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Method for guided missile overall multi-disciplinary design oriented to multi-level performance

A design method, multi-disciplinary technology, applied in computing, special data processing applications, instruments, etc., can solve the problem of limited missile design space, large gaps in missile design and performance requirements, difficult to analyze the performance of guidance accuracy and kill probability level, etc. question

Active Publication Date: 2014-11-26
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0003] The existing overall multidisciplinary design method for missiles integrates fewer disciplines, which will lead to two problems: first, the performance analysis of missiles can only stay at the level of flight performance, and it is difficult to analyze the level of guidance accuracy and kill probability. Performance, which is far from the real missile design and performance requirements, and its use in the actual engineering field is limited
Second, the design space of the missile is largely limited, and it does not have the ability to construct solutions in a large-scale design space

Method used

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  • Method for guided missile overall multi-disciplinary design oriented to multi-level performance
  • Method for guided missile overall multi-disciplinary design oriented to multi-level performance
  • Method for guided missile overall multi-disciplinary design oriented to multi-level performance

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Embodiment Construction

[0032] Describe the present invention below in conjunction with specific embodiment:

[0033] Refer to attached figure 1 , the overall multidisciplinary design method of the missile facing the multi-level performance of the present invention comprises the following steps:

[0034] Step 1: According to the mission requirements, the basic configuration design of the missile is carried out in combination with the configuration of the missile. The design content of the basic configuration design of the missile includes the layout form of the missile, the number of wing surfaces, and whether there is a booster;

[0035] Step 2: On the basis of completing the basic configuration design of the missile, carry out the power system design of the missile; according to the design results of the power system, use the method of numerical estimation to analyze the performance of the engine, and obtain the power parameters; if the engine type in the design result of the power system is For a...

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Abstract

The invention provides a method for guided missile overall multi-disciplinary design oriented to multi-level performance. Shape design, power device design, part arrangement, trajectory design, guidance control system design, structural design, heat protection scheme design and warhead design are integrated. The method is supportive to scheme construction in a large range design space from the disciplines of shapes, power, layouts, trajectories, heat protection, structures, guidance control, warheads, invisibility and the like, and the performance analysis on three levels of guided missile flight performance, guidance accuracy and the kill probability can be achieved.

Description

technical field [0001] The invention relates to the technical field of multidisciplinary design, in particular to an overall multidisciplinary design method for missiles oriented to multilevel performance. Background technique [0002] The overall missile design is the top-level design activity throughout the missile development process. According to the division of the missile development process, the overall design can be divided into scheme demonstration, scheme design, and detailed design. The main tasks include: determining the main characteristics of the missile, providing guidance and basis for the design and development of subsystems; system to form a closed design scheme; complete the assessment of tactical and technical requirements, etc. [0003] The existing overall multidisciplinary design method for missiles integrates fewer disciplines, which will lead to two problems: first, the performance analysis of missiles can only stay at the level of flight performanc...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 龚春林谷良贤赵成泽申智韩远鹏万佳庆
Owner NORTHWESTERN POLYTECHNICAL UNIV
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