冲量，动量的改变；火箭方程；随机运动的压力作用点。
Impulse and momentum change; rocket equation; origin of pressure from random motion.
火箭方程式是为了源源不断的特定推进任务，通过加入牛顿第二定律而得到的。
The rocket equation is obtained for a constant specific impulse mission by integration of Newton's second law.
本文建立了火箭发动机在管内点燃情况下，串联结构的高低压无后座力发射器的内弹道方程，并对试验弹进行了数值计算。
This paper established the internal ballistics equation for the high-low pressure launcher with tandem construction when the rocket motor is ignited in the launch tube.
以轴对称非定常欧拉方程为基础，建立了激光推进火箭发动机吸收室内纯气相单组分、以激光等离子体为内热源的流场模型。
A gas flow model with laser plasma as heat source was developed based on axial symmetric Euler equations in the laser propulsion rocket engine absorption chamber.
针对采用液体推进剂火箭发动机的空间推进系统，推导了系统液路和气路的通用积分形式方程。
The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine.
发动机喷管与火箭固联时的横向运动方程序及其相应的边界条件是分析工作的基础。
The equations of transverse movement when nozzle connected rigidly with rocket and related boundary conditions form the basis for analyses.
根据滚转火箭弹的动力学方程，给出了在弹体坐标系下无控低速滚转火箭弹在被动飞行段的锥形运动方程组。
The nonlinear coning motion equations in body coordinates on the force moment coefficients of low speed spinning rocket were obtained based on the dynamics equations.
本文在精确的六自由度运动方程的基础上，建立了计算航空火箭弹散布的优化模型。
In this thesis. Based on the accurate six freedom degrees kinetic equations of the air rocket, an optimizing model of calculating air rocket dispersion is established.
以12组分9反应方程模型为例，利用编制的计算程序，对某火箭燃气自由射流流场进行了模拟。
Taking 9 reaction equations with 12 components as an example and utilizing the established calculation program, the free jetting flow field of the rocket is simulated.
研究了运载火箭的基本控制理论，建立了运载火箭六自由度动力学和运动学方程组。
First, basic theories are about the guidance and control method of greater launch vehicle are introduced, the kinematic and kinetic equations of six-degree of freedom of launch vehicle are set up.
基于有限元分析的基本原理，建立了热-机耦合问题分析的有限元基本方程，并对固体火箭发动机药柱在固化冷却过程进行了数值仿真。
Based on the FEA, the numerical method of thermal-mechanical coupling is presented. With this method, solid grains during its curing process is simulated.
基于有限元分析的基本原理，建立了热-机耦合问题分析的有限元基本方程，并对固体火箭发动机药柱在固化冷却过程进行了数值仿真。
Based on the FEA, the numerical method of thermal-mechanical coupling is presented. With this method, solid grains during its curing process is simulated.
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