Method for simulating deviation of guidance of solid rocket launch vehicle

A solid motor and launch vehicle technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as inconvenient guidance system Monte Carlo simulation, difficult to analyze the influence of solid motor deviation on the guidance system, etc., to achieve Strong engineering application value, strong practicability, and the effect of improving confidence

Active Publication Date: 2018-01-09
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology

The guidance system generally uses the Monte Carlo method to simulate and analyze various deviations, and the form of the upper deviation and lower deviation of the inner trajectory only provides two envelope curves, which is not convenient for the Monte Carlo simulation of the guidance system, so it is difficult to analyze the solid engine The effect of deviation on the guidance system

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  • Method for simulating deviation of guidance of solid rocket launch vehicle
  • Method for simulating deviation of guidance of solid rocket launch vehicle
  • Method for simulating deviation of guidance of solid rocket launch vehicle

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Embodiment Construction

[0037] In order to make the above-mentioned purpose, features and advantages of the present invention more obvious and understandable, the specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0038] In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention can be implemented in many other ways that are different from those described here, and those skilled in the art can make similar extensions without departing from the connotation of the present invention, so the present invention is not limited by the specific implementation disclosed below.

[0039] see figure 1 , in one embodiment, launch vehicle solid motor guidance deviation simulation method, comprises the following steps:

[0040] S1: Calculate the theoretical average specific impulse and theoretical total charge according to the ...

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Abstract

The present invention provides a method for simulating the deviation of guidance of a solid rocket launch vehicle. The method comprises the following steps: S1: calculating a theoretical average specific impulse and a theoretical total charge according to a nominal internal ballistic parameter of a solid engine; S2: according to the theoretical average specific impulse, theoretical total charge, the average specific impulse deviation, and the total charge deviation, calculating the total impulse of the solid engine in the deviation state; S3: according the theoretical total charge, the total charge deviation, the rated working time, and the working time deviation, calculating the average second consumption, and calculating the average thrust according to the total impulse, the rated working time and the working time deviation; and S4: calculating the equation of the center of mass motion of the guidance system by using the average second consumption and the average thrust so as to carry out simulation analysis of the deviation of the solid engine on the guidance system. The method provided by the present invention is simple in calculation and strong in practicability, and has strong engineering application value for the launch vehicle guidance system to carry out Monte Carlo simulation analysis on the influence of the deviation of the solid engine.

Description

technical field [0001] The invention relates to the field of launch vehicle guidance control, in particular to a simulation method for guidance deviation of a launch vehicle solid engine. Background technique [0002] Solid motors are chemical rocket motors that use solid propellants. The solid motor of the launch vehicle generally provides the internal ballistic rated parameters for the guidance system, and the deviation of the solid motor is generally provided in the form of the upper deviation of the inner ballistic and the lower deviation of the inner ballistic. The guidance system generally uses the Monte Carlo method to simulate and analyze various deviations, and the form of the upper deviation and lower deviation of the inner trajectory only provides two envelope curves, which is not convenient for the Monte Carlo simulation of the guidance system, so it is difficult to analyze the solid engine Effects of deviations on the guidance system. Contents of the inventio...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 邱伟毛承元陈韦贤张开宝丁秀峰郝钏钏
Owner SHANGHAI AEROSPACE SYST ENG INST
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