1996 IEEE Aerospace Applications Conference. Proceedings最新文献_第7页

A new Deep Space Network for the next century 下个世纪的新深空网络

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495884

L. Deutsch

{"title":"A new Deep Space Network for the next century","authors":"L. Deutsch","doi":"10.1109/AERO.1996.495884","DOIUrl":"https://doi.org/10.1109/AERO.1996.495884","url":null,"abstract":"NASA's Deep Space Network (DSN) is responsible for providing communications, tracking, and science services to most of the world's non-geostationary spacecraft that travel beyond low Earth orbit. Changes occurring to the DSN's customers are forcing the DSN to change substantially. Spacecraft tracked by the DSN are becoming smaller and cheaper, while still requiring significant science returns. This places increased demands on the DSN to adopt new technologies and improve the quality of the services it provides. Some of these technologies include beam waveguide antennas, Ka-band communications, cooled HEMT amplifiers, adaptive microwave optics, new error correcting codes, and ultra-stable ionic frequency standards. At the same time, budget constraints from NASA have resulted in a significant decrease in funds spent on mission operations-including the DSN. This means the DSN must adopt all this new technology while halving the average cost for each tracking hour it provides. The DSN will achieve this increase in efficiency by a complete reengineering of its operations processes-redefining operations jobs and taking advantage of advances in information systems technology and automation. This paper describes both the new technologies and new operations concepts that, together, will allow the DSN to continue its leadership in deep space communications and tracking.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"1 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":"126145069","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: 5

Genetic algorithm design of antenna arrays 天线阵列的遗传算法设计

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495875

R. Haupt

引用次数: 29

Unwanted microwave oscillator frequency shifts induced by bipolar junction transistor die attach 由双极结晶体管芯片引起的不必要的微波振荡器频移

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.499682

T. Folk, L. Mallette, J. Ulmer

引用次数: 0

Improved efficiency for users of the Global Positioning System 提高全球定位系统用户的使用效率

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.499410

W. Straka, W. Gregorwich

引用次数: 1

Hypercars: the next Industrial Revolution 超级跑车:下一次工业革命

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495873

A. Lovins

引用次数: 44

A new family of microcontrollers simplify aerospace communications systems 一个新的微控制器家族简化了航空航天通信系统

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495899

A. Jackson

{"title":"A new family of microcontrollers simplify aerospace communications systems","authors":"A. Jackson","doi":"10.1109/AERO.1996.495899","DOIUrl":"https://doi.org/10.1109/AERO.1996.495899","url":null,"abstract":"Recent advances in very large scale integrated (VLSI) semiconductors have led to a family of advanced microcontrollers that can be of great benefit to designers of aerospace communications systems. This paper discusses some of the important technological breakthroughs made possible by the alliance of IBM, Motorola and Apple Computer, that culminated in the PowerPC microprocessor. This architecture is now being used in a new, powerful family of communications controllers that are described in this paper. The Motorola MPC860, also referred to as the Power QUICC, is a new family of high-speed communications controllers designed for a wide range of data communication applications. This family currently includes five devices. Typical aerospace applications include navigation and control systems, local area networks (LANs), wide area networks (WANs), bridges, routers and digital voice/data systems for aircraft and spacecraft. This new PowerPC-based family of microcontrollers can greatly improve and simplify the design of aerospace communications systems. The MPC860 family combines a PowerPC core processor in conjunction with a powerful communications module on the same die. The PowerPC, a reduced instruction set computing (RISC) processor, is one of the most powerful processors available today. The communications processor, also of a RISC-based design, automatically handles various communication protocols. To help promote cost-effective designs, each chip includes additional system functions such as a memory controller and a PCMCIA interface. Members of the family offer various combinations of the number of serial communications channels (10 megabits per second each) and available communication protocols. This paper presents a brief review of the development of the PowerPC Architecture and describes the innovations made by the unique PowerPC design team composed of Apple, IBM and Motorola employees at the Somerset Design Center in Austin, Texas. The MPC860 is then described and a number of typical aerospace applications are explored.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"122 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":"121479958","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

A revolution in robotic space exploration: ten times as many missions at ten percent of the cost per mission 机器人太空探索的革命:十倍的任务，每项任务的成本是十分之一

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495978

J.L. Smith

引用次数: 2

Mars Pathfinder flight system design and implementation 火星探路者飞行系统的设计与实现

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495974

B. Muirhead

{"title":"Mars Pathfinder flight system design and implementation","authors":"B. Muirhead","doi":"10.1109/AERO.1996.495974","DOIUrl":"https://doi.org/10.1109/AERO.1996.495974","url":null,"abstract":"This paper describes the system architecture, design and implementation highlights for the Mars Pathfinder flight system scheduled to land on the surface of Mars on July 4, 1997. Mars Pathfinder is one of the new series of small, challenging missions doing significant science/engineering on a fast schedule and cost capped budget. The Mars Pathfinder spacecraft is actually three spacecraft: cruise stage, entry vehicle and lander. The cruise stage carries the entry and lander vehicles to Mars and is jettisoned prior to entry. The entry vehicle, including aeroshell, parachute and deceleration rockets, protects the lander during the direct entry and reduces its velocity from 7.6 to 0 km/s in stages during the 5 minute entry sequence. The lander's touchdown is softened by airbags which are retracted once stopped on the surface. The lander then uprights itself opens up fully and begins surface operations including deploying its camera and rover. The project is 2 years into its 3 year development cycle with most flight hardware delivered and in system test. This paper overviews the mission design, system architecture and configuration. Descriptions of key subsystems are given, including the entry, descent and landing system elements. The implementation approach is discussed from the point of view of the new ways of doing business needed to accomplish this challenging mission within the schedule and cost constraints.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"102 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":"122603443","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: 9

Transition Region and Coronal Explorer Mission 过渡区和日冕探测任务

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495926

I. J. Burt

{"title":"Transition Region and Coronal Explorer Mission","authors":"I. J. Burt","doi":"10.1109/AERO.1996.495926","DOIUrl":"https://doi.org/10.1109/AERO.1996.495926","url":null,"abstract":"The Transition Region and Coronal Explorer (TRACE) mission is the fourth mission in the Small Explorer (SMEX) program series at the National Aeronautics and Space Administration's Goddard Space Flight Center. The primary objective of the TRACE mission is to explore the connections between the fine scale magnetic fields in the solar surface and features in the solar photosphere, chromosphere, transition region, and corona. The TRACE spacecraft, including the instrument, weighs 250 kilograms, uses 200 watts of power, and will cost approximately 35 million dollars for the entire mission. It will launch into a Sun-synchronous Low Earth Orbit (LEO) in September 1997 and collect movie-like images of the Sun with one are second spatial and 1 second temporal resolution; these images will be made available on the Internet daily. This paper shows NASA's approach to small spacecraft development It discusses some trades in the design of each subsystem to accommodate instrument and spacecraft heritage as well as new mission requirements. Topics include: a solid state Command and Data Handling (C&DH) system, solid state memory using 20 Megabyte modules approximately 1\"/spl times/1\"/spl times/0.2\" each; a fully digital Attitude Control System (ACS); a guide telescope fine error sensor for spacecraft attitude and control as well as image motion compensation to better than are second levels. Adaptations in ground systems and operations are also included as well as the systems engineering approach.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"83 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":"123182770","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

Autonomous attitude determination and control system for the Orsted satellite 奥斯特卫星自主姿态确定与控制系统

1996 IEEE Aerospace Applications Conference. Proceedings Pub Date : 1996-02-03 DOI: 10.1109/AERO.1996.495975

Thomas Bak, Rafal Wisniewski, M. Blanke

{"title":"Autonomous attitude determination and control system for the Orsted satellite","authors":"Thomas Bak, Rafal Wisniewski, M. Blanke","doi":"10.1109/AERO.1996.495975","DOIUrl":"https://doi.org/10.1109/AERO.1996.495975","url":null,"abstract":"The Orsted satellite mission imposes comparatively high requirements on autonomy of the attitude control system. Cost requirements, on the other hand, impose simple hardware and cheap actuators in form of magnetorquer coils. These conflicting requirements are fulfilled through development of novel attitude and control algorithms and wide on-board autonomy. The entire control and attitude determination system has the ability to reconfigure in real time, based on mission phase and contingency operation requirements. Attitude determination embraces three different strategies, dependent on the availability of attitude sensors. Possible sensor faults are detected and a control system supervisor autonomously reconfigures attitude determination. Estimated satellite attitude and angular velocity are used in the attitude controller. Control tasks vary with the mission phase. Initially, after release from the launch vehicle, the angular velocity is controlled. In subsequent mission phases, the satellite is three-axis stabilized. The main contributions are development of novel algorithms for attitude control applying magnetic torquing, attitude determination schemes based on the geomagnetic field measurements, and integration into a supervisory control architecture. The salient feature of this system is fault tolerant autonomous operation with a minimum of hardware redundancy.","PeriodicalId":262646,"journal":{"name":"1996 IEEE Aerospace Applications Conference. Proceedings","volume":"53 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":"130106397","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: 38