Electric Propulsion: Systems Analysis and Potential Application in Space Exploration (original) (raw)
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Spacecraft Electric Propulsion – A review
A short review of the status of electric propulsion (EP) is presented to serve as an introduction to the more specialized technical papers. The principles of operation and the several types of thrusters that are either operational or in advanced development are discussed. The stimulus for development of electrically driven space propulsion systems is nothing less fundamental than Newton’s laws of dynamics. Since a rocket propelled spacecraft in free flight derives its only acceleration from discharge of propellant mass, its equation of motion follows directly from conservation of the total momentum of the spacecraft and its exhaust stream. Keywords: Electric propulsion, thrusters, rocket, propellant, spacecraft
iii Many spacecraft application are now focusing on using electric propulsion technology, because, electric propulsion technology has not yet only proven its sound engineering solution but also has proven how cost effective it can be. In recent years more experiment have been done on the electric propulsion for example; In Chemical Propulsion Information System, form 1960 to 1997 it was only 100 spacecraft which had flown 300 electric propulsion. But since 1998 to 2010 which is a short period of time compared to the previous, more than 150 spacecraft have used I one way or the other the electric propulsion devices.
Spacecraft Electric Propulsion -An Overview
A short review of the status of electric propulsion (EP) is presented to serve as an introduction to the more specialized technical papers also appearing in this Special Issue (Journal of Propulsion and Power, Vol. 14, No. 5, Sept. -Oct. 1998). The principles of operation and the several types of thrusters that are either operational or in advanced development are discussed rst, followed by some considerations on the necessary power sources. A few prototypical missions are then described to highlight the operational peculiarities of EP, including spacecraft interactions. We conclude with a historical summary of the accumulated ight experience using this technology.
Electric Propulsion Concepts Enabled by High Power Systems for Space Exploration
2nd International Energy Conversion Engineering Conference, 2004
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Activities In Electric Propulsion Development at IRS
Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan, 2009
More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme=IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. Among the described electric propulsion systems are recent developments in the field of applied field MPD but also from high power hybrid thrusters. In addition, new concepts such as the hybrid systems Thermal-Inductively heated Hybrid-Thruster of the University of Stuttgart (TIHTUS) and the so-called Coupled Tether/Ion Engine Propulsion (CETEP) are analysed.
Overview on Electric Propulsion Development at IRS
More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme = IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. In addition, several advanced plasma propulsion designs have been developed and characterized at IRS in the past 10 years. Among them are the hybrid thruster TIHTUS, steady state...
Electric Propulsion: Which One For My Spacecraft?
2000
this article as a pointer to otherdocumentation sources as it is not meant to be an authoritative source of principles, design requirements,constraints, or data. Be also cautioned that research for the article tapped the resources of theworld wide web extensively, and many of the references point to pages which have half-lives shorterthan academic cycles. Occasionally, more conventional references are cited
Electric Propulsion Research and Development at JPL
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
Electric propulsion enables many missions that satisfy the strategic goals of JPL and NASA to explore our Solar System, to detect "other earths" in neighboring planetary systems, and to search for life beyond the confines of Earth. Electric propulsion (EP) technology development at JPL is designed to support these types of JPL missions by introducing and infusing new technologies into JPL projects. In this paper, we will describe the EP technologies of interest and our role in developing and interjecting these technologies into JPL missions. Our technical approach is to understand the basic physics of the devices with sufficient fidelity to provide performance and life models critical to mission planning and assurance. In some cases, advanced capabilities and unique facilities enable us to lead in the development of the thruster technology. In addition, we actively investigate the EP plume interactions with spacecraft to ensure that the instruments and power components not compromised by the EP system and that the mission goals can be satisfied.
Electromagnetic propulsion for spacecraft
Nasa Sti Recon Technical Report N, 1993
Three electromagnetic propulsion technologies, solid propellant pulsed plasma thrusters (PPT), magnetoplasmadynamic (MPD) thrusters, and pulsed inductive thrusters (PIT) have been developed for application to auxiliary and primary spacecraft propulsion. Both the PPT and MPD thrusters have been flown in space, though only PPTs have been used on operational satellites. The performance of operational PPTs is quite poor, providing only about 8 percent efficiency at about 1000 sec specific impulse. Laboratory PPTs yielding 34 percent efficiency at 5170 sec specific impulse have been demonstrated. Laboratory MPD thrusters have been demonstrated with up to 70 percent efficiency and 7000 sec specific impulse. Recent PIT performance measurements using ammonia and hydrazine propellants are extremely encouraging, reaching 50 percent efficiency for specific impulses between 4000 and 8000 sec.
Overview on Electric Propulsion Developments at IRS
2011
More than three decades of experience have been gained in the field of electric propulsion at the Institute of Space Systems (Institut für Raumfahrtsysteme = IRS). Recent developments within the field of electric propulsion are summarized and foremost results are highlighted. The various types of electric propulsion systems are not considered as to be competitive. Here, system analysis shows that optimum parameter such as the required exhaust velocity or specific impulse result taking into account both the mission profile and system related sizes such as the power conditioner efficiency, the thrust efficiency and the specific mass of the corresponding power unit. Correspondingly, ion thrusters, Hall thrusters, thermal arcjets, or magnetoplasmadynamics (MPD) thrusters are preferable depending on the mission. In addition, several advanced plasma propulsion designs have been developed and characterized at IRS in the past 10 years. Among them are the hybrid thruster TIHTUS, steady state applied field thrusters and the iMPD IMAX. These concepts have been experimentally and numerically characterized and show promising potential for future missions. The paper will discuss the design and the operational features of the devices. In addition, more advanced systems are under investigation. Here, a focus is in the field of fusion driven systems and M2P2 (magnetic sail systems).