Solar power system analyses for electric propulsion missions
نویسندگان
چکیده
منابع مشابه
Electric Propulsion for Solar System Exploration
The use of ion propulsion for deep-space missions will become a reality in 1998 with the ight of the ion-propelled, New Millennium Deep Space 1 (DS1) spacecraft. The anticipation of this event is stimulating the call for improved ion propulsion technologies, a trend that is expected to continue. This paper describes the evaluation of possible advanced solar electric propulsion technologies an...
متن کاملPower Accounting for Ship Electric Propulsion
Coarse and accurate power accounting methods for ship electric propulsion are observed and compared. For the purpose of analysis, the propulsion system has been separated into two units, namely the ship load and the motor drive. In the load model, variation of such factors like static and dynamic hull resistance and efficiency is explored while the supply characteristics, drive loading, propell...
متن کاملPerformance Characterization of the Low-Power Halo Electric Propulsion System
Performance measurements have been obtained of a novel propulsion concept called the Halo thruster under developmentwithin theUniversity of Surrey. TheHalo thruster, a type of cusped-field thrusterwith close similarity to the cylindrical Hall thruster, is motivated by the need for low-power and low-cost electric propulsion for the small satellite sector. Two versions of the device are investiga...
متن کاملSolar Electric Performance for Medlite and Delta Class Planetary Missions
The current emphasis on small, low-cost planetary missions using Delta and Medlite Class launch vehicles has prompted the examination of the use of Solar Electric Propulsion (SEP) spacecraft to either enable or enhance the performance of some of the more demanding planetary missions. Planetary missions that appear most attractive for a small solar electric propulsion system include those missio...
متن کاملConcept designs for NASA’s Solar Electric Propulsion Technology Demonstration Mission
Multiple Solar Electric Propulsion Technology Demonstration Mission were developed to assess vehicle performance and estimated mission cost. Concepts ranged from a 10,000 kg spacecraft capable of delivering 4000 kg of payload to one of the Earth Moon Lagrange points in support of future human-crewed outposts to a 180 kg spacecraft capable of performing an asteroid rendezvous mission after launc...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: IEEE Aerospace and Electronic Systems Magazine
سال: 2001
ISSN: 0885-8985
DOI: 10.1109/62.894171