Iterative design method for hypersonic-velocity aircraft model

A hypersonic, iterative design technology, applied in the field of aircraft, can solve the problems of time-consuming data acquisition process, unfavorable model optimization iterative design, control function fusion and other problems

Active Publication Date: 2017-12-15
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0003] However, the traditional hypersonic vehicle modeling process is often based on wind tunnel and test data, and the workload is huge and expensive; in addition, the data acquisition process takes a long time, which is not conducive to the optimal iterative design of the model, and the control effect is difficult to integrate with other overall parameters. fusion

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  • Iterative design method for hypersonic-velocity aircraft model
  • Iterative design method for hypersonic-velocity aircraft model
  • Iterative design method for hypersonic-velocity aircraft model

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Embodiment Construction

[0048] Such as figure 1 As shown, a hypersonic vehicle model iterative design method includes the following steps:

[0049] (1) Construct a parametric model of hypersonic vehicle through geometric design method;

[0050] (2) Extract the key model parameters of the hypersonic vehicle through the sensitivity method, simplify the parameterized model, and obtain the proxy model for the iterative design of the hypersonic vehicle;

[0051] (3) Optimizing the model parameters of the hypersonic vehicle by using the pigeon group optimization algorithm to obtain the equilibrium state of the model under different flight conditions;

[0052] (4) Determine the expected performance index of the hypersonic vehicle, iterate the equilibrium state of the model, and obtain the optimal design model of the vehicle.

[0053] Aiming at the characteristics of multi-disciplinary coupling of hypersonic aircraft, the present invention proposes a new model iterative design method. By constructing a par...

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Abstract

The invention discloses an iterative design method for a hypersonic-velocity aircraft model. The method comprises the steps that a parameterized model of a hypersonic-velocity aircraft is built through a geometric design method; a key model parameter of the hypersonic-velocity aircraft is extracted through a sensitivity approach, the parameterized model is simplified, and a surrogate model of the hypersonic-velocity aircraft for the iterative design is obtained; the model parameter of the hypersonic-velocity aircraft is optimized by using a pigeon-inspired optimization algorithm, and the balance states of the model in different flight conditions are obtained; a desired performance index of the hypersonic-velocity aircraft is determined, the balance states of the model are subjected to iteration, and the optimal design model of the aircraft is obtained. In complex flight conditions, the optimal design model is obtained by using the pigeon-inspired optimization algorithm according to the desired performance index, the optimal model parameter meeting the desired performance index is quickly obtained, all flight envelopes can be covered, and a good model optimizing tool is provided for the design of the hypersonic-velocity aircraft.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an iterative design method for a hypersonic aircraft model. Background technique [0002] Hypersonic aircraft has great military and civilian value due to its high Mach number and high-altitude flight characteristics. The hypersonic flight system integrates multi-disciplinary cutting-edge technologies, and the interaction between disciplines is complex. It is necessary to obtain the optimal aircraft model through comprehensive design. [0003] However, the traditional hypersonic vehicle modeling process is often based on wind tunnel and test data, and the workload is huge and expensive; in addition, the data acquisition process takes a long time, which is not conducive to the optimal iterative design of the model, and the control effect is difficult to integrate with other overall parameters. fusion. The present invention proposes a hypersonic vehicle model iterative design me...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 刘燕斌李昱辉陈柏屹沈海东金飞腾
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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