1996 IEEE Aerospace Applications Conference. Proceedings最新文献_第9页

Simulation of an air defense radio protocol 防空无线电协议的模拟

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.496079

T. Huynh, J. Lordi

{"title":"Simulation of an air defense radio protocol","authors":"T. Huynh, J. Lordi","doi":"10.1109/AERO.1996.496079","DOIUrl":"https://doi.org/10.1109/AERO.1996.496079","url":null,"abstract":"We employ SES/workbench to model and simulate a Carrier Sense Multiple Access (CSMA) Network protocol for a single channel Air Defense radio. Using the SES/workbench radio model, we obtain the mean delay of a launch command message as a function of the launch rate and the size of the launcher net, under both errorless and error channel conditions. To validate the SES/workbench model, we develop the Pollaczek-Khinchin (P-K) formula and compare the theoretical (P-K) results with the SES/workbench simulation results. The results are found to be in excellent agreement. Like the SES/workbench model, the P-K formula provides quick estimates of the mean launch command delay as a function of the protocol parameters, such as the message size, the acknowledgment hold time, and the time between transmit and receive. This work assesses the ability of the protocol to handle, for a launch rate related to an air defense scenario and a maximum delay in a launch command, the maximum number of launchers in an air defense launcher net. It also demonstrates the utility of commercial tools such as SES/workbench in modeling and simulation of communication protocol for air and space applications.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124080739","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

Integrated processors in internetworking applications 互联网络应用中的集成处理器

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495898

A. Chame

引用次数: 1

Electromagnetic interference: a tutorial 电磁干扰:教程

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.496062

William H. Bill

{"title":"Electromagnetic interference: a tutorial","authors":"William H. Bill","doi":"10.1109/AERO.1996.496062","DOIUrl":"https://doi.org/10.1109/AERO.1996.496062","url":null,"abstract":"The treatment of electromagnetic interference (EMI) problems is perceived by many engineers as a generally unscientific, hit or miss, procedure. The intent of this tutorial is to present a practical, understandable, and straightforward approach to solving interference problems. The paper will address the concepts of circuit-to-world mutual isolation and effective energy-blocking boundaries between equipment and environment, and will cover in some detail problem detection, problem analysis, and possible problem. The emphasis will be on electromagnetic compatibility between equipment and its environment, including neighboring equipment and EMI test specification limits, in a cost-effective manner with reasonable margins of safety. The need to analyze a problem before attempting to solve it will be stressed. Common fix methods will be discussed, including grounding, bonding, filtering, and shielding. Common mistakes will be discussed. Both \"rules of thumb\" and simple, but helpful, equations will be listed. The EMI implications of ever increasing digital computer clock speeds and lowered logic voltages on future emissions and susceptibility fix methods will be presented. The author has extensive professional experience in aerospace and military EMI control (since 1973), yet the concepts presented in the paper are equally applicable to medical, and industrial Specification limits, test methods, and allowed fixes in these diverse fields vary, but the physical laws involved are identical.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"128 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131702609","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

The theory of single sensor altitude determination 单传感器测高原理

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.496053

H. Evans, B. Hibbeln

{"title":"The theory of single sensor altitude determination","authors":"H. Evans, B. Hibbeln","doi":"10.1109/AERO.1996.496053","DOIUrl":"https://doi.org/10.1109/AERO.1996.496053","url":null,"abstract":"Beginning with the phenomenological equations of remote sensing and atmospheric transmission, we show that the altitude of a bright, point-source target (such as a missile or afterburning aircraft) within the atmosphere can be determined with a single spaceborne multispectral sensor. Our calculation assumes that the target signal can be isolated from its background, and we do not consider noise. Essentially, we are measuring an attenuating molecule's column density along the line of sight, and the value of the molecule's vertical number density which satisfies our equations to determine the target's altitude. The column density measurement requires the sensor to simultaneously (or alternately) collect in two or more spectral bands associated with the attenuating molecule, and depends on the key assumptions that (1) we know the relative spectral emission of the target (i.e., we can classify the target) and (2) we know the attenuating molecule's vertical number density distribution. We evaluate the effects of uncertainty in our knowledge of these two key parameters by using a hydrocarbon-burning missile and carbon dioxide as examples. We demonstrate that the error in our determination of altitude is a small fraction of one scale height of the attenuating molecule (assuming an exponentially characterized atmosphere). We suggest how this method could be applied to rapidly determine a missile's direction of flight.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133914952","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

The development, demonstration and integration of advanced technologies to improve the life cycle costs of space systems 发展、示范和整合先进技术，以提高空间系统的生命周期成本

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495886

R. Vacek, M. Hopkins, W.H. MacPherson

{"title":"The development, demonstration and integration of advanced technologies to improve the life cycle costs of space systems","authors":"R. Vacek, M. Hopkins, W.H. MacPherson","doi":"10.1109/AERO.1996.495886","DOIUrl":"https://doi.org/10.1109/AERO.1996.495886","url":null,"abstract":"This paper will review some of the satellite technology developments that Phillips Lab is working on with industry and the system engineering approaches in use which are relevant to increasing the capability of small satellites. Small satellites become beneficial when they can deliver meaningful products at a reasonable cost. Technology, both evolutionary and revolutionary, is the key to capability. The technologies discussed will enable a reduction in size of satellites and significantly increase their capability. As small satellites become more capable, they will increasingly take over jobs that were once performed by large satellites. More satellites can be launched on any given launch vehicle thereby reducing launch costs. Small satellites can have the advantage of shorter production times, thereby decreasing cost and schedules. Integration efforts can achieve significant savings in weight, and realize increases in performance for both satellites. The Phillips Ground Demonstration Lab provides the capability to do ground demonstrations of integrated technologies in an environment that is traceable to space.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"144 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133948423","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

The Midcourse Space Experiment (MSX) 中途空间实验(MSX)

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495885

B. D. Guilmain

{"title":"The Midcourse Space Experiment (MSX)","authors":"B. D. Guilmain","doi":"10.1109/AERO.1996.495885","DOIUrl":"https://doi.org/10.1109/AERO.1996.495885","url":null,"abstract":"The MSX is designed and built around an infrastructure of eight scientific teams; it will be the first and only extended duration, multiwavelength (0.1 to 28 /spl mu/m) phenomenology measurement program funded and managed by BMDO. During its 16 month cryogen lifetime and five year satellite lifetime, MSX will provide high quality target, Earth, Earthlimb, and celestial multiwavelength phenomenology data. This data is essential to fill critical gaps in phenomenology and discrimination data bases, furthering development of robust models of representative scenes, and assessing optical discrimination algorithms. The MSX organization is comprised of self-directed work teams in six functional areas. Experiments formulated by each of the eight scientific teams will be executed on the satellite in a 903 km near polar orbit (99.23/spl deg/ inclination), with an eccentricity of 0.001, argument of perigee of 0, and the right ascension of the ascending node is 250.0025. Two dedicated target missions are planned consisting of one Strategic Target System launch and two Low Cost Launch Vehicles launches. These target missions will deploy various targets, enabling the MSX principal investigator teams to study key issues such as metric discrimination, deployment phase tracking, cluster tracking, fragment bulk filtering, tumbling re-entry vehicle signatures, etc. A data management infrastructure to ensure that the data is processed, analyzed, and archived will be available at launch time. The raw data and its associated calibration files and software will be archived, providing the customer with a cataloged database. This paper describes the MSX program objectives, target missions, data management architecture, and organization.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130021275","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: 23

Pressure sensitive paint flight test 压敏涂料飞行试验

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.499665

S. Houck, R. Hepp, M. J. Morris, M. Benne

引用次数: 6

SIR-C/X-SAR: An Advanced Radar SIR-C/X-SAR:一种先进雷达

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495910

F. Stuhr, R. Jordan, M. Werner

引用次数: 3

Near Earth asteroid rendezvous spacecraft overview 近地小行星交会航天器概览

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495972

A. Santo, S.C. Lee, A. Cheng

引用次数: 5

Adapting commercial satellites to military communication needs 使商业卫星适应军事通信需求

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.496078

L. Jocic, S.A. Hovanessian, J.K. Kreng, M. Schultz

{"title":"Adapting commercial satellites to military communication needs","authors":"L. Jocic, S.A. Hovanessian, J.K. Kreng, M. Schultz","doi":"10.1109/AERO.1996.496078","DOIUrl":"https://doi.org/10.1109/AERO.1996.496078","url":null,"abstract":"Increased reliance on commercial equipment by the military is necessary in today's defense environment. Potential cost reductions due to leveraging off the commercial satellite communication (satcom) base are a strong factor in planning for future military satcom (milsatcom) systems. Commercial satcom services are being extended to the \"Ka\" frequency band (30/20 GHz) to accommodate increasing demands for higher throughput and smaller ground terminals. Similar demands are being made of milsatcom systems. Military unique requirements for jam resistance, however, will likely precipitate the need to modify commercial designs. This paper describes a simple approach to add interference protection to a notional, broadband, transparent Ka-band satellite built for commercial satcom needs. Frequency hopping and channelized filtering of individual signals are added on-board the satellite, while signal processing is done on the ground. Unlike current advanced milsatcom designs, the signals are not demodulated on the satellite. Antenna nulling could also be added, if necessary, to the beam-shaping antennas. Two operational modes could be incorporated. In the wide-band mode, the payload can provide commercial-like high-data-rate and direct broadcast services. In the anti-jam hopping mode, the satcom payload is compatible with existing medium-data-rate military processing terminals. With individual satellite channels dedicated to each user network, network control is simplified through elimination of the need for power balancing among simultaneous users of the same wideband transponder.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130726312","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