Evaluation of Multipoint Interaction in the Design of a Thin Diffraction-Limited Active Mirror

Active control of a thin, deformable mirror is one approach to obtaining diffraction-limited performance from large orbiting telescopes. The control system design requires knowledge of the mirror reaction to the multiple forces used to maintain the desired mirror figure. A structural analysis program is used to obtain estimates of the static deflections of a point-loaded, thin, shallow, spherical primary mirror. The calculated deflections are compared to experimentally measured deflections for a specific configuration.     

Electronically steerable plasma mirror based radar-concept andcharacteristics

An alternative to using a phased array to steer a radar beam is to electronically control the orientation of an inertialess broadband microwave reflector. Recent experiments have demonstrated that a planar plasma mirror immersed in a magnetic field can be formed with electron densities high enough to reflect X-band microwave beams. A plasma mirror performs like a metal mirror, but it is inertialess. Compared to high performance phased array systems, a plasma mirror based radar system is much simpler and is therefore more affordable. Electronic steering of microwave beams using a plasma mirror permits the use of wide instantaneous bandwidth waveforms. Potential areas of application for a plasma mirror based antenna system include ship self-defense, high-resolution radar imaging, target identification, electronic countermeasures, high data rate communications, spread spectrum links and remote sensing. As a reflector, the plasma mirror exhibits extremely low loss and the reflectivity is very nearly 100%. Since a perfectly reflecting object cannot radiate, the noise temperature contribution of the plasma mirror to the antenna temperature is likely to be small. The plasma sheet can be steered in elevation by tilting the magnetic field, and steering in azimuth may be accomplished by designating cathode initiation sites. Switching times between successive mirror orientations may be less than 20 μs     

Multi-sensor control for precise assembly of optical components

In order to perform an optical assembly accurately, a multi-sensor control strategy is developed which includes an attitude measurement system, a vision system, a loss measurement system and a force sensor. A 3-DOF attitude measuring method using linear variable differential transformers （LVDT） is designed to adjust the relation of position and attitude between the spher- ical mirror and the resonator. A micro vision feedback system is set up to extract the light beam and the diaphragm, which can achieve the coarse positioning of the spherical mirror in the optical assembly process. A rapid self-correlation method is presented to analyze the spectrum signal for the fine positioning. In order to prevent the damage of the optical components and realize sealing of the resonator, a hybrid force-position control is constructed to control the contact force of the optical components. The experimental results show that the proposed multi-sensor control strategy succeeds in accomplishing the precise assembly of the optical components, which consists of parallel adjustment, macro coarse adjustment, macro approach, micro fine adjustment, micro approach and optical contact. Therefore, the results validate the multi-sensor control strategy.     

Rotation and Shape of High Altitude Reflectors Controlled from the Ground

Passive, inverted-dish shaped communications mirrors made of a thin wire mesh may be maintained in a stationary position above most of the atmosphere by the pressure of reflected radiation beamed at the mirror from the ground. We show that by beaming at the mirror an appropriate mixture of linearly and circularly polarized radiation, and by inducing small periodic variations of the plane of polarization, one can monitor and sufficiently control wire orientation in the mirror, which allows one to reduce mirror weight and/or set the mirror in rotation. Mirror rotation in turn can modify mirror shape, open up flaps, and allow synchronized messages to be sent to prechosen locations.     

FD-09风洞单点腹支撑系统研制

为了在风洞中发展新型的腹支撑方式,基于FD-09风洞现有的下大迎角机构,设计研制了一套新型的单点腹支撑系统。单点腹支撑系统具有系统简便实用、模型设计简单、支撑干扰相对稳定等特点。在地面效应试验中使用布置光栅尺位移传感器的新方法取代了传统的测量方法,大大提高了控制精度和试验效率。风洞试验表明：单点腹支撑系统的试验重复性精度较高,部分指标已经接近国军标的先进指标;单点腹支撑系统的支杆干扰量是稳定的,并且对大部分气动分量的干扰量是小量;与双点腹支撑系统比较而言,单点腹支撑系统具有支杆干扰较小的优势。     

可重构飞行控制系统研究

对自修复飞控系统的关键技术－－可重构飞控系统进行了论述。介绍了目前主要的一些重构控制方法的特点，并对控制算法的优缺点及实现条件进行了分析；针对已进行了的可重构飞控系统的飞行试验进行了分析，并对试验结果做出了评价；指出了未来可重构飞控系统的实现途径和发展趋势。     

卫星激光通信终端控制系统稳定性设计

卫星激光通信终端控制系统的稳定性是激光通信链路建立与保持过程中的重要性能指标.以终端天线与快速倾斜镜(FSM)个内回路控制器设计为基础,建立了当电荷耦合(CCD)探测器获得对方终端位置信息构成激光闭合回路时整个激光通信控制系统模型,并根据时滞依赖稳定性定理推导了系统渐近稳定的充分条件,在此基础上对不稳定情况,结合锥补法...     

Closing the Loop in Optical System Design

The process of "closing the loop" in a design process relates to the flow of quantitative data regarding lens or mirror performance among all engineers involved in the production of an optical system. Recent developments in applied optics have made this a computerized process. The history and significance of the process is described, with stress placed on the automation of interferometric lens or mirror test methods.     

Deployment dynamics for flexible deployable primary mirror of space telescope with paraboloidal and laminated structure by using absolute node coordinate method

A nonlinear dynamic modeling method for primary mirror of Flower-like Deployable Space Telescope (F-DST) undergoing large deployment motion is proposed in this paper. To ensure pointing accuracy and attitude stability of the paraboloidal primary mirror, the mirror is discretized into equal thickness shell elements by considering shell curvature. And the material nonlinear constitutive relation of flexible mirror is acquired using Absolute Nodal Coordinate Formulation (ANCF). Furthermore, the primary mirror of F-DST can be regarded as a clustered multi-body system, and its dynamic equations of elastic deformation and deployment motion are established by virtual work principle. Finally, the deployment motion of primary mirror by different driving conditions are simulated, the results show that the vibrations of mirrors that driven by elastic hinge device are more than that driven by servo motor. In addition, single sub-mirror deployment process will perturb the pointing accuracy of primary mirror, and the multiple sub-mirrors simultaneously deploying will seriously affect all the sub-mirrors surface accuracy because of the coupling effect. Thus, there are theoretical value and practical significance for the controlling surface accuracy and attitude accuracy of space telescope.     

某型涡轴发动机数控系统的机械液压备份控制方案研究

综合国内外涡轴发动机控制系统的发展趋势及成熟度的基础上,提出了一种带机械液压备份功能的控制系统方案,该方案的机械液压备份功能模块能跟随数字控制功能模块,并能够在数字控制失效后平稳切换到机械液压备份控制,具有在包线范围内实现发动机的燃油和导叶机械液压备份控制功能,保证涡轴发动机安全工作和直升机的安全返航.该方案通过工程设计、试制,开展了半物理试验和台架试验验证,验证结果表明:该备份控制方案的动力涡轮转速控制精度优于±0.5%,导叶控制精度优于4°,具有良好的工程应用性.      

航空发动机分布式控制系统技术分析及系统方案

分析了航空发动机分布式控制系统的系统结构、通讯总线、智能元件、高温电子元器件及分布式电源总线等领域的研究现状,并进行技术成熟度评估.结果表明:航空发动机分布式控制系统研究处于基础研究阶段,各项技术成熟度(TRL)主要处于TRL1~TRL2.针对某涡扇发动机提出基于TTCAN(时间触发控制器局域网协议)总线的过渡分布式和部分分布式两种控制系统方案,分析了各方案中系统结构、控制功能和信号交互特点,以期为航空发动机分布式控制系统进一步研究提供参考.      

Automated air defense system using knowledge-based system

The proposed KAAD (knowledge-based automated air defense) system demonstrates a man-machine environment for airspace defense systems. When the unknown aircraft is hostile, a threat rating and response methods are generated by the system. It serves as a double-check decision-making system for a war control center. In addition to this application, the KAAD system can also be a useful tool as a training program for the war controller. The capabilities of the system are limited due to the shortage of knowledge resources. It requires communications among war controllers and air fighter pilots to organize a practical knowledge base. It is shown that the KAAD system can be combined with an automated ATC (air traffic control) system to become a practical system for air defense applications     

Lyapunov-based decentralized adaptive control for laser beam tracking systems

A successful controller design is crucial for establishing and maintaining an optical link between free-space communication stations engaged in a laser communication session. This task is quite difficult due to nonlinear behavior, cross-coupled dynamics, and time-varying characteristics of all known beam steering technologies. A novel adaptive control technique utilizing Lyapunov function to ensure global asymptotic stability of the system, thus resulting in a highly robust system performance, is developed. The technique applied to a piezo-electric mirror setup results in a highly efficient controller design that does not require prior knowledge of system dynamics, while providing independent access to azimuth and elevation positions of the laser beam. The basic algorithm is presented and the results of its application are demonstrated.     

弹用涡喷发动机数控实时仿真系统设计及试验

以弹用小型涡喷发动机为研究对象，在充分考虑了发动机数字控制系统设计过程中的实时仿真、数控台架试车、数控系统成型装备飞机与导弹等实际情况的基础上，采用PC／104为数控系统控制器，以计算机模型替代真实发动机，设计了发动机数控含实物实时仿真系统。具体介绍了系统硬件设计；自适应预测控制器设计及其试验研究等。仿真结果表明：系统能实时地反映在控制系统作用下发动机的运行情况，为发动机全权限数字电子控制（FADEC）系统研究提供了良好的试验手段。     

Design of Boeing 777 electric system

The electric power system for the Boeing 777 is comprised of two independent electrical systems, the main and the backup. The main electric system includes two engine-driven integrated drive generators, a generator driven by the auxiliary power unit, three generator control units, and a bus power control unit. The backup electric system includes two engine-drive generators and one integrated converter/control unit to provide the redundancy of electrical sources equivalent to a three-engine airplane. Automation of the system is achieved by the use of state-of-the-art, microprocessor-based control units that perform system control, protection, and built-in-test functions. Each control unit has redundant two-way communication through an ARINC 629 communication bus that requires significantly fewer discrete wires than similar systems, allowing considerable reduction of the interface circuits and reduction in weight     

Design and feedforward control of large-rotation two-axis scan mirror assembly with MEMS sensor integration

As a key component of electro-optical systems, a Two-axis Scan mirror AssemblY(TSAY) is usually used for Line-of-Sight(LOS) precision pointing, tracking, scanning, and stabilizing. Therefore, it is necessary for a TSAY to have a large angular range, high dynamic characteristics, and small mirror surface distortion. Furthermore, vibration from carriers of electro-optical systems, such as spacecraft and airplanes, is inevitable, so it is critical to guarantee the control accuracy of a TSAY under vibration. In this paper, a TSAY prototype is designed and developed. To increase the control bandwidth, structural topology optimization is applied to the TSAY's elliptical mirror to reduce the moment of inertia, meanwhile keeping surface flatness. A flexible hinge is adopted to achieve a large angular range. To suppress the angular perturbation caused by the base linear vibration, an adaptive feedforward loop with base-integrated Micro-Electro-Mechanical System(MEMS) accelerators is constructed to enhance the TSAY's feedback loop. Simulation and experimental results show that the TSAY prototype's two-axis mechanical angular ranges are more than ±3.2°, the mirror surface flatness Root Mean Square(RMS) value is better than 0.04 k, and the closed-loop bandwidth is beyond 330 Hz. These are suitable for most applications. Besides, the angular perturbation caused by the base vibration can be suppressed more than 37.7% with the addition of the adaptive feedforward loop.     

涡扇发动机燃油综合控制半实物仿真试验系统

建立了某涡扇发动机气动热力学模型和该型发动机综合电子调节器、主燃油泵调节器的实验室工作环境。发动机数学模型运行在计算机上,通过VXI总线技术,将其与控制器和执行机构实物连接,组建了某涡扇发动机燃油综合控制半实物仿真试验系统。对该半实物仿真试验系统进行试验,结果表明:该半实物仿真试验系统能有效地对该型发动机燃油进行静态和动态控制,为开展发动机的全权限数字电子控制(FADEC)系统研究和先进控制理论在发动机控制中的应用研究奠定了试验基础。     

Modeling of helicopter behavior dynamics under the controlling action of the stabilization and control system

A possibility of evaluating dynamic response of a mechanical system to controlling actions of the automatic stabilization and control system is considered on the basis of a numerical experiment. Examples of design analysis are presented for a light-weight helicopter in which an autopilot is part of the control system. The finite element analysis is used in this paper.     

液体冲压发动机数字电子控制系统

为某型号整体式液体冲压发动机设计了数字电子－液压机械控制系统，介绍了该系统的控制方案、工作原理和工作方式。数字电子－液压机械控制系统和冲压发动机与弹体数字仿真器等组成液体冲压发动机、弹体／发动机控制系统半实物仿真系统，对数字电子－液压机械控制系统的功能及工作协调性进行了检验，半实物仿真试验结果证明，该系统满足设计要求。     

Variable structure robust flight control system for the F-14

In this paper, a flight control law for a simplified F-14 aircraft model is designed based on variable structure control (VSC) theory. For m-input, q-output linear uncertain systems (q相似文献