Integrated modeling method for hypersonic flight vehicle engine body and internal contraction air inlet channel
A modeling method and hypersonic technology, applied in the fields of instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as inability to actually design, complex modeling method parameters, and design methods remaining in basic configuration research, etc. To achieve the effect of convenient evaluation and simple modeling process
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[0041] The present invention will be described in detail below with reference to the drawings and specific embodiments:
[0042] The flow chart of the overall modeling method of the present invention is as figure 1 Shown.
[0043] Given the overall design index, determine the overall coordinate system:
[0044] The overall design parameters need to be given, including the length of the front body, the length of the rear body, the maximum width of the fuselage, the maximum thickness of the fuselage, the area of the wing, the aspect ratio, the tip ratio, the sweep angle of the leading edge, and the air inlet. Control parameters. The coordinate system is selected as the rectangular coordinate system, the axis of the fuselage is the x direction, the wingspan direction is the y direction, and the z direction is the height direction of the aircraft. Determine the expression of the rectangular coordinate system
[0045] Solve the control parameters of each surface:
[0046] In order to so...
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