Lessons learned from the autonomous power system

The autonomous power system (APS) project at the NASA Lewis Research Center is described. The project is designed to demonstrate the applications of integrated intelligent diagnosis, control, and scheduling techniques to space power distribution systems. It consists of the autonomous power expert system (APEX) for fault detection, isolation, and recovery; the autonomous intelligent power scheduler, for efficient assignment of activity start times and resources; and power hardware (Brassboard) to emulate a space-based power system. Each part of the system was critiqued based on individual performance as well as the ability to interact with the other portions of the APS project. These critiques were used to determine guidelines for new and improved components     

Solid-state power controller for the next generation

The design philosophies of an electrical load management center (ELMC) for military platforms and the advantages and features made possible only through the use of real-time solid-state power controllers (SSPCs) are discussed. Computer control of power distribution systems will be required to off-load crews and increase system reliability, with improved fault handling, while also protecting the wire and load. The electrical, mechanical, and special competitive features of the SSPC series, the military screening and mechanical specifications, and other product options are highlighted     

270-VDC/hybrid 115-VAC electric power generating system technologydemonstrator

The approach, system architecture, instrumentation, and performance of a technology demonstrator system for the application of 270-VDC/hybrid 115-VAC electrical power generation and distribution to future military aircraft are examined. The design has focused on assembling a highly flexible test system. The loads are typical of those in a hybrid electrical system. The system consists of a single 3-phase, 115-VAC electrical generator whose output is rectified, filtered, and supplied through DC contactors to both a 270-VDC load bus and to the input of an inverter, which supplies a 400-Hz, 115-VAC load bus. A variable-frequency, 115-VAC bus is also available directly from the generator. A prototype variable-speed constant-frequency 120-kVA generator is used. The test facility is designed to provide loads to all power types capable of being produced by the system. The system has provided particularly good insight into various aspects of 270-VDC/115-VAC hybrid systems and their components     

Terminal control monitor for ATC using knowledge-based system

A knowledge-based system for air traffic control (ATC) in terminal control regions is designed for improving service and operation. Domain knowledge is established following rules, regulations, and comments from controllers. An expert system is adopted for approach control and airport control in the terminal control region. The proposed system was implemented in PC-AT with Turbo Prolog. The air terminal control monitor was checked with regard to flight information input, real-time data refreshment, air traffic rescheduling, constraint violation double checking, emergency responses, and normal monitoring. Simulation results are given     

Aircraft VSCF generator expert system

VSCF (variable-speed constant-frequency) electrical systems are designed using standard modules to reduce the manufacturing cost and improve the product quality and services. An expert system that automatically configures the modules required for a particular application is described. It is a rule-based synthesis system with a domain that encompasses the matrix of standard modules. The module functions include electrical generation, conversion, the control. All the modules must be placed in a proper package to fit the space available inside the particular airplane. The configuration system is built by using a rule-based expert system development tool, OPS5, in a VAX 11/750 computer. It has the domain-specific knowledge necessary to configure the generators embedded in its rulebased and exhibits expertise to place the modules in the proper arrangement based on customer specifications and design criteria. The system can also help the engineers and salespersons to determine the configuration at quotation time and to point out any new design which is required     

Generic functional modelling of multi-pulse auto-transformer rectifier units for more-electric aircraft applications

The Auto-Transformer Rectifier Unit (ATRU) is one preferred solution for high-power AC/DC power conversion in aircraft. This is mainly due to its simple structure, high reliability and reduced kVA ratings. Indeed, the ATRU has become a preferred AC/DC solution to supply power to the electric environment control system on-board future aircraft. In this paper, a general modelling method for ATRUs is introduced. The developed model is based on the fact that the DC voltage and current are strongly related to the voltage and current vectors at the AC terminals of ATRUs. In this paper, we carry on our research in modelling symmetric 18-pulse ATRUs and develop a generic modelling technique. The developed generic model can study not only symmetric but also asymmetric ATRUs. An 18-pulse asymmetric ATRU is used to demonstrate the accuracy and efficiency of the developed model by comparing with corresponding detailed switching SABER models provided by our industrial partner. The functional models also allow accelerated and accurate simulations and thus enable whole-scale more-electric aircraft electrical power system studies in the future.     

应用于航空变频电源系统的新型串沥混合有源滤波器

 目前变频交流(AC)电源系统开始逐渐应用到新型多电飞机(MEA)中,传统有源滤波器无法满足宽输入频率变化要求,为此需要设计一种适合于宽变频航空电源系统的有源滤波器。本文研究了一种应用于航空变频电源系统的新型串联混合有源滤波器(SHAPF),该有源滤波器直接根据基波电流进行补偿,针对各种频率输入均能起到较好的抑制谐波作用。讨论了这种新型SHAPF的变频谐波抑制原理,给出了该滤波器的控制系统详细设计过程,包括基于双数字信号处理器（DSP）的控制平台设计和逐点动态检测基波电流的算法设计,最后进行了样机实验,对比了加入滤波器前后系统输入电流实验波形和谐波分析,加入滤波器后系统输入电流总谐波失真度（THD）由174.00%变化至4.80%,滤波效果良好;在360 Hz,400 Hz和720 Hz不同输入频率进行了滤波实验,验证系统在宽变频输入条件下均具有良好控制性能,满足航空变频输入时输入功率因数校正要求。     

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     

Parametric cost model for solar space power and DIPS systems

A detailed cost model has been developed to parametrically determine the program development and production cost of photovoltaic, solar dynamic, and dynamic isotope (DIPS) space power systems. The model is applicable in the net electrical power range of 3 to 300 kWe for solar power and 0.5 to 10 kWe for DIPS. Application of the cost model allows spacecraft or space-based power system architecture and design trade studies or budgetary forecasting and cost benefit analyses. The cost model considers all major power subsystems (i.e., power generation, power conversion, energy storage, thermal management, and power management/distribution/control). It also considers system cost effects such as integration, testing, and management. The cost breakdown structure, model assumptions, ground rules, bases, cost estimation relationship format, and rationale are presented, and the application of the cost model to 100-kWe solar space power plants and to a 1.0-kWe DIPS is demonstrated     

基于 STC15单片机和 LabVIEW的电参数监测系统设计

电参数的实时监测对保障用电设备的安全和供配电系统的可靠运行具有重要意义。基于 STC15W4K56S4单片机和 LabVIEW相结合的方式,设计了 1种由上位机、主控模块和测量模块组成的无线交流电参数监测系统。测量模块以 STC15W4K56S4单片机为控制器,采用专用电能测量模块 CS5463测量电压、电流等参数,用液晶模块 OLED显示,无线数据传送采用 nRF24L01模块实现,基于 LabVIEW的上位机程序进行电参数信息显示、参数设置等,实现了远程实时监测。该系统具有测量精度高、电路设计简单、监测灵活方便、易于扩展、人机界面友好等特点。     

试验室环境试验试验项目剪裁专家系统

说明了某型军用飞机机载设备试验室环境试验试验项目剪裁专家系统的基本情况, 定义了试验室环境试验试验项目剪裁专家系统, 同时利用关系型数据库语言VF6. 0编写了环境试验剪裁专家系统软件,说明了建立的过程及方法, 介绍了剪裁专家系统软件的部分功能及使用方法。为说明专家系统应用的实际过程, 文章最后结合某型飞机机载设备环境试验工作的具体情况, 利用本文介绍的专家系统对某型号任务计算机进行了试验室环境试验试验项目剪裁分析。     

基于SOC的多轴稳定系统回路控制

围绕基于多通道信号处理与控制SOC芯片实现惯性平台系统典型控制回路,进行了设计方法、流程及最终实现结果的阐述.首先,依据平台系统的要求制定系统工作流程;之后根据硬件资源进行各工作流程的分配和调整;再进行数据采集处理、算法实现、过程数据处理、PWM输出处理、其他输出量处理;最终通过功率级将电信号传输给平台上的执行元件,实现平台系统四条典型控制回路.此方法能够适应多种算法和系统需求,可实现自主化、小型化,且功耗小、可靠性高.     

An intelligent landing system based on a human skill model

An automatic landing system (ALS) is developed on the basis of a human skill model. The model is expressed as a nonlinear I/O mapping from the aircraft state to the control command provided by a human expert. In this system, all the I/O data provided by the human expert are stored in a database a priori, and a local model to answer the current aircraft state is built to generate a control input close to the human operation. A gain adaptation technique is introduced for improving the robustness     

小型无人机发电系统的研制

本文介绍了一种适用于无人机的专用电源系统的设计方案,该方案由永磁同步发电机和宽电压输入范围的电源变换/调节装置组成.该方案具有系统结构简单、可靠性高、电源品质高和转速范围宽的优点,并对电源系统进行了实验验证,实验结果和理论分析一致.     

Periodic Job Scheduling in a Distributed Processor System

This investigation considers the problem of the nonpreemptive scheduling of a set of independent periodic jobs in a computer system characterized by a collection of processors, memories, and interconnection mechanisms. Such a collection of resources can be used to perform the functions of a process control environment as are found, for example, in the avionics of a military or commercial aircraft. The distribution of these resources permits weight, volume, power, cost, and reliability requirements to be satisfied. Each periodic job is characterized by its frequency and its execution time. The inverse of the frequency, the period, is assumed to be an integer, and the initiation time and the completion time of job must be strictly met. An optimal algorithm is developed for a job set whose members are related by a binary frequency distribution. That is, if the jobs in the set are ordered in terms of decreasing job execution frequency, then fi = 2fi+1. The optimal result is generalized to include conditions in which the jobs are related by fi = kfi+1, where k is an integer.     

PWM full-bridge converter with natural input power factor correction

A pulsewidth modulated (PWM) full-bridge converter that simultaneously performs input power factor correction (PFC) and DC-DC conversion is proposed. The converter is the same as the standard voltage-fed PWM full-bridge converter with a diode-bridge low-pass filter front end, but with a slight modification that results in an improvement in power factor that is sufficient to satisfy the EN61000-3-2 requirements for electrical equipment. The operation of the converter is explained and analyzed, and the results of the analysis are used to determine the converter's steady-state characteristics, which are discussed in detail. A design procedure for the selection of components is then derived and demonstrated with an example. The feasibility of the converter and its ability to satisfy EN61000-3-2 requirements on electrical equipment is shown with results obtained from an experimental prototype.     

Battery charger design for the Columbus MTFF power system

A novel pulsewidth-modulated (PWM) dc-dc converter topology is proposed for the battery charge regulator (BCR) of the Columbus Man-Tended Free-Flyer (MTFF) power system. The system is a regulated bus system. Bus voltage control is implemented at the input of the BCR. The use of a conventional buck topology with PWM conductance control at the input results in a second-order behavior. A study of new PWM dc-dc converter topologies has been made to attain a suitable topology. The proposed converter topology is designed and a breadboard including the control loop has been built and tested. The experimental results show that the converter operates according to the design constraints.     

Integrated power and attitude control with two flywheels

Energy storage and attitude control are two distinct subsystems of the typical satellite. Energy storage is provided using batteries and active attitude control is accomplished with control moment gyroscopes or reaction wheels. A system mass savings can be achieved if these two subsystems are combined using multiple flywheels for simultaneous kinetic energy storage and momentum transfer. This paper develops, simulates, and experimentally demonstrates the control algorithms to accomplish integrated power and single-axis attitude control using two flywheels.