Pneumatic/structure/static aeroelasticity coupling optimizing method for high-aspect-ratio wing

A technology with a large aspect ratio and an optimization method, which is applied in design optimization/simulation, computer-aided design, special data processing applications, etc., to achieve the effects of improving wing performance and safety, ensuring design accuracy, and increasing search intervals

Active Publication Date: 2017-03-22
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

At present, no one has conducted in-depth research on this field. The present invention will enrich the research work in this field and promote the development of multidisciplinary optimization of wings with large aspect ratio.

Method used

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  • Pneumatic/structure/static aeroelasticity coupling optimizing method for high-aspect-ratio wing
  • Pneumatic/structure/static aeroelasticity coupling optimizing method for high-aspect-ratio wing
  • Pneumatic/structure/static aeroelasticity coupling optimizing method for high-aspect-ratio wing

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Embodiment Construction

[0045] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0046] Such as image 3 As shown, the present invention proposes an aerodynamic / structure / static aeroelastic coupling optimization method for a large aspect ratio wing, comprising the following steps:

[0047] (1) Select the fuselage slenderness ratio, wing aspect ratio, root ratio, and sweep angle as the global optimization variables, and set the upper and lower bounds of the global optimization variables.

[0048] (2) Select the initial value of the global optimization variable.

[0049] (3) Select the wing installation angle and the wing section torsion angle as the optimization variables of the aerodynamic subsystem level, and set the upper and lower bounds of the optimization variables of the aerodynamic subsystem level.

[0050] (4) Generate sample points in the design space composed of the aerodynamic subsystem-level optimization varia...

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Abstract

The invention discloses a pneumatic/structure/static aeroelasticity coupling optimizing method for a high-aspect-ratio wing. The pneumatic/structure/static aeroelasticity coupling optimizing method is based on the system decomposition strategy in multidisciplinary optimization for system-level decomposition and subsystem-level decomposition. In pneumatic subsystem-level decomposition, the pneumatic performance under the cruising appearance serves as an optimal object, and the rigidity-appearance pneumatic performance in traditional pneumatic optimization is replaced; after pneumatic subsystem-level decomposition is completed, and pneumatic loads, pneumatic appearance design parameters and structural configuration parameters serve as the input conditions for structure subsystem-level optimization; after pneumatic subsystem-level decomposition and structure subsystem-level decomposition are completed, the target quantity of system-level decomposition is output, system-level decomposition is returned, and therefore the pneumatic/structure/static aeroelasticity multidisciplinary comprehensive optimization design process is achieved through iterative optimization of the pneumatic appearance parameters and the structure parameters.

Description

technical field [0001] The invention relates to the field of multidisciplinary optimization methods for large aspect ratio wings, in particular to an aerodynamic / structure / static aeroelastic coupling optimization method for large aspect ratio wings. This method considers the aerodynamic / structural / static aeroelastic multidisciplinary coupling and comprehensive optimization framework design and formulation under the wing cruise state. Background technique [0002] UAV's unique advantages such as low cost, reusability and strong maneuverability make it have broad market application prospects in military and civilian fields. The demand for future information warfare and the continuous pursuit of earth remote sensing and disaster monitoring have made the development of high-altitude and long-endurance UAVs receive unprecedented attention worldwide. Due to its excellent lift-to-drag ratio characteristics, the large aspect ratio wing can effectively improve the flight time of UAV...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20G06F2113/28Y02T90/00
Inventor 王晓军刘冠华郑宇宁王磊张泽晟罗振先
Owner BEIHANG UNIV
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