压电式加速度传感器灵敏度校准虚拟仪器设计

虚拟仪器是计算机技术与仪器技术深层次结合产生的全新概念的仪器，它实现了测量仪器的智能化、多样化、模块化特点。在虚拟仪器的硬件平台确定后，选用LabVIEW软件作为虚拟仪器软件平台，并利用其图形化编程特点，在虚拟信号发生器程序设计基础上设计了传感器灵敏度校准程序，并应用该程序实现了压电式加速度传感器灵敏度校准。与使用传统仪器进行压电式加速度传感器校准相比，具有校准过程速度快、操作简单、且校准结果准确的特点。     

基于虚拟仪器的位置伺服实验系统

介绍一种利用虚拟仪器软件开发环境LabWindows/CVI开发的位置伺服实验系统,在其上面可以方便地试验各种控制算法,为控制工程师提供了一个简单的控制器实验平台.采用软硬件结合的方法完成系统的设计,并通过实验说明了系统的有效性.     

Using interchangeable virtual instrument (IVI) drivers to increasetest system performance

Instrument driver technology has evolved tremendously over the last decade. Initiatives such as SCPI and VXIplug&play have simplified remote instrument programming with standardized command messages and high-level utility functions. The latest initiative is the Interchangeable Virtual Instrument (IVI) Foundation. IVI defines standards for instrument drivers that offer benefits to provide higher performance. These benefits include instrument interchangeability, instrument simulation, and instrument state-caching. Because instrument drivers are an integral part of a modern test system, IVI promises to provide developers with the tools to increase their system performance significantly. This paper reviews the technical aspects of the IVI specification and the TVI architecture and describes how IVI can help the test system developer improve performance and lower long-term software maintenance costs     

Implementing reusable, instrument independent test programs in thefactory

Development of computer programs that control test sequences on Automatic Test Equipment (ATE) is costly and time consuming. Test Programs are usually written by specifying the instruments to be used in the ATE and the sequence of the setup and measurement parameters for these instruments. Reuse of test program software on other ATE is usually not possible without rewriting, revalidating and re-releasing the programs. This paper describes an implementation of a test program software development system and a standard of software runtime architecture used in our factories. The object-oriented development environment and its associated class libraries allow test programs to be written without knowledge of the ATE on which they will be run. Two main principles guided the design: the software architecture was based on recognized formal and industry standards; and our implementation used commercial off-the-shelf software products when possible. Emerging standards such as the IEEE-1226 (ABBET) as well as defacto industry standards including VXI Plug and Play have made our implementation possible. The current draft of the ABBET and P&P standards do not promote this instrument independence, but it is hoped that this will be added as the standards mature. Three immediate benefits are: cost savings that result from reusing validated test programs; cycle time reductions that result from concurrently developing test program software and ATE; and software defect reductions that result from using proven software     

面向航天器系统级测试的虚拟测试方法及应用

航天器总体设计正确性和接口实现正确性的及时验证,是提高航天器这类复杂系统可靠性的重要手段。本文提出一种基于模型检测的虚拟测试方法。方法采用窗口树模型(WTM)对复杂系统进行建模,采用状态转移图(STG)作为系统规约刻画系统行为的正确性。方法通过提出基于自动机的模型检测机制,实现了一种面向航天器系统级测试的虚拟测试平台(VTP)原型系统。该平台支持虚拟测试准备、虚拟测试执行和虚拟测试评估等功能,模拟并实现复杂系统总体设计正确性的验证和接口实现正确性的验证。     

五维空间一体化试验体系的发展与思考

空、天、地、海、赛博五维空间一体化作战环境已成为现代化战争的新模式,现有的试验测试体系已经不能满足未来一体化作战网络系统试验与评估的发展要求.从需求出发,首先分析了美国DoD在军工武器试验领域的投资研究计划,其次提出了我军一体化试验与测试体系的发展构想,可为未来大系统联合试验与评估提供参考.     

SDM标模大迎角动态特性试验研究

介绍了CARDC高速所进行的SDM模型大迎角的动导数和大迎角大振幅动态试验情况与试验结果.SDM标模的试验结果表明:试验结果与国外文献数据具有较好的一致性.试验结果随马赫数和迎角的变化表现出明显的非线性,而减缩频率的影响并不显著.天平与测试系统的重复性精度较高.在试验条件下,减缩频率、振幅、平均迎角及来流肘数均对模型的动态气动特性有影响,其影响量值的大小与具体的试验条件有关.在迎角约为15°～75°范围内,试验曲线存在着迟滞环.     

Initial virtual flight test for a dynamically similar aircraft model with control augmentation system

To satisfy the validation requirements of flight control law for advanced aircraft,a wind tunnel based virtual flight testing has been implemented in a low speed wind tunnel.A 3-degree-offreedom gimbal,ventrally installed in the model,was used in conjunction with an actively controlled dynamically similar model of aircraft,which was equipped with the inertial measurement unit,attitude and heading reference system,embedded computer and servo-actuators.The model,which could be rotated around its center of gravity freely by the aerodynamic moments,together with the flow field,operator and real time control system made up the closed-loop testing circuit.The model is statically unstable in longitudinal direction,and it can fly stably in wind tunnel with the function of control augmentation of the flight control laws.The experimental results indicate that the model responds well to the operator's instructions.The response of the model in the tests shows reasonable agreement with the simulation results.The difference of response of angle of attack is less than 0.5°.The effect of stability augmentation and attitude control law was validated in the test,meanwhile the feasibility of virtual flight test technique treated as preliminary evaluation tool for advanced flight vehicle configuration research was also verified.     

Identification of aircraft longitudinal aerodynamic parameters using an online corrective test for wind tunnel virtual flight

The identification of aerodynamic parameters is accomplished through the test data of the dynamic movement of scaled aircraft models flying dynamically in wind tunnel,which can real-ize the accurate acquisition of the aerodynamic model of the aircraft in the preliminary stage for aircraft design,and it is of great significance for improving the efficiency of aircraft design.How-ever,the translational motion of the test model in the wind tunnel virtual flight is subject to con-straints that result in distinct flight dynamics compared to free flight.These constraints have implications for the accuracy of aerodynamic derivatives obtained through the identification of wind tunnel test data.With this issue in mind,the research studies the differences in longitudinal dynamic characteristics between unconstrained free flight and wind tunnel virtual flight,and inno-vatively proposes an online correction test based wind tunnel virtual flight test technique.The lon-gitudinal trajectory and velocity changes of the model are solved online by the aerodynamic forces measured during the test,and then the coupled relationship between aircraft translation and rota-tion is used to correct the model's pitch attitude motion online.For the first time,the problem of solving the data approximation for free flight has been solved,eliminating the difference between the dynamics of wind tunnel virtual flight and free flight,and improving the accuracy of the aero-dynamic derivative identification results.The experiment's findings show that accurate aerodynamic derivatives can be identified based on the online correction test data,and the observed behaviour of the identified motion model has similarities to that of the free flight motion model.     

A methodology for aircraft mission effectiveness evaluation and design space exploration based on virtual operational test

The early involvement of test and evaluation can significantly reduce the cost of modifying issues and errors found in the later stages of aircraft development and design process.This paper presents a methodology for aircraft mission effectiveness evaluation and design space exploration based on Virtual Operational Test (VOT),incorporating Virtual Open Scenario (VOS) and User in Scenarios (UIS) concepts.By employing modeling and simulation technologies in the early stages of aircraft development and design,a virtual environment can be constructed,allowing aircraft users to participate more closely and conveniently in the design process.Virtual tests conducted by users within the mission context provide data on mission effectiveness and critical user feedback.This paper outlines the main components of the virtual operational test process and related conceptual methods,and discusses an open support system framework that supports VOT.The effectiveness and adaptability of the method are demonstrated through two case studies:a beyond-visual-range air combat scenario and a helicopter ground attack scenario.These case studies demonstrate the evaluation of aircraft mission effectiveness and the sensitivity analysis and optimization of design and operational parameters based on VOT.     

Accurate attitude estimation of HB2 standard model based on QNCF in hypersonic wind tunnel test

The accuracy of the HB2 standard model attitude measurement has an important impact on the hypersonic wind tunnel data assessment. The limited size of the model and the existence of external vibrations make it challenging to obtain real-time reliable attitude measurement. To reduce the influence of attitude errors on test results, this paper proposes a Quaternion Nonlinear Complementary Filter(QNCF) attitude determination algorithm based on Microelectromechanical Inertial Measurement Unit(MEMS-IMU). Firstly, the threshold-based PI control strategy is adopted to eliminate noise effect according to the Acceleration Magnitude Detector(AMD). Then, the flexible quaternion method is updated to carry out attitude estimation which is operational and easy to be embedded in the Field Programmable Gate Array(FPGA). Finally, a high-precision three-axis turntable test and a hypersonic wind tunnel test are performed. The results show that the pitchroll attitude errors are within 0.05° and 0.08° in the high-precision three-axis turntable test in a calculation time of 100 s respectively, and the attitude error is within 0.3° after the elastic angle correction in the hypersonic wind tunnel test. The proposed method can provide accurate real-time attitude reference for the analysis of the actual movement of the model, exhibiting certain engineering application value with robustness and simplicity.     

Aviation data networks: security issues and network architecture

The information technology (IT) revolution, combined with people's need to access information quickly, has resulted in the explosive growth of the Internet in the past decade. Ubiquitous access to the Internet has become an essential component of a mobile workforce, and multiple mechanisms are being devised to ensure seamless connectivity to corporate resources. An integrated security framework requires careful consideration of the security features of the network within an airplane. Potentially, the aircraft could consist of three kinds of networks, namely: passenger network, crew network, and control network. The security protocol implemented must ensure a proper separation of these networks and also watch for any security protocol violations. In this paper, the authors review existing aircraft data network standards, security provisioning, and security threats associated with the aircraft data networks. In addition, the authors also analyze the security threats associated with different network architectures.     

Software architecture for building

Test system developers can benefit greatly from a software architecture that allows for easy interchangeability of instruments in those systems. Using open industry standard software architectures such as Virtual Instrument Software Architecture (VISA), and Interchangeable Virtual Instruments (IVI), developers are able to create systems with interchangeable test instrumentation. This paper describes the VISA and IVI software standards and demonstrates how their use within a broader software architecture, which includes standard development environments and flexible test executive software, facilitates the creation of interchangeable test systems     

Empirical virtual sliding target guidance law design: an aerodynamic approach

We present a novel empirical virtual sliding target (VST) guidance law for the midcourse phase of a long range surface-to-air missile that uses the simplicity of the conventional proportional navigation (PN) guidance law while exploiting the aerodynamic characteristics of a missile's flight through the atmosphere to enable the missile to achieve superior performance than that achieved by conventional PN guidance laws. The missile trajectory emulates the trajectory of an optimal control based guidance law formulated on a realistic aerodynamic model of the missile-target engagement. The trajectory of the missile is controlled by controlling the speed of a virtual target that slides towards a predicted intercept point during the midcourse phase. Several sliding schemes, both linear and nonlinear, are proposed and the effect of the variation of the sliding parameters, which control the sliding speed of the virtual target, on the missile performance, are examined through extensive simulations that take into account the atmospheric characteristics as well as limitations on the missile in terms of the energy available and lateral acceleration limits. Launch envelopes for these sliding schemes for approaching and receding targets are also obtained. These results amply demonstrate the superiority of the proposed guidance law over the conventional PN law.     

Engineering in a virtual environment

The authors review virtual environment technology and its application to the aerospace industry. Virtual environment systems have three components: sensors, effectors, and interlinkage hardware and software. Virtual environment tools used by the aerospace industry include the Multi-dimensional, User-oriented, Synthetic Environment (MUSE); Cave Automatic Virtual Environment (CAVE); and Immersadesk. Engineering applications include design and manufacture of aerospace systems, maintenance, and repair.     

Commercial technology & avionics architecture

As commercial technology has become more embedded in the military community, there have been attendant effects caused by the rapid progress in technology and by obsolescence. Industry has generated many solutions to mitigate these effects, but their limitations are emerging with time. This is a discussion of higher-level approaches to obsolescence solutions and technology insertion problems that have not hitherto been addressed.     

IEEE 1394: a growing computer connectivity standard for automatedtest

This paper describes the latest trends in the IEEE 1394 (“firewire^TM” or “iLink^TM”) standards and why it is becoming the connectivity standard of choice for automatic test applications. Why move to IEEE 1394, what are the possible risks with doing so, what are some of the myths associated with IEEE 1394 and a practical example of an automatic test application will all be presented with the prime emphasis on giving the latest information that will help you get IEEE 1394 integrated into your automatic test system     

基于小波分析的虚拟仪器

以小波分析原理为基础,开发出可视化和可操作的虚拟仪器,用于处理实验数据与药物分析.应用小波变换实现数据消噪,利用LabVIEW 和MATLAB软件开发出虚拟仪器.用该仪器可实现对数据进行消噪;在不经分离的情况下,对药物实现多组分的含量测定及对实验结果进行分析和预测,采用的方法和开发的软件在药学领域有其独到的应用价值.     

Communication system architecture for planetary exploration

Future human missions to Mars will require effective communications supporting exploration activities and scientific field data collection. Constraints on cost, size, weight, and power consumption for all communications equipment make optimization of these systems very important. These information and communication systems connect people and systems together into coherent teams performing the difficult and hazardous tasks inherent in planetary exploration. The communication network supporting vehicle telemetry data, mission operations, and scientific collaboration must have excellent reliability and flexibility. We propose hybrid communication architectures consisting of space-based links, a surface-based deployable mid-range communications network and a cluster of short-range links to solve the problems of connectivity and bandwidth, while meeting the other constraints of weight and power. A network of orbiting satellites could cover much of the planet surface, but this space-based capability may not be optimal for cost or performance. Specifically, a minimal space-based capability can be augmented using mobile cellular repeaters deployable by robots and human EVA. This method results in an increase in the number of radio nodes, but the distances separating them is decreased. This results in a significant increase in bandwidth and decrease in radio power, and therefore, node size, complexity, and power consumption. This paper will discuss the results of field testing such hybrid radio systems for the support of scientific surveys. System analysis of design tradeoffs will yield insight into optimal solutions that will be compared to other approaches providing a method of effectively evaluating new candidate architectures