求解机场终端区飞机着陆调度问题的遗传算法

空中管制员需为到达的飞机安排跑道并计算着陆时间,以飞机空中延误最小为出发点研究了多跑道的飞机着陆调度问题,约束条件为每架飞机的着陆时间应落在规定的时间窗内及相邻两架飞机应满足最小时间间隔。针对该问题设计了一种遗传算法对问题进行求解,其中染色体由飞机排序链表和跑道链表组成,相应的交叉和变异算子也做了改进设计。仿真实验用数据库OR-Library中的实例验证了该算法的有效性。     

进近阶段飞机着陆调度优化

飞机着陆调度问题属于NP-hard问题,文中建立了进近阶段调度模型,在此模型基础上提出了一种改进的遗传算法来求解此问题.该算法基于双染色体编码方案,构建了满足MPS约束的初始种群,给出了启发式选择算子和自适应变异算子.针对多跑道飞机着陆调度问题,提出了随机分配和选择分配两种跑道分配策略.仿真结果表明,该方法能有效地减少飞机着陆调度中的总延迟,使待着陆飞机快速有序地进入机场着陆.     

Interval-based optimization of aircraft wings under landing loads

An interval-based automated optimization of aircraft wing structures subjected to landing loads is discussed in this paper. The interaction between landing gear and flexible airplane structure is considered as a coupled system. The uncertain system parameters are described as interval numbers. The computational aspects of the optimization procedure are illustrated with two examples – symmetric double-wedge airfoil, and supersonic airplane wing. Since, in most cases only the ranges of uncertain parameters are known with their probability distribution functions unknown, the present methodology is expected to be more realistic for the optimum design of aircraft structures under landing loads.     

An efficient hybrid meta-heuristic for aircraft landing problem

Aircraft landing problem is to assign an airport's runways to the arrival aircrafts as well as to schedule the landing time of these aircrafts. In this paper, first a mixed integer goal programming model is developed. Then, due to the complexity of the problem, which is NP-hard, we design a hybrid meta-heuristic applying simulated annealing framework. The computational results show that the proposed algorithm can obtain the optimal solution for instances up to 100 aircrafts, and also it is capable of finding very high quality and comparable solutions for the problems with up to 500 aircrafts and 5 runways in a short time.     

经验粒子群算法在飞机着陆调度中的应用

为高效解决飞机着陆调度问题,对其离散解空间进行连续化编码,提出经验粒子群（experiential particle swarm optimization , EPSO）算法。提炼飞机着陆调度问题中的领域知识作为每个粒子的经验,优化粒子群算法的寻优过程,增加算法的稳定性。引入控制工程领域中的滚动时域控制（receding horizon control , RHC）策略,在尽量考虑问题完整性的前提下,最大限度降低求解的复杂度,形成最终的RHC‐EPSO算法。实验结果表明,该算法能够比现有算法更加高效和稳定地找到飞机着陆调度问题的最优解。     

舰载机纵向自动着舰控制

对舰载机纵向着舰控制系统进了分析和研究,根据舰船甲板运动引起舰载机着舰点不断变化的问题,加入甲板运动补偿环节,并对补偿律进行了设计;对常规的纵向导引控制律进行了改进设计,引入模糊控制.仿真结果表明,引入甲板运动补偿环节,有效地减小了由于甲板运动造成的着舰误差,提高了着舰的安全性,模糊PID导引控制律比常规的PID导引控...     

飞机起落架收放系统运动模拟

使用三维设计软件CATIA模拟了起落架收放系统的运动规律,消除了各零件之间的干涉现象.用软件计算了关键部位的速度和加速度随时间曲线和机轮上3点的运动轨迹,最后计算了各运动件的扫过体积.计算结果表明,收起和放下的过程并不完全对称,机轮的最大速度值为0.019m/s,缓冲支柱下表面的最大速度为0.031m/s,机轮的最大加速度值为11m/s2,缓冲支柱下表面的最大速度为14m/s2,收起过程的最大速度更大.在系统所有零件中,机轮扫过体积最大.     

Application of generalised neural network for aircraft landing control system

 It is observed that landing performance is the most typical phase of an aircraft performance. During landing operation the stability and controllability are the major considerations. To achieve a safe landing, an aircraft has to be controlled in such a way that its wheels touch the ground comfortably and gently within the paved surface of the runway. The conventional control theory found very successful in solving well defined problems, which are described precisely with definite and clearly mentioned boundaries. In real life systems the boundaries can't be defined clearly and conventional controller does not give satisfactory results. Whenever, an aircraft deviates from its glide path (gliding angle) during landing operation, it will affect the landing field, landing area as well as touch down point on the runway. To control correct gliding angle (glide path) of an aircraft while landing, various traditional controllers like PID controller or state space controller as well as maneuvering of pilots are used, but due to the presence of non-linearities of actuators and pilots these controllers do not give satisfactory results. Since artificial neural network can be used as an intelligent control technique and are able to control the correct gliding angle i.e. correct gliding path of an aircraft while landing through learning which can easily accommodate the aforesaid non-linearities. The existing neural network has various drawbacks such as large training time, large number of neurons and hidden layers required to deal with complex problems. To overcome these drawbacks and develop a non-linear controller for aircraft landing system a generalized neural network has been developed.     

舰载机前起落架突伸性能优化

为提高舰载机的起飞性能,通过对双腔油气缓冲器阻尼油孔截面积随行程变化的控制,实现某舰载机前起落架突伸性能优化. 该方法选取二质量弹簧-阻尼器系统作为前起落架突伸运动的力学模型,将阻尼油孔面积随行程变化的函数代入突伸运动微分方程,建立以突伸时间为优化目标的数学模型. 采用黄金分割优化方法,得到优化后突伸运动位移和速度曲线. 经与3组不同直径常截面油孔在同样结构参数和初始填充参数下曲线的对比分析,证明采用变截面油孔缓冲器优化前起落架突伸性能的合理性.     

Ultra-low risk assessment under the confirmed compliance of automatic aircraft landing characteristics with airworthiness requirements

Two techniques for approximating the tails of the probability distribution of automatic aircraft landing characteristics are considered: an approximation technique based on the Pareto distribution and a spline approximation technique. Computational algorithms designed based on these techniques allow assessing ultra-low risks (on the order of 10^–6–10^–8) under the confirmed compliance of aircraft landing characteristics with airworthiness requirements. The modeling shows good agreement between the results obtained by these techniques, which makes it possible to implement a simpler technique based on the Pareto distribution. This technique reduces the amount of statistical modeling by predicting accuracy characteristics in the unobservable range of their variation.     

Adaptive trajectory generation based on real-time estimated parameters for impaired aircraft landing

ABSTRACT

This paper is motivated by a need to address the challenge of securing a safe landing after suffering from inflight impairment. In this paper, a new adaptive generalised model predictive static programming (G-MPSP) is developed to generate a safe emergency landing trajectory for impaired aircraft. Utilising the computationally efficient G-MPSP framework, the proposed algorithm enables adaptation of model parameters based on the prediction errors to ensure reasonable guidance performance. Based on the estimated parameters, a feasible landing trajectory is then generated by the flexible finite-horizon G-MPSP with input constraints. The integrated approach features explicit closed-form solutions for both parameter estimation and trajectory generation. Its effectiveness is demonstrated by simulations in the presence of parameter uncertainties and noises and by comparison studies with the non-adaptive G-MPSP.     

基于起降性能模型的军用飞机起降规划与计算

为解决军用飞机快速出击及作战规划调度中的起降规划与计算问题,提出了一种基于起降性能模型的军用飞机起降规划与仿真计算方法。分析了军用飞机典型的起飞与着陆过程,通过对起降过程中飞机的受力情况分析及推理得到飞机的起降性能模型。在此基础上,设计了军用飞机起降规划与计算的流程,并进行了包括起飞距离与时间、着陆距离与时间等在内的相关计算。仿真计算结果与实际情况基本吻合,表明了该计算方法的可行性和有效性。     

复杂环境下基于价格时间自动机飞机着陆调度

目前航空运输系统飞机着陆调度环节普遍存在调度策略单一、效率低、附加成本较高等不足,提出了以价格时间自动机作为基础模型架构的飞机着陆调度设计,在满足着陆时间窗、最小尾流间隔等约束条件下优化额外成本消耗,并考虑复杂气候地理环境,构建出飞机着陆过程中各交互实体的价格时间自动机模型,采用UPPAAL CORA中的分支界定算法求解飞机着陆调度最优成本的可达性.仿真实验结果表明:此研究方法可应用于复杂环境下、大吞吐量的飞机着陆调度,能够显著降低着陆消耗,提升跑道容量,具有安全性、智能性与经济性.     

Subclasses of solvable problems from classes of combinatorial optimization problems

Well-known subclasses of solvable problems from classes of combinatorial optimization are reviewed. For solvable problems such as the traveling salesman problem, location problem, assignment problem, and clustering problem, the changes in the objective function on a given ordering of combinatorial configurations are analyzed. Translated from Kibernetika i Sistemnyi Analiz, No. 2, pp. 97–105, March–April 2009.     

Nonatomic problems of location of extended objects with finitely manyk-equivalence classes

Solution of nonatomic location problems is reduced to minimization of a quadratic form on a closed convex subset in a Hilbert space. Some examples are considered.Translated from Kibernetika i Sistemnyi Analiz, No. 2, pp. 165–170, March–April, 1992.     

Software development technology with automatic configuration to classes of image processing problems

A scheme is proposed to develop image processing and analysis software based on the generation of thesaurus tables in the interpreter’s kernel. The scheme is based on the combined features of dynamic libraries and an interpreter with a set of functions for image processing. As a result, the program can be divided into two parts: the first is aimed at professional software developers, and the second at users. The interpreter is able to use extra functions of dynamic libraries. It makes it possible to change the properties of the software without compilation. On the other hand, users can change the graphical interface to improve the convenience of the workplace.     

Equivalence of regularizations in abstract problems with different classes of admissible controls

Conclusion Theorems 4.1, 4.2 and 6.1, 6.2 respectively admit a natural specialization for the problem of constructing the reachability region of the linear controlled system from Sec. 1. Informally, this specialization has the following form. If the vector functions b(·) and S(·) from Sec. 1 are “not too discontinuous” (admit a uniform approximation by piecewise-constant and right-continuous maps on [t₀, v_oD, then, given a common resource constraintc, the controlled analogues of reachability regions are identical for the class of controls with an integral constraint (on the total pulse) and the class of “pure pulse” shock controls, whereas the “ordinary” reachability regions corresponding to unperturbed conditions (see, e.g., they− constraint in (1.2)) may be different. This is illustrated by the examples of Sees. 1, 5. The regularized version of the problem of constructing the reachability region of a linear system is thus insensitive to a change of the class of admissible controls. The study was supported by the Russian Foundation for Basic Research (94-01-00350). Translated from Kibernetika i Sistemnyi Analiz, No. 3, pp. 3–17, May–June, 1998.     

Singular perturbation methods for variational problems in aircraft flight

The solution of variational problems by singular perturbation methods is discussed. In addition to the benefits of order reduction, these methods also can serve as practical devices for treating the singularities arising in problems where the control appears linearly and/or in state-constrained control problems. Furthermore, approximate feedback solutions can be derived for problem formulations that currently result in a nonlinear two-point boundary value problem. To illustrate an application, a feedback solution for aircraft, three-dimensional minimum lime turns is derived and discussed. Numerical results are presented for an F-106 and an F-4E aircraft.