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Flat-top-type first-stage pneumatic layout design method for horizontal take-off and landing two-stage to-orbit aircraft

A technology of aerodynamic layout and design method, which is applied to aircraft parts, ground devices, transportation and packaging, etc., can solve problems such as unrealizable, low propulsion efficiency and mass scale of aerodynamic efficiency, and achieve improved aerodynamic efficiency, better combustion efficiency and higher Effects of resistance ratio characteristics and ease of processing

Inactive Publication Date: 2019-08-16
CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among them, the single-stage horizontal take-off and landing vehicle has the best reusability, but the problem is that the low propulsion efficiency and aerodynamic efficiency in the initial stage of acceleration and climbing are the balance of the huge mass scale, so it cannot be realized in the short term.

Method used

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  • Flat-top-type first-stage pneumatic layout design method for horizontal take-off and landing two-stage to-orbit aircraft
  • Flat-top-type first-stage pneumatic layout design method for horizontal take-off and landing two-stage to-orbit aircraft
  • Flat-top-type first-stage pneumatic layout design method for horizontal take-off and landing two-stage to-orbit aircraft

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Embodiment Construction

[0034] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0035] Any feature disclosed in this specification, unless specifically stated, can be replaced by other alternative features that are equivalent or have similar purposes. That is, unless expressly stated otherwise, each feature is one example only of a series of equivalent or similar features.

[0036] Such as Figure 1-7 As shown, a method for designing the first-level aerodynamic layout of a flat-top horizontal take-off and landing two-stage orbiting vehicle of the present embodiment includes the following steps:

[0037] Step 1: Design the cross-sectional shape of the left and right symmetrical planes of the aircraft, and specify the radius R of the aircraft head h =500mm, take three sections of wave-riding slopes on the lower surface of the head, and the horizontal lengths are L in turn...

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Abstract

The invention discloses a flat-top-type first-stage pneumatic layout design method for a horizontal take-off and landing two-stage to-orbit aircraft. The flat-top-type first-stage pneumatic layout design method comprises the steps that first, the shape of section which are symmetrical in the left-right direction of the aircraft is designed; second, the shape of a front end arc face and the shape of a tangent plane of a fuselage are determined; third, a bevel on the lower part of the fuselage is determined; fourth, wings of the aircraft are designed; fifth, a vertical fin and a rudder of the aircraft are designed; and sixth, the wing and the vertical fin are assembled on the fuselage, and the aircraft appearance is obtained. By adopting the flat-top-type first-stage pneumatic layout designmethod for the horizontal take-off and landing two-stage to-orbit aircraft, the appearance can be quickly generated under the different parameter and size constraint conditions, and the appearance generated through the method can be completely parameterized.

Description

technical field [0001] The invention relates to a method for designing the aerodynamic layout of a flat-top type first-stage aircraft for a horizontal take-off and landing two-stage aerospace vehicle, and belongs to the technical field of aircraft aerodynamic layout design. Background technique [0002] Inexpensive, fast, and efficient access to space is the main requirement for the development of the current space-to-earth shuttle system. In order to meet this requirement, reusable vehicles have become the key development direction of current aircraft design. Reusable vehicles show a variety of development trends according to different power configurations, mission modes, load scales, and on-orbit states. Among them, the horizontal take-off and landing single-stage orbiting vehicle has the best reusability, but the problem is the balance between the low propulsion efficiency and aerodynamic efficiency and the huge mass scale during the initial acceleration and climbing stag...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 余雷张健唐伟段焰辉张培红赵鹏刘深深朱言旦刘骁魏东
Owner CHINA AERODYNAMICS RES & DEV CENT
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