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Separation reliability simulation platform for multistage carrying spacecraft

A simulation platform and spacecraft technology, applied in design optimization/simulation, aerospace vehicles, instruments, etc., can solve the problems of reliability analysis, scheme and product launch of the separation system without multi-stage carrier spacecraft

Active Publication Date: 2018-09-11
NAT UNIV OF DEFENSE TECH
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AI Technical Summary

Problems solved by technology

However, there are currently no plans and products specifically designed for reliability analysis of the separation system of multi-stage launch vehicles.

Method used

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  • Separation reliability simulation platform for multistage carrying spacecraft
  • Separation reliability simulation platform for multistage carrying spacecraft
  • Separation reliability simulation platform for multistage carrying spacecraft

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Embodiment Construction

[0093] refer to figure 1 , the present invention provides a multi-stage carrier spacecraft separation reliability simulation platform, the multi-stage carrier spacecraft includes an upper level and a lower level, and the simulation platform includes a test parameter setting subsystem, a separation dynamics simulation subsystem and a reliability analysis Subsystem:

[0094] refer to figure 1 and figure 2 , the test parameter setting subsystem is the bottom layer of the simulation platform. It configures the random test parameters by reading the standard parameter setting file and uses the interface to adjust and modify some parameters. The test parameter setting subsystem includes a simulation parameter setting module, a dynamic parameter setting module, a load parameter setting module, a pneumatic configuration module, a deviation configuration unit, and a reliability analysis parameter configuration module. The simulation parameter setting module is used to configure simul...

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Abstract

The invention discloses a separation reliability simulation platform for a multistage carrying spacecraft. The multistage carrying spacecraft comprises an upper stage and a lower stage, and the simulation platform comprises a test parameter setting subsystem, a separation dynamics simulation subsystem and a reliability analyzing subsystem. The test parameter setting subsystem serves as a bottom layer of the simulation platform, configures random test parameters by reading a standard parameter setting file, and utilizes an interface to adjust and modify part of parameters. The separation dynamics simulation subsystem conducts separation dynamics simulation on the multistage carrying spacecraft according to three stages. The reliability analyzing subsystem analyzes the separation reliabilityand significance level of the whole separation stage according to data obtained in multiple simulation processes of the separation dynamics simulation subsystem. According to the separation reliability simulation platform for the multistage carrying spacecraft, a separation system is combined with a reliability theory, and integrated analysis from configuration, simulation to reliability verification is achieved.

Description

technical field [0001] The invention relates to the technical field of spacecraft separation reliability analysis, in particular to a simulation platform for separation reliability of multi-stage carrier spacecraft. Background technique [0002] The research objects of vehicle separation are very extensive, usually including common multi-stage rockets, missiles, special escape vehicles and other vehicles. These aircraft need to rely on the separation system to separate the discarded parts from the carrier body according to the plan during the flight mission. This can improve the quality characteristics of the carrier and increase the carrying capacity, thereby ensuring that the performance and functions of the carrier meet the mission requirements. Successfully completed the follow-up flight mission. The separation of the carrier runs through multiple stages of the rocket and missile flight missions, and the separation operation is closely related to multiple systems such a...

Claims

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Application Information

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IPC IPC(8): B64G1/00G06F17/50
CPCB64G1/00G06F30/15G06F30/20
Inventor 李海阳周晚萌黄悦琛黄峰
Owner NAT UNIV OF DEFENSE TECH
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