| 1. | Exact computation of the burning surface area is lengthy .
燃烧面积的精确计算是非常繁难的。 |
| 2. | The burning surface area remains constant during the entire firing .
在整个燃烧期间的燃烧面积是常值。 |
| 3. | The burning surface of the powder then increases, the pressure rises and the rocket may be blown up .
此时，无烟药燃烧表面增加，压力上升，火箭可能爆炸。 |
| 4. | Burning surface augmentation
燃烧面增大 |
| 5. | This paper describes a new computer program ( regresssd ) to simulate the regression of complex 3 _ d grain cavity and calculate the burning surface area
本论文介绍了一种新的固体火箭发动机复杂三维药柱内腔燃烧推移和燃面计算的动态仿真和计算系统。 |
| 6. | This paper aims at developing a new method that can calculate burning surface of complicated 3d grain and defects grain to improve precision of interinal ballistic performance simulation and grain design level
本文旨在发展一种能精确计算复杂三维装药和含缺陷装药的燃面计算方法，以提高装药设计水平和内弹道预示精度。 |
| 7. | Level set method was used in this paper to attain burning surface variety regulation of arbitrary configuration grain by tracing interface of grain surface burnback . the work of this thesis can be summaried as follow : 1
本文运用等值面函数法( levelset ) ，追踪固体推进剂燃烧界面的变化，从而获得了任意结构型面装药的燃面变化规律，本文的主要工作及创新点概括如下： 1 |
| 8. | Burning surface calculation of complicated geometry grain . grain with flaw . grain with changing burning rate or multi - burning rate was performed . the results show that this new method has very high precision , and it provides a helpful method for the quality analysis of grain with defect
利用本燃面算法对复杂构形装药、含缺陷装药、变燃速和多燃速装药的燃面进行了计算，取得了较高精度的计算结果。 |
| 9. | The improvement to internal ballistic calculation precision of solid rocket motor ( srm ) is important to capture target of missile . and to accomplish it ' s task . calculation of burning surface of propellant grain is essential to interinal ballistic performance calculation
提高固体火箭发动机内弹道的计算精度对导弹准确捕获目标、完成任务有着重要的作用，而发动机工作时瞬态燃面计算是内弹道性能计算的基础。 |
| 10. | It has a large region of application in solid rocket motor grain design and has made new improvements compared with other available codes . user can easily and rapidly build his initial grain shapes and then obtain geometric information of his design . according to the theory describeds in the paper , the regressions of the burning surface area and the pressure are obtainded
该系统扩展了固体火箭发动机装药的设计能力，用户可利用它简捷地构造出三维药柱的初始形状，并获得设计所需的各个几何参数，进而依据本论文提出的复杂三维药柱内腔燃烧推移和燃面计算的方法，计算出燃面变化和压强变化，得到推力随时间变化的曲线，再依据这些计算结果进行再设计，直至达到满意的结果为止。 |
