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Design method for reusable sky-earth aircraft configuration

A design method and aircraft technology, applied in the direction of instruments, calculations, sustainable transportation, etc., can solve the problems of aircraft lift-to-drag ratio and volume utilization ratio, and achieve excellent aerodynamic performance, good practicability, and good heat resistance.

Active Publication Date: 2017-09-19
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

However, for a practical hypersonic vehicle, the overall constraint requirements of the vehicle’s volume, volume utilization rate, and side surface area must also be taken into account, especially the segmental loading requirements, and the lift-to-drag ratio and volume utilization rate of the aircraft are usually mutually correlated. contradiction

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  • Design method for reusable sky-earth aircraft configuration
  • Design method for reusable sky-earth aircraft configuration
  • Design method for reusable sky-earth aircraft configuration

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Embodiment Construction

[0020] A method for designing the shape of a reusable space-to-ground shuttle vehicle, comprising the following steps:

[0021] 1. According to the design requirements, given the re-entry flight Mach number Ma, re-entry flight height H, fuselage length L and width W, radius R of the fuselage head, and different cross-sectional positions x i height limit h at i .

[0022] 2. Determine the upper and lower contour control lines of the fuselage, and determine the upper and lower contour lines according to the length of the fuselage and the size constraints at different sections. According to the initial plan of the aerodynamic shape, the contour line segment is split into a combination of multiple conic curves and straight line segments. At the splicing points of each line segment, the slope of the contour line is guaranteed to be the same to ensure its smoothness.

[0023] The lower contour is a combination of a ball head (arc segment), a quadratic curve and a straight line. T...

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Abstract

The invention discloses a design method for reusable sky-earth aircraft configuration. According to the method, an up-down contour control line and a left-right width contour line of a fuselage are determined, a quadratic curve and a CST method based on a type function and a shape function are adopted to generate a corresponding section shape, and therefore a key stance shape of the whole fuselage is obtained; the shape of the whole fuselage is obtained through a surface lofting technology; a numerical computation method is adopted to compute a flow field; matching design is performed on a control plane; and aerodynamic configuration is optimized. Compared with the prior art, the method has the advantages that high supersonic velocity lift-to-drag ratio characteristics and sub-cross-ultralow velocity entrance characteristics are comprehensively considered, the reusable sky-earth aircraft configuration with all velocity domains meeting design demands is designed, and an aircraft obtained through optimization has excellent aerodynamic performance and good heat resistance as well as good practicability.

Description

technical field [0001] The invention relates to a shape design method of a reusable space-to-earth shuttle aircraft meeting practical requirements. Background technique [0002] The design of aircraft shape is the core technology of aircraft development. It is a complex and comprehensive design process of multi-disciplinary cross-coupling. , considering the impact of various design constraints on the performance of the aircraft, repeated iterations between various disciplines, compromise and balance, and optimize the combination. Different strategic goals, use modes and launch platforms have led to innovative and diversified development of hypersonic vehicle aerodynamic layout and flight methods. Reusable space-to-ground shuttle vehicles have always been one of the current focuses in the hypersonic field. [0003] The reusable space-to-ground shuttle system must meet the basic requirements of "fast, maneuverable, cheap, and reliable", and have the characteristics of high ma...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 冯毅唐伟刘深深黄勇孙俊峰肖光明卢风顺陈波余雷
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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