共查询到20条相似文献,搜索用时 15 毫秒
1.
Ivanenok J.F. III Sievers R.K. Hunt T.K. Johnson G.A. 《Aerospace and Electronic Systems Magazine, IEEE》1993,8(12):35-39
The authors describe and compare small (two-module) and larger (16-module) AMTEC (alkali metal thermal-to-electric converter) radioisotope powered systems and describe the computer model developed to predict their performance. The high efficiency and static conversion process combined with minimized parasitic losses and operating temperatures that allow the use of current materials while still maintaining a competitive radiator area are found to make AMTEC an excellent candidate for enhanced performance space power systems. AMTEC has the capability of reducing mission costs relative to other static conversion systems because of its high efficiency. AMTEC can also reduce cost relative to dynamic systems simply by being less massive (10 to 5000 W level), and its use eliminates the torque and vibration issues of dynamic systems 相似文献
2.
A detailed computer representation of four Mapham inverters connected in a series-parallel arrangement has been implemented. System performance is illustrated by computer traces for the four Mapham inverters connected to a Litz cable with parallel resistance and DC receiver loads at the receiving end of the transmission cable. Methods of voltage control and load sharing between the inverters are demonstrated. The computer representation is used to design and demonstrate the advantages of a feedforward voltage-control strategy. It is shown that with a computer simulation of this type, the performance and control of spacecraft power systems can be investigated with relative ease and facility 相似文献
3.
Keng Wu 《IEEE transactions on aerospace and electronic systems》1994,30(4):1049-1053
A novel approach of deriving the loop gain of a spacecraft switched shunt power system is presented. The system hardware elements contain both the analog and the digital components. Transfer functions of the analog circuits are easily identified employing the conventional approach. Gain function of the digital block is however conceived following a quite unconventional route. The digital gain is shown to include the effects of comparator thresholds, digital clock, shift register, sinusoidal amplitude, and ac frequency. The dependence of the digital gain on voltage thresholds, clocking period, and the integrational property of threshold comparator is expected. The dependence on sinusoidal amplitude contradicts the traditional concept of small signal analysis. The overall loop gain in the analytic form yields a computational result that matches the actual measurement very well. This fact proves, to some extent, the validity of the digital gain function and the basis of its derivation 相似文献
4.
N. N. Inozemtsev 《Russian Aeronautics (Iz VUZ)》2010,53(4):443-449
A problem of applying closed multiloop thermodynamic cycles with mixing of dissimilar working gases in spacecraft power plants has been considered. The advantage of these cycles that is due to reduction of a heat quantity being rejected into space has been shown for ecologically clean generation of electric energy in prolonged space flights. 相似文献
5.
Lee J.R. Cho B.H. Kim S.J. Lee F.C. 《IEEE transactions on aerospace and electronic systems》1988,24(3):295-304
Modeling of a complete spacecraft power processing system is presented, using the Boeing EASYS software. Component models are developed, and several system models including a solar array switching system, a partially shunted solar system, and cosmic background explorer (COBE) system are simulated. The modes of operation of the power system, such as shunt mode, battery-charge mode, and battery-discharge mode, are simulated for a complete orbit cycle 相似文献
6.
浮空器太阳辐射模型研究 总被引:2,自引:0,他引:2
采用理论分析和试验测定相结合的办法,对浮空器太阳辐射进行了研究,建立太阳直射辐射模型、天空散射辐射模型和地面反射辐射模型,计算值与试验测定值吻合较好。 相似文献
7.
Bourgasov M.P. Kvasnikov L.A. Smakhtin A.P. Tchuyan R.K. Tolyarenko N.V. 《Aerospace and Electronic Systems Magazine, IEEE》1997,12(10):3-7
A reliable power supply for spacecraft is one of the central problems determining the future development of space technology. The traditional solution to this problem implies having an autonomous power plant on board each spacecraft. The most widely used are power plants with solar cells. However, there exists an alternative power supply concept of using a centralized power supply system (CPSS) and power transmission to the user satellites by laser or microwave beams. Use of a CPSS has a number of advantages. In particular, it allows the spacecraft to increase power supply level and service life as well as to decrease the spacecraft mass and cost. However, it sets new physical and technical problems associated with long distance power transmission and requires some changes in spacecraft structure and concepts. The feasibility study of CPSS development and use has to rely on existing or firmly forecastable technologies. An attempt of such an analysis has been done by a group of scientists at Moscow State Aviation Institute during 1994-1996. The very first results have already been published. This paper discusses new results obtained lately regarding a space based CPSS 相似文献
8.
A modular state-variable approach is presented for DC spacecraft power system modeling and simulation. Each modular component is treated as a multiport network, and a state model is written with the port voltages as the inputs. The state model of a component is solved independently of the other components, using its state transition matrix. The state variables of each component are updated, assuming that the inputs are constant. Network analysis principles are then utilized to calculate the component inputs 相似文献
9.
Zhenhua Jiang Shengyi Liu Dougal R.A. 《IEEE transactions on aerospace and electronic systems》2003,39(3):976-989
A study is presented on the design and testing of spacecraft power systems using the virtual test bed (VTB). The interdisciplinary components such as solar array and battery systems were first modeled in native VTB format and validated by experiment data. The shunt regulator and battery charge controller were designed in Simulink according to the system requirements and imported to VTB. Two spacecraft power systems were then designed and tested together with the control systems. 相似文献
10.
L. A. Frank J. B. Sigwarth J. D. Craven J. P. Cravens J. S. Dolan M. R. Dvorsky P. K. Hardebeck J. D. Harvey D. W. Muller 《Space Science Reviews》1995,71(1-4):297-328
The Visible Imaging System (VIS) is a set of three low-light-level cameras to be flown on the POLAR spacecraft of the Global Geospace Science (GGS) program which is an element of the International Solar-Terrestrial Physics (ISTP) campaign. Two of these cameras share primary and some secondary optics and are designed to provide images of the nighttime auroral oval at visible wavelengths. A third camera is used to monitor the directions of the fields-of-view of these sensitive auroral cameras with respect to sunlit Earth. The auroral emissions of interest include those from N
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at 391.4 nm, Oi at 557.7 and 630.0 nm, Hi at 656.3 nm, and Oii at 732.0 nm. The two auroral cameras have different spatial resolutions. These resolutions are about 10 and 20 km from a spacecraft altitude of 8R
e
. The time to acquire and telemeter a 256×256-pixel image is about 12 s. The primary scientific objectives of this imaging instrumentation, together with thein-situ observations from the ensemble of ISTP spacecraft, are (1) quantitative assessment of the dissipation of magnetospheric energy into the auroral ionosphere, (2) an instantaneous reference system for thein-situ measurements, (3) development of a substantial model for energy flow within the magnetosphere, (4) investigation of the topology of the magnetosphere, and (5) delineation of the responses of the magnetosphere to substorms and variable solar wind conditions. 相似文献
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《COSPAR's Information Bulletin》1985,1985(103):91-92
13.
《中国航空学报》2023,36(2):241-255
This paper presents a discrete-time attitude control strategy with equi-global practical stabilizability for aligning the attitude of multiple spacecraft to a predesigned configuration according to a time-variant reference. By utilizing the interference of the wireless channel, the communication scheme designed in this paper can save communication resources, amount of computation, and energy proportionally to the number of spacecraft. The exact discrete-time model and approximate discrete-time model of the consensus-based spacecraft tracking system are given. Then the framework for the design of an event-triggered control scheme for the exact discrete-time system via its approximate models is developed, which avoids the periodic actuation, and Zeno behavior is proved to be excluded. Furthermore, the control scheme can handle the presence of the unknown fading channel. Finally, simulation results are presented to demonstrate the effectiveness of the control strategy. 相似文献
14.
This paper reviews a large number of silicon solar cell irradiation experiments performed over the last 10 years, including 1-MeV and energy spectrum electron studies, and low-(100-keV) and high-energy (up to 155-MeV) proton studies on bare and covered silicon solar cells of several types. The results of satellite flight experiments on individual solar cells are also presented, as well as data from complete solar arrays and data on the new high-efficiency solar cells. Experimental evidence indicates that the percentage of degradation is smaller in thin solar cells than in thick ones, and that cells with high resistivity (10 ?·cm) degrade less than cells with lower resistivity (1 ?·cm). It is shown that high-efficiency silicon solar cells produced at COMSAT Laboratories and pilot production groups of these cells retain most of their increased power output under irradiation. It is emphasized that all surfaces and edges of the solar cells must be completely shielded from the large flux protons in the space environment. Insufficiencies in the published data are noted in certain areas, and recommendations for additional research are presented. Finally, an extensive bibliography is included. 相似文献
15.
O. M. Alifanov Yu. G. Egorov V. M. Kul’kov V. V. Terent’ev S. O. Firsyuk 《Russian Aeronautics (Iz VUZ)》2015,58(4):376-382
The elements for various types of attitude control systems used in a number of small spacecraft are considered. An approach for assessment of such system effectiveness based on design requirements for spacecraft purpose and restriction in accuracy, mass and energy is proposed. 相似文献
16.
Emmanuel Lellouch 《Space Science Reviews》1995,74(1-2):1-7
This paper aims at placing infrared (IR) and submillimeter (submm) observations of the Solar Sytem in the context of future space missions. First, the information that mm, submm and IR observations bring on planets, satellites and comets is reviewed. Then, some lines of future research in this field are explored, and a number of observations that could enhance our understanding of Solar System objects are suggested. Finally, the adequacy of future space missions in this respect is discussed. The specific cases of ISO, FIRST and the proposed Edison are considered. 相似文献
17.
O'Neill M.J. McDanal A.J. Piszczor M.F. George P.J. Edwards D.L. Brandhorst H.W. Eskenazi M.I. Botke M.M. Jaster P.M. 《Aerospace and Electronic Systems Magazine, IEEE》2003,18(1):3-9
At IECEC 2001, this team presented a paper on the new stretched lens array (SLA), including its evolution from the successful SCARLET array on the NASA/JPL Deep Space 1 spacecraft. Since that conference, the SLA team has made significant advances in SLA technology, including component-level improvements, array-level optimization, space environment exposure testing, and prototype hardware fabrication and evaluation. This paper describes the evolved version of the SLA, highlighting recent improvements in the lens, solar cell, photovoltaic receiver, rigid panel structure, and complete solar array wing. In addition to excellent durability in the space environment, the near-term SLA will provide outstanding wing-level performance parameters: 180 W/kg specific power; 300 W/m/sup 2/ power density; 300 V operational voltage; 85% savings in cell area (cm/sup 2//W) and cell-related cost ($/W) compared to planar arrays; 9 kW/m/sup 3/ stowed power at launch. 相似文献
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The paper presents a technique of forming and evaluating the allowable clearance between a launch vehicle fairing and spacecraft. 相似文献
20.
Halpin S.M. Grigsby L.L. 《IEEE transactions on aerospace and electronic systems》1992,28(4):1033-1041
Alternative methods for power flow and fault analysis of single-phase distribution systems are presented. The algorithms for both power flow and fault analysis utilize a generalized approach to network modeling. The generalized admittance matrix, formed using elements of linear graph theory, is an accurate network model for all possible single-phase network configurations. Unlike the standard nodal admittance matrix formulation algorithms, the generalized approach uses generalized component models for the transmission line and transformer. The standard assumption of a common node voltage reference point is not required to construct the generalized admittance matrix. Therefore, truly accurate simulation results can be obtained for networks that cannot be modeled using traditional techniques 相似文献