基于弹丸膛内运动参数和压力测试的火炮膛内燃气温度估算方法
Estimation Method for Gas Temperature in Bore Based on Motion Parameters of the Projectile and Pressure Testing
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摘要:为了解决火炮膛内测试环境恶劣而导致发射药燃气温度测试难度大的问题，基于微波干涉仪、压力测试系统，结合发射药配方性能计算理论、装药内弹道性能计算模型等理论，建立了一种基于实测参数的火炮膛内燃气温度估算方法，并开展了试验研究。结果表明：火炮膛内燃气温度的最高值约为2 631.8 K，随着弹丸运动迅速降低，弹丸出炮口时膛内燃气温度降低到约1 858.4 K；建立的火炮膛内发射药燃气温度估算方法可以有效地获得火炮整个内弹道过程中火药燃气温度随时间的变化规律，为低烧蚀发射药及装药的研制提供了一种新的研究手段。
Abstract:To solve the problem that it is difficult to accurately measure the gas temperature in the gun bore because of the harsh testing environment, based on microwave interferometer and pressure testing system, and combined with the calculation theory of the propellant formula performance and the interior ballistic performance, a method for estimating transient temperature of gas in bore was established based on the measured parameters, and the tests were conducted. The results show that the maximum gas temperature in bore is about 2 631.8 K, the gas temperature decreases rapidly with the projectile movement, and the gas temperature in bore drops to 1 858.4 K when the projectile exits the muzzle. With this method, the change law of gas temperature in bore with time can be obtained effectively, which provides a new mean for the research on low-ablation propellants and charges.
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