机载光电/惯性组合着舰导引算法的地面验证

研究了机载光电/惯性组合着舰导引新算法,综合光电探测系统获得的跑道成像信息和机载惯性导航信息,建立导引参数与成像信息之间的数学模型,利用最小二乘法估计舰/机相对位姿,补偿舰船纵摇、横摇及沉浮运动并预测舰载机着舰位置,以实现近程导引舰载机半自动或自动安全着舰。在算法研究的基础上,进行了地面车载验证实验。实验采用缩比方案,以着降跑道模拟器模拟运动中的着降跑道。试验车模拟舰载机,通过相对位姿关系的一致性模拟着舰过程。试验结果验证了着舰导引系统方案的可行性和有效性,为飞行实验奠定技术基础,有利于提高其安全性。     

基于LabVIEW Vision的无人机自主着降系统设计与实现

四旋翼无人机具有低成本、垂直起降、机动性好等优点,在民用领域诸如航拍、植保、物流、电力巡线等场合得到了广泛的关注和应用。随着四旋翼无人机应用的普及,一些新的问题也随之出现,其中一个厄待解决的问题是如何提高无人机的降落精度和可靠性,特别在超视距应用场景下,这一需求尤为突出。通过采用机器视觉技术,利用LabVIEW Vision编制视觉识别软件,可以控制四旋翼无人机实现高精度的自主降落。     

Investigation on landing impact dynamic and low-gravity experiments for deep space lander

Herein symmetrical four-legged suspension lunar lander was used as the research object, the six-degree-of-freedom dynamic model was built and the model of the lunar soil friction coefficient was improved. For the low-gravity simulation on objects outside earth for future work, the law of dynamic similarity for detectors was deduced. A new method was proposed for simulating the low-gravity field on the surface of objects outside earth, which was achieved by changing initial conditions of the landing by the probe and by subsequent treatment of experimental data. The prototype tested the limitation of this method was verified. It is shown that the prototypes of detectors can be used in detectors low-gravity simulation test with this method, and equipments are simple and operationally effective. This method can be used for later lunar exploration, and low-gravity simulations on extraterrestrial objects.     

Autonomous control methods in logistics – A mathematical perspective

We model general autonomously controlled production networks by means of nonlinear differential equations and implement autonomous control methods, where transportation times and disturbances in the transportation times are taken into account. Autonomous control enables intelligent logistic objects to route themselves through a logistic network. Based on this model we investigate a certain scenario of a production network, where we show advantages and disadvantages of the implementation of autonomous control methods from a mathematical perspective in view of robustness and stability.     

Adaptive control for autonomous rendezvous of spacecraft on elliptical orbit

A strategy for spacecraft autonomous rendezvous on an elliptical orbit in situation of no orbit information is developed. Lawden equation is used to describe relative motion of two spacecraft. Then an adaptive gain factor is introduced, and an adaptive control law for auton- omous rendezvous on the elliptical orbit is designed using Lyapunov approach. The relative motion is proved to be ultimately bounded under this control law, and the final relative position error can achieve the expected magnitude. Simulation results indicate that the adaptive control law can realize autonomous rendezvous on the elliptical orbit with relative state information only.     

自治差分方程的稳定性

本文首先给出了文献[2]中关于一次近似系统不稳定性定理的一个反例,然后给出了关于自治差分方程利用其一次近似系统的不稳定性来判别原系统不稳定性的判别定理。     

某型机进近段高精度相对姿态实时测量技术

某型机在飞行训练过程中,进近段的二维相对姿态数据对于该型机安全着陆有着至关重要的作用。基于无线网络电台的双向数据传输系统能够实时获取进近段飞机相对理想着陆点的水平、垂直相对位置数据。通过上行链路上传着陆点的姿态数据,下行链路实时下传动动差分后的差分数据,最后在中心控制站进行二次数据处理。该技术获得的进近段二维相对姿态精度达到厘米级,满足飞行训练的需求。同时结合飞机显控数据以及视景图,以多角化动态关联的方式将实时获取的姿态数据等呈现给指挥员,更好地辅助指挥员进行着陆指挥工作。     

A nonconvex dissipative system and its applications (I)

In order to study the uniformly translating solution of some non-linear evolution equations such as the complex Ginzburg–Landau equation, this paper presents a qualitative analysis to a Duffing–van der Pol non-linear oscillator. Monotonic property of the bounded exact solution is established based on the construction of a convex domain. Under certain parametric choices, one first integral to the Duffing–van der Pol non-linear system is obtained by using the Lie symmetry analysis, which constitutes one of the bases for further work of obtaining uniformly translating solutions of the complex Ginzburg–Landau equation. Dedicated to Professor G. Strang on the occasion of his 70th birthday     

Nonlinear parametric identification using periodic equilibrium states

The subject of this paper is the development and assessment of a new nonlinear parametric identification method for dynamic systems using periodic equilibrium states or outputs. The method consists of a modified Bayesian point estimation technique which can be used in combination with a time discretization method or a shooting method to obtain the periodic equilibrium states. It is assumed that the specific excited and measured periodic solution can be computed directly from a static initial guess. An important feature of this estimator is the possibility to estimate the best parameters based on all experiments of the complete experimental set-up. The choice of using periodic states appears to be computationally efficient compared to using transient states. The new method is applied to multiple sets of nonlinear shaker-test measurements of a uniaxially loaded F-16 nose landing gear damper, for which a standard 1 dof mechanical model and a more comprehensive 2 dof thermo-mechanical model are postulated. Finally, the predictive power of the method is assessed by comparison of predictions for a transient drop-test load case of the best 2 dof model with corresponding parameters and real drop-test measurements.Notation a,b partial derivative of a with respect to vector b - % MathType!MTEF!2!1!+-% feaafeart1ev1aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLn% hiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr% 4rNCHbGeaGqiVu0Je9sqqrpepC0xbbL8F4rqqrFfpeea0xe9Lq-Jc9% vqaqpepm0xbba9pwe9Q8fs0-yqaqpepae9pg0FirpepeKkFr0xfr-x% fr-xb9adbaqaaeGaciGaaiaabeqaamaabaabaaGcbaWaaCbiaeaaca% WGHbaaleqabaGaaiOlaaaaaaa!37CD!\[\mathop a\limits^. \] total derivative of a with respect to time t - a total derivative of a with respect to the dimensionless time - â predicted value of a - mean value of a - ã approximate equations a - e residuals - f output equations - f _e external excitation frequency - F force - g ordinary differential equations - l number of parameters - n number of samples in each experiment - N number of experiments - % MathType!MTEF!2!1!+-% feaafeart1ev1aaatCvAUfeBSjuyZL2yd9gzLbvyNv2CaerbuLwBLn% hiov2DGi1BTfMBaeXatLxBI9gBaerbd9wDYLwzYbItLDharqqtubsr% 4rNCHbGeaGqiVu0Je9sqqrpepC0xbbL8F4rqqrFfpeea0xe9Lq-Jc9% vqaqpepm0xbba9pwe9Q8fs0-yqaqpepae9pg0FirpepeKkFr0xfr-x% fr-xb9adbaqaaeGaciGaaiaabeqaamaabaabaaGcbaWefv3ySLgznf% gDOfdaryqr1ngBPrginfgDObYtUvgaiuGacqWFneVtdaWgaaWcbaGa% amyyaaqabaGccaGGOaGaamOyaiaacYcacqWFce-qcaGGPaaaaa!4710!\[{\cal N}_a (b,{\cal C})\] a-dimensional normal distribution (mean b and covariance C) - p pressure - q degrees of freedom - s number of outputs - t time - T absolute temperature     

起落架结构参数对飞机机轮摆振的影响

建立了飞机机轮摆振运动方程,详细研究了起落架三个重要结构参数;稳定距、支柱刚度和减摆器传动系统扭转刚度对飞机机轮摆振的影响,考虑了各参数之间的耦合作用,严格区分“轮胎型”摆振和“结构型”摆振,并分别予以研究,所得结论为新机防摆设计和现役飞机防摆维护提供了理论依据。