| 1. | 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 |
| 2. | Investigated the basic theory of the coupled cfd / csd simulation of nonlinear unsteady aerodynamics and prepared basic data for reduced order model . 2
探讨了cfd csd耦合技术预测非线性非定常气动力的基本原理，为非定常气动力降阶模型准备数据。 |
| 3. | The paper investigated some problems related to the application of minimum - state approximation of the unsteady aerodynamics through two typical models , and pointed out the relative conclusions
摘要用两个典型的对象，研究了非定常空气动力最小状态拟合方法应用中的问题，并给出了相应的结论。 |
| 4. | Based on linear state space model , put forward two elementary practical methods of constructing bilinear state space model for nonlinear unsteady aerodynamics with contribution to nonlinear ase technology
2在线性状态空间模型的基础上，初步提出了基于volterra核建立非线性非定常气动力双线性模型的两种实用方案，向非线性ase领域迈进了一步。 |
| 5. | Investigated the reduced order model for nonlinear unsteady aerodynamics based on volterra series , especially the identification method of the volterra kernels and studied the application domain and accuracy of the model
研究了volterra级数在非定常气动力降阶模型中的应用，特别是volterra核的计算，并对volterra级数模型的适用范围和精度进行了评价。 |
| 6. | 3 . investigated the direct model construction method of unsteady aerodynamics state space equation from volterra kernels , including linear state space model and bilinear state space model . the general model construction method for ase was brought forward
研究了基于volterra核直接建立非定常气动力状态空间模型的方法，包括线性状态空间模型和双线性状态空间模型，并提出了将其用于ase系统建模的一般方法。 |
| 7. | In chapter 4 , the aeroelastic model of the whole test rig is first established by using jones ’ s approximation of theodorsen ’ s unsteady aerodynamics load . then , the numerical simulations and wind tunnel experiments for the sub - optimal flutter suppression of the airfoil model are presented
数值仿真和风洞实验研究表明,以超声电机为控制面作动器可以有效地抑制翼段模型的颤振,颤振临界速度提高了13 . 4 % ,数值仿真和风洞实验结果基本吻合。 |
| 8. | Accurate calculation of aircraft steady and unsteady aerodynamics and flutter characteristics , especially in the transonic speed range is a crucial problem for aircraft designers . it is very important for us to develop an efficient , accurate , robust navier - stokes / euler flow solver that could be used to study transonic steady and unsteady flowfields
飞行器的定常和非定常气动力的准确数值求解及颤振特性研究，特别是跨音速范围内的准确数值求解及研究，一直以来都是飞行器设计工作者必须面对的重要研究难题。 |
| 9. | This model is formulated as a non - linear state - space representation of helicopter flight dynamics , incorporating with blade element unsteady aerodynamics , a finite state dynamic inflow wake model , and flapping / lead - lag blade dynamic model . the formulation of the coupled rotor and fuselage equations enables the use of common solution techniques for trim and linearization in arbitrary steady flight condition as well as control response calculations
本项研究针对新机研制过程必须解决的品质评定、飞控系统设计等问题，按照ads - 33军用品质规范的要求，建立了一个较完整的直升机非线性的、具有状态空间表达形式的飞行动力学模型，进行了模型验证工作，并以某样例直升机为例，计算了ads - 33品质规范（ 3 |
| 10. | Flutter is the most important instable problem and it restricts the flight envelope and performance of a vehicle . aeroservoelasticity , including active flutter suppression technology , is a multidisciplinary optimization technology that studies the interaction of flexible structure , unsteady aerodynamics and flight control system
以主动颤振抑制系统设计为代表的气动伺服弹性力学( ase )是一门涉及柔性结构、飞行器运动引起的定常和非定常气动力以及飞行控制系统相互作用的多学科技术。 |
