| 1. | Analysis of nozzleless solid propellant rocket motor performance
无喷管固体火箭发动机内弹道计算 |
| 2. | As combat simulation frame and as missile trajectory simulation model are setup in the paper
建立了空地作战任务仿真框架和空地导弹的弹道计算模型。 |
| 3. | The accuracy of the parameters is improved by linking the aerodynamic calculation and ballistic calculation
将气动力的计算与弹道计算联系起来，提高了在干扰流场下气动力计算的精度。 |
| 4. | This thesis introduces the design of aero - dynamic calculation module , trajectory calculation module , and the visualization simulation module . at the last a example of visualization simulation of a kind of air - to - air missile was given
第五章讲述气动计算模块，弹道计算模块以及可视化仿真模块的程序设计，并对某空空导弹的飞行过程进行了可视化仿真。 |
| 5. | It can bring errors on the impact point . sometimes the errors can reach hundreds of meters or even more . so in order to insure the precision of the missile , the disturbing gravitation is must be take into account when we calculating the ballistic trajectories
作用在远程导弹弹道上的扰动引力对导弹落点偏差的影响是不可忽略，它对导弹落点偏差的影响可达数百甚至千米数量级，所以要保证导弹的命中精度就必须在弹道计算中考虑扰动引力的影响。 |
| 6. | In this paper , we not only analysed the different effects of the disturbing gravitation on the trajectories of different ranges , but also discussed shortcomeings of the spherical harmonics model by which the external gravitation potential of the earth is shown usually . when the model is applied directly to the calculation of the trajectory , since the recurrent calculation can not be avoided , an increase in orders of model will result on a decrease in the speed of calculation
本文重点分析了扰动引力对不同射程导弹的落点偏差的影响，并且讨论了原有计算扰动引力的球谐函数法在计算速度上的缺陷(由于勒让德函数的递推计算，使得随着模型阶数的增加模型的计算速度下降) ，然后对其进行改进使其能更好的适用于弹道计算。 |
| 7. | C . based on a lot of referenced documents and tunnel experiment data , the phenomenon of lateral jet interception are analyzed , and the diagrams of the interaction factor " kcn " is presented . following , the airdefence missile model , trajectory model including attitude - control direct lateral force are constructed
3 、根据大量参考文献和试验数据，分析了侧向喷流的干扰特性，并给出不同状况下干扰因子k _ ( cn )的变化曲线，在上述工作的基础上，建立了带有姿控侧向力装置的防空导弹模型和弹道计算模型。 |
| 8. | Design of two propulsion systems is studied - solid rocket ramjet and liquid ramjet . the performance analysis models and design methods are set up for these two kinds of engines . the different characteristics are analyzed and compared , which provide basis for farther trajectory computation and conceptual optimization design
( 4 )研究了两种动力装置? ?固体火箭冲压发动机和液体燃料冲压发动机的设计问题，建立了两种发动机的性能分析模型和计算方法，对固体火箭冲压发动机和液体燃料冲压发动机的特性进行计算分析及比较，为弹道计算及总体优化设计提供依据。 |
| 9. | The interface technology of cartridge and rocket system is developed , specified and realized . the software integration of autocad , c language , ms office , the calculations of some characteristic parameters , the computations of interior ballistics and exterior ballistics is successfully realized . the database of models and methods is carried out also
论文主要研究了弹箭设计集成软件系统的骨架和界面设计；弹箭数据库的开发及设计；弹箭系统接口技术的开发、设定和实现； autocad 、 c语言、 msoffice 、特征数计算、内弹道计算、刚体(质点)外弹道计算等软件的搭载实现；模型库和方法库的开发等。 |
| 10. | With the recurrent calculation got rid of , the speed of calculation is increased . practical calculations have shown that the new model not only have the high precision but also enables us to enhance the speed of calculation 6 or 7 times . so it is testified that the new model is superior to the spherical harmonics model
通过将换极后的球谐函数用于弹道计算，得出换极后的球谐函数不仅在计算精度上可达较高要求，而且计算速度也明显优于未换极的球谐函数(新模型的计算速度是约为换极前模型的6 7倍) 。 |
