Multi-objective optimization method for parametric design of nacelles
A multi-objective optimization and parametric design technology, applied in the field of aircraft manufacturing, can solve the problems of mutual influence, numerous geometric parameters of nacelle shape, etc., to achieve the effect of improving design efficiency, shortening design cycle and development cost, and simplifying design process
Active Publication Date: 2018-10-16
SHANGHAI JIAO TONG UNIV
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Problems solved by technology
However, there are many geometric parameters of the shape of the nacelle, and they are easy to interact with each other, so it is impossible to use the exhaustive scheme to complete the design of the nacelle
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[0014] In this embodiment, the engine nacelle profile of a wide-body airliner is taken as the research object, and the parametric design is carried out for the inner and outer profiles of the nacelle model, and the multi-objective optimization method is used to optimize simultaneously; the engine nacelle The design needs to take into account the stability of the internal airflow and the minimum external frictional resistance, so this embodiment takes the highest total pressure recovery coefficient of the internal airflow and the lowest frictional resistance of the external airflow as the two optimization goals of this research object, specifically including The following steps:
[0015] 1. Determine the optimization objective of the nacelle design and the multi-objective optimization process (such as figure 1 shown), the optimization objective in this embodiment is carried out on the external frictional resistance of the nacelle geometry and the total pressure recovery coeffic...
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The invention provides a multi-objective optimization method for a parameterized design of nacelles. With the external friction resistance of the nacelle geometry and the total pressure recovery coefficient of a fan inlet as the design target, the multi-objective optimization method for the parameterized design of nacelles selects the key geometric parameters of the inner and outer profiles of thenacelle geometry as reference variables, uses the Latin Hypercube (LHS) method to select the model library of the sample, carries out model building, mesh generation and numerical calculation of thenacelles corresponding to different geometric parameters, and then uses the radial basis neural network as an agent model according to the distribution law of the sample objective function, utilizes the multi-objective optimization algorithm for optimizing computation of the agent model, and finally selects the optimal nacelle line plan, that is, the higher total pressure recovery of the fan inletand the lower nacelle external friction resistance. The multi-objective optimization method for the parameterized design of nacelles can quickly find the optimal design value of the nacelle parameter, improving the design efficiency, shortening the design cycle and reducing the development cost.
Description
technical field [0001] The invention relates to a technology in the field of aircraft manufacturing, in particular to a multi-objective optimization method for nacelle parametric design. Background technique [0002] With the development of aviation technology in the world today, aircraft engine technology has also made great progress. The engine can effectively reduce the fuel rate of the aircraft engine while achieving a longer range. The realization of these advances requires that the engine must work in a stable and controllable operating state during the flight, while the engine as a whole is subject to less frictional resistance, and the nacelle device is used as the bleed air device and installation platform of the engine. The role in stabilizing airflow and reducing resistance is particularly significant. A correct nacelle design can effectively improve the total pressure recovery, flow coefficient and flow field uniformity at the fan inlet, significantly improve th...
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Login to View More IPC IPC(8): G06F17/50G06N3/04G06N3/12
CPCG06N3/04G06N3/126G06F30/15G06F30/17Y02T90/00
Inventor 崔玉超王鹏滕金芳卢少鹏
Owner SHANGHAI JIAO TONG UNIV