2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)最新文献

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Electronic packaging for extended Mars surface missions 扩展火星表面任务的电子封装
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-13 DOI: 10.1109/AERO.2004.1368046
A. Shapiro, S. Ling, S. Ganesan, R. Cozy, D. Hunter, D. Schatzel, M. Mojarradi, E. Kolawa
{"title":"Electronic packaging for extended Mars surface missions","authors":"A. Shapiro, S. Ling, S. Ganesan, R. Cozy, D. Hunter, D. Schatzel, M. Mojarradi, E. Kolawa","doi":"10.1109/AERO.2004.1368046","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368046","url":null,"abstract":"Extended Mars missions require vehicles to survive a large number of extended temperature cycles. To address this issue for electronics, previous strategies have placed electronics in a \"warm electronics box\" where thermal management is more easily maintained. However, that strategy limits number and location of electronics. An alternative strategy allows electronics to be remotely located on actuator and wheel arms with no heating, which has the advantage of distributed control. This strategy requires the electronics to survive the Martian extremes of -120 to +20/spl deg/C for the duration of the mission. In addition, wheel motor controllers were mounted directly on the motor casing extending the temperature range on the warm side to +85/spl deg/C (including some margin). Since missions may last 18 months or more and with day-night cycles on Mars at about 26 hours this means exposure to approximately 500 cycles. Typical testing is performed to 3/spl times/ the number of cycles giving the electronics a testing requirement of -120 to +85/spl deg/C for 1,500 cycles. A chip on board strategy was selected and a parallel approach of materials characterization and physics of failure with engineering experimentation is being used to address the issues of a large temperature swing with many cycles. A full factorial experiment, designed to highlight expected failure modes from the physics of failure analysis, is being conducted. The experiment is designed to evaluate different substrate materials, different die attach materials and different encapsulants or coatings. Combinations of these materials are being evaluated on a test vehicle with a range of die sizes in an effort to determine lifetime and to verify failure modes. Initial results were presented.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131625156","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 12
Military/civilian mixed-mode Global Positioning System (GPS) receiver (MMGR) 军用/民用混合模式全球定位系统(GPS)接收机
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-13 DOI: 10.1109/AERO.2004.1368065
A. Peczalski, J. Kriz, S. Carlson, S. Sampson
{"title":"Military/civilian mixed-mode Global Positioning System (GPS) receiver (MMGR)","authors":"A. Peczalski, J. Kriz, S. Carlson, S. Sampson","doi":"10.1109/AERO.2004.1368065","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368065","url":null,"abstract":"This paper describes plans and progress made on the MMGR program funded jointly by Air Force Research Laboratory (AFRL), GPS Joint Program Office (JPO) and industry that started in April 2003. The Honeywell/Rockwell Collins MMGR program starts with a minimum configuration of the GPS receiver (e.g. low end commercial GPS) and develop a new RF front-end design using mixed mode CMOS technology with lowest cost components and processes over the first year of the program. The front-end Application Specific Integrated Circuit (ASIC) design have a modular and flexible architecture based on reuseable macro-cells. This initial RF front-end design is evolved and targeted to meet specific commercial, military and space application requirements during the subsequent development iterations over the last two years of the program and beyond. Rockwell Collins demonstrates feasibility of using a digital device to create an M-code capable, high anti-jam GPS system. This shows a path to an adaptable MMGR that enables flexibility and easy upgradeability for both military and commercial GPS receivers and adheres to GPS Modernization/GPS III receiver specifications. The emphasis of the Rockwell Collins task is to improve anti-jam (AJ) and anti-interference capability of the GPS receivers through miniaturization of the anti-jamming (AJ) electronics and improvements in ultra-tight coupling (UTC) of a GPS receiver and an Inertial Measurement Unit (IMU).","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"56 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132226116","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 6
Thermo-mechanical analysis of MEMS pressure sensor die-attach for high temperature applications 用于高温应用的MEMS压力传感器贴片的热力学分析
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-13 DOI: 10.1109/AERO.2004.1368049
K. Meyyappan, P. McCluskey, Liangyu Chen
{"title":"Thermo-mechanical analysis of MEMS pressure sensor die-attach for high temperature applications","authors":"K. Meyyappan, P. McCluskey, Liangyu Chen","doi":"10.1109/AERO.2004.1368049","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368049","url":null,"abstract":"The thermomechanical stress generated by the mismatch of the coefficients of thermal expansion (CTE) of the sensor base material (SiC) and the packaging has a significant impact on the reliability of the packaged sensor. In the current work, non-linear finite element analysis was performed to determine the peeling, shear stresses and the von Mises stresses, in the SiC pressure sensor and the die attach which is intended for high temperature operation. A parametric study has been conducted to study the effects of the substrate material and reference (stress-free) temperature.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"178 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124431962","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 3
Modeling matrix failure in composites due to cryogenic temperatures 低温下复合材料中基体失效的建模
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-13 DOI: 10.1109/AERO.2004.1368070
S. Nickerson, J. Mayes, C. Paul, J. Welsh
{"title":"Modeling matrix failure in composites due to cryogenic temperatures","authors":"S. Nickerson, J. Mayes, C. Paul, J. Welsh","doi":"10.1109/AERO.2004.1368070","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368070","url":null,"abstract":"A drastic reduction in structural weight is an indispensable prerequisite to realize future high altitude area defense systems or single stage to orbit space vehicles. Boost defense programs such as the Airborne Laser (ABL) and Space-Based Laser (SBL) as well as numerous optical-based systems require the storage, transport and dispensing of large amounts of cryogenic fluids. All elements contributing to the mass of the cryogenic systems must be as light as possible, particularly the tanks which are one of the most challenging parts. Today, the majority of cryogenic tanks are made of insulated aluminum, stainless steel, or a metal liner with composite overwrap. While these tanks have high damage tolerance and chemical resistance, they do so with a relatively high mass penalty. Advanced composite materials can provide significant mass reduction due to their high specific strength and stiffness ratios, compared to metals, but are susceptible to cracking under thermal cycling. Thermally induced cracking is the result of large internal stresses generated at cryogenic temperatures due to a mismatch in coefficients of thermal expansion between the fiber and the matrix. Cracking of composite cryogenic tanks is classified as a component failure because the increased permeability of the tank results in significant loss of stored cryogens. Current state-of-the-practice analysis technologies, such as linear elastic fracture mechanics, micromechanics, and classical lamination theory have been found to be lacking in their capability to be applied in the general design of composite cryogenic tanks. Primarily in their ability to accurately and easily model thermally induced cracking in advanced composite materials. Faster and more accurate analysis techniques were needed as enabling technologies for improving composite cryogenic tank design. Thus, a research effort was initiated by the Missile Defense Agency to improve prediction and analysis methods. An alternative analysis method, called Multi-Continuum Theory (MCT), uses a classic Hill strain decomposition technique to solve for the phase averaged stress and strains in each constituent of the composite with a minimum of computational complexity and virtually no time penalty. Constituent information is valuable because thermal damage in a composite begins at the constituent level and may in fact be limited to only one constituent. Accurate prediction of constituent failure at a single point enables the analysis of progressive damage growth throughout the composite. In this paper, we describe how MCT was used to predict thermally induced composite damage, primary matrix cracking, of carbon fiber reinforced plastic composite specimens. The MCT results were benchmarked against existing analytical methods to assess any improvements in accuracy and ease of use.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126298727","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 1
Atlas V Secondary Payload Carrier Systems - development approach, issues, and solutions 阿特拉斯5次有效载荷运载系统——开发方法、问题和解决方案
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-13 DOI: 10.1109/AERO.2004.1368078
K.W. Cope
{"title":"Atlas V Secondary Payload Carrier Systems - development approach, issues, and solutions","authors":"K.W. Cope","doi":"10.1109/AERO.2004.1368078","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368078","url":null,"abstract":"Lockheed Martin Space Systems Company has developed an innovative approach to providing small, secondary payload class spacecraft access to space. This alternate approach to the traditional use of dedicated small launch vehicles is based on offering flight for up to five secondary payloads on Atlas V missions with excess capacity through the use of the Atlas V Secondary Payload Carrier (SPC) and/or Internal Payload Carrier (IPC). In 2002, Lockheed Martin sought and was awarded two contracts by the National Reconnaissance (NRO) Office of Space Launch (OSL) to continue the development of the SPC concept. The contract tasks included developing the concept to a preliminary design review level, and an assessment of the effects of the presence of the SPC on the primary payload. Work accomplished on the SPC design since that time culminated in a PDR in February 2003 and a final out-brief on coupled loads results, separation analyses, and expected SP environments to the OSL customer in June 2003. In addition to the SPC, Lockheed Martin developed a concept for an Internal Payload Carrier (IPC) to permit efficient flight of smaller, single secondary payloads. This paper presents the design approach used in developing the SPC and the IPC and addresses technical and programmatic issues encountered during the development phase, as well as the associated solutions to those issues. The paper includes the current design status, features, and capabilities of the SPC and IPC, and how they integrate with the Atlas V launch vehicle and the primary payload.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"83 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126397077","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Novel digital platform for deep space transponders: the transmitter side 新型深空应答器数字平台:发射机侧
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-06 DOI: 10.1109/AERO.2004.1367920
Lorenzo Simone, D. Gelfiisa, S. Cocchi, M. C. Comparini, D. Fiore, V. Piloni, A. Rapposelli, M. Capannolo
{"title":"Novel digital platform for deep space transponders: the transmitter side","authors":"Lorenzo Simone, D. Gelfiisa, S. Cocchi, M. C. Comparini, D. Fiore, V. Piloni, A. Rapposelli, M. Capannolo","doi":"10.1109/AERO.2004.1367920","DOIUrl":"https://doi.org/10.1109/AERO.2004.1367920","url":null,"abstract":"Aim of the paper is to present a novel digital platform for the transmitting side (NDP-Tx) of a deep space transponder which has been developed by Alenia Spazio in the frame of the ESA study on \"Digital Techniques for TT&C Transponder\". The proposed design has unique features in terms of flexibility and interfacing with the spacecraft command data sub-system (CDS). The NDP-Tx supports standard telemetry modulation formats based on residual carrier and more advanced schemes aiming to improve the space-to-earth link performance. In fact, in case of limited available power, as for satellite transmitters, the power efficiency is maximised driving the power amplifier in saturation, i.e. in the non-linear region of its transfer characteristic. Using constant (i.e. GMSK) or quasi-constant (i.e. Square-Root Raised Cosine SRRC-Filtered OQPSK) envelope modulation allows the transmitter stage to operate in saturation without the drawback of the non-linear distortion (i.e. adjacent channel interference due to sidelobes spreading and regeneration).","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115142359","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 2
Vehicle tracking using a network of small acoustic arrays 使用小型声学阵列网络进行车辆跟踪
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-06 DOI: 10.1117/12.541490
V. Calloway, R. Hodges, S. Harman, A. Hume, D. Beale
{"title":"Vehicle tracking using a network of small acoustic arrays","authors":"V. Calloway, R. Hodges, S. Harman, A. Hume, D. Beale","doi":"10.1117/12.541490","DOIUrl":"https://doi.org/10.1117/12.541490","url":null,"abstract":"Major advances in base technologies of computer processors and low cost communications have paved the way for a resurgence of interest in unattended ground sensors. Networks of sensors offer the potential of low cost persistent surveillance capability in any area that the sensor network can be placed. Key to this is the choice of sensor on each node. If the system is to be randomly deployed then nonline of sight sensor become a necessity. Acoustic sensors potentially offer the greatest level of capability and will be considered here. As a passive sensor, only time of arrival or bearing information can be obtained from an acoustic array, thus the tracking of targets must be done in this domain. This work explores the critical step between array processing and implementation of the tracking algorithm. Specifically, unlike previous implementations of such a system, the bearings from each frequency interval of interest are not averaged but are used as data points within a Kalman filter. Thus data is not averaged and then filtered but all data is put into the tracking filter.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115611234","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 7
Reducing risks and costs in automated operations 降低自动化操作的风险和成本
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-06 DOI: 10.1109/AERO.2004.1368199
A. Monham, D. Quigley
{"title":"Reducing risks and costs in automated operations","authors":"A. Monham, D. Quigley","doi":"10.1109/AERO.2004.1368199","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368199","url":null,"abstract":"Pressure to cut operations costs is increasing for all mission classes. One potential solution is to introduce automation into the execution of procedures. However, this is associated with a level of complexity and risk which many operations managers would consider incompatible with the achievement of their mission objectives. This perception is compounded by operations language based tools, which often obscure on-going satellite operations, making operator intervention difficult in case of anomalies. An approach to automation using the \"MOIS\" product addresses these issues by ensuring that the same procedures used for traditional manual operations can be executed without modification, and that human readability is maintained at all times as automation is introduced into an organization. Furthermore, MOIS provides a much safer route to full \"lights-out\" operations. MOIS therefore provides a clear way forward to reduce risks and costs in automated operations.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":" 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120832602","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 3
Zero gravity simulation technique of five freedom docking test bed 五自由度对接试验台零重力仿真技术
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-06 DOI: 10.1109/AERO.2004.1368224
Zhang Chong-jun, Lai Yinan, Zhang Guangyu
{"title":"Zero gravity simulation technique of five freedom docking test bed","authors":"Zhang Chong-jun, Lai Yinan, Zhang Guangyu","doi":"10.1109/AERO.2004.1368224","DOIUrl":"https://doi.org/10.1109/AERO.2004.1368224","url":null,"abstract":"The paper aimed to solve the weightless problem of the active docking ring (ADR) of a docking mechanism. The paper proposes a lift-on zero gravity simulation method with compact structure, which has an internal support rope for the active docking ring in the space docking process. The internal support structure ensures that the ADR rotates freely in three-axis direction. The intelligent fixed torque mechanism not only provides high precision balance force to gravitation, but also moves up and down with the ADR as well, realizing the motion of Y direction. The lateral motion (including X and Z directions ) of the ADR simply needs to overcome the friction torque of hinge by a swing link-double hinge mechanism resistance is small even in the top speed of the docking process due to the application of the longitudinal servocontrol mechanism. The paper gives relevant calculation and design data, and also some parameters experimental and balance simulation. The zero gravity simulation mechanism is installed in the internal walkway of a docking mechanism that could realize zero gravity simulation in the whole process of space docking. The respond time is 5 ms. The error of simulated weightlessness is about 1%-2% in each direction.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"126 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120941749","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Multi-hypothesis structures and taxonomies for combat identification fusion 战斗识别融合的多假设结构与分类
2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720) Pub Date : 2004-03-06 DOI: 10.1109/AERO.2004.1367984
T. Schuck, J. Bockett Hunter, D. D. Wilson
{"title":"Multi-hypothesis structures and taxonomies for combat identification fusion","authors":"T. Schuck, J. Bockett Hunter, D. D. Wilson","doi":"10.1109/AERO.2004.1367984","DOIUrl":"https://doi.org/10.1109/AERO.2004.1367984","url":null,"abstract":"One of the greatest difficulties in developing a fusion process is determining the type, quantity, and quality of the information provided. Even when this is accomplished, the utility (relationship) of the information is often difficult to establish. For the problem of combat identification (combat ID or CID) this is especially taxing. Often numerous sources provide information, but relationship guidelines are not well developed, or are ambiguous or inconsistent. This deficiency leads to poorly constructed fusion architectures and methodologies because information is either ignored or improperly combined in the fusion process. Using the Joint Directors of Laboratories (JDL) information fusion model as a guide, this paper address the movement of attribute information across multiple hypothesis classes (with some examination of kinematic information) as it relates to developing the identification of different objects, and how it can be combined both within and between JDL fusion levels. The result of this analysis leads to an information architecture that is naturally adaptive to information regardless of quality, level, or specificity.","PeriodicalId":208052,"journal":{"name":"2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121123797","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 4
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