X—31A飞机的设计特点和试飞情况

综述了为验证增强战斗机机动性(EFM)计划、衡量过失速机动飞行的可行性及其在近距空战中的战术价值,X-31A飞机在气动布局、大迎角抗偏离设施、推力矢量系统以及飞控系统方面的特点;介绍了X-31A飞机的有关飞行试验情况,特别是循序渐近的四种过失速机动动作以及空战效能评估结果。结果表明,X-31A飞机气动布局合理,能完成过失速机动飞行。且过失速机动技术和推力矢量组合,可以大大地提高飞机近距空战的作战效能。     

Military Satellite Communications Using Small Earth Terminals

Satellite communications technology has reached the stage at which it is feasible to develop a reliable military tactical communications system using small transportable Earth terminals. This paper discusses the design considerations involved for a multiple-access system, with particular reference to the Earth terminals.     

战术弹飞行力学软件系统设计

从战术弹飞行力学软件系统的设计开发角度，提出了软件系统的设计指导思想，对软件系统基本运行流程进行了分析研究，完成导弹设计不同阶段有关飞行力学问题研究的应用软件设计开发。编制了系统的符号词典和软件文档。在软件系统设计时考虑多种语言程序之间的接口设计及运行环境，并就软件系统进一步开发研究进行了探讨。完成了战术弹飞行力学软件系统的设计。     

Automatic Electronic Switching for a Field Army

A family of 4-wire electronic equipments is being developed for use in a tactical switching system for the field army. The characteristics and design of two automatic switchboards to be used in the system are discussed, as well as the signaling methods and numbering plan that are employed.     

Digital Autopilot Design for a Microprocessor-Controlled Small Tactical Terminal Homing Missile

A digital autopilot design was developed for a small laser-guidedtactical missile. The multiloop design was developed in the w plane and analyzed by time domain simulation. Performance is as good or better than the current analog version, thus demonstrationg the feasibility of digital guidance technology in tactical missile applications.     

高过载微惯性器件研究现状

微惯性器件是目前制导战术武器的核心元器件,具有成本低、体积小、寿命长等优点,但是其如何在火炮膛内、侵彻着靶等过程中存活甚至正常工作,一直是各军事大国科研院所发展精确打击制导武器的重要研究方向。查阅了相关国内外文献,然后详细评述了目前关于应用于高过载环境下的微机械陀螺与微机械加速度计研究现状,指出了目前高过载环境微惯性器件的发展趋势与各国的研究进程,为我国发展高过载微惯性器件提供了方向与指导。     

飞行轨迹指令综合跟踪控制器设计

运用多重尺度奇异摄动理论,结合动态逆解耦理论和动态平衡点邻区域优化线性化系统的优化解耦控制律理论,研究了战术任务综合飞行管理系统的综合飞行轨迹指令跟踪控制器系统化设计方法。对F-15飞机,设计了综合飞行轨迹跟踪控制器。数字仿真结果表明,设计的跟踪控制器能够控制飞机精确跟踪不同时标集的飞行指令。     

MEMS inertial rate and acceleration sensor

Development of the μSCIRAS^TM (pronounced micro-Cyrus) multisensor for a period of over six years has produced a practical MEMS Inertial Measurement Unit (IMU). Using only three silicon sensors, a full-up IMU suitable for tactical grade navigation and guidance applications has been achieved. Iterative improvements in silicon sensor design and bulk micromachining processes have matured to the point where an IMU with an attractive price/performance ratio is now producible. This paper summarizes the design features and test results for an IMU with <100 deg/hr performance. Test results are shown for rate bias and acceleration bias over temperature. Production of this initial member of the μSCIRAS product family begins this year to support applications including guided artillery shells, technology insertion to decrease missile costs, navigation of remotely-piloted vehicles, dismounted soldier location devices and other navigation aids. The small size of this silicon multisensor and its ability to measure both angular rotation rate and linear acceleration provides a useful advantage in product packaging, cost, size, and system testing. The μSCIRAS Inertial Sensor Assembly (ISA) is housed in a 2 cubic inch package weighing less than 5 ounces (140 grams) requires less than 0.8 Watts of power. Continuing development will lead to greatly improved performance on the order of 1 deg/hr at low prices in high-volume production     

Implementation of tactical maneuvers with maneuver libraries

This study creates and combines the general maneuver libraries for fixed-wing aircraft to implement tactical maneuvers. First, the generalized maneuver libraries are established by analyzing the characteristics of tactical maneuvers required in battlefields. The 7th order polynomial is applied to both the creation of the maneuver libraries and the generation of the trajectories or flight paths for modal inputs. To track the desired trajectory, we design the Attitude Command Attitude Hold (ACAH) system and the Rate Command Rate Hold (RCRH) system using Model Following Controller (MFC). Moreover, the Line-of-Sight (LOS) guidance law is designed. In particular, the CONDUIT® is employed to optimize the gains so that the control systems meet the aircraft Handling Qualities (HQ) criteria. Finally, flight simulations are performed for the longitudinal loop, immelmann-turn, and climb-slalom-descent maneuvers to verify that tactical aggressive maneuvers are realizable via the combination of maneuver libraries. This study can contribute to the development of flight techniques for aircraft tactical maneuvers and to the revision of air force operational manuals.     

战术无人机总体与性能参数相关性分析

按照飞行器设计的基本原理并结合无人机特点,对侦察、监视类战术无人机总体参数与性能参数进行了相关性分析,找出了两者可能存在的数学关系,得到10个经验公式和一些重要参数的取值范围,可为战术无人机的概念设计提供有用的数据和参考。     

A Family of SHF Tactical Satellite Communication Ground Terminals

On February 8, 1969, an experimental tactical communications satellite, TACSAT I, was successfully placed in synchronous orbit at the equator off the coast of South America. This paper concerns itself with a family of SHF tactical satellite communications ground terminals utilizing the SHF capability of that satellite. The material presented provides the system concepts necessary for the understanding of the ground terminals, their relationship to the satellite, and some insight into the design problems encountered during the development of a family of five types of terminals. The system concepts are presented in terms of communication modes, frequency assignments, and implementation of the respective modes. The beacon system for frequency control and signal acquisiticn siticn is described along with the factors involved in design of equipment implementing the analog FM, the alert message, frequency hopping, and, differential phase-shift keyed (DPSK) modes. The final configurations of each of the five terminals are described and illustrated through photographs and generalized block diagrams, and the capability of each is briefly outlined.     

仿真系统在型号研制中的作用和地位

仿真技术的应用范围已从作战领域扩展到武器型号研制领域。阐述仿真、仿真模型和仿真系统的基本概念和特点，以及分布交互仿真和虚拟仿真与型号研制的关系。以战术导弹为例探讨了仿真系统在型号研制、试验、评估和降低成本中的重要作用。     

战术飞行实时轨迹优化系统设计

介绍了在所开发的“战术飞行轨迹优化系统”中采用的轨迹优化方法－启发式搜索算法的改进方案。为了加快搜索速度，建立了专家系统，介绍了专家系统的规则。为了验证方法的有效性，建立了基于局域网的地面实时仿真系统，详细介绍了专家系统的设计。仿真计算结果表明，所开发的飞行轨迹优化系统是可行的。     

塔康仿真系统的设计

塔康是战术空中导航系统,能完成测距和测位的任务。塔康仿真器是具有塔康设备功能的计算机仿真系统,它可以代替塔康设备参与航空电子系统的综合试验,而且能取得很好的效果。本文在分析塔康工作原理的基础上,对塔康仿真器的硬件结构和软件设计做了较为详细的介绍,同时,对塔康信标的仿真也做了扼要的说明。     

MILDATA?A Study of Post-1975 Command Control Information Systems

MILDATA was an Army-sponsored exploratory development study in the area of digital computer technology. Its objective was to explore and evaluate new organizational concepts for hardware and software in a tactical command control information system (CCIS) and to develop new measures of effectiveness and methods for evaluating system performance. It was assumed that the MILDATA system would be operational in the field army during the time frame 1975-1985. A unique feature of the MILDATA concept is an unprecedented degree of modularity which provides flexibility to fulfill a wide variety of tactical data processing requirements. This paper supplies necessary background on CCIS requirements and develops modular design criteria. It then summarizes MILDATA study requirements and the general nature of the results obtained and outlines a program of future work. Finally, an attempt is made to systematize the experience gained during MILDATA as an aid to the organization of future exploratory development studies.     

飞行力学在图像制导导弹设计中的应用

为满足作战需要 ,改善导弹的总体性能 ,又有利于降低研制成本 ,对图像制导导弹的导引头最大跟踪角速度、极限框架角、搜索方案以及导弹的速度方案 ,进行了分析设计。以此为例 ,对飞行力学在导弹总体与分系统设计中的应用进行了说明。研究结果表明 :飞行力学是协调导弹总体与各分系统之间关系的重要手段 ,在导弹总体和各分系统的设计过程中 ,积极主动地应用飞行力学进行综合设计 ,可获得最佳的总体性能。     

Minitact gyroscope-the low cost alternative

The allure of the solid state optical gyros is being challenged by the invention of a new spinning mass device, providing superior low noise drift performance, high reliability at a very low cost. The Minitact is a unique two axis gyroscope advancing the technology of spinning mass devices to set new low cost standards. Minitact provides all the low noise performance benefits of tuned rotor gyroscopes without the vagaries of fixture suspension systems. The Minitact design integrates together the advantages of a spherical hydrodynamic gas bearing and a three axis permanent magnet DC commutated, motor and torquer, into miniature two aids gyroscope with a dynamic range of greater than 10^-7. The design is described and performance data presented illustrating the capability of this low cost next generation rate gyroscope. The Minitact is the result of Integrated Product Development (IPD) and Design to Unit Production Cost (DTUPC) design processes and is expected to become the tactical performance benchmark     

Night vision devices for ground environment

The PM N-V/RSTA is procuring the Driver's Vision Enhancer (DVE) thermal imaging system for use in combat and tactical wheeled vehicles. The DVE uses uncooled forward looking infrared technology compared to the I² technology currently in the field. During the development of the DVE several issues were raised regarding how specific aspects of system design were related to driver performance. As a result, DCS Corporation developed a data collection effort to provide the DVE project leader with needed performance data that could act as a foundation for making program decisions     

综合飞行/推进控制系统的鲁棒设计方法

基于凸多面体线性系统族镇定方法和航迹准稳态运动概念，研究了现代攻击机的综合飞行／推进控制系统的鲁棒设计方法。该方法根据航迹准稳态运动的条件。生成航迹准稳态运动的期望控制量和状态量，以航迹准稳态运动为基准运动建立综合系统的线性系统族模型，采用凸多面体线性系统族鲁棒镇定方法设计了综合控制系统的反馈调节控制器。数学仿真表明，所设计的综合控制系统对攻击机推进系统输出推力的变化具有大范围的鲁棒性，在推力开环控制下能够获得良好的系统动态性能和战术性能。     

Advances in high voltage power switching with GTOs

A high-voltage opening switch that uses gate-turnoff thyristors (GTOs) in series and successfully operates at voltages higher than the rated voltage of the individual devices has been demonstrated. The switch design and construction are described, and experimental results are given. The demonstration system is rated at 5 kV and uses 1-kV devices. A larger 24-kV system is under design and will use 4.5-kV devices. In order to design the 24-kV switch, the safe operating area of the large devices must be thoroughly known