点火药量对双脉冲固体火箭发动机点火过程影响

Translated title of the contribution: Impact of ignition charge on ignition process of dual⁃pulse solid rocket motor

Dingguo Xia, Guiyang Xu, Zhijun Wei, Weiqi Zhang

Research output: Contribution to journalArticlepeer-review

2 Citations (Scopus)

Abstract

In order to find out the impact of ignition charge on ignition process in the second pulse, a model was established.The axisymmetric unsteady Navier⁃Stokes equation and the standard k⁃ε turbulence model were used to simulate the second pulse ignition process.Based on that, the impacts of the igniter working duration and ignition gas flow rate on the ignition delay were studied.The results showed that:when the ignition gas flow rate was constant, increasing the igniter working duration can effectively shorten the second pulse ignition delay, and there existed a limit value of the ignition delay, which was defined as the minimum ignition delay.Different ignition gas flow rates corresponded to different minimum ignition delay, and the bigger ignition gas flow rate indicated the smaller minimum ignition delay.The ignition gas flow rate had a negative exponential relationship with the minimum ignition delay.Choosing the free volume as the sum of the first and second pulse free volumes is more reasonable when calculating the second pulse ignition charge.

Translated title of the contributionImpact of ignition charge on ignition process of dual⁃pulse solid rocket motor
Original languageChinese (Traditional)
Pages (from-to)433-442
Number of pages10
JournalHangkong Dongli Xuebao/Journal of Aerospace Power
Volume37
Issue number2
DOIs
Publication statusPublished - Feb 2022
Externally publishedYes

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