| 1. | The vertical tail is less affected by the remainder of the airplane .
垂尾受飞机其它部分的影响较小。 |
| 2. | The sideslipping airplane gives rise to a side force on the vertical tail .
侧滑的飞机在垂直尾翼上引起侧力。 |
| 3. | The vertical tail size is not set to avoid spiral instability because this mode is not critical .
垂尾的大小不是根据避免螺旋不稳定来确定的。因为这种运动模态不是设计状态。 |
| 4. | Optimal design of vertical tail using genetic - neural network algorithms
神经网络算法优化飞机垂尾 |
| 5. | The wind - tunnel investigation of the characteristics and mechanism of twin - vertical tail buffet of leading - edge extension configuration
边条翼布局双垂尾抖振特性与机理风洞实验研究 |
| 6. | Double - wing micro air vehicles adopts the aerodynamic shape : no tail , only wings and vertical tail placing in wing
双翼式微型飞行器采用无尾式,且只有机翼,垂尾也置于机翼上的气动布局。 |
| 7. | Meanwhile , the soft of measured load calculation based on strain method and the soft of theory calculating load on vertical tail are programmed by fortran language
采用fortran语言编制了应变法实测载荷回归计算程序，垂尾载荷理论计算程序。 |
| 8. | The active vibration control aimed at aircraft empennage has huge practical values in the aspects of adding the fatigue life of vertical tail , increasing the capability and availability of the aircraft , reducing the through - life - support costs and so on
飞行器垂直尾翼的振动主动控制对于提高尾翼的疲劳寿命、飞行器的机动性以及减小飞行器的维护成本具有较大的实际意义。 |
| 9. | The material characteristic and principle of piezoelectric material ( pzt ) and macro - fiber composite ( mfc ) is analyzed . cada - x structural dynamics analytic software is used to carry on the experimental modeling and mode analysis of the vertical tail . consequently , the disposal scheme of sensor and actuator is confirmed
本文的主要研究内容为:一、分析了压电陶瓷和压电纤维复合材料的特性及工作原理,采用比利时lms公司的cada - x结构动力学分析软件对尾翼模型进行实验建模与模态分析,根据模态实验结果,确定了传感/驱动元件的布置方案。 |
| 10. | This paper aims at model of vertical tail based on certain type aircraft . the method of distributed actively vibration control based on multi dsp has been carried on this model . a distributed actively vibration control system based on dsps is designed to real timely control the structural vibration of two modes
本文以某型飞机的尾翼模型为目标,采用基于多dsp处理器的分布式控制方法实现对垂直尾翼模型的振动主动控制,开发出了一套基于dsp的振动主动控制系统,针对结构的两阶模态振动实施了分布式振动主动控制,并进行了相关的理论和实验研究。 |
