InSight Mars Lander Robotics Instrument Deployment System

The InSight Mars Lander is equipped with an Instrument Deployment System (IDS) and science payload with accompanying auxiliary peripherals mounted on the Lander. The InSight science payload includes a seismometer (SEIS) and Wind and Thermal Shield (WTS), heat flow probe (Heat Flow and Physical Properties Package, HP³) and a precision tracking system (RISE) to measure the size and state of the core, mantle and crust of Mars. The InSight flight system is a close copy of the Mars Phoenix Lander and comprises a Lander, cruise stage, heatshield and backshell. The IDS comprises an Instrument Deployment Arm (IDA), scoop, five finger “claw” grapple, motor controller, arm-mounted Instrument Deployment Camera (IDC), lander-mounted Instrument Context Camera (ICC), and control software. IDS is responsible for the first precision robotic instrument placement and release of SEIS and HP³ on a planetary surface that will enable scientists to perform the first comprehensive surface-based geophysical investigation of Mars’ interior structure. This paper describes the design and operations of the Instrument Deployment Systems (IDS), a critical subsystem of the InSight Mars Lander necessary to achieve the primary scientific goals of the mission including robotic arm geology and physical properties (soil mechanics) investigations at the Landing site. In addition, we present test results of flight IDS Verification and Validation activities including thermal characterization and InSight 2017 Assembly, Test, and Launch Operations (ATLO), Deployment Scenario Test at Lockheed Martin, Denver, where all the flight payloads were successfully deployed with a balloon gravity offload fixture to compensate for Mars to Earth gravity.     

基于FQFD的太阳能无人机设计指标排序方法

为解决太阳能无人机（UAV）总体设计中任务需求表达模糊、技术指标重要度排序决策困难的问题,提出了基于模糊质量功能展开（FQFD）的太阳能无人机总体设计指标排序方法。该方法在传统质量功能展开（QFD）质量屋的基础上,引入三角模糊数,表征任务需求的不确定性和模糊性;在模糊隶属度函数未知的情况下,采用α加权修正水平截集去模糊化方法计算技术指标重要度,获得技术指标重要度排序,为总体设计优化决策提供依据。最后以长航时太阳能无人机的总体设计为例,对任务需求—工程特性—技术指标的两级质量屋模型进行计算分析,得到续航能力、巡航高度、动力系统效率、巡航速度和气动效率是太阳能无人机最重要的5个技术指标的结果。此方法客观性较强,可处理复杂的系统不确定性,为太阳能无人机总体方案设计及决策应用提供参考依据。     

质量功能展开(QFD)方法及其在航空公司质量管理中的应用

在介绍质量功能展开（ＱＦＤ）方法的概念和原理的基础上,紧密结合当前中国民航运输企业质量管理中存在的问题,对这一行之有效的方法在航空公司质量管理中的应用进行了探索性的研究和论述。     

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     

Near-Infrared Mapping Spectrometer experiment on Galileo

The Galileo Near-Infrared Mapping Spectrometer (NIMS) is a combination of imaging and spectroscopic methods. Simultaneous use of these two methods yields a powerful combination, far greater than when used individually. For geological studies of surfaces, it can be used to map morphological features, while simultaneously determining their composition and mineralogy, providing data to investigate the evolution of surface geology. For atmospheres, many of the most interesting phenomena are transitory, with unpredictable locations. With concurrent mapping and spectroscopy, such features can be found and spectroscopically analyzed. In addition, the spatial/compositional aspects of known features can be fully investigated. The NIMS experiment will investigate Jupiter and the Galilean satellites during the two year orbital operation period, commencing December 1995. Prior to that, Galileo will have flown past Venus, the Earth/Moon system (twice), and two asteroids; obtaining scientific measurements for all of these objects.The NIMS instrument covers the spectral range 0.7 to 5.2 , which includes the reflected-sunlight and thermal-radiation regimes for many solar system objects. This spectral region contains diagnostic spectral signatures, arising from molecular vibrational transitions (and some electronic transitions) of both solid and gaseous species. Imaging is performed by a combination of one-dimensional instrument spatial scanning, coupled with orthogonal spacecraft scan-platform motion, yielding two-dimensional images for each of the NIMS wavelengths.The instrument consists of a telescope, with one dimension of spatial scanning, and a diffraction grating spectrometer. Both are passively cooled to low temperatures in order to reduce background photon shot noise. The detectors consist of an array of indium antimonide and silicon photovoltaic diodes, contained within a focal-plane-assembly, and cooled to cryogenic temperatures using a radiative cooler. Spectral and spatial scanning is accomplished by electro-mechanical devices, with motions executed using commandable instrument modes.Particular attention was given to the thermal and contamination aspects of the Galileo spacecraft, both of which could profoundly affect NIMS performance. Various protective measures have been implemented, including shades to protect against thruster firings as well as thermal radiation from the spacecraft.The Near Infrared Mapping Spectrometer (NIMS) Engineering and Science Teams consist of I. Aptaker (Instrument Manager), G. Bailey (Detectors), K. Baines (Science Coordinator), R. Burns (Digital Electronics), R. Carlson (Principal Investigator), E. Carpenter (Structures), K. Curry (Radiative Cooler), G. Danielson (Co-Investigator), T. Encrenaz (Co-Investigator), H. Enmark (Instrument Engineer), F. Fanale (Co-Investigator), M. Gram (Mechanisms), M. Hernandez (NIMS Orbiter Engineering Team), R. Hickok (Support Equipment Software), G. Jenkins (Support Equipment), T. Johnson (Co-Investigator), S. Jones (Optical-Mechanical Assembly), H. Kieffer (Co-Investigator), C. LaBaw (Spacecraft Calibration Targets), R. Lockhart (Instrument Manager), S. Macenka (Optics), J. Mahoney (Instrument Engineer), J. Marino (Instrument Engineer), H. Masursky (Co-Investigator), D. Matson (Co-Investigator), T. McCord (Co-Investigator), K. Mehaffey (Analog Electronics), A. Ocampo (Science Coordinator), G. Root (Instrument System Analysis), R. Salazar (Radiative Cooler and Thermal Design), D. Sevilla (Cover Mechanisms), W. Sleigh (Instrument Engineer), W. Smythe (Co-Investigator and Science Coordinator), L. Soderblom (Co-Investigator), L. Steimle (Optics), R. Steinkraus (Digital Electronics), F. Taylor (Co-Investigator), P. Weissman (Co-Investigator and Science Coordinator), and D. Wilson (Manufacturing Engineer).     

建立与硬件无关通用测试程序的方法

IVI 驱动技术是当今受人推崇的软件控制新技术。文中阐述了 IVI 技术的应用,真正实现了仪器的可互换性.使得工程人员的测试程序可以应用于不同的仪器设备。文中介绍了 IVI驱动机制、使用工具、建立虚拟仪器等方面的相关问题。     

Design of an image radiation monitor for ILS glide slope

The design of a monitor that measures changes in ground reflected image radiation is presented. This monitor is shown to be theoretically capable of determining the effects of snow cover and standing water in the vicinity of an Instrument Landing System (ILS) image-type glide slope, thereby reducing the number and length of outages. A discussion of errors and calibration are presented, along with an example of a practical design     

Atmospheric Science with InSight

In November 2018, for the first time a dedicated geophysical station, the InSight lander, will be deployed on the surface of Mars. Along with the two main geophysical packages, the Seismic Experiment for Interior Structure (SEIS) and the Heat-Flow and Physical Properties Package (HP³), the InSight lander holds a highly sensitive pressure sensor (PS) and the Temperature and Winds for InSight (TWINS) instrument, both of which (along with the InSight FluxGate (IFG) Magnetometer) form the Auxiliary Sensor Payload Suite (APSS). Associated with the RADiometer (RAD) instrument which will measure the surface brightness temperature, and the Instrument Deployment Camera (IDC) which will be used to quantify atmospheric opacity, this will make InSight capable to act as a meteorological station at the surface of Mars. While probing the internal structure of Mars is the primary scientific goal of the mission, atmospheric science remains a key science objective for InSight. InSight has the potential to provide a more continuous and higher-frequency record of pressure, air temperature and winds at the surface of Mars than previous in situ missions. In the paper, key results from multiscale meteorological modeling, from Global Climate Models to Large-Eddy Simulations, are described as a reference for future studies based on the InSight measurements during operations. We summarize the capabilities of InSight for atmospheric observations, from profiling during Entry, Descent and Landing to surface measurements (pressure, temperature, winds, angular momentum), and the plans for how InSight’s sensors will be used during operations, as well as possible synergies with orbital observations. In a dedicated section, we describe the seismic impact of atmospheric phenomena (from the point of view of both “noise” to be decorrelated from the seismic signal and “signal” to provide information on atmospheric processes). We discuss in this framework Planetary Boundary Layer turbulence, with a focus on convective vortices and dust devils, gravity waves (with idealized modeling), and large-scale circulations. Our paper also presents possible new, exploratory, studies with the InSight instrumentation: surface layer scaling and exploration of the Monin-Obukhov model, aeolian surface changes and saltation / lifing studies, and monitoring of secular pressure changes. The InSight mission will be instrumental in broadening the knowledge of the Martian atmosphere, with a unique set of measurements from the surface of Mars.     

配对进近模式分析及研究进展

配对进近模式是在近距平行跑道上运行的,旨在提高仪表气象条件下的进场效率的一种高效进近模 式,该模式的完整流程在国内鲜有阐述。本文重点分析配对进近程序在近距平行跑道上运行时各阶段的流程, 以及配对进近程序的实施对机型、设备以及人员的具体要求;结合目前国内近距平行跑道的运行情况,国际上 对配对进近模式的研究和应用现状,指出我国引进配对进近模式的迫切性以及该模式今后的研究和发展趋势。     

虚拟仪器技术在航空发动机智能检测中的应用

利用NI公司的LabW indows/CVI虚拟仪器作为开发平台,设计了一套适用于某型航空发动机地面试车的智能检测系统。实际检测结果表明:该系统较真实地反映了被测航空发动机的试车参数、工作状态及试车曲线。与传统的检测方法相比,既节省了成本,又提高了检测效率。     

The Electron Beam Instrument (F6) on Freja

The Electron Beam Instrument (F6) onFreja is the first attempt to apply the electron drift technique in a region of large ambient magnetic fields. The paper describes the operational principles, the technical realization, and the difficulties encountered in the derivation of the electric fields.     

质量功能配置软件工具中的模糊处理

在QFD（QualityFunctionDeployment）软件工具系统的开发中,发现在质量功能分解与部署过程中存在着外部概念的不精确性与计算机内部处理的精确性之间的矛盾,或表达定性化与处理定量化之间的矛盾。因此有必要引入有效的表达工具,以实现对上述问题的模糊处理。语言变量是处理QFD过程中模糊性描述、评价的有效工具,并对两种模糊语言变量的定义及实现进行了探讨,比较了它们各自的优缺点。     

便携式粮仓温度巡检仪的研制

本文就便携式粮仓温度巡检仪的组成及工作原理,热敏电阻的线性化及便携式仪表的节电运行方式进行了论述.     

飞机自动进近和自动着陆的分析研究

本文首先概述了当前民航客机的自动导航、进近、着陆的全过程。随着重点分析了波音737飞机利用SP-77自动飞行控制系统与仪表着陆系然的航向信标仪和下滑仪及机载无线电高度表等设备实现向跑道自动进近和自动着陆的工作过程,并系统介绍了在实现上述过程中,SP-77自动飞行控制系统的自动驾驶仪横滚通道和俯仰通道控制逻辑的建立,系统工作电路的转换,系统的控制规律和工作特点。     

Demonstration of MLS advanced approach techniques

Instrument approach designs and flight-test results using the microwave landing system (MLS) are presented. A general-aviation aircraft was flown on linear computed centerline and curved approach paths with MLS guidance displayed on basic course-deviation indicator and horizontal situation indicator instruments. Approach performance was documented using a ground tracker system, recording three-dimensional position information. These tests demonstrated the flyability of such advanced paths with basic cockpit instrumentation     

Specifying an IVI class for digital test instrumentation

This paper presents an overview of work being done by Teradyne in conjunction with the IVI Foundation to specify an IVI class for digital instrumentation. The Interchangeable Virtual Instruments (IVI) Foundation was formed in August 1997 to define standard specifications for programming common test instrument capabilities. The paper will present the major architectural aspects of digital test instrumentation and how those features can be grouped into classes for the purpose of writing an instrument independent driver. Topics discussed will include derivation of capability classes, class extensions, simulation, and range checking. Examples of how the IVI digital class would apply to the Teradyne M9-Series Digital Test Instrument will be included. Conclusions will summarize the unique attributes of digital test instrumentation, the benefits which can be achieved through standardization, and the tradeoffs associated with utilizing class extensions     

C─8587A型多参数表面粗糙度测量仪参数运算软件分析

介绍了C-8587A型多参数表面粗糙度测量仪各项参数的定义、测量、数学模型、流程控制、功能特点，用单片机实现仪器的各项功能，利用宏汇编语言的编程技巧得以实现，表现了仪器的优越性。     

The Characterisation of Titan's Atmospheric Physical Properties by the Huygens Atmospheric Structure Instrument (Hasi)

The Huygens Atmospheric Structure Instrument (HASI) is a multi-sensor package which has been designed to measure the physical quantities characterising the atmosphere of Titan during the Huygens probe descent on Titan and at the surface. HASI sensors are devoted to the study of Titan's atmospheric structure and electric properties, and to provide information on its surface, whether solid or liquid. This revised version was published online in August 2006 with corrections to the Cover Date.     

Comments on “Effect of wet snow an the null-reference ILSsystem”

The subject paper (July 1993) has raised some issues regarding the probability of the Instrument Landing System (ILS) radiating out-of-tolerance vertical guidance signals. An independent study has substantiated the findings of that paper and adds further concern regarding some FAA ILS snow procedures. The principal conclusions of this paper are: 1) an analysis, based on Walton's discovery of rare snow conditions that cause the null-reference ILS antenna image to disappear, indicates that these conditions can cause out-of-tolerance guidance signals, 2) operation without a monitor of the image radiation can result in signal-in-space guidance signal errors that are significantly beyond the intended limit values, and 3) the integrity of image glide path equipment in snow environments does not satisfy the ILS integrity requirements