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排序方式: 共有83条查询结果,搜索用时 31 毫秒
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L. Barbareschi C. La Padula M. Mastropietro F. Perotti G. Villa A. Bazzano L. Boccaccini R. Patriarca V.F. Polcaro P. Ubertini R.C. Butler G. Di Cocco G. Spada J.N. Carter P. Charalambous A.J. Dean J.B. Stephen 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》1983,3(4):91-93
In order to improve the low energy capability (15 ÷ 150 KeV) of the balloon borne “ZEBRA” low energy gamma imaging telescope (150 KeV-20 MeV), a large area, high spectral resolution (5% at 60 KeV), low background detector has been designed and is now under development.It consists of two MultiWire Spectroscopic Proportional Counter (SPC), escape gated, that have a sensitive area of 6000 cm2, and are placed above the large area array of sodiumiodide position sensitive elements. 相似文献
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Over the past several years Satellites International has developed an integrated suite of satellite sub-systems and small satellite buses. The sub-systems include S-band communications, attitude sensing and control, power conversion and distribution, and on-board data handling. They are inherently modular and readily adaptable to different satellite configurations, a concept known as semi-standardisation. This concept has been adopted by two generic low-cost buses: MicroSIL for satellites in the mass range 40–80kg; and MiniSIL for satellites in the range 100–500kg. Their architecture is based on the semi-standard sub-systems, but easily modified to utilise sub-systems from other manufacturers. They can support all stabilisation methods including spinning, 3-axis control and gravity gradient and are adaptable to a wide variety of missions including Earth resources, scientific, communications and technology demonstration. The Company also manufactures a range of low cost ground support equipment and complete ground stations to complement the space-borne systems. 相似文献
35.
余雄庆 《南京航空航天大学学报(英文版)》2000,17(2)
应用并行子空间设计算法对低雷诺数电动无人机进行了初步设计.电动无人机涉及多门学科,包括气动、重量、推进系统、性能和操稳.首先开发了电动无人机多学科系统分析软件.并行子空间设计算法利用基于人工神经网络的响应面技术作为系统分析的近似模型.电动无人机初步设计中的设计变量共有29个,其中连续设计变量25个,离散设计变量4个.研究表明,并行子空间设计算法能以较少的系统分析次数在可行域内寻找出一个较好的设计点,并在设计过程中具有适应设计要求(约束)可变性的要求,它为飞行器一体化设计提供了一条途径. 相似文献
36.
Stephen M. Pompea 《Space Science Reviews》1995,74(1-2):181-193
The performance of infrared and submillimeter systems can be severely degraded by stray light. Stray light includes off-axis radiation, system diffraction and scattering effects, and thermal self-emission. The purpose of this paper is to identify several keys to preventing system degradation due to stray radiation. The first key is to apply stray light design rules and analysis techniques early in the program before the design is finalized. A systems level analysis using stray light analysis software is often necessary in order to identify more subtle problems and to assess the magnitude of their effect on system performance. Another key is to address contamination control and the choice of surface coatings early in the program. The management of stray radiation issues is extremely cost-effective, if begun early in the program, and can reduce later schedule hardships. 相似文献
37.
The low-energy neutral atom imager for IMAGE 总被引:1,自引:0,他引:1
Moore T.E. Chornay D.J. Collier M.R. Herrero F.A. Johnson J. Johnson M.A. Keller J.W. Laudadio J.F. Lobell J.F. Ogilvie K.W. Rozmarynowski P. Fuselier S.A. Ghielmetti A.G. Hertzberg E. Hamilton D.C. Lundgren R. Wilson P. Walpole P. Stephen T.M. Peko B.L. Van Zyl B. Wurz P. Quinn J.M. Wilson G.R. 《Space Science Reviews》2000,91(1-2):155-195
The `Imager for Magnetosphere-to-Aurora Global Exploration (IMAGE) will be launched early in the year 2000. It will be the first mission dedicated to imaging, with the capability to determine how the magnetosphere changes globally in response to solar storm effects in the solar wind, on time scales as short as a few minutes. The low energy neutral atom (LENA) imager uses a new atom-to-negative ion surface conversion technology to image the neutral atom flux and measure its composition (H and O) and energy distribution (10 to 750 eV). LENA uses electrostatic optics techniques for energy (per charge) discrimination and carbon foil time-of-flight techniques for mass discrimination. It has a 90°×° field-of-view in 12 pixels, each nominally 8°×°. Spacecraft spin provides a total field-of-view of 90°×360°, comprised of 12×45 pixels. LENA is designed to image fast neutral atom fluxes in its energy range, emitted by auroral ionospheres or the sun, or penetrating from the interstellar medium. It will thereby determine how superthermal plasma heating is distributed in space, how and why it varies on short time scales, and how this heating is driven by solar activity as reflected in solar wind conditions. 相似文献
38.
Nikos Mastrodemos Daniel G. Kubitschek Stephen P. Synnott 《Space Science Reviews》2005,117(1-2):95-121
The engineering goal of the Deep Impact mission is to impact comet Tempel 1 on July 4, 2005, with a 370 kg active Impactor
spacecraft (s/c). The impact velocity will be just over 10 km/s and is expected to excavate a crater approximately 20 m deep
and 100 m wide. The Impactor s/c will be delivered to the vicinity of Tempel 1 by the Flyby s/c, which is also the key observing
platform for the event. Following Impactor release, the Flyby will change course to pass the nucleus at an altitude of 500
km and at the same time slow down in order to allow approximately 800 s of observation of the impact event, ejecta plume expansion,
and crater formation. Deep Impact will use the autonomous optical navigation (AutoNav) software system to guide the Impactor
s/c to intercept the nucleus of Tempel 1 at a location that is illuminated and viewable from the Flyby. The Flyby s/c uses
identical software to determine its comet-relative trajectory and provide the attitude determination and control system (ADCS)
with the relative position information necessary to point the High Resolution Imager (HRI) and Medium Resolution Imager (MRI)
instruments at the impact site during the encounter. This paper describes the Impactor s/c autonomous targeting design and
the Flyby s/c autonomous tracking design, including image processing and navigation (trajectory estimation and maneuver computation).
We also discuss the analysis that led to the current design, the expected system performance as compared to the key mission
requirements and the sensitivity to various s/c subsystems and Tempel 1 environmental factors. 相似文献
39.
Farzad Kamalabadi Jianqi Qin Brian J. Harding Dimitrios Iliou Jonathan J. Makela R. R. Meier Scott L. England Harald U. Frey Stephen B. Mende Thomas J. Immel 《Space Science Reviews》2018,214(4):70
The Ionospheric Connection Explorer (ICON) Far Ultraviolet (FUV) imager, ICON FUV, will measure altitude profiles of OI 135.6 nm emissions to infer nighttime ionospheric parameters. Accurate estimation of the ionospheric state requires the development of a comprehensive radiative transfer model from first principles to quantify the effects of physical processes on the production and transport of the 135.6 nm photons in the ionosphere including the mutual neutralization contribution as well as the effect of resonant scattering by atomic oxygen and pure absorption by oxygen molecules. This forward model is then used in conjunction with a constrained optimization algorithm to invert the anticipated ICON FUV line-of-sight integrated measurements. In this paper, we describe the connection between ICON FUV measurements and the nighttime ionosphere, along with the approach to inverting the measured emission profiles to derive the associated O+ profiles from 150–450 km in the nighttime ionosphere that directly reflect the electron density in the F-region of the ionosphere. 相似文献
40.
GEOSAR (synthetic aperture radar on geosynchronous satellite) becomes a potential method of space-borne geoscience remote sensing. Though it has attractive characters such as extra long observing time and very large observing area the unique geometry and relative motion are quite different from straight line required by SAR, and long integration time also causes delay by troposphere and ionosphere. Curvature of the Earth is no long negligible in GEOSAR. Especially, principle of azimuth compression in GEOSAR should be different from that of traditional SAR.In order to fulfill practical GEOSAR such problems should be solved. A new solution of azimuth compression together with motion compensation is presented here by taking the advantages of GEOSAR movement. A new method to overcome the Earth curvature in range compression of EACH footprint is testified. After compensating the Earth curvature traditional methods for range cell migration correction can be used in GEOSAR. Multi-sub-aperture method is applied to eliminate the phase delay caused by troposphere. This modified imaging algorithm makes it possible for GEOSAR to have long integration time and high resolution. 相似文献