Numerical Simulation of Uncontrolled Ignition Process in Missile Engine Compartment

ZHANG Dingxiong; PAN Meng; LI Yafei

doi:10.7643/issn.1672-9242.2026.08.011

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Equipment Environmental Engineering ›› 2026, Vol. 23 ›› Issue (8) : 83-97. DOI: 10.7643/issn.1672-9242.2026.08.011

Weapons Equipment

Numerical Simulation of Uncontrolled Ignition Process in Missile Engine Compartment

ZHANG Dingxiong, PAN Meng, LI Yafei

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Abstract

The work aims to reveal the evolution mechanism of the gas flow field under uncontrolled ignition conditions inside a missile engine compartment and clarify the effects of pressure relief structures on internal pressure release and the thermal safety of adjacent missiles. Numerical simulations of the uncontrolled ignition process of missile engines inside the compartment were carried out through the commercial CFD software based on the species transport model and the Realizable k-ε turbulence model. Emphasis was placed on analyzing the distribution characteristics of temperature and pressure inside the compartment after ignition, the temperature rise law on the surface of adjacent missile bodies, as well as the effects of pressure relief port area on the above-mentioned parameters. After the uncontrolled ignition of the missile engine, secondary combustion mainly occurred in the turbulent mixing zone and the fully-developed jet zone. No secondary combustion took place in the jet core zone with the highest flow velocity, and the maximum temperature of the flow field inside the compartment reached 2 879 K at this time. The installation of pressure relief devices could significantly suppress pressure accumulation inside the compartment. Nevertheless, the overall temperature inside the compartment rose after the pressure relief device was activated, and only the region beneath the pressure relief port maintained a relatively low temperature. The secondary combustion behavior of a missile engine under uncontrolled ignition in a confined space is jointly determined by the degree of gas-air mixing and flow conditions, rather than merely by temperature conditions. There exists a prominent coupling effect between pressure relief structures and jet-induced heat input. Although pressure relief devices can effectively prevent pressure-overload risks, they aggravate overall thermal accumulation inside the compartment. Thus, the two factors need to be comprehensively balanced and optimized in design. The layout of pressure relief ports directly governs the thermal safety boundary of adjacent missile bodies. Placing high-risk missiles in the region beneath pressure relief ports can effectively delay their thermal response process and improve the overall safety redundancy of the ammunition compartment.

Key words

missile engine / gas flow field / ignition / thermal safety / gas jet zone / numerical simulation

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ZHANG Dingxiong, PAN Meng, LI Yafei. Numerical Simulation of Uncontrolled Ignition Process in Missile Engine Compartment[J]. Equipment Environmental Engineering. 2026, 23(8): 83-97 https://doi.org/10.7643/issn.1672-9242.2026.08.011

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