L'avion,plateforme d'observations scientifiques

Transition between high altitude manned observatories and unmanned balloon-borne or rocket-borne experiments is achieved with high flying aircrafts, at altitudes above tropopause (>12 km), which became readily available, at reasonable cost and reliability, in the past five or ten years.This paper reviews the development of scientific uses of aircrafts, especially for astronomy and geophysics, with some emphasis placed on infrared problems, closely related to the scale height of the chief infrared absorber, i.e. telluric water vapor.Absorbers distribution vs altitude and spectral characteristics are summarized (Figures 1, 2, 3).Capabilities of various available aircrafts are compared (Table I) and the various ways to consider modifications are discussed: structural modifications or design problems to fit telescopes or light collectors on board. Tables II and III list the advantages of airborne observations, compared to other spatial carriers, and also the specific problems connected with aircrafts. Adopted solutions to these problems are exposed (Figures 4, 5, 6, 7) and costs are briefly discussed.Finally, a few examples of scientific results, gathered in the few past years from aircraft, are given, both in astronomy and in geophysics.     

Variation of Polar Coronal Hole Profiles with Solar Cycle

We compared the H I Lyα polar coronal hole profiles obtained during the three Spartan 201 flights (in 1993, 1994, and 1995) and during the more recent UVCS/SOHO mission. We found that at 2.1 R_⊙ there are no significant variations of the line shape over the several years of the descending phase of the solar cycle. However, there may be some evidence for the 1.8 R_⊙ profiles being broader towards solar minimum. The profiles at 2.1 R_⊙ are different from profiles obtained at 1.8 R_⊙; they have clearly narrower cores and wide wings. We fitted the profiles with single and/or multiple Gaussian functions and calculated their typical 1/e half widths. This revised version was published online in June 2006 with corrections to the Cover Date.     

建模与仿真的校核、验证和确认工作模式

根据当前国内外研究进展状况,对建模与仿真的校核,验证和确认技术进行了讨论。首先介绍了ＶＶ＆Ａ的概念以及应用于建模与仿真过程的意义。然后着重阐述了建模与仿真的ＶＶ＆Ａ的一般工作模式和其中应当考虑的问题,最后进一步介绍了分布交互仿真的ＶＶ＆Ａ的九个步骤,这九个步骤也可推广适用于其它建模与仿真。     

Motor drive technologies for the Power-By-Wire (PBW) program:options, trends and tradeoffs. II. Power electronic converters anddevices

For pt. I see ibid., vol. 10, pp. 37-41 (1995). This is the second of two papers on the motor drive technology options for the Power-By-Wire (PBW). The organization of this paper is based on the four components of the electrical actuator (EA) system and the options available to suit the PBW program as given in the PBW studies. The first paper discussed the options available for the motor and the controller parts of a drive. This paper discusses the power electronic converter and device options. The power converter options are divided into hard-, snubbered- and soft-switching converters. The power device options are the MOSFET, the Insulated Gate Transistor (IGT), the gate turn-off thyristor (GTO) and the MOS Controlled Thyristor (MCT)     

The Local Bubble and Interstellar Material Near the Sun

The properties of interstellar matter at the Sun are regulated by our location with respect to a void in the local matter distribution, known as the Local Bubble. The Local Bubble (LB) is bounded by associations of massive stars and fossil supernovae that have disrupted dense interstellar matter (ISM), driving low density intermediate velocity ISM into the void. The Sun appears to be located in one of these flows of low density material. This nearby interstellar matter, dubbed the Local Fluff, has a bulk velocity of ∼19 km s⁻¹ in the local standard of rest. The flow is coming from the direction of the gas and dust ring formed where the Loop I supernova remnant merges into the LB. Optical polarization data suggest that the local interstellar magnetic field lines are draped over the heliosphere. A longstanding discrepancy between the high thermal pressure of plasma filling the LB and low thermal pressures in the embedded Local Fluff cloudlets is partially mitigated when the ram pressure component parallel to the cloudlet flow direction is included.     

空心气冷低压涡轮动叶气热耦合数值模拟

以空心气冷低压涡轮动叶为研究对象,采用高质量的流体域和固体域网格控制技术,带转捩模型的双方程SST湍流模型,开展了基于CFD方法的叶片气热耦合问题研究。获得了不同冷气流量比(分别为1.0%,1.38%,1.8%和2.2%)、温比(分别为2.1,2.25,2.3,2.4和2.5)和压比(分别为1.4,1.6和1.8)对叶片换热特性的影响规律,设计状态中截面按弧长平均的叶片壁面金属温度计算值较试验值偏小0.3%,气热耦合计算的叶片壁面温度分布与试验结果吻合良好,验证了气热强耦合计算方法的精度,为涡轮叶片温度场分析提供了一种有效的方法。     

Testing for Year 2000 readiness: technical and management issues

The approach of the Year 2000 (Y2K) has called into question the condition of readiness of computer systems upon which organizations depend. Will these systems operate reliably after midnight, January 1, 2000, or will problems associated with date calculations cause failures that adversely affect users? This question has caused organizations to identify their critical systems, test these systems for Y2K problems, and take corrective action where necessary to ensure Y2K readiness. This paper examines various technical and management issues that Southwest Research Institute has dealt with in solving these problems     

A Family of SHF Tactical Satellite Communication Ground Terminals

On February 8, 1969, an experimental tactical communications satellite, TACSAT I, was successfully placed in synchronous orbit at the equator off the coast of South America. This paper concerns itself with a family of SHF tactical satellite communications ground terminals utilizing the SHF capability of that satellite. The material presented provides the system concepts necessary for the understanding of the ground terminals, their relationship to the satellite, and some insight into the design problems encountered during the development of a family of five types of terminals. The system concepts are presented in terms of communication modes, frequency assignments, and implementation of the respective modes. The beacon system for frequency control and signal acquisiticn siticn is described along with the factors involved in design of equipment implementing the analog FM, the alert message, frequency hopping, and, differential phase-shift keyed (DPSK) modes. The final configurations of each of the five terminals are described and illustrated through photographs and generalized block diagrams, and the capability of each is briefly outlined.     

Software testing: from theory to practice

This paper is about the disparity between what is known and what is being learned in academia and what is being used in industry. The author believes there are many reasons. Some of these represent accidental and some essential problems. Most are part of a general issue of quality in the software products. Most problems that make it more difficult to apply testing techniques are part of a larger problem which make them more cost-effective to produce high quality software. The author presents a list of reasons industry does not use the highly advanced, and in some cases, highly developed software testing techniques that are available. The problems are divided into three broad categories: problems in industry; problems in academic research and education; and problems in the interface between the two     

Aging avionics: the problems and the challenges

Aging avionics have become a problem because aircraft are being kept in service far longer than the original plan. This paper discusses the four key problems of aging avionics: (1) determining the systems that are the high cost drivers in order to select those that should receive priority; (2) determining the requirements for the replacement; (3) identifying alternative technologies that will satisfy the requirements and are affordable; and (4) determining the funding required and acquiring the funding needed to replace the aging avionics. Challenges encountered in solving these problems include management and technical. The problem of aging avionics is not limited to a single aircraft, but occurs across all aircraft. Cost-effective modernization requires cutting horizontally across all aging aircraft, and coordination with the end users and the existing management structure. A key technical challenge is to select an architecture that is upgradeable since the funding limitations may ensure parts will become obsolete prior to the completion of a drawn-out production.     

Magnetosphere–Ionosphere Convection as a Compound System

Convection is the most fundamental process in understanding the structure of geospace and disturbances observed in the magnetosphere–ionosphere (M–I) system. In this paper, a self-consistent configuration of the global convection system is considered under the real topology as a compound system. Investigations are made based on the M–I coupling scheme by analyzing numerical results obtained from magnetohydrodynamic (MHD) simulations which guarantee the self-consistency in the whole system under the Bv (magnetic field and velocity) paradigm. It is emphasized in the M–I coupling scheme that convection and field-aligned current (FAC) are different aspects of same physical process characterizing the open magnetosphere. Special attention is given in this paper to the energy supplying (dynamo) process that drives the FAC system. In the convection system, the dynamo must be constructed from shear motion together with plasma population regimes to steadily drive the convection. Convection patterns observed in the ionosphere are also the manifestation of achievement in global self-consistency. A primary approach to apply these concepts to the study of geospace is to consider how the M–I system adjusts the relative motion between the compressible magnetosphere and the incompressible ionosphere when responding to given solar-wind conditions. The above principle is also applicable for the study of disturbance phenomena such as the substorm as well as for the study of apparently unique processes such as the flux transfer event (FTE), the sudden commencement (SC), and the theta aurora. Finally, an attempt is made to understand the substorm as the extension of enhanced convection under the southward interplanetary magnetic field (IMF) condition.     

Cost-equivalencing discretization of a class of bang-bang guidance laws

Bang-bang guidance laws are encountered in several situations like in the saddle-point solution of some continuous-time pursuit-evasion games, and in the solution of time-optimal control problems. For the purpose of digital implementation, these continuous-time bang-bang control laws must be converted into digital control laws. The paper presents a novel technique for optimal digital implementation of a class of bang-bang control laws in linear systems. This technique delivers a discretization of the continuous-time laws and is shown: 1) to achieve the same cost as the optimal sample and hold (SH) approximation of the continuous-time laws, and 2) to be implementable (the optimal SH approximation is not). The cost-equivalencing technique is applied to the digital implementation of the continuous-time DGL/0, DGL/1, and DGL/C game theoretic guidance laws.     

An Overview of the Instrument Suite for the Deep Impact Mission

A suite of three optical instruments has been developed to observe Comet 9P/Tempel 1, the impact of a dedicated impactor spacecraft, and the resulting crater formation for the Deep Impact mission. The high-resolution instrument (HRI) consists of an f/35 telescope with 10.5 m focal length, and a combined filtered CCD camera and IR spectrometer. The medium-resolution instrument (MRI) consists of an f/17.5 telescope with a 2.1 m focal length feeding a filtered CCD camera. The HRI and MRI are mounted on an instrument platform on the flyby spacecraft, along with the spacecraft star trackers and inertial reference unit. The third instrument is a simple unfiltered CCD camera with the same telescope as MRI, mounted within the impactor spacecraft. All three instruments use a Fairchild split-frame-transfer CCD with 1,024× 1,024 active pixels. The IR spectrometer is a two-prism (CaF₂ and ZnSe) imaging spectrometer imaged on a Rockwell HAWAII-1R HgCdTe MWIR array. The CCDs and IR FPA are read out and digitized to 14 bits by a set of dedicated instrument electronics, one set per instrument. Each electronics box is controlled by a radiation-hard TSC695F microprocessor. Software running on the microprocessor executes imaging commands from a sequence engine on the spacecraft. Commands and telemetry are transmitted via a MIL-STD-1553 interface, while image data are transmitted to the spacecraft via a low-voltage differential signaling (LVDS) interface standard. The instruments are used as the science instruments and are used for the optical navigation of both spacecraft. This paper presents an overview of the instrument suite designs, functionality, calibration and operational considerations.     

The design of a nuclear power supply with a 50 year lifeexpectancy: the JPL Voyager's SiGe MHW RTG

Between 25 and 30 years ago, the IECEC Proceedings carried a series of papers by the present authors and other members of a JPL team on the problems and the desirable design features associated with the MHW RTGs to be used to power JPL's Voyager I and II spacecraft. The Voyager I and II spacecraft successfully completed their original 12 year missions 10 years ago and are at distances of over 55 AU and 70 AU from the sun. The power systems worked almost precisely as predicted. The Voyager spacecraft seem to have several decades of life left to make measurements outside the solar system. This paper gives a technical overview of the design process and problems     

Ni-7.3%Si-2.2%B合金快淬组织与深过冷快凝机制

 采用B_2O_3玻璃和纯循环过热净化相结合的方法去除液态金属中的异质晶核,使液态Ni-7.3％Si-2.2％B合金获得了330K的过冷度。对比分析了该合金在低温基板上的快淬薄片与大体积深过冷试样的微观组织。借助计算机和红外测温系统,快速采集了熔体的再辉过程。数据处理发现,在深过冷液态金属的整个再辉区间,温度的上升速率呈瞬态变化特征,再辉时间随初始过冷度的提高而减小。最后,由再辉曲线确定出深过冷液态金属再辉过程中的固相分数与时间以及凝固速度与瞬时过冷度的关系。     

Extensions and critique of minimum-relative-entropy spectralestimation

Insight is provided into minimum-relative-entropy spectral estimation (MRESE), which has proved very successful in some applications. There are, however, shortcoming inherent in MRESE as it has so far developed; e.g. it would be desirable to incorporated objective, absolute (rather than subjective, relative) weighting for prior estimates. Such problems are pointed out, and solutions are offered for some of them. A few of these problems are common to MRESE and minimum-entropy spectral estimation. The unsolved problems are offered as topics for further research     

Detection Performance of Soft-Limited Phase-Coded Signals

General analytic expressions are developed for the soft-limited digital pulse compressor (matched filter). This theoretical development is then used for the hardware realization of a two-channel (I,Q), 3-bit-limited digital pulse compressor with a compression ratio of 255: 1. The realized hardware uses state of the art integrated circuit devices. An experimental laboratory setup is described. This setup is used to study hard-limited versus 3-bit-limited matched-filter performance characteristics with the data in the following areas: 1) constant false alarm rate (CFAR) characteristics as a function of threshold settings and noise levels; 2) single target detection characteristics as a function of input signal-to-noise ratio (SNR); and 3) two target performance characteristics: a) the amplitude of a weaker target as a function of target ratio and target overlap; and b) the detection characteristics of a weaker target as a function of weaker target SNR, strong target SNR, and target overlap.     

Impact of receiver inter-frequency bias residual uncertainty on dual-frequency GBAS integrity

Dual-Frequency Ground-Based Augmentation Systems(GBAS) can be affected by receiver Inter-Frequency Bias(IFB) when Ionosphere-Free(Ifree) smoothing is applied. In the framework of the proposed GBAS Approach Service Type F(GAST-F), the IFB in the Ifree smoothed pseudorange can be corrected. However, IFB residual uncertainty still exists, which may threaten the integrity of the system. This paper presents an improved algorithm for the airborne protection level considering the residual uncertainty o...     

JBYQC软件设计关键问题

 <正> 1.问题的提出 JBYQC是卫星壳体结构优化设计人机交互式软件。软件适用机型为IBM-PC/AT或XT型微机,操作系统为DOS Version 3.00,该软件很适合在设计室中使用,并极易推广。 JBYQC是商品软件,对结构优化设计来讲,图文并茂的交互式屏幕是必须的,因此,交互式屏幕怎样设计,就成了第一个关键问题。