航空电子系统的发展趋势

在分析作战飞机效能、作战能力指数、航空电子系统功能的基础上,介绍联合式航电系统、综合航电系统、先进的综合航电系统的现状,根据各国进行的电子战、传感器、数据链、导航和通信系统的研究现状和计划,分析未来航空电子系统发展的特点、特征、技术措施和趋势。     

现代作战飞机方案评估与决策系统的设计与实现

作战飞机方案的评估,是现代军事和作战问题研究的重要组成部分,也是飞机改进改型和方案优选的重要依据。根据确立的现代作战飞机方案评估的五个层次及相应的计算方法,采用VisualC＋＋的MFC模块设计并开发了一种通用的作战飞机方案评估和决策系统。该系统综合了解析评估法、专家评估法和计算机仿真等多种方法,能够进行飞机综合作战能力、综合作战效能、综合使用效能、综合使用效费和方案评估决策五个层次的量化评估,并可以提供数据文件和可视化图形两种结果形式。采用该系统对多个飞机方案进行评估,结果表明：该系统功能齐全、操作简便、易于通用和拓展,能够提高了飞机方案评估的效率、科学性和综合性,对现代作战飞机及其他武器系统的方案评估和优选提供参考价值。     

航空发动机作战试验探索性研究

航空发动机作战试验（可分为作战效能和作战适用性）是在发动机研制和使用初期,在近似实战的环境下,对其进行考 核与评估的综合过程。为了提高航空发动机综合战技效能、优化发动机体系结构、确定编配运用原则和为训练保障要素提供参考 依据,初步构建包含2类103项试验内容的作战试验体系。采用综合评估分析法初步建立了效能评估模型,对发动机的综合效能 进行初步研究,结果将为航空发动机作战使用与保障提供方法指导。     

反舰导弹武器系统作战效能评估模型研究

在综合研究国内外多种效能评估理论和方法的基础上,建立了基于模糊综合评判法的主战、保障、指挥分系统作战效能及全系统作战效能评估模型,并通过示例验证了其正确性和可行性。     

战斗机综合作战效能评估的改进灰色关联模型

一机多能、功能复合是战斗机发展的一个重要趋势。为了评估战斗机综合作战效能,首先结合空空和空地作战需求,建立了效能评估指标体系;然后针对传统方法主观性较强的问题,并考虑到作战效能评估的灰色特征,采用较客观的灰色关联法,建立了战斗机综合作战效能评估模型。对于模型分辨系数取0.5不一定能使关联度具有明显区分性的问题,采用关联度的灰熵均衡度函数建模,优化分辨系数取值;而对于模型的等权不合理问题,则通过引入改进的综合权重、构造加权关联度计算式解决;最后,对采用本文模型、传统灰色关联度模型、LM神经网络模型针对6种机型的评估结果进行了对比分析,验证了所建模型的可用性和合理性。     

基于效能的先进战斗机航电系统动态重构方法

为满足未来先进战斗机全战斗过程的对敌压制能力需求，分析了作战任务与航电系统支持能力间的关系，建立了"作战任务-航电能力-资源需求"间的关系矩阵和航电系统效能模型；以最大化全飞行阶段航电功能整体效能和飞行安全为目标设计了针对不同作战场景的航电系统动态重构策略及重构流程；通过数值分析，对比了动态重构航电系统与静态配置航电系统在不同作战区边界的效能，表明动态重构特性能有效提高战斗机各阶段的作战效能，提高有限资源条件下的阶段优势。     

战机作战效能的综合指数评估研究

基于信息化条件下的现代作战需求,分析了影响战机作战效能综合评价的主要指标因素,包括直接攻击指标因素和各种保障指标因素,在一般指数法的基础上建立了战机作战效能的综合指数评价模型框架,并用该方法对国外部分主战战机作战效能开展了评估研究。     

潜射反舰导弹武器系统作战效能指标体系设计

根据潜射反舰导弹武器系统作战使用情况,在借鉴WSEIAC系统效能分析方法及有关作战效能指标体系设计方法基础上,结合作战运用效能分析方法和层次分析法,分析了影响作战效能的主要因素,建立了反舰导弹武器系统作战效能的评价指标体系,并详细阐述了评价指标体系的组成要素。     

侦察/打击一体化无人机作战效能分析方法研究

结合"捕食者"侦察/打击一体化无人机的作战特点,在对有人机作战效能评估方法分析研究的基础上,提出了侦察/打击一体化无人机作战效能评估指标体系,初步建立了作战效能的评估准则和数学模型.该模型综合考虑了可靠性、使用环境、适用于侦察/打击一体化无人机的新式设备以及操作人员等因素的影响,对"捕食者"侦察/打击一体化无人机作战效能进行了计算、分析,给出了影响作战效能的相关因素.     

战斗机作战效能分析的数学描述

在讨论战斗机作战效能评估定义的基础上,综述了战斗机作战效能评定的方法;给出了现代战斗机作战效能分析与综合的定义以及数学描述。     

战术任务飞行管理系统

现代战争中,军用飞机需要与外界进行广泛的信息交换,实时的全面掌握战场态势,保证有效完成作战任务。面对日益复杂的作战态势,飞行员难以承担如此繁重的人工管理和决策,由此产生了战术任务飞行管理系统。文章从介绍战术飞行管理技术的发展开始,闸释了战术飞行管理与任务规划系统综合发展的必然趋势,分析了军用飞机战术任务飞行管理系统的功...     

飞行器体系优化设计问题

针对传统的飞行器设计与体系（SOS）设计相互独立造成的飞行器实际作战效能不足的问题,对同时考虑飞行器与体系耦合设计的飞行器体系优化设计问题展开研究。首先,根据体系工程（SOSE）原理给出了耦合飞行器设计与体系结构设计的飞行器体系优化设计问题的基本概念与通用数学定义;其次,基于多层体系架构,构建了飞行器体系设计优化模型,提出了包含问题定义、体系架构建模、学科建模、优化求解4个步骤的通用建模求解流程;最后,以巡飞/精确打击武器协同作战为例,构建了面向任务成本最低、时间最短的协同作战体系最优化问题并对其进行优化求解。与先设计飞行器后设计体系结构的解耦设计结果对比表明,解耦优化设计忽略了体系结构与飞行器的强耦合特征,无法最优化体系效能;耦合优化设计能够获得体系效能最大化的飞行器设计方案。     

Architectures and GPS/INS integration: impact on missionaccomplishment

The GPS (Global Positioning System) signal contains information which, when properly combined with information from INS and other sensors, provides exceptionally high accuracy position, velocity, attitude, and time measurements. These ten elements of information (three each in position, velocity, and attitude, and one in time) are common, in various combinations, to most avionics functions. When viewed from a system perspective, this high-precision information can be thought of as an integration basis, or a reference set, which offers opportunities for reconfiguration of the offensive, defensive, communication, navigation, and other sensors. Various integration architectures for fusion of these sensors can inherently enhance, enable, or severely limit these potential mission capabilities. The choice of integration architecture, can directly and profoundly affect performance, cost of integration, cost of ownership, and exploitation of much greater mission capability. This is illustrated by an example     

机群编队对地攻击飞机武器系统作战模型研究

从机群编队对地攻击飞机武器系统作战顶层人手，建立了同类型机群及混合机群对地攻击飞机武器系统编队作战行动模型，给出了总体效能指标与飞机武器系统飞行阶段的效能指标关系，并进行了综合优化分析，为对地攻击飞机武器系统作战效能分析与综合打下了基础。     

Reliable flight performance assessment of multirotor based on interacting multiple model particle filter and health degree

Multirotor has been applied to many military and civilian mission scenarios. From the perspective of reliability, it is difficult to ensure that multirotors do not generate hardware and software failures or performance anomalies during the flight process. These failures and anomalies may result in mission interruptions, crashes, and even threats to the lives and property of human beings. Thus, the study of flight reliability problems of multirotors is conductive to the development of the drone industry and has theoretical significance and engineering value. This paper proposes a reliable flight performance assessment method of multirotors based on an Interacting Multiple Model Particle Filter (IMMPF) algorithm and health degree as the performance indicator. First, the multirotor is modeled by the Stochastic Hybrid System (SHS) model, and the problem of reliable flight performance assessment is formulated. In order to solve the problem, the IMMPF algorithm is presented to estimate the real-time probability distribution of hybrid state of the established SHS-based multirotor model, since it can decrease estimation errors compared with the standard interacting multiple model algorithm based on extended Kalman filter. Then, the reliable flight performance is assessed with health degree based on the estimation result. Finally, a case study of a multirotor suffering from sensor anomalies is presented to validate the effectiveness of the proposed method.     

High-torque density integrated electro-mechanical flight actuators

Electro-mechanical flight actuators (EMFAs) are core flight-critical vehicle components. Fly-by-wire or fly-by-light control of EMFAs is performed by flight management systems (flight, mission, propulsion, and integrated controls that manage any combination of specific flight, mission, and propulsion functions). Reported here are novel results in the analysis of EMFAs with permanent-magnet synchronous motors, with particular interest in the application of brushless high-torque density motors which have superior characteristics compared with other state-of-the-art motor technologies. It is shown that due to nonlinearities and bounds, new control algorithms must be developed and implemented to achieve a spectrum of performance and requirements for EMFAs. A number of important issues in control, analysis, model development, integration, and verification are studied. Tracking control algorithms are synthesized, stability studied, and novel analysis results are reported. Advanced computer-aided engineering software tools and emerging simulation-based design environments are used to guarantee high fidelity modeling and analysis within data intensive simulation. Proof-of-concept demonstration testbeds for the design of advanced EMFAs and their components are developed, and EMFA imitator performance thoroughly studied. Verification of the concepts reported are formed and documented. Precise tracking, disturbance attenuation, accuracy, stability, robustness, and excellent acceleration capabilities are reported. A demonstration is performed to substantiate the theoretical analyses to add credence to its applicability as an approach and method that the designer of future EMFAs can use to design a new class of actuators for aircraft flight control surfaces     

Impact of mission requirements and constraints on conceptual launch vehicle design

The objective of this paper is to analyse the impact of mission requirements and constraints on both the optimum vehicle design and the effects on flight path selection for two types of reusable two-stage-to-orbit launch vehicles. The first vehicle type considered provides horizontal take-off and landing capabilities and is intended to be propelled by an airbreathing propulsion system during stage 1 flight. The second vehicle type assumes a vertical launch and is accelerated by a rocket propulsion system during the booster stage ascent flight. The analysis employs a design tool for simultaneous system and mission optimization. It consists of a CAD-based preliminary vehicle design tool, aerodynamic and aerothermodynamic calculation software, flight simulation programs, and a two-level decomposition optimization algorithm enabling simultaneous system and flight optimization. The results to be presented show that the cruise flight requirement for an European launched mission of the airbreathing vehicle results in a loss of 60 % payload mass as compared to a mere accelerated ascent for a near equatorial mission into the same target orbit assuming constant take-off mass. The strong dependencies of mission requirements on both the optimal vehicle design and the ascent performance are determined for the rocket-powered vehicle type by varying the inclination and altitude of the target orbit.     

X-33 redundancy management system

The X-33 is an unmanned advanced technology demonstrator with a mission to validate new technologies for the next generation of Reusable Launch Vehicles. Various system redundancies are designed in the X-33 to enhance the probability of successfully completing its mission in the event of faults and failures during flight. One such redundant system is the Vehicle and Mission Computer that controls the X-33 ea, and manages the avionics subsystems. Historically, redundancy management and applications such as flight control and vehicle management tended to be highly coupled. One of the technologies that the X-33 will demonstrate is the Redundancy Management System (RMS) that uncouples the applications from the redundancy management details, in the same way that real-time operating systems have uncoupled applications from task scheduling, communication and synchronization details     

先进重构飞行控制技术和方法研究

重构飞行控制技术本质上是一种容错飞行控制技术，它使飞控系统具有适应未知故障和损伤的能力，从而可以有效地提高安全性和任务效能。先进重构飞行控制技术在原有的基础上更加强调自适应的能力，而不再依赖故障诊断和隔离（FDI）系统，因而促进了鲁棒控制、智能控制和逢适应控制技术在该领域的交叉和融合。首先回顾了重构飞行控制技术的发展现状，然后给出了几种先进重构控制方法，并总结了先进重构飞行控制技术的主要技术优势，最后展望了它的发展趋势和应用前景。