Spacecraft Design for Multipurpose Solar Electric Propulsion Missions PDF Download
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Author: J. H. Molitor
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 36
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Author: J. H. Molitor
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 36
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721583942
Category :
Languages : en
Pages : 34
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Book Description
This presentation reviews Solar Electric Propulsion (SEP) Mission Architectures with a slant towards power system technologies and challenges. The low-mass, high-performance attributes of SEP systems have attracted spacecraft designers and mission planners alike and have led to a myriad of proposed Earth orbiting and planetary exploration missions. These SEP missions are discussed from the earliest missions in the 1960's, to first demonstrate electric thrusters, to the multi-megawatt missions envisioned many decades hence. The technical challenges and benefits of applying high-voltage arrays, thin film and low-intensity, low-temperature (LILT) photovoltaics, gossamer structure solar arrays, thruster articulating systems and microsat systems to SEP spacecraft power system designs are addressed. The overarching conclusion from this review is that SEP systems enhance, and many times enable, a wide class of space missions. Kerslake, Thomas W. Glenn Research Center NASA/TM-2003-212456, NAS 1.15:212456, E-13995
Author: Mudar Sadi Abu-Saymeh
Publisher:
ISBN:
Category : Space trajectories
Languages : en
Pages : 152
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 82
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721679263
Category :
Languages : en
Pages : 30
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Book Description
A study was conducted that shows how a single Radioisotope Electric Propulsion (REP) spacecraft design could be used for various missions throughout the solar system. This spacecraft design is based on a REP feasibility design from a study performed by NASA Glenn Research Center and the Johns Hopkins University Applied Physics Laboratory. The study also identifies technologies that need development to enable these missions. The mission baseline for the REP feasibility design study is a Trojan asteroid orbiter. This mission sends an REP spacecraft to Jupiter s leading Lagrange point where it would orbit and examine several Trojan asteroids. The spacecraft design from the REP feasibility study would also be applicable to missions to the Centaurs, and through some change of payload configuration, could accommodate a comet sample-return mission. Missions to small bodies throughout the outer solar system are also within reach of this spacecraft design. This set of missions, utilizing the common REP spacecraft design, is examined and required design modifications for specific missions are outlined. Fiehler, Douglas and Oleson, Steven Glenn Research Center NASA/TM-2004-213357, IAC-04-IAA.3.6.4.01, E?14825
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721572557
Category :
Languages : en
Pages : 34
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This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for system voltages of 28-V, 50-V, 120-V, and 300-V using state-of-the-art or advanced technologies. A 300-V 'direct-drive' architecture was also analyzed to assess the benefits of directly powering the electric thruster from the photovoltaic array without up-conversion. Fortran and spreadsheet computational models were exercised to predict the performance and size power system components to meet spacecraft mission requirements. Pertinent space environments, such as electron and proton radiation, were calculated along the spiral trajectory. In addition, a simplified electron current collection model was developed to estimate photovoltaic array losses for the orbital plasma environment and that created by the thruster plume. The secondary benefits of power system mass savings for spacecraft propulsion and attitude control systems were also quantified. Results indicate that considerable spacecraft wet mass savings were achieved by the 300-V and 300-V direct-drive architectures. Kerslake, Thomas W. Glenn Research Center NASA/TM-2003-212304, E-13876, NAS 1.15:212304
Author: William C. Strack
Publisher:
ISBN:
Category : Electric propulsion
Languages : en
Pages : 28
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Current technology for solar-electric propulsion is used to assess the potential performance advantages of low-thrust propulsion for an out-of-the-ecliptic mission. Simple normal-to-the-orbit thrust steering is assumed with coast subarcs permitted. The electric spacecraft is launched onto an Earth escape trajectory by an Atlas (SLV3C)-Centaur or a Titan IIIC. Comparisons with a similarly launched uprated Burner II stage reveal that significant performance gains are possible using the electric stage with 250- to 475-day flight times.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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