Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Download Spacecraft Design For Multipurpose Solar Electric Propulsion Missions full books in PDF, epub, and Kindle. Read online Spacecraft Design For Multipurpose Solar Electric Propulsion Missions ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author : J. H. Molitor
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (449 download)
Download or read book Spacecraft Design for Multipurpose Solar Electric Propulsion Missions written by J. H. Molitor and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721583942
Total Pages : 34 pages
Book Rating : 4.5/5 (839 download)
Download or read book Solar Electric Propulsion Mission Architectures written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 13 :
Total Pages : 152 pages
Book Rating : 4.:/5 (441 download)
Download or read book Mercury Mission Design Using Solar Electric Propulsion Spacecraft written by Mudar Sadi Abu-Saymeh and published by . This book was released on 1998 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Solar Electric Propulsion Mission Architectures written by and published by . This book was released on 2003 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 82 pages
Book Rating : 4.:/5 (317 download)
Download or read book Study of a Common Solar-electric-propulsion Upper Stage for High-energy Unmanned Missions. Volume 1 - Summary Final Report written by and published by . This book was released on 1971 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Structural Design Concepts for a Multi-megawatt Solar Electric Propulsion (SEP) Spacecraft written by and published by . This book was released on 1991 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721679263
Total Pages : 30 pages
Book Rating : 4.6/5 (792 download)
Download or read book Radioisotope Electric Propulsion Missions Utilizing a Common Spacecraft Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-21 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 13 : 9781721572557
Total Pages : 34 pages
Book Rating : 4.5/5 (725 download)
Download or read book Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Early Application of Solar-electric Propulsion to a 1-astronomical-unit Out-of-the-ecliptic Mission written by William C. Strack and published by . This book was released on 1970 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (317 download)
Download or read book Solar Power System Options for the Radiation and Technology Demonstration Spacecraft written by and published by . This book was released on 2000 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book Solar Power System Analyses for Electric Propulsion Missions written by and published by . This book was released on 1999 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : H. Schlingloff
Publisher :
ISBN 13 :
Total Pages : 7 pages
Book Rating : 4.:/5 (11 download)
Download or read book Trajectory Optimization Techniques with Application to Mission Design of Solar-electric Propulsion Spacecraft written by H. Schlingloff and published by . This book was released on 1987 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : H. S. Youssef
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Solar Electric Propulsion Cargo Spacecraft for Mars Missions written by H. S. Youssef and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
ISBN 13 : 9781728904511
Total Pages : 26 pages
Book Rating : 4.9/5 (45 download)
Download or read book Trajectory Optimization of an Interstellar Mission Using Solar Electric Propulsion written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-18 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents several mission designs for heliospheric boundary exploration using spacecraft with low-thrust ion engines as the primary mode of propulsion The mission design goal is to transfer a 200-kg spacecraft to the heliospheric boundary in minimum time. The mission design is a combined trajectory and propulsion system optimization problem. Trajectory design variables include launch date, launch energy, burn and coast arc switch times, thrust steering direction, and planetary flyby conditions. Propulsion system design parameters include input power and specific impulse. Both SEP and NEP spacecraft arc considered and a wide range of launch vehicle options are investigated. Numerical results are presented and comparisons with the all chemical heliospheric missions from Ref 9 are made. Kluever, Craig A. Glenn Research Center NAG3-1731
Author :
Publisher :
ISBN 13 :
Total Pages : 106 pages
Book Rating : 4.:/5 (317 download)
Download or read book Evaluation of the Use of On-board Spacecraft Energy Storage for Electric Propulsion Missions written by and published by . This book was released on 1983 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. National Aeronautics and Space Administration
Publisher :
ISBN 13 :
Total Pages : 1000 pages
Book Rating : 4.:/5 (35 download)
Download or read book NASA Technical Note written by United States. National Aeronautics and Space Administration and published by . This book was released on 1971 with total page 1000 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781723506031
Total Pages : 298 pages
Book Rating : 4.5/5 (6 download)
Download or read book Advanced Solar-Propelled Cargo Spacecraft for Mars Missions written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 298 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three concepts for an unmanned, solar powered, cargo spacecraft for Mars support missions were investigated. These spacecraft are designed to carry a 50,000 kg payload from a low Earth orbit to a low Mars orbit. Each design uses a distinctly different propulsion system: A Solar Radiation Absorption (SRA) system, a Solar-Pumped Laser (SPL) system and a solar powered magnetoplasmadynamic (MPD) arc system. The SRA directly converts solar energy to thermal energy in the propellant through a novel process. In the SPL system, a pair of solar-pumped, multi-megawatt, CO2 lasers in sunsynchronous Earth orbit converts solar energy to laser energy. The MPD system used indium phosphide solar cells to convert sunlight to electricity, which powers the propulsion system. Various orbital transfer options are examined for these concepts. In the SRA system, the mother ship transfers the payload into a very high Earth orbit and a small auxiliary propulsion system boosts the payload into a Hohmann transfer to Mars. The SPL spacecraft and the SPL powered spacecraft return to Earth for subsequent missions. The MPD propelled spacecraft, however, remains at Mars as an orbiting space station. A patched conic approximation was used to determine a heliocentric interplanetary transfer orbit for the MPD propelled spacecraft. All three solar-powered spacecraft use an aerobrake procedure to place the payload into a low Mars parking orbit. The payload delivery times range from 160 days to 873 days (2.39 years). Auziasdeturenne, Jacqueline and Beall, Mark and Burianek, Joseph and Cinniger, Anna and Dunmire, Barbrina and Haberman, Eric and Iwamoto, James and Johnson, Stephen and Mccracken, Shawn and Miller, Melanie Unspecified Center NASA-CR-186218, NAS 1.26:186218 NASW-4435...
