An experimental investigation on static directional stability

A generic aircraft usually loses its static directional stability at moderate angle of attack (typically 20–30?). In this research, wind tunnel studies were performed using an aircraft model with moderate swept wing and a conventional vertical tail. The purpose of this study was to investigate flow mechanisms responsible for static directional stability. Measurements of force, surface pressure and spatial flow field were carried out for angles of attack from 0? to 46? and sideslip angles from ?8? to 8?. Results of the wind tunnel experiments show that the vertical tail is the main contributor to static directional stability, while the fuselage is the main contributor to static directional instabil-ity of the model. In the sideslip attitude for moderate angles of attack, the fuselage vortex and the wing vortex merged together and changed asymmetrically as angle of attack increased on the wind-ward side and leeward side of the vertical tail. The separated asymmetrical vortex flow around the vertical tail is the main reason for reduction in the static directional stability. Compared with the wing vortices, the fuselage vortices are more concentrated and closer to the vertical tail, so the yaw-ing moment of vertical tail is more unstable than that when the wings are absent. On the other hand, the attached asymmetrical flow over the fuselage in sideslip leads to the static directional instability of the fuselage being exacerbated. It is mainly due to the predominant model contour blockage effect on the windward side flow over the model in sideslip, which is strongly affected by angle of attack.     

模型预混燃烧室线性稳定性分析

针对钝体火焰稳定器结构的模型预混燃烧室进行了线性稳定性分析.利用COMSOL Multiphysics软件求解了三维Helmoholtz方程,方程的源项为耦合指数-延迟时间模型.对模型预混燃烧室进行非定常计算得到了化学反应速率的周期性变化,确定了非定常热释放发生在火焰的尖端.由压力和温度信号的相位差得到了当量比为0.72,0.8,0.88,0.97四个工况的延迟时间,分别为0.6,0.3,0.9,0.6ms.线性稳定性分析得到了模型预混燃烧室系统纵向模态频率的实部和虚部,当虚部为负数时表示线性不稳定.结果显示:系统的前5阶纵向模态中,2~4阶是线性不稳定的.其中3阶纵向模态的虚部绝对值最大,它的物理意义是对小扰动的增长率最大.因此在有扰动时,3阶纵向模态最有可能线性失稳,产生燃烧不稳定性现象.      

不同攻角条件下偏转头弹箭流场与气动特性

基于DES（detached eddy simulation,分离涡模拟）方法及AUSM（advection upstream splitting method,对流迎风分裂方法）格式,对不同偏角的偏转头弹箭在非零攻角下的超声速流场和气动特性进行了数值模拟.结果表明:在非零攻角情况下,与常规弹箭流场相比,偏转头弹箭头部迎风面激波更强;而当有效入射角相等时,即使弹箭的攻角不一样,其头部流场结构仍相同,且尾翼流场基本不受头部偏角影响.另外,由气动力系数变化曲线可知,偏转头弹箭具有良好的纵向静稳定性,且升力系数随攻角的增长率大于阻力系数,即升阻比大于常规弹箭,因此适当增大攻角可以提高偏转头弹箭的气动特性.      

导弹姿态控制系统鲁棒稳定性分析

研究了某型导弹弹体模型及其在飞行中的运动特性，对其姿态控制系统模型进行了简化，分析了导弹姿态控制系统在参数摄动条件下的动态特性，并时影响系统性能的不同参数偏差间的相互补偿进行了研究。结果表明，在某些测试参数偏差超出允许的条件下，如果系统有足够稳定裕度，只要不是功能性问题，仍可以进行发射。     

Experimental investigation on SPS casing treatment with bias flow

Generally, casing treatment（CT） is a passivity method to enhance the stall margin of fan/compressor. A novel casing treatment based on the small disturbance theory and vortex and wave interaction suggestion is a method combining passive control and active control, which has been proved effective at enhancing the stall margin of fan/compressor in experiment. In order to investigate the mechanism of this kind of casing treatment, an experimental investigation of a stall precursor-suppressed（SPS） casing treatment with air suction or blowing air is conducted in the present paper. The SPS casing treatment is designed to suppressing stall precursors to realize stall margin enhancement in turbomachinery. The experimental results show that the casing treatment with blowing air of small quantity can improve the stall margin by about 8% with about 1% efficiency loss. By contrast, the SPS casing treatment with micro-bias flow does not improve the stall margin much more than that without bias flow, even worse. Meanwhile, the present investigation has also attempted to reveal the mechanism of stall margin improvement with the casing treatment.It is found that the stall margin improvements vary with the modification of the unsteady shedding flow and the unsteady wall boundary impedance. The experimental results agree fairly well with the theoretical prediction using a flow stability model of rotating stall.     

分数阶Cohen-Grossberg神经网络的Mittag-Leffler稳定性

在整数阶 Cohen-Grossberg神经网络与分数阶理论及分数阶神经网络的基础上,提出了分数阶 Cohen-Grossberg神经网络。为了研究该类型神经网络,引入 Mittag-Leffler函数并利用 Mittag-Leffler函数及分数阶导数的相关性质,进而通过构造 Lyapunov函数的方法,研究了分数阶 Cohen-Grossberg神经网络的 Mittag-Leffler稳定性,并最终给出了相应的充分性条件。最后,通过实例仿真验证了结论的正确性。     

探测器月面起飞稳定性边界条件研究

探测器起飞稳定性是上升器月面起飞的重要性能指标,研究其特性对上升器返回地面具有重要的意义。选择上升器起飞稳定性主要影响因素,结合优化拉丁超立方试验设计方法和径向基神经网络建立了上升器起飞过程动力学近似模型,定量地判定出姿态角位移、姿态角速度对各影响因素的敏感程度。以上升器的姿态角位移和角速度分别为5°和5（°）/s为稳定判定条件,给出了单个影响因素的取值边界。编写了上升器起飞稳定性多因素边界条件分析程序,采用三维空间的方式建立了上升器起飞稳定性边界条件表达式,并以样例确定了起飞稳定性边界条件。     

轴向间距对压气机气动稳定性的影响

针对低速轴流压缩系统 ,从理论分析和试验验证两个方面论述了静子在轴流压气机气动稳定性方面的作用。理论上论证了 ,当静子非首先失速部件时 ,其作用有利于抑制扰动的发展 ,增强压气机的气动稳定性 ;试验验证了 ,随着转静子之间轴向间距的减小 ,静子的增稳作用增强 ,压气机的失速流量减小      

考虑临近车道行人对交通流影响的改进跟驰模型

基于实际人车混合行驶的情形,提出了一个改进的车辆动力学模型。该模型考虑了邻车道或横向的行人、自行车等对主干道车辆的驾驶行为影响。基于经典的最优速度模型,将主干道车辆与行人之间的横向距离和纵向距离作为参数引入最优速度模型中。为了验证所提模型的稳定性和有效性,利用线性稳定性理论,推导出模型的稳定性条件和非稳定性条件,绘制中性稳定性曲线,直观描述了交通流稳定区域大小。理论结果表明:考虑横向行人干扰因素的改进跟驰模型比传统的只考虑单一车道车辆因素的跟驰模型更加的稳定,并且不同参数的变化,所引起的稳态区域也会发生变化。采用了更加真实的优化速度方程,通过仿真实验来描述车辆的驾驶行为;仿真实验列举了2种实际场景:行人稀少和行人较多时。分别绘制了车辆的速度-时间变化曲线以及车辆的时空图,实验结果表明:横向行人的确会干扰车辆的正常驾驶;不同场景下,行人数量的多寡也会对车辆的驾驶行为造成不同程度的影响。      

The classical Laplace plane as a stable disposal orbit for geostationary satellites

The classical Laplace plane is a frozen orbit, or equilibrium solution for the averaged dynamics arising from Earth oblateness and lunisolar gravitational perturbations. The pole of the orbital plane of uncontrolled GEO satellites regress around the pole of the Laplace plane at nearly constant inclination and rate. In accordance with Friesen et al. (1993), we show how this stable plane can be used as a robust long-term disposal orbit. The current graveyard regions for end-of-life retirement of GEO payloads, which is several hundred kilometers above GEO depending on the spacecraft characteristics, cannot contain the newly discovered high area-to-mass ratio debris population. Such objects are highly susceptible to the effects of solar radiation pressure exhibiting dramatic variations in eccentricity and inclination over short periods of time. The Laplace plane graveyard, on the contrary, would trap this debris and would not allow these objects to rain down through GEO. Since placing a satellite in this inclined orbit can be expensive, we discuss some alternative disposal schemes that have acceptable cost-to-benefit ratios.