?AL Proyecto Azimut?La Industria Aeronáutica en el ámbito de la Comunidad Económica de América Latina ?AL Azimuth Project?Aeronautical Industry for the Latin-American Conmmon Market

The purpose of this paper is to promote the establishment of standards and basic requirements to direct development of preliminary orientational studies for the organic and financial structure, in the incipient period, of a Latin-American Aeronautical Industry, which is urgently needed to be incorporated into the integration plans of the Latin-American Common Market. Immediate action is recommended in view of statistical data analyzed for Mexican import and export values, for aircraft and its spare parts, that give $122 091 000 (U. S. currency) in the period from 1957 to 1964, with an average value of $6.55 per pound. Indices are also given for modern flight equipment in the range of $40 to $60 per pound, with a tendency to increase to the range of $80 to $90 per pound in the next five years.     

The Confederation of European Aerospace Societies — CEAS supporting people in aerospace

The aerospace societies of 8 European countries — France, Germany, Italy, The Netherlands, Spain, Sweden, Switzerland and The United Kingdom - ten years ago formed a Confederation to help member societies and their 25 000 individual members through collaborative efforts: ‘Confederation of European Aerospace Societies’ - CEAS. What is its history? What are its objectives? What is its present status and perspectives for the future? At the time of European mergers in aerospace industry, is the CEAS an opportunity for Europe?     

Investment Costs of Terrestrial Long-Haul Telecommunication Facilities

The investment costs of long-haul, modern, radio relay and coaxialcable systems, as determined from data submitted to the Federal Communications Commission, are presented. Formulas to determine costs per voice-circuit-mile, and per television-channel-mile, are developed. The specific facilities investigated are the TD-2, TD-3, and TH radio relay systems, and the L-3 12-tube and L-4 20-tube coaxial cable systems. The radio relay systems are significantly, with one exception, less expensive than coaxial cable systems over their design capacity ranges. The L-4 20-tube coaxial cable system (32 400 voice circuits) and the TD-3 radio relaysystem (12 000 voice circuits) have approximately equal investment costs per voice-circuit-mile ($3.40) at full capacity.     

An Ultrahigh Speed CAMAC Interface for a Large Flight Simulator System

The real-time simulation subsystem (RTSS) at the NASA Langley Research Center in Hampton, VA, consists of several CDC CYBER computers and over 20 flight simulation sites. This simulation network is used by the Langley Center to advance the state of aeronautics and to improve air safety. The current simulator interface system at NASA-Langley was installed in 1968 and uses centrally located analog and discrete conversion equipment. Of the alternatives studied by NASA for a replacement RTSS, only the network and input/output (I/O) system conforming to the international computer automated measurement and control (CAMAC) standards meets their requirements. The CAMAC serial highway provides a distributed I/O system with an extremely high data throughput approaching 24 000 000 information bits/per second. Fiber-optic links transmit the data over paths to 1 km. For multisite simulations, a computer-controlled electronic switch configures site highways in any combination. The CAMAC system uses analog-to-digital converters (ADCs), digital-to-analog converters (DACs), and synchro converters with 16 bits of resolution to give the needed system performance. The time to acquire data from 80 16-bit ADCs and 960 discrete inputs and transfer them to the CYBER central memory is less than 320 ?s. Similarly, the time from CYBER central memory to the setting of 256 16-bit DACs and 960 discrete outputs is less than 650 ?s.     

Dust in and Around the Heliosphere and Astrospheres

Space Science Reviews - The ESA Swarm mission, launched on 22 November 2013, consists of three spacecraft each equipped with a Micro Advanced Stellar Compass ( $\mu $ ASC) from the Technical...     

Managing change through roadmapping [changes in aviation electronics]

Presently the USAF is operating with 90 different Model Design Series (MDS) aircraft. The 90 MDS aircraft make up a total of 5778 airframes, each with a different number of Line Replaceable Units (LRUs) which make up the avionics systems. Some of the MDSs have as few as 53 avionics LRUs while others as many as 495. The total dollar value of the USAF aircraft avionics LRUs is approximately $42.4B and $30.68B in spares. Depot repairable cost to maintain these components each year is approximately $1.2B. Each MDS is assigned specific missions and the avionics systems are developed to support those missions. Due to the evolution of mission types and user needs, change is constant for the avionics manager.     

高速频繁起停球轴承设计与试验

为解决涡轮起动机用轴承在高速、频繁起停工况下易失效的问题,结合轴承设计准则,进行涡轮起动机用轴承结构参数设计和材料选取。基于轴承动力学理论,建立了动力学模型并进行了仿真分析,研究高速、频繁起停工况下的轴承动力学行为。在自主研发的试验机上进行轴承试验,试验过程中监测轴承温升及振动加速度值,轴承频繁起停、最高转速达12 000 r/min时,试验轴承温度低于130 ℃,振动加速度低于3.0g,试验后轴承无异常,验证了轴承设计和材料选取合理。通过优化设计和试验验证结果表明:轴承转速可达12 000 r/min,起动时间仅需60 s,停止时间仅需40 s,轴承能够完成连续频繁起停3 000次以上。      

Analysis of Warning Times For Collision Avoidance Systems

The time required to execute a successful escape maneuver must be deduced from considerations of the following times: time required to gain adequate altitude separation, delay time due to pilot reaction, aircraft servo-system delay, delay due to missed data, delay due to data arrival time, alarm delay due to ? errors, time to stop turning, and time to level off. Since each of these times is a random variable, the required escape time must be determined in a probabilistic sense. By assigning appropriate probability density functions to each of the times involved, formulas are derived for the escape times required by the CAS hazard logic. The results of a simulation of 10 000 aircraft encounters verify the suitability of the formulas.     

The International Space Station: a question of federal funding andpolicy implications

A summary form is given of the author's full paper (ibid. vol. 33, p. 7, 1998). The ISS program is a huge investment by the U.S. government. It is estimated by NASA that the program will cost the American public more than $70 billion over a period of 30 years. Since the scientific impact of this program is relatively unknown (and uncertain), the question that policy makers will have to struggle with is whether the federal government should continue to fund the program, or to pull out from the program altogether, thus saving American taxpayers close to $30 billion. Although funding is a major concern, since the inclusion of Russia in the program, the ISS has also become a foreign policy tool. Therefore, additional questions about policy implications of the ISS program need to be addressed     

Projectile Detection of Luminous and Nonluminous Bodies

In a large hyperballistics range, detection of projectiles atstations becomes more complex. Range length permits variation of projectile luminosity and requires greater area for detection. A technique has been devised, using electrooptics, triggering instrumented stations with luminous or nonluminous projectiles. The phototube circuit response, effect of velocity, and effect of light screen thickness on performance are discussed. Data on performance are presented for velocities of 10 000 to 21 000 feet per second. Performance is predicted for velocities of 40 000 and 60 000 feet per second. Nonluminous models as small as 3/16-inch diameter spheres have been detected at a velocity of 21 000 feet per second.     

For aerospace programs,the crises continue

The Legislative Update column reports on President Bush's supplemental budget request for the war in Iraq, the formation of a defense caucus in the House of Representatives, stabilized funding for airport security, the Department of Homeland Security budget, NASA's budget request, funding for NASA's aeronautics program, and NASA's new authorization. NASA's FY04 budget request is $15.47 billion, less than 1% more than FY03. The aeronautics program budget request for FY04 is $959 million, a decrease of 8.5% from FY03. Congress is working to introduce a multiyear authorization for NASA during the 108th session.     

双层壳型涡轮叶片中冲击旋流换热增益效果试验

以双层壳型涡轮叶片内冷通道中旋流换热特性为研究对象,采用热膜法,对双层壳型冷却结构中的狭小受限通道中,旋流作用下换热特性的变化规律开展了细致的试验研究。重点分析了冷却空气的旋流作用对换热的强化增益效果。试验中通过改变冲击Re数(10 000～20 000),冲击间距和冲击孔直径之比H/D(0.35～1.7)等参数,研究了其对旋流的形成及内表面局部换热系数的影响规律。研究发现:由于双层壳型叶片内冷通道的空间受限,冷却空气在通道内形成了旋流结构,该旋流结构显著影响了内表面的局部换热系数并可以有效提高换热效果。研究结果表明:内表面局部换热系数对冲击间距和冲击孔直径之比H/D最为敏感,对于不同冲击Re数,存在一个最佳的H/D使得旋流换热增益效果达到最大(Re=10 000时,最佳H/D为0.95;Re=15 000,20 000,最佳H/D=0.63)。     

The Solar Electron and Proton Telescope for the STEREO Mission

The Solar Electron and Proton Telescope (SEPT), one of four instruments of the Solar Energetic Particle (SEP) suite for the IMPACT investigation, is designed to provide the three-dimensional distribution of energetic electrons and protons with good energy and time resolution. This knowledge is essential for characterizing the dynamic behaviour of CME associated and solar flare associated events. SEPT consists of two dual double-ended magnet/foil particle telescopes which cleanly separate and measure electrons in the energy range from 30–400 keV and protons from 60–7?000 keV. Anisotropy information on a non-spinning spacecraft is provided by the two separate telescopes: SEPT-E looking in the ecliptic plane along the Parker spiral magnetic field both towards and away from the Sun, and SEPT-NS looking vertical to the ecliptic plane towards North and South. The dual set-up refers to two adjacent sensor apertures for each of the four view directions: one for protons, one for electrons. The double-ended set-up refers to the detector stack with view cones in two opposite directions: one side (electron side) is covered by a thin foil, the other side (proton side) is surrounded by a magnet. The thin foil leaves the electron spectrum essentially unchanged but stops low energy protons. The magnet sweeps away electrons but lets ions pass. The total geometry factor for electrons and protons is 0.52 cm²?sr and 0.68 cm²?sr, respectively. This paper describes the design and calibration of SEPT as well as the scientific objectives that the instrument will address.     

航空发动机限寿件表面特征概率损伤容限评估

为满足航空发动机适航规章(FAR/CCAR33.70)限寿件安全性评估要求,系统总结了基于特殊材料数据库、线弹性断裂力学分析与表面特征失效概率分析的表面特征概率损伤容限评估方法.以表面孔特征为例,总结分析符合适航规章要求的孔特征概率损伤容限评估流程,描述优化的孔特征评估方法,根据咨询通告AC33.70-2中带孔特征轮盘...     

Engineering and Electrical Engineering?Supply and Demand

Change in employment of engineers is shown to be related to the Deutsch and Shea Index of Engineering Demand. A relationship is given that shows the changes in engineering employment on a quarterly and annual basis. Engineering employment has turned upward for the first time since the last quarter of 1969. We have displaced and stored over 90 000 qualified engineers since 1969, in addition to displacing over 40 000 not qualified by an engineering education. Estimates by some of the need for 48 000 engineers per year is shown to be highly questionable. Current demand is still insufficient to absorb the current output without displacing some currently employed. It is suggested that demand in specialties can be determined by advertising lineage devoted to specialties in the same manner that the engineering demand is determined by the Deutsch and Shea Index. The years 1970, 1971, and 1972 were characterized by a decrease in employment of 62 000 engineers, 150 000 new graduates, 25 000 immigrants, and only 55 000 normal retirements and deaths.     

Theory and Modeling of Planetary Dynamos

Numerical dynamo models are increasingly successful in modeling many features of the geomagnetic field. Moreover, they have proven to be a useful tool for understanding how the observations connect to the dynamo mechanism. More recently, dynamo simulations have also ventured to explain the surprising diversity of planetary fields found in our solar system. Here, we describe the underlying model equations, concentrating on the Boussinesq approximations, briefly discuss the numerical methods, and give an overview of existing model variations. We explain how the solutions depend on the model parameters and introduce the primary dynamo regimes. Of particular interest is the dependence on the Ekman number which is many orders of magnitude too large in the models for numerical reasons. We show that a minor change in the solution seems to happen at $\mbox {E}=3\mbox {$\times 10^{-6}$}$ whose significance, however, needs to be explored in the future. We also review three topics that have been a focus of recent research: field reversal mechanisms, torsional oscillations, and the influence of Earth’s thermal mantle structure on the dynamo. Finally we discuss the possibility of tidally or precession driven planetary dynamos.     

Statistical Analysis of EUV and UV Lines Inside and Outside of Solar Coronal Holes

Two studies performed with SUMER (the Solar Ultraviolet Measurements of Emitted Radiation spectrometer on SOHO) in September 1996 are presented. Spatial scans, a long exposure time and a broad spectral window provide reliable line profiles for various regions of the Sun (off-limb corona, coronal hole, quiet Sun, bright and dark regions on disk) and for different formation temperatures (Si II, 14 000 K; C IV, 100 000 K; Ne VIII, 630 000 K). Line intensity, position and width distributions are presented together with the line positions relative to the wavelength seen above the limb. This revised version was published online in June 2006 with corrections to the Cover Date.     

DC Characteristics of Gamma-ray Irradiated SiGe HBT in Comparison with Si BJT

The changes of DC characteristics of SiGe HBT after being submitted to γ-ray irradiation of 700 krad, 7 000 krad and 10 000 krad were compared to those of Si BJT. Generally speaking, Ib and Ib–Ib0 increase with the doses increasing. For SiGe HBT, with the doses increasing, Ic and Ic–Ic0 as well as the related changes of the current gain (β) will decrease at higher Vbe, while for Si BJT, with the doses increasing, after irradiation, Ib and Ic–Ic0 increase; β and its related changes also decrease with their differences, however, tending to be very small at high doses of 7 000 krad and 10 000 krad. Moreover, given the same doses, the decreases of β are much larger than SiGe HBT, which shows that SiGe HBT’s anti-radiation performance proves to be better than Si BJT. Still, in SiGe HBT, some strange phe-nomena were observed: Ic–Ic0 will increase after the radiation of 7 000 krad in less than 0.65 V and as will β in less than 0.75 V. The mechanism of radiation-induced change in DC characteristics was also discussed.     

带交错肋结构涡轮叶片复合通道的实验

采用实验的方法,研究带交错肋结构和纵向隔板的涡轮叶片内冷通道的流动与换热.实验采用相变加热的方法,为模型实验件提供等壁温边界条件,实验在Re=10 000～60 000之间进行.实验模型采用了交错肋结构和扰流柱结构,分别与两种纵向隔板组合进行实验,以期望得到综合传热效果最优的组合.实验件的一侧外壁面被分成10个区域以期望了解实验件局部换热情况.实验结果表明:带交错肋结构的通道的换热效果好于带扰流柱结构的通道的换热效果.当Re<30 000时,综合传热性能最佳的是带波形隔板加交错肋0612组合结构的通道,当Re>30 000时,综合传热性能最佳的是带波形隔板加交错肋0412组合结构的通道.