simulated rocket

According to the internal ballistic foreshowing models of solid rocket motors, the interior ballistic performances were simulated and computed by using Monte-Carlo method.

根据固体发动机内弹道性能预示模型，采用Monte Carlo法进行内弹道性能的模拟计算。

The complex flow was simulated with sequential and parallel SIMPLE algorithm in the combustion chamber of liquid rocket engine.

用串行和并行SIMPLE算法对液体火箭发动机燃烧室内的复杂流动进行了数值模拟。

The two phase turbulent combustion steady process and high combustion instability in the liquid rocket engine are simulated with the method of computational combustion dynamics.

采用计算燃烧学的方法对发动机燃烧室内的湍流两相燃烧过程的稳定燃烧状态和高频不稳定燃烧现象进行了数值模拟。

Through two methods measuring cutoff thrust and pressure of com-bustion chamber when testing liquid propellant rocket engine on ground, cu-toff impulse as simulated altitude condition is obtained. These methods are revie-wed simply, too.

本文叙述在地面条件下试验液体火箭发动机时，通过测量发动机后效段推力与测量发动机燃烧室压力两种方法来求得模拟高空后效冲量，并对这两种方法作简单评论。