IRJET- Electric propulsion system -ION Thruster (original) (raw)
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Review of Scientific Instruments
The transition from OLD SPACE to NEW SPACE along with increasing commercialization has a major impact on space flight, in general, and on electric propulsion (EP) by ion thrusters, in particular. Ion thrusters are nowadays used as primary propulsion systems in space. This article describes how these changes related to NEW SPACE affect various aspects that are important for the development of EP systems. Starting with a historical overview of the development of space flight and of the technology of EP systems, a number of important missions with EP and the underlying technologies are presented. The focus of our discussion is the technology of the radio frequency ion thruster as a prominent member of the gridded ion engine family. Based on this discussion, we give an overview of important research topics such as the search for alternative propellants, the development of reliable neutralizer concepts based on novel insert materials, as well as promising neutralizer-free propulsion concepts. In addition, aspects of thruster modeling and requirements for test facilities are discussed. Furthermore, we address aspects of space electronics with regard to the development of highly efficient electronic components as well as aspects of electromagnetic compatibility and radiation hardness. This article concludes with a presentation of the interaction of EP systems with the spacecraft.
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...
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).
Electric Propulsion: Systems Analysis and Potential Application in Space Exploration
Electric propulsion is a technology which has the potential to achieve success in deep space interstellar travel as well as space tourism. Electric propulsion is the new age technology, emerging into a more practical concept and enabling us to foster new capabilities and achievements for space missions. The first phase of electric propulsion i.e. the history accounts from the first electric propulsion demonstration of Ion propulsion in SERT-1, 1964 to the NSTAR thruster which has 16,246 hours of operation and the successful missions to which electric propulsion was associated. The purity of the concept is embedded in the understanding of fundamentals and principles i.e. rocket acceleration ∝ discharge of propellant mass, its equation of motion follows directly from conservation of the total momentum of the spacecraft and its exhaust stream matching the propeller and the engine, one must pay particular attention to the dependency between the power P and the generated thrust k. Electric propulsion systems and its particular application-based design is classified in ion & plasma drives and non-ion drives, where the former is sub-classified in electrostatic, electrothermal and electromagnetic propulsion while the latter into photonic propulsion and unconventional propulsion. The comparative analysis provides critical information about the parameters deciding its application in real time scenario such as exhaust emission, efficiency, SPED value, power-to-weight ratio along with the future scope for potential research.
IRJET- A REVIEW ON ION THRUSTER PLASMA GENERATORS
IRJET, 2020
Ion thrusters are characterized by electrostatic acceleration of ions extracted from the plasma generators. This paper discusses the construction and working principles of plasma generators used in space flight, we would discussing the four primary thruster designs namely the DC ion generator, Kaufmann generator, RF generators & Microwave generators.
Development of a Prototype Model Ion Thruster for the NEXT System
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004
The NASA Evolutionary Xenon Thruster (NEXT) program, led by the NASA Glenn Research Center, is developing the next generation of ion thruster systems for solar system exploration. The team is led by NASA Glenn Research Center and includes Aerojet, the Jet Propulsion Lab, and Boeing. Aerojet is responsible for the development of the Prototype Model Electric Propulsion Thruster, the Engineering Model Propellant Management System, and the Digital Control Interface Unit simulator. The thruster has a 40cm beam diameter, providing twice the effective area of the NASA Solar electric propulsion Technology Application Readiness (NSTAR) thruster. All efforts have been made to preserve critical design heritage from NSTAR while also incorporating new technologies and processes to extend power, throttle range and throughput, reduce specific mass, and minimize cost. In Phase 1, NASA Glenn developed the Engineering Model thruster design, produced three thrusters, and conducted performance, wear, vibration and integration testing. This paper describes Aerojet's Phase 2 program to design, build and deliver two Prototype Model thrusters to support performance, environmental and system integration testing. The paper reviews the lessons learned and design heritage maintained from the NSTAR flight and extended life test units, and the Engineering Model NEXT thrusters. The principal design features of the Prototype Model NEXT thruster, discharge cathode and neutralizer cathode are outlined. Finally, the results of structural and thermal analysis are presented.
IRJET- OPERATION AND GENERATION OF ION WIND IN ION THRUSTER
IRJET, 2020
Ion propulsion is one of the advanced propulsion methods for space travel when significant amount of thrust is not required. In other words, an ion thruster or ion drive is a form of electric propulsion used for spacecraft propulsion. It is still under research facility in their improvement stage. In this type of propulsion any natural gas is ionized by the electrons which is been extracted by the atoms of specific elements resulting in large number of positive ions which is based upon electrostatics. This paper is based on the operation and generation of the ion wind by an ion thruster. The process involves in the space between the sharp edge object and the smooth edge object which is connected to each other by a high voltage source. The basic principle and the complete one to one activity of the release of electrons from the sharp object to the generation of ion wind and how do charged particles gain their speed in an electric field that is the variation in kinetic energy of the particles are explained.
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.
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