Multi-agent Based Hierarchy Simulation Models of Carrier-based Aircraft Catapult Launch

With the aid of multi-agent based modeling approach to complex systems, the hierarchy simulation models of carrier-based aircraft catapult launch are developed. Ocean, carrier, aircraft, and atmosphere are treated as aggregation agents, the detailed components like catapult, landing gears, and disturbances are considered as meta-agents, which belong to their aggregation agent. Thus, the model with two layers is formed i.e. the aggregation agent layer and the meta-agent layer. The information communication among all agents is described. The meta-agents within one aggregation agent communicate with each other directly by information sharing, but the meta-agents, which belong to different aggregation agents exchange their information through the aggregation layer first, and then perceive it from the sharing environment, that is the aggregation agent. Thus, not only the hierarchy model is built, but also the environment perceived by each agent is specified. Meanwhile, the problem of balancing the independency of agent and the resource consumption brought by real-time communication within multi-agent system （MAS） is resolved. Each agent involved in carrier-based aircraft catapult launch is depicted, with considering the interaction within disturbed atmospheric environment and multiple motion bodies including carrier, aircraft, and landing gears. The models of reactive agents among them are derived based on tensors, and the perceived messages and inner frameworks of each agent are characterized. Finally, some results of a simulation instance are given. The simulation and modeling of dynamic system based on multi-agent system is of benefit to express physical concepts and logical hierarchy clearly and precisely. The system model can easily draw in kinds of other agents to achieve a precise simulation of more complex system. This modeling technique makes the complex integral dynamic equations of multibodies decompose into parallel operations of single agent, and it is convenient to expand, maintain, and reuse the program codes.

Parameter Optimization of Nose Landing Gear Considering Both Take-off and Landing Performance of Catapult Take-off Carrier-Based Aircraft

Optimization of the parameters of landing gear systems with double-stage air springs of catapult take-off carrier-based aircraft is here studied based on the mathematical equations of the classic dual mass spring-damper dynamic model.Certain standards for both take-off and landing performance are put forward.The contradictory factors between take-off and landing processes are analyzed.The optimization of oil in the pin area and the area near the rear oil hole is performed.Then these optimized parameters are used to assess the influence of the initial pressure of the low chamber,the ratio of the high chamber to the low chamber,and the tire inflation pressure on the performance of arresting landing and catapult take-off.The influences of these parameters on carrier-based aircraft and the aircraft-carrier on aircraft catapult take-off is also assessed.Based on the results of the simulation,respective take-off criteria must be drafted considering different types of aircraft and different take-off load cases,all of which must be matched to parameters relevant to catapult take-off.

Guidance and Control Techniques of Carrier-Based Aircraft for Automatic Carrier Landing

We summarize the guidance and control techniques of automatic carrier landing for carrier-based aircraft.First,we analyze the carrier landing operations of the manned fixed-wing aircraft,unmanned fixed-wing aircraft and helicopters.Second,we look into the navigation and guidance system and the flight control methods for current different aircraft.Finally,we draw several conclusions of the development prospects for aircraft carrier landing,including the precision landing control techniques,precision approach and landing guidance techniques,and adaptive,reconfigurable and intelligent flight control techniques.

Modeling of Carrier-based Aircraft Ski Jump Take-off Based on Tensor

A general mathematical model of carrier-based aircraft ski jump take-off is derived based on tensor. The carrier, the aircraft body and the movable parts of the landing gears are treated as independent entities. These entities are assembled into a multi-rigid-body system with flexible links. Dynamical equations of each entity are derived on the basis of the Newton law and the Euler transformation. Using the invariance property of the tensor, the dynamical and kinematical equations are converted to tensor forms which are invariant under time-dependent coordinate transformations. Then the tensor-formed equations are expressed by the matrix operation. Differential equation group of the matrix form is formulated for the programming. The closure of the model is discussed, and the simulation results are given.

Dynamics Analysis of Carrier-Based Aircraft with Off-Center Catapult Launch

In order to enhance the safety of the catapult launch of the carrier-based aircraft,the catapult launch multibody dynamic model is established aiming at the problem of off center catapult launch.The whole catapult process including four stages which are buffering,tensioning,releasing and taxiing is taken into consideration and the body dynamics of the off-center catapult during each stage is analyzed.The catapult launch dynamic differences between the conditions only considering taxiing and that considering four stages are compared,and the effects of the different initial off center distances considering four stages on the attitude,landing gear load and acceleration of the carrier based aircraft during catapult launch are discussed.The results show that only considering taxiing may underestimate the dynamics of the carrier-based aircraft substantially.When taking four stages into consideration,the initial off-center distance has small influence on the aircraft dynamic characteristics during buffering and tensioning but has larger influence on that during releasing and taxiing.The increase of the off-center distance will cause the enhancement of the aircraft rolling and yawing,which may lead to the load difference between the left and right landing gears and the increase of the aircraft lateral acceleration.The establishment and simulation of the catapult launch multi body dynamic model founded on buffering,tensioning,releasing and taxiing provide reference for the carrier-based aircraft design and analysis of the catapult launch dynamics.

Optimal Preview Control for Automatic Carrier Landing System of Carrier-Based Aircraft with Air Wake

Carrier-based aircraft carrier landing is a special kind of tracking control problem and not suitable for classical control methods,which may miss the desired performance or result in overdesign.Therefore,we present an optimal preview control for automatic carrier landing system(ACLS)by using state information of system,as well as future reference information,which can avoid the shortcomings of classical control methods.Since the flight performance of carrier-based aircraft is disturbed by air wake when the aircraft flies near the area of carrier stern,we design a disturbance rejection strategy to ensure that aircraft track the glide path with high precision and robustness.Further,carrier-based aircraft is a complex nonlinear system.However,the nonlinear model of carrier-based aircraft can be linearized at equilibrium landing state and decoupled into the longitudinal model and the lateral model.Therefore,an optimal preview control system is designed.The simulation results of a carrier-based aircraft show that the optimal preview control system can effectively suppress air wake.Tracking accuracy of optimal preview controller is higher than that of the proportional integral differential(PID)control system.

两代天基红外传感器对隐身飞机尾焰探测能力分析

为了对比两代天基红外传感器对隐身飞机尾焰的探测能力,以美国SBIRS-GEO和Next-Gen OPIR星座作为研究对象,通过建立高轨红外探测模型以及构建对应的预警探测场景,对两代探测器在不同飞行状态时飞机尾焰的辐亮度响应特性和模拟成像效果进行量化对比.研究结果表明,两代天基红外探测器都可以用来探测飞机尾焰信号;飞机加力对尾焰温度和外形有显著影响,成为影响天基红外传感器探测性能的关键因素;Next-Gen OPIR搭载的新一代传感器可以在36000 km高度捕获和发现处于非加力状态的尾焰,其成像信噪比明显高于SBIRS-GEO传感器对处于加力状态尾焰的信噪比.

羽毛球运动训练对航母舰载机飞行学员颈痛的干预效果研究

目的评估羽毛球运动对舰载机飞行学员颈痛的干预效果,为该运动预防和缓解舰载机飞行学员颈痛提供科学依据。方法根据纳入和排除标准筛选16名航母舰载机飞行学员作为受试者,随机分为运动康复组和对照组,每组各8人。运动康复组除进行部队日常训练外,另进行每周3次,每次1 h的羽毛球运动;对照组进行部队日常训练,不做其他干预。研究为期3个月。颈痛的干预效果以实验前后颈椎功能障碍指数(NDI)评分、视觉模拟疼痛量表(VAS)、颈椎活动度(CROM)、颈部最大肌力、表面肌电信号均方根值(RMS)、积分肌电值(iEMG)作为评价指标。结果运动康复组NDI评分较干预前具有显著性差异(P<0.05),对照组NDI评分较干预前无显著性差异(P>0.05)。运动康复组VAS评分较干预前有显著性差异(P<0.01),对照组VAS评分较干预前无显著性差异(P>0.05)。运动康复组受试者干预后颈椎最大活动度在各方向均有所增加,且左屈、右屈活动度较干预前具有显著性差异(P<0.05),其余方向无显著性差异(P>0.05);对照组颈椎各方向最大活动度较干预前无显著性差异(P>0.05)。运动康复组受试者颈部最大肌力在前屈、后伸、左屈方向较干预前具有显著性差异(P<0.01),右屈、左旋、右旋值较干预前具有显著性差异(P<0.05);左右侧胸锁乳突肌RMS在四个方向动作中无显著性差异(P>0.05),左侧斜方肌上束在前屈和右屈动作中RMS具有显著性差异(P<0.05),在后伸和左屈动作中无显著性差异(P>0.05),右侧斜方肌上束在四个方向动作中无显著性差异(P>0.05)。运动康复组受试者干预后在前屈、后伸以及右屈运动中,4块肌肉iEMG均大于干预前,但无显著性差异(P>0.05)。在左屈动作中,左侧胸锁乳突肌与右侧斜方肌上束iEMG大于干预后,右侧胸锁乳突肌和左侧斜方肌上束iEMG小于干预后,但均无显著性差异(P>0.05)。结论羽毛球运动干预能够缓解航母舰载机飞行学员的颈部疼痛,使其颈椎功能障碍得到一定程度的恢复,并且能够增加颈部灵活性,增强颈部肌力,同时激活深层肌肉参与维持颈部稳定,有效提升颈部肌肉群的抗疲劳能力。

航母舰载无人机全自动着舰技术特点分析

全自动着舰技术是无人机上舰必须解决的“使能”技术。2013年,美军已完成X-47B无人机验证机在航母上的全自动着舰试验验证,为其发展MQ-25A“黄貂鱼”航母舰载无人机装备奠定了良好的技术基础。在梳理飞机着陆与着舰差异的基础上,给出航母舰载无人机全自动着舰的通用流程;从地位作用、工作范围、系统构架、系统要求、实现手段以及关键技术支撑等角度,对比有人机重点分析了航母舰载无人机全自动着舰的特点,为后续关键技术研究和武器装备建设发展提供参考。

星基ADS-B系统空天链路的建模与仿真

星基广播式自动相关监视(ADS-B,automatic dependent surveillance-broadcast)系统是一种新型的航空器监视技术,在未来空中交通管理系统中具有广阔的应用前景。为了深入研究星基ADS-B系统中航空器到卫星的空天链路通信性能,将专业软件Matlab和STK(system tool kit)有效联合,构建符合国际标准的星基ADS-B空天链路完整模型;通过离散事件动态交互模拟ADS-B消息的发送与接收全过程,最后统计得出体现星基ADS-B空天链路通信性能的消息识别概率(POI,possibility of identify)、消息检测概率(POD,possibility of detective)、信号接收功率、信号冲突概率、卫星覆盖范围等指标。仿真结果表明,随着区域内航空器数量上升,POI、POD下降,消息冲突概率上升。

基于改进Informed-RRT^(*)算法的舰载机甲板平面路径规划

针对舰载机甲板路径规划问题,在Informed-RRT^(*)(informed rapidly-exploring random tree)的椭圆采样基础上,提出使用正态分布方式采样的IN-RRT^(*)(informed normal-RRT^(*))算法。首先,针对舰载机与运动场景建模,定义舰载机运动约束和避障策略;其次,将正态分布采样策略与椭圆采样相结合,获取优质高效采样点;引入人工势场法,自适应调节随机树的搜索步长值;使用向心Catmull-Rom样条插值法对路径进行平滑优化处理;提出针对动态障碍改进的动态窗口法,实现局部动态避障。最后,运用甲板平面环境实验检验算法性能。结果表明,IN-RRT^(*)算法能显著优化搜索时间和搜索路径质量,可应对动态场景规划出合理可行的平滑路径。

面向智能辅助决策的飞行器安控系统构建研究

新一代人工智能技术能够提高飞行器试验安控系统的辅助决策能力,满足地面安控目标数量增多、故判规则量增大、故判时效性高等新需求,具有广阔的应用前景。在对飞行器试验地面安控需求分析的基础上,设计面向智能辅助决策的地面安控系统总体框架,增加了数据与模型管理模块;接着构建了辅助决策知识库,主要包括故障弹判据、速度判据、位置判据和预示落点判据等规则库;在此基础上提出数据和规则协同驱动的故障预测方法。该系统既利用历史积累试验数据对深度神经网络模型进行训练,又利用规则库提高专家经验对模型预测精度的贡献,能够提高故障智能预测能力,满足飞行器安控智能辅助决策需求。

基于教与学优化的舰载机起飞出动动态调度

本文针对弹射器故障情形下的舰载机起飞出动调度,建立了舰载机起飞出动的多约束分布式流水线调度模型;结合基于扩展随机序解的编码和解码策略、动态调整策略,设计了基于教与学优化的舰载机起飞出动动态调度算法;最后,通过对仿真案例分析、故障预测精度对动态调度的影响分析,及动态调度算法的运行时间分析,结果验证了所设计的算法对舰载机起飞出动动态调度的可行性和有效性。

面向声爆/气动力的飞行器布局设计知识挖掘

声爆抑制是发展新一代超声速民机必须突破的关键技术。飞行器总体布局参数对其声爆特性有重要影响。数据挖掘(DM)可以从大量的数据中通过算法搜索隐藏的信息,是飞行器设计知识提取的有力工具。选取后掠角、展弦比、梢根比、上反角、机身长细比5个总体布局参数作为设计变量,目标函数定义为远场感知噪声级,同时计算升、阻力系数作为气动力衡量指标。基于总变差分析(ANOVA)、决策树算法、自组织映射(SOM)网络组成的数据挖掘体系提取低声爆设计知识库。获得所选设计变量与声爆/气动力的相关度,并实现对设计变量的分层与降维。后掠角有最高设计优先级,长细比、上反角重要程度次之,展弦比与梢根比为低敏感变量。对于算例中的飞行器,在合理区间内选择较大的后掠角、上反角能够使声爆最小化的同时,设计适于超声速巡航的小展弦比布局。

舰载机弹药保障调度仿真系统

针对航空母舰飞行甲板上舰载机弹药保障面临的调度效率不高的问题,提出一种基于Unity3D的舰载机弹药调度三维虚拟演示方法,构建了面向航空母舰飞行甲板上舰载机弹药调度的三维虚拟仿真系统。通过定义系统,建立面向航空母舰舰载机弹药运输、装载调度过程的问题模型以及路径确定、顺序约束、装载位置补偿等处理规则,使用改进离散灰狼优化算法实现了调度过程优化求解。参照公开的场景信息搭建了航空母舰飞行甲板上舰载机弹药调度保障虚拟交互场景,设计了执行不同控制任务并能实现彼此之间交互控制的系统脚本,通过在系统虚拟场景实体模型上分别加载实现了虚拟场景的可控实时演示。对场景实例的优化求解与仿真演示验证了所提方法的有效性和可行性。

舰载机及其尾钩的动力学建模与分析

为了研究舰载机尾钩的动力学特性对阻拦结果的影响,建立了舰载机的平面运动刚体动力学模型和考虑尾钩纵向缓冲作用的尾钩空间运动刚体动力学模型。使用拉格朗日第一类方程建立了舰载机及其尾钩之间的转动副模型,进而构建了舰载机及其尾钩组成的系统动力学模型,将该模型与阻拦装置的系统模型联合组成了完整的阻拦动态仿真模型。开展了飞机的阻拦试验,并将试验结果与仿真结果进行对比分析,结果验证了舰载机及其尾钩动力学模型的有效性和准确性,揭示了尾钩特性对舰载机阻拦过载的重要影响。

高置信水平结构逆可靠度分析与优化方法研究进展

不确定性客观存在于工程结构生产制造以及服役等各环节之中并对结构的承载性能影响显著.特别是对于服役条件苛刻的航空航天承载装备,在设计阶段考虑多源不确定性的影响对于结构安全至关重要.在众多不确定性分析方法中,逆可靠度分析方法在效率和稳健性方面具有一定优势.为此,国内外学者在高置信水平结构逆可靠度分析与优化方法方面开展了大量研究并取得了长足进步,包括自适应迭代控制算法、先进可靠度优化策略与非充分样本下的高置信水平设计方法等.本文首先对国内外逆可靠度分析与优化方法取得的进展进行了系统梳理与总结,特别是逆可靠度分析方法的发展历程以及面临的挑战问题,主要包括强非线性功能函数、多设计点以及低失效概率问题.进一步,针对长期困扰可靠度方法实际应用的小样本问题,重点从结构高置信水平可靠度分析与优化理论角度开展系统介绍,详细论述了小样本诱发的认知不确定性到可靠度置信水平的传播链条.最后,基于现有成果和国家重大前沿需求,重点围绕航天装备可重复使用需求对结构可靠度未来研究方向进行了思考与展望,期望相关研究成果能够进一步助力我国航空航天结构实现高可靠性与极致轻量化设计.

Harmony SE在民用飞机设计中的应用

随着民用飞机技术精细化和产品复杂性的提高,民用飞机设计已从传统的基于文档的系统工程转变为基于模型的系统工程,系统表达也从以文档为中心转变为以模型为中心。为进一步提高民用飞机设计中系统建模的模型质量与正确性,进而缩短设计的开发周期与成本,探究以模型驱动及验证为主导的系统工程方法在民用飞机设计领域的适用性,建立民用飞机设计的系统工程框架,用以支持民用飞机的可靠设计与高效交付。以Harmony SE建模方法为切入点,介绍其工作流程和建模思想;分析民用飞机在系统工程实践中出现的突出问题,说明Harmony SE方法在民用飞机系统工程领域的适用性,建立民用飞机设计的系统工程实践体系;以油箱增压组件为研究对象,应用实践体系开展组件级系统工程实践。结果表明,文中所提出的民用飞机设计系统工程体系和方法能够正确合理地分配设计需求并建立完整的系统模型,有助于提升现阶段民用飞机设计的效率与准确性。

考虑强风干扰的固定翼飞行器“神经元”飞行气动建模

大气环境中的风是影响飞行器实际飞行的主要动态环境干扰因素之一,强风干扰下的复杂空气动力学是固定翼飞行器安全稳定飞行面临的严峻挑战。为提高强风干扰下固定翼飞行器的环境适应能力,发展了一种基于深度元学习的创新固定翼飞行器“神经元”飞行气动建模方法,该方法采用相对于地面坐标系的变量进行描述,根据多元函数的切比雪夫级数理论,将气动力和气动力矩函数分解为不同变量函数的乘积和,通过生成对抗网络技术构建强风干扰下飞行器空气动力模型的共性基函数模型,进而预测飞行器在飞行过程中受到的气动力(矩)。研究结果表明,文章建立的固定翼无人机空气动力共性基函数模型准确,可以较好地预测未知风况条件下飞行器的气动力与气动力矩,为实时空气动力学建模的迁移应用奠定良好基础。

舰载机阻拦着舰系统建模与仿真

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