| 1. | An profile evaluating method based on least square principle is described
在该系统中给出了一种基于最小二乘原理的弹翼轮廓误差评价方法。 |
| 2. | At last , the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed
最后，初步分析了高超声速弹翼表面发生烧蚀后对其外弹道特性的影响。 |
| 3. | To overcome the shortcomings of low efficiency and high uncertainty in the measurment of wings ' cross section shape by using a templet , a nc non - contact measuring system is designed
摘要为解决使用专用样板进行弹翼测量效率低、误检率高的缺点，设计了一种数控非接触测量系统。 |
| 4. | The model is solved with the finite difference method , the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns
采用有限差分法进行数值求解，并编制了较为通用的仿真软件，用于模拟诸如由电热化学炮发射的高超声速穿甲弹弹翼前缘的瞬时热效应。 |
| 5. | Numerical results are in good agreement with some data and the method and procedure presented in this paper are verified . and then the wing ? flutter characters of a missile wing are numerical simulated with the examples of a missile wing
以某导弹翼面为算例，对弹翼的亚、跨、超音速的颤振临界速度进行了数值计算，部分计算结果与风洞计算结果相比较，一致性很好。 |
| 6. | Because these projectiles attain hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads , the survivability of the front region of projectile wing is very important for designer to consider
由于这类弹丸在大气中高速飞行，并受到剧烈的气动加热及空气动力负荷的作用，因此，弹翼前缘部的生存能力就成为弹丸设计中必须要考虑的问题。 |
| 7. | The first part improves the rigid of the structure and second part decreases the weight . a composite wing - cabin structure is analyzed and optimized in this paper . the result shows that the rigid and the weight of the structure are improved obviously
本文通过对一个全复合材料的弹翼、舱段组合结构按上述方法进行了优化设计，计算结果表明，结构在刚度、重量方面均可得到明显的改善。 |
| 8. | The interior temperature distribution and ablation model of projectile wing is established from general transmitting heat differential equation ; at the same time , the heat flow density and pressure distribution model of projectile wing is also established
从一般形式的导热微分方程出发，逐步建立了弹翼内部温度分布和烧蚀的数学计算模型；与此同时，建立了弹翼表面的热流密度和压力分布的数学模型。 |
| 9. | The paper simulate the transient thermal response of projectile wing according to the simulation software , and discuss the ablation characteristic when the projectile wing is in different initial velocity , in different wing shape , in different atmosphere condition and in different material condition
本文通过仿真软件模拟了弹翼的瞬时烧蚀外形，并详细讨论了不同初速、不同翼形、不同气象条件及不同材料条件下的烧蚀特性。 |
| 10. | The 3 - d complex flowfield of rocket - missile with wings and empennages induced by the interaction between by base jet and the flow around the body has been numerically simulated . the main work is as follows : first , the gordon - mcbride program was developed to make it more friendly and efficient to the users
本文对带弹翼/尾翼弹箭的三维喷流绕流复杂流场进行了数值模拟，其主要研究内容有：首先，对gordon - mcbride火箭程序作了改进，使改进后的软件具有了非常友好的人机交互界面。 |
