Method and device for evaluating carrying capacity of solid carrier rocket

A launch vehicle and carrying capacity technology, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as low computing efficiency and complicated computing process, and achieve improved computing efficiency, simple computing process, and computational efficiency Improved effect

Pending Publication Date: 2022-02-25
航天科工火箭技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The embodiment of the present application provides a method and device for rapid evaluation of the carrying capacity of a solid launch vehicle, which solves the problems in the prior art that the calculati

Method used

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  • Method and device for evaluating carrying capacity of solid carrier rocket
  • Method and device for evaluating carrying capacity of solid carrier rocket
  • Method and device for evaluating carrying capacity of solid carrier rocket

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Embodiment

[0045] Such as figure 1 As shown, the present embodiment provides a method for evaluating the carrying capacity of a solid launch vehicle, the method comprising

[0046] S101: Obtain the carrying capacity table under the ballistic envelope of the working condition of the solid launch vehicle;

[0047] Specifically, the carrying capacity number table may be read from a database pre-stored with the carrying capacity number table to obtain the carrying capacity number table.

[0048] Specifically, the operating conditions of the solid launch vehicle include, for example, entering one or more of target orbits with different orbital inclination angles and heights, etc., so that the data in the carrying capacity table includes the data of the solid launch vehicle under each operating condition . Of course, the data in the carrying capacity table may also include the data of the solid launch vehicle under some working conditions.

[0049]In the embodiment of this specification, th...

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Abstract

The invention discloses a method and a device for quickly evaluating the carrying capacity of a solid carrier rocket. The method comprises the following steps: acquiring a carrying capacity table of the solid carrier rocket under ballistic envelopes under different working conditions, for example, a carrying capacity table under ballistic envelopes under working conditions such as target orbits with different orbit inclination angles and heights entry; analyzing the carrying capacity data table through multiple linear regression analysis, and establishing a fitting function; and acquiring current launching data of the target solid carrier rocket, and inputting the current launching data into the fitting function to obtain current carrying parameters of the target solid carrier rocket. According to the evaluation method for the carrying capacity of the solid carrier rocket, the technical problems that in the prior art, the calculation process is complex and needs to be completed by trajectory professionals, and the calculation efficiency is low are solved.

Description

technical field [0001] The invention relates to the technical field of launch vehicle trajectory design, in particular to a method and device for evaluating the carrying capacity of a solid launch vehicle. Background technique [0002] In the trajectory design of solid launch vehicles, it is necessary to evaluate the carrying capacity of the current rocket on the target orbit to determine the feasibility of the rocket launch mission. For a multi-stage solid launch vehicle, for example, a four-stage solid launch vehicle composed of a three-stage solid motor and a first-stage attitude control motor, the first three stages use energy-depleted solid propulsion motors, and the final stage uses liquid or solid motors, responsible for Correct the flight deviation of the first three stages and provide the necessary orbital speed increment. The general structural quality of this type of rocket is relatively fixed, and the timing of the first three stages is fixed, so the carrying ca...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20
Inventor 黎桪邹延兵李晓苏汪潋刘克龙左湛周鑫周一凡张昌涌王震姜航刘欣赵爽陈辰罗喜望
Owner 航天科工火箭技术有限公司
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