| 1. | Dual - mode optimization asymmetry fuzzy logic controller design for x aeroengine mfp
某涡扇发动机主燃油通道模糊控制器设计 |
| 2. | Construction of weighting matrixes in mixed sensitivities h controller design for aeroengine
涡扇发动机转速鲁棒控制器设计及试验 |
| 3. | On a novel multi - objective fsqp algorithm for multi - variable nonlinear control of turbofan engine
算法实现涡扇发动机多变量非线性控制 |
| 4. | Numerically assessing aerodynamic stability of compression component running in turbofan engine
涡扇发动机整机环境下压缩部件稳定工作边界计算方法 |
| 5. | But such is the reliability and power of modern high - bypass turbofan engines that it has ceased to be a worry
但现代涡扇发动机的可靠性和强劲的动力打消了人们的疑虑。 |
| 6. | The simulation accuracy can be improved by above model for the turbofan engine transient performance
上述模型的建立将有效的提高涡扇发动机过渡过程性能模拟程序的精度。 |
| 7. | The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine
喷管中的气流由主流燃气和次流空气组成，用以模拟涡扇发动机的喷管。 |
| 8. | The mathematical model of a twin - spool turbofan engine is set up , and the “ one ? pass through algorithm ” is used to construct the real time dynamic model
利用部件级建模方法建立了某大型涡扇发动机数学模型,采用一步通过算法使过渡过程计算满足实时性。 |
| 9. | And based on these , the application of sequential quadratic programming ( sqp ) to the turbofan engine performance seeking control is investigated
并在此基础上，运用序列二次规划法对涡扇发动机的加、减速和加力加速等过渡过程寻优控制问题进行了研究。 |
| 10. | The mission section , the constrain conditions , the weight composition of the maneuverable missile , and the model of used in turbofan engine maneuverable missile were presented
简述了飞航导弹任务剖面、约束条件的给定、导弹的重量组成以及涡扇发动机模型。 |
