Built-in test maturation concepts using test program set andrelational database technologies

Continual improvement of avionic built-in test (BIT) is critical to mission readiness and capability. This paper discusses how test program set (TPS) and relational database (RDB) technologies can be used for this purpose. Important aspects for continually improving avionic BIT and TPS operation are discussed     

充气式再入飞行器柔性热防护系统的发展状况

讨论了充气式再入飞行器对柔性热防护系统的具体要求，归纳了柔性热防护系统设计的一般准则。概述了柔性热防护系统在充气式再入飞行器中的应用现状，并指出在多层隔热毡(MLI)外表敷设耐高温涂层是柔性热防护系统的理想方案。介绍了柔性热防护系统的材料技术，指出轻质、柔性和耐高温是柔性热防护材料的主要特征，并建议在充气式再入飞行器的总体设计过程中采用Nextel312作为主要候选材料来完成相应的热防护设计。     

重复使用金属热防护系统研究进展

综述了金属热防护系统的国外研究最新进展,重点介绍了国内相关研究和试验的最新情况.指出金属热防护系统仍是下一代重复使用运载器大面积表面热防护系统的优选方案之一.     

民用飞机涡扇发动机短舱TPS低速构型数值模拟

TPS(Turbofan Propulsion Simulator)本身的失速特性对于运输类飞机低速带动力风洞试验有着重要的影响,而当代大量的低速带动力试验均采用TPS来模拟涡扇发动机的喷流效应。通过对TPS初始构型和修形后两个构型的数值模拟,研究了TPS唇口下垂位置和头部半径对失速特性的影响。结果表明,TPS唇口处较高的负压峰值和较大的逆压梯度引起TPS构型本身的大面积分离;将TPS唇口下垂和增大唇口头部半径能够有效降低TPS唇口处的负压峰值和逆压梯度,明显改善TPS构型的失速特性。     

Sustainment of legacy automatic test systems: lessons learned on TPS transportability

Sustainment of legacy automatic test systems (ATS) saves cost through the re-use of software and hardware. The ATS consists of the automatic test equipment (ATE), the test program sets (TPSs), and associated software. The associated software includes the architecture the TPSs run on, known as the control software or test station test executive. In some cases, to sustain the legacy ATS, it is more practical to develop a replacement ATE with the latest instrumentation, often in the form of commercial off-the-shelf (COTS) hardware and software. The existing TPSs, including their hardware and test programs, then need to be transported, or translated, to the new test station. In order to understand how to sustain a legacy ATS by translating TPSs, one must realize the full architecture of the legacy ATS to be replaced. It must be understood that TPS transportability does not only include translating the original TPS from an existing language (such as ATLAS) to a new language (such as "C") to run on a new test station, but includes transporting the run-time environment created by the legacy ATS. This paper examines the similarities and differences of legacy ATE and modern COTS ATE architectures, how the ATS testing philosophy impacts the ease of TPS transportability from legacy ATE to modern-day platforms, and what SEI has done to address the issues that arise out of TPS transportability.     

Smart test program set (TPS)

The Boeing Company has several research and development efforts focused on improving interoperability of the test station with other external systems as well as the interoperability within the test station itself. This includes integrating UUT data, test set-up, test execution, test results, repair and replace actions with other systems to provide a "closed-loop" system. One example of the "closed-loop" system is a non-intrusive tool referred to as Smart TPS (Test Program Set). Smart TPS will provide informational services to the user that reduce diagnostic test times and provide an ordered list of replacement actions based on historical data. Where possible, data are exchanged via the automatic test markup language (ATML).     

Bridging the gap between ATLAS and C: an open-systems approach toTPS re-host

As the DoD focuses on commercialization and open-architecture standards, the need to migrate existing TPSs from proprietary ATLAS-based platforms to an Open Systems platform becomes more critical. This paper will focus on a solution which leverages COTS software tools and emerging industry standards and technologies to implement object-oriented database tools which enable the conversion of an ATLAS TPS to an ANSI C environment     

有翼再入飞行器气动外形集成设计优化

气动外形设计是有翼再入飞行器（RV-W）的关键技术之一。分析了气动参数对再入飞行性能的影响,探讨了有翼再入飞行器气动外形设计的规律和准则。基于上述设计准则,以类X-37B飞行器为研究对象,集成几何参数化建模、气动力、气动热、热防护等学科快速分析方法,采用多学科设计优化方法,以最优气动特性为目标对飞行器气动外形进行了优化;得到优化气动外形后,对飞行器热防护系统（TPS）进行了轻量化设计优化。结果表明,优化外形的气动特性相比初始外形得到了较大的提升,设计优化得到的热防护系统重量占比（8.7%）优于同类飞行器的热防护系统重量占比统计数据,说明了本文有翼再入飞行器气动外形集成设计优化方法的有效性,可为同类飞行器提供参考。     

Proposal to TPS delivery in 4 months?

Decreasing the often lengthy Test Program Set (TPS) development time is a high priority for both DoD and commercial industry. A protracted test development time for a commercial product can make or break its success. It can impact time-to-market goals for a product, which in turn, can result in a loss of market share. Though the DoD world has different objectives, they, too, are concerned with long test development times which can increase costs and jeopardize a weapon system's mission readiness. The case study for this paper is a test system developed by BAE Systems in less than four months to meet a commercial customer's stringent schedule requirements. The factors that contributed to the success of this project are examined, as is their relevance to the DoD world. The desire is to apply relevant lessons learned from the commercial industry to DoD programs, yielding a decrease in TPS development time     

8米×6米风洞TPS反推力试验技术

TPS(涡扇动力模拟器)试验技术是风洞中模拟发动机反推力状态最有效的手段.开展反推力试验的目的是获得反推力发动机对飞机气动特性的影响,确定反推力发动机的再吸入速度边界.为满足我国大飞机研制的试验技术需求,中国空气动力研究与发展中心在8米×6米风洞发展了全模TPS反推力试验技术.自主研制了TPS反推力试验专用的高精度六分量杆式应变天平、大流量空气桥和流量控制单元、TPS监视报警系统、数据采集系统、综合显示系统等TPS反推力试验系统,制定了试验模拟准则、试验流程和试验方法,建立了完善的全模TPS反推力试验技术.利用TPS反推力试验技术,开展了国内首期全模TPS反推力风洞试验,研究了某型飞机反推力发动机的再吸入特性,获得了反推力发动机的再吸入速度边界.     

Rehosting legacy test program sets from military ATE

This paper describes some of the key issues developers must address in a test program set (TPS) rehosting plan. Examples and success stories are used to describe the translation of three legacy test program sets onto modern board test equipment, thereby extending the useful life of fielded systems and preserving the considerable investment made in developing the TPSs     

金属热防护系统设计的有限元分析

对可重复使用运载飞行器金属热防护系统进行了有限元分析,计算发现超耐热合金防热结构中下层蜂窝夹芯板的存在会增加结构的质量,但是并不会提高绝热性能,因此改进型防热系统取代了超耐热合金防热系统。比较分析了板间缝隙宽度和辐射率对防热结构底部最大温度的影响,表明减小板间缝隙是消除缝隙辐射的最好办法。分析了模拟条件对热防护系统尺寸设计的影响:初始温度为0℃时比为40℃时最大可以减少17%的厚度和7.7%的质量;考虑热损失厚度最小可以降低26%,质量最小可以降低7%。     

飞行器典型热密封结构

对航天飞机、X-38和X-51等飞行器的热密封结构进行了综合评述.分析了机身TPS、机身开口部位及控制面三个安装部位的热密封结构特点,综述了其热密封组件的研究历程和使用现状.     

Development of a TPS reuse library using COTS tools

In the past, functional test requirements (FTR) or test requirement documents (TRD) and test program sets (TPS) were standalone items developed by individual engineers. In some cases, one engineer would write the FTR/TRD and another would develop the TPS. Commercial ATLAS FTRs are prepared in ARINC 616 and 626 ATLAS. Military TRDs are written in IEEE ATLAS 716 versions. Previous test reuse attempts have not been successful because additional software, like browsers, is required to support these efforts. It was difficult to justify writing new software; for example, browsers to manage the application software. Today, commercial-off-the-shelf (COTS) tools are in place to browse and view information from circuit diagrams to documents to source code. These tools can develop hierarchies to organize the information. These COTS tools are available throughout Boeing on many types of workstations and personal computers on every engineer's desk. This paper discusses how a reusable test library (RTL) is being developed using commercial-off-the-shelf (COTS) tools, such as Mosaic, to address commercial and military test applications. It describes each of the tools and the process to develop TPSs using the reuse library. It defines the metrics and benefits achieved     

发动机动力模拟风洞试验中的空气桥技术

介绍了发动机动力模拟风洞试验中的空气桥设计技术和影响修正方法.通过自由度分析,选择了合理空气桥布局,采用有限元方法对空气桥关键受力梁进行了优化,建立了空气桥天平一体化数值模拟技术,使得空气桥和天平刚度更加匹配.通过这些设计及优化使得空气桥的作用力最小,并具有较强的克服压力影响、温度影响的能力.通过试验建立了空气桥附加刚度影响、内部压力影响、温度影响和内部流量影响的修正方法,进一步减小了空气桥对天平的影响.在8m×6m低速风洞进行了某大展弦比飞机全模涡扇动力模拟器(TPS)短舱动力模拟试验.试验结果重复性好,阻力系数精度达到0.0003,和相关文献吻合.这表明空气桥技术是成功的,满足了TPS短舱动力模拟试验要求.      

金属热防护系统材料与结构研究进展

简要综述了金属热防护系统的国外研究进展，重点介绍了美国高温合金热防护系统材料与结构以及钛合金热防护材料与结构的研究概况，并对国内情况作了一些简介。指出金属热防护系统是下一代重复使用运载器大面积表面热防护的第一方案。     

自动测试系统通用性的实现技术

文章分析了与开发通用ATS密切相关的标准/规范,从软、硬件两方面讨论了ATS通用性的实现途径,包括硬件配置及接口技术、IVI技术以及面向信号方法。ATS通用性的实现可以实现被测对象的跨平台测试以及测试程序的可移植,能带来显著的军事及经济效益。     

凹腔尺寸对迎风凹腔与逆向喷流组合热防护系统性能的影响

针对高超声速飞行器热防护系统(TPS)的设计,对迎风凹腔与逆向喷流组合热防护系统展开研究.在数值方法实验验证的基础上,通过求解Navier-Stokes方程得到了带组合热防护系统的鼻锥的流场结构以及壁面热流分布.验证了组合热防护系统的有效性.在逆向喷流条件不变的情况下,进一步研究了凹腔的尺寸变化对其防热能力的影响.研究发现:凹腔的直径越小,深度越深,气动加热值越低.自由来流与逆向喷流形成的回流区在减少鼻锥的气动加热上起到关键的作用.相对于凹腔深度的变化,鼻锥壁面的气动加热更敏感于凹腔直径的变化.      

美国金属热防护系统研究进展

简述了美国为可重复使用运载器研制的金属热防护系统的研究现状及其发展趋势。详细介绍了金属热防护系统的结构组成及其分析设计和测试。金属热防护系统与传统热防护系统相比，防热层和承力结构一体化，无需气动外壳，可以减轻系统质量，防热面板容易安装和拆卸，可以大大节省维护时间和成本，适合可重复使用运载器降低成本、提高可靠性的要求。     

Using built-in-test to reduce TPS run times and improve TPSreliability

This paper addresses using information derived from Built-in-Test (BIT) to fault diagnose Units Under Test (UUTs), wherever possible. This philosophic approach to diagnostic testing is not new. It has been studied over the past 20 years under the visor of “Integrated Diagnostics”, but it has yet to be truly implemented in a “real life” military diagnostic test environment. The mindset of Test Program Set design engineering, along with customer and contractor management alike, remains “complete diagnostic testing based upon single catastrophic component failure modes”. If we are to generate cost efficient Test Program Sets (TPSs) under reduced military budget constraints, this will have to change! The test engineer must be encouraged to use methodologies to speed up development time and decrease TPS run times. Using present technology, this is possible now, and as the technology matures, will become a truly viable approach in the future. For the purpose of this paper, the author relies heavily on his extensive US Navy Automatic Test Equipment (ATE) and Test Program Set (TPS) experience, as well as on previous studies performed on using BIT to fault diagnose Unit Under Test failures on US Naval Air weapon systems