wave curve of the dual-inlet hypersonic waverider aircraft ride, and the outer band 1 of the shock wave curve of the dual-inlet hypersonic waverider aircraft. The shock curve of the supersonic waverider aircraft rides on the wave band 2, and the shock wave curve of the hypersonic wa...

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Abstract

The invention relates to near space aerocrafts, in particular to a method for designing a double-air-inlet hypersonic-velocity wave-rider aircraft. Aerodynamic features are firstly designated, and then a design scheme meeting the features is reversely derived. A certain three-dimensional shock wave curved surface in a complex shape is designated, and the change rule of the transverse curvature center of the three-dimensional shock wave curved surface is obtained. A series of basic flow fields needed in wave rider design are reversely derived. Flow line tracking with different curvature centers and different longitudinal positions is carried out in the basic flow field at each circumferential position. Finally, a wave rider device capable of generating the designated complex three-dimensional shock wave curved surface is obtained, and the design scheme of the double-air-inlet hypersonic-velocity wave-rider aircraft is completed. Integration of the aircraft and air inlets is achieved, meanwhile, double-air-inlet design is achieved, and a solving method is provided for the design of a double-engine hypersonic-velocity aircraft.

Description

technical field [0001] The invention relates to near-space vehicles, in particular to a hypersonic waverider vehicle with dual inlets. Background technique [0002] The development of near-space vehicles involves national security and the peaceful use of space, and is one of the focuses of the current international competition for space technology, and the research on near-space hypersonic long-range maneuvering vehicles has become the focus of the development of near-space vehicles because of its important strategic significance heavy. World powers represented by the United States and Russia are vigorously promoting their own hypersonic flight development programs (Joseph, M.H, James S.M.Richard C.M., The X-51AScramjet Engine Flight Demonstration Program, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008). A large number of studies since the 1960s (Heiser, W.H.andPratt, D.T., Hypersonic AirbreathingPropulsion.AIAAInc., Washington...

Claims

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Application Information

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IPC IPC(8): B64C21/00
Inventor 李怡庆尤延铖滕健潘成剑
Owner 厦门翔腾新材料科技有限公司
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