| 1. | On the sensitivity of aircraft longitudinal flying qualities to aerodynamic derivatives at high angle of attack
飞机纵向飞行品质对大迎角气动导数的敏感性研究 |
| 2. | This attitude helps to generate greater lift and reduce the distance needed for takeoff or landing
合适的大迎角，有利于在较低的速度下产生足够的升力，以便于减少起飞滑跑距离。 |
| 3. | The shm ( single hole microblowing ) as a new perturbation active control technique has been applied to the slender body with different model noses at zero sideslip and high angle of attack
摘要在亚临界流动范围内，对具有不同头部形状的尖拱形细长旋成体在无侧滑大迎角下进行单孔位微吹气扰动控制实验。 |
| 4. | The analyses indicate that the shm ' s control ability has strong adaptability to various slender body at high angles of attack , and its control ability is determined by the original state of the flowfield around the slender body
实验分析表明，单孔位微吹气扰动这一大迎角非对称控制手段具有较强的适应能力，其控制能力的大小则由该头部形状的初始状态决定。 |
| 5. | The separation flows of the onera m6 wing , slender body of missile and delta wing are simulated , the simulation capability of b - l model on large eddy is tested , the computational results agree well with experimental data
对oneram6机翼、细长旋成导弹体和大后掠三角翼的分离流进行了模拟。检验b - l模型对大迎角分离流动的模拟能力，取得了较好的计算结果。 |
| 6. | This method not only have the high estimated precise in kinds of maneuvering fly and good robustness to atmosphere turbulence or the change of flight stat , but also have the good ability of real - time . this paper also gives a project for the engineering application . 4
对上面两种方法在带有大气紊流和阵风影响的飞行环境下，特别是针对第四代飞机中典型的超大迎角飞行过程进行了详细仿真计算验证，证明这两种方法能够在不同飞行条件下均具有很好的估计效果。 |
| 7. | The angle of attack and the sideslip angle are the two important measured quantities for the aircraft navigation / control aerodynamics analysis and structure analysis . for the different kinds of disturbance influence , now the sensors ca n ' t measure it accurately , in the high angle of attack , the error will add with the angle of attack increase
迎角和侧滑角是飞机飞行导航控制、航电等方面重要的两个测量量，由于受到各种干扰因素的影响，现代传感器很难对其精确测量，在超大迎角飞行过程中，其测量误差随迎角增加而增加。 |
| 8. | All models can predict the attached and little separation flows . for the high angle - of - attack separated flows with distinct history effects , the j - k and k - g models perform better than b - l model . for multi - body and multi - block mesh system , model k - g , which does not need the distance normal - to - wall , performs much better adaptability for complex geometries
所有模型都可以很好地模拟附体及和小分离流动;对于具有明显上游历程效应的大迎角分离流动， j一k和k - s模型的模拟能力较强;对于多体干扰和多块网格系统， k - s模型无需计算网格单元至物面的垂直距离，具有较强的适应能力，且计算效果最佳。 |
| 9. | The mechanism of two possible ways of thrust vectoring control : force and moment control are analyzed . the effects of thrust vectoring on aircraft supersonic performance , take - off and landing performance , low speed and high angle of attack performance are studied . the air combat effectiveness of thrust vectoring control and post - stall maneuvers are also analyzed
5 、分析了推力矢量的两种应用方式：力控制和力矩控制的机理，研究了推力矢量对飞机超音速性能、起降性能、低速大迎角性能的影响，讨论了推力矢量与过失速机动对空战效能的影响。 |
| 10. | This platform implements the combination of 3d animation and real - time calculation . besides detail presentation of the network programming technique , the 3d engineer principle of opengl and its application to 3d animation is also discussed . furthermore , a two - axis movement control system used as the analog of actuator is introduced at length , then the semi - physical simulation platform is constructed
首先利用visualc + +开发了分布式数字仿真平台，设计了友好的用户界面，介绍了opengl三维引擎以及用opengl实现三维动画的原理和方法，详细讨论了基于局域网的网络编程技术，实现了三维动画演示和实时计算的结合；然后在此基础上引入双轴运动控制系统来模拟舵回路的工作，建立了半实物仿真系统，并对双轴运动控制系统及相应的编程技术进行了详细的介绍；最后对大迎角机动进行了半实物仿真。 |
