In order to analyze the temperature fields, temperature grads, thermal stress and thermal strain of large caliber machine gun barrel during firing, an analysis model was established for large caliber machine gun. The finite element analyze model are founded and the boundary condition of the model are loaded. The results indicated the temperature, temperature grads, thermal stress and thermal strain of the large caliber gun tube during continuous shots. The effect of thermal pulse loading on thermal stress, thermal strain is very obviously. So, thermal pulse loading is the primary origin of thermal stress, thermal strain of the large caliber machine gun barrel. At the same time, the thermal pulse loading is one of the important factors affecting the life of the gun tube.
To further understand the muzzle combustion mechanism in high-altitude firing, the influence of supersonic flow on the muzzle combustion phenomenon is investigated. The set of internal ballistic equations is employed, providing accurate velocity and pressure when the projectile moves to the muzzle. The multispecies transport Navier-Stokes equations with complex chemical reactions is solved by coupling a real gas equation of state, the Soave-Redlich-Kwong Model, and a detailed chemical reaction kinetic model. The development of muzzle flow with chemical reaction is simulated. The interaction of chemical reactions with the muzzle flow field is obtained by numerical simulation in order to explain the muzzle combustion phenomenon of fire at supersonic flight. The mechanism of muzzle combustion influenced by supersonic incoming flow is analyzed in detail. It is demonstrated from the results that the shock wave and the expansion of the jet are restrained so that the combustion is compressed behind the projectile, at the same time generating a second region of combustion behind the muzzle under the influence of supersonic incoming flow.
This paper presents a servo control method for the multiple launch rocket system (MLRS) launcher during marching fire operations. The MLRS, being a complex nonlinear system, presents challenges in designing its servo controller. To address this, we introduce the fuzzy adaptive sliding mode control (FASMC) approach. The permanent magnet synchronous motor (PMSM) and controller of the MLRS were simulated in the MATLAB/Simulink environment. The dynamic model of the MLRS during marching fire was established using multi-body system theory, vehicle mechanics, and launch dynamics. The dynamic model was then integrated with the FASMC-based controller using the Adams/View module. Numerical calculations were performed to demonstrate the control performance and the effectiveness and applicability of the proposed approach were validated through a comparison experiment between FASMC and other common control methods.
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