| 1. | Discussion on aeroelasticity of large aspect - ratio wing
基于结构优化的大展弦比机翼质量估算 |
| 2. | Design method of active control law based on reduced order model of unsteady aerodynamics for aeroelasticity
基于非定常气动力低阶模型的气动弹性主动控制律设计 |
| 3. | Using above methods to solve unsteady pressure distribution , coupling structure equations , the supersonic or hypersonic aeroelasticity is simulated in time - domain
运用上述的非定常气动力求解方法，耦合结构动力学方程，实现超音速、高超音速气动弹性的模拟。 |
| 4. | Basing on the static aeroelasticity , the jig - shape and the attack angle design have been studied . generally , much computing time is needed in unsteady flow computation
利用现有条件自主开发出适合定常、非定常流场计算和气动弹性研究的分布式并行计算机系统。 |
| 5. | At present , the equivalent plate methodology based on global ritz solution technique has been used in the studies of aeroelasticity and aeroelastic optimization of composite wing structures , but it stiff exits space to develop
鉴于此，常常采用连续的等效板模型( equivalentplatemodel ，简称epm ) 。目前，基于全局ritz求解技术的复合材料翼面结构等效板方法已用于气动弹性的基本研究和优化设计，但还不够成熟。 |
| 6. | This paper , on the basis of the theory of aeroelasticity , analysed the galloping phenomenon which the cord was undergone the excitation of the horizontal wind . and also built up the mechanic model when galloping . this model provided the theoretical foundation for the case that the cord begins violently vibrating just after the speed of the horizontal wind reaches a certain level
以气动弹性力学理论为基础，分析了悬索在受到水平方向横风激励时的驰振现象，并建立了其发生驰振时的力学模型，该模型为悬索在横风速度达到一定数值时发生激烈的振动提供了理论依据。 |
| 7. | Then the steady and unsteady subsonic , transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated . the 3 - dimensional unsteady navier - stokes equations are solved using the implicit lu - nnd algorithm , with baldwin - lomax turbulent model . on the basis of simulating unsteady viscous flow , coupling the structure dynamics equations , the problems of static aeroelasticity and flutter are investigated for wings and elevator
在模拟非定常粘性绕流的基础上，与颤振运动方程相耦合，分别对机翼和全机流固耦合现象中颤振问题进行了研究，准确求解跨音速颤振临界速度，分析机翼和全机的从亚音速到超音速范围的颤振规律，并研究分析了机翼飞行迎角变化对颤振速度的影响。 |
| 8. | In order to reduce the computing time and improve efficiency , the procedure has been paralleled and the distributed parallel computation is accomplished in a net with four pcs . the parallel computation of static aeroelasticity and flutter has been initiated at home . on this basis , the work includes four parts
通过对单机串行程序进行分布式并行化改造，在国内首次实现了基于微机网络上的静气动弹性和颤振分布式并行计算，解决了数值求解气动弹性问题难以避免的耗时巨大的问题。 |
| 9. | Using the engineering methods of supersonic and hypersonic flow or local piston theory developed in this paper to compute unsteady aerodynamic loads , and coupling structural equations , the supersonic or hypersonic aeroelasticity with a typical servo system under thermal environment is simulated in time - domain
运用超音速、高超音速气动力工程计算方法和本文发展的当地流活塞理论计算非定常气动力，耦合结构运动方程，实现了热环境中带有伺服机构的气动弹性的时域仿真。 |
