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Guo Q.-Y.,Unit 63963 of PLA | Li L.-C.,Unit 63963 of PLA | Wu X.,Unit 63963 of PLA | Chang Y.,Unit 63966 of PLA
Binggong Xuebao/Acta Armamentarii | Year: 2015

The temperature and pressure of nozzle of launch tube have effect on missile launch. An axis symmetric model is built to simulate the launching process of missile, and the structured grid is partitioned. The dynamic grid method is used to compute the launching process of missile. The initial values of simulated temperature and pressure are given, and the displacement, speed and pressure parameters as well as the flow field distribution are obtained. The numerically simulated results are in well agreement with the experimental data. © 2015, China Ordnance Society. All right reserved.

Guo Q.-Y.,Unit 63963 of PLA | Shi Y.-Q.,Unit 63963 of PLA | Zhang C.-Q.,Unit 63963 of PLA | Zhong D.-X.,Unit 63963 of PLA
Binggong Xuebao/Acta Armamentarii | Year: 2012

The flow characteristics of gun-launched missile at transonic speed were investigated by a numerical method. Based on Euler equation solver, a mixed mesh N-S equation solver was developed using S-A turbulence model. Some fast convergence methods and proper dissipation terms model are included in the solver. The 3D N-S equation solver developed in this paper converges quickly and is more stable. Computational aerodynamic characteristics are found to be in good agreement with wind tunnel test results. The results indicate the computation result can offer a basis and reference for shape design of missile.

Guo Q.-Y.,Unit 63963 of PLA | Li L.-C.,Unit 63963 of PLA | Niu S.-R.,Unit 63963 of PLA | Liu Y.,Unit 63963 of PLA | Li D.-Y.,Unit 63963 of PLA
Beijing Ligong Daxue Xuebao/Transaction of Beijing Institute of Technology | Year: 2013

Wind tunnel experiment is used in the investigation of aerodynamic characteristics of gun-launched missile. A series of wind tunnel experiment models were designed with a modularized method, and 6-component measuring experiments were conducted to study the aerodynamic characteristics of gun-launched missile under the conditions of Ma=0.8~1.2, α=0°~12° and δz=0°~15°. Parameters of the aerodynamic characteristics of gun-launched missile are obtained through wind tunnel experiment and the results will provide evidence to optimize the configuration of gun-launched missile in engineering design.

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