No abstract

Recoil reduction is one of the most important issues for the design of aircraft gun. Traditional approaches for this purpose will produce back-blast, which constitutes a hazard to fighter planes or attack helicopters. This paper presents a closed type gas reflection device for the aircraft gun aiming to reduce the recoil force without ejecting the propellant gas rearward. The launching process is modeled by coupling the classical interior ballistic model and the flow equations for the closed type gas reflection device. The fourth order Runge-Kutta method is adopted to solve the modified interior ballistic model to obtain the recoil efficiency of the closed type gas reflection device. On this basis, effects of various parameters on the recoil efficiency and muzzle velocity are studied systematically. Finally, shooting experiments are carried out upon a 30mm caliber aircraft gun. The simulated results agree well with the experiment ones. The results show that, by using the closed type gas reflection device, the recoil efficiency of 26.01% is attained without ejecting the propellant gas rearward, nor decreasing the muzzle velocity dramatically.

This article theory is based on steady-state heat transfer. According to the positional relationship between Communications base stations and the position of sun, it is calculated by solar radiation intensity and its integrated temperature generated design. Also, Communications base on stations steady-state thermal physical model. The measured data independent Communications base stations building envelope, the internal temperature of the base station communications equipment and other total heat input model, we can simulate the temperature data communication within the base station. The model established for communication base station enclosure structure optimization design, simulation and prediction, performance evaluation and base station auxiliary energy saving equipment research provides convenient and practical and reliable simulation platform.