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Advanced Electric Propulsion System
Rowan Forest: Creating article on ion engine: Advanced Electric Propulsion System ('''AEPS''')
'''Advanced Electric Propulsion System''' ('''AEPS''') is a [[solar electric propulsion]] system for spacecraft that is being designed, developed and tested by [[NASA]] and [[Aerojet Rocketdyne]] for large-scale science missions and cargo transportation.<ref name='AEPS 2017'>[https://ift.tt/2OorcqL Overview of the Development and Mission Application of the Advanced Electric Propulsion System (AEPS)]. (PDF). Daniel A. Herman, Todd A. Tofil, Walter Santiago, Hani Kamhawi, James E. Polk, John S. Snyder, Richard R. Hofer, Frank Q. Picha, Jerry Jackson and May Allen. NASA; NASA/TM—2018-219761. 35th International Electric Propulsion Conference. Atlanta, Georgia, October 8–12, 2017. Accessed: 27 July 2018.</ref> It is "the most likely engine"<ref name='AEPS 2017'/> to propel the PPE module of the planned [[Lunar Orbital Platform-Gateway]] to be launched in 2022. Four identical AEPS engines would consume most of the 50 kW generated by solar power.<ref name='AEPS 2017'/>
The Power and Propulsion Element (PPE) for the Lunar Gateway will have a mass of 8-9 metric tons and will be capable of generating 50 kW<ref name='Nov 3'>[https://ift.tt/2yudTAu NASA issues study contracts for Deep Space Gateway element]. Jeff Foust, ''Space News''. 3 November 2017.</ref> of [[solar electric power]] for its [[ion thruster]]s for maneuverability, which can be supported by chemical propulsion.<ref name="Flight_20170406"></ref>
==Overview==
Solar-electric propulsion has shown to be reliable, efficient and allows a significant mass reduction of spacecraft. High-power solar electric propulsion is a key technology that has been prioritized because of its significant exploration benefits in cis-lunar space and crewed missions to Mars.<ref name='AEPS 2017'/>
The AEPS Hall thruster system was originally developed since 2015 by [[NASA Glenn Research Center]] and the [[Jet Propulsion Laboratory]] to be used on the now cancelled [[Asteroid Redirect Mission]]. Work on the thruster did not stop following the mission cancellation in April 2017 because there is demand of such thrusters for a range of NASA, defense and commercial missions in deep space.<ref name='AEPS 2017'/><ref name="defunded"></ref><ref name='Rocketdyne 2016'/> Since May 2016,<ref>[https://ift.tt/2hzqo5z NASA Works to Improve Solar Electric Propulsion for Deep Space Exploration]. NASA News. April 19, 2016. Accessed 27 July 2018.</ref> further work on AEPS has been transitioned to [[Aerojet Rocketdyne]] via a competitive contract, that is currently designing and testing the engineering-model hardware.<ref name='AEPS 2017'/>
==Preliminary design==
{| class="wikitable floatright"
|-
! AEPS !! Performance<ref name='AEPS 2017'/>
|-
| Power requirement || 40 kW
|-
| Maximum [[specific impulse]] (''I<sub>sp</sub>'') || 2,600 s
|-
| [[Thrust]] || 589 [[Newton (unit)|mN]]
|-
| Distance range from Sun || 0.8 to 1.7 [[Astronomical unit|AU]]
|-
| Input voltage range || 95 - 140 V
|-
| System mass || 100 kg x 4 engines
|-
| [[Xenon]] propellant mass || 5,000 kg
|}
AEPS is based on the 12.5 kW development model thruster called 'Hall Effect Rocket with Magnetic Shielding' (HERMeS). The AEPS solar electric engine makes use of the [[Hall-effect thruster]] in which the [[propellant]] is ionized and accelerated by an [[electric field]] to produce [[thrust]]. Four identical 14 kW AEPS engines would consume most the 50 kW generated by [[Solar panels on spacecraft|solar panels]]. <ref name='AEPS 2017'/>
The engineering model is also undergoing various vibration tests, thruster dynamic and thermal environment tests.<ref name='AEPS 2017'/> AEPS is expected to accumulate about 5,000 hr by the end of the contract and the design aims to achieve a flight model that offers a half-life of at least 23,000 hours<ref name='AEPS 2017'/> and a full life of about 50,000 hours.<ref name='Rocketdyne 2016'>[https://ift.tt/2vfF2D8 Aerojet Rocketdyne Signs Contract to Develop Advanced Electric Propulsion System for NASA]. Aerojet Rocketdyne. Press release, 28 April 2016. Accessed: 27 July 2018.</ref>
The three main components of the AEPS propulsion engine are: a Hall thruster, Power Processor Unit (PPU), and the Xenon Flow Controller (XFC). The thrusters are throatable over an input power range of 6.67 - 40 kW with input voltages ranging from 95 to
140 V.<ref name='AEPS 2017'/> The estimated [[xenon]] propellant mass for the Lunar Gateway would be 5,000 kg.<ref name='AEPS 2017'/> The Preliminary Design Review took place in August 2017.<ref>[https://ift.tt/2OorcXN 13kW Advanced Electric Propulsion Flight System Development and Qualification]. (PDF). Jerry Jackson, May Allen, Roger Myers, Erich Soendker, Benjamin Welander, Artie Tolentino, Chris Sheehan, Joseph Cardin, John Steven Snyder, Richard R. Hofer, Todd Tofil1, Dan Herman, Sam Hablitze and Chyrl Yeatts. The 35th International Electric Propulsion Conference. Atlanta, Georgia, USA. October 8 – 12, 2017.</ref> It was concluded that "The Power Processing Unit successfully demonstrated stable operation of the propulsion system and responded appropriately to all of our planned contingency scenarios."<ref>[https://ift.tt/2vfF3aa Advanced Electric Propulsion System successfully tested at NASA's Glenn Research Center]. Jason Rhian, ''Spaceflight Insider''. 8 July 2017.</ref>
==References==
Liquid error: wrong number of arguments (1 for 2)
[[Category:Hall effect]]
[[Category:Ion engines]]
[[Category:Magnetic propulsion devices]]
[[Category:Spacecraft propulsion]]
The Power and Propulsion Element (PPE) for the Lunar Gateway will have a mass of 8-9 metric tons and will be capable of generating 50 kW<ref name='Nov 3'>[https://ift.tt/2yudTAu NASA issues study contracts for Deep Space Gateway element]. Jeff Foust, ''Space News''. 3 November 2017.</ref> of [[solar electric power]] for its [[ion thruster]]s for maneuverability, which can be supported by chemical propulsion.<ref name="Flight_20170406"></ref>
==Overview==
Solar-electric propulsion has shown to be reliable, efficient and allows a significant mass reduction of spacecraft. High-power solar electric propulsion is a key technology that has been prioritized because of its significant exploration benefits in cis-lunar space and crewed missions to Mars.<ref name='AEPS 2017'/>
The AEPS Hall thruster system was originally developed since 2015 by [[NASA Glenn Research Center]] and the [[Jet Propulsion Laboratory]] to be used on the now cancelled [[Asteroid Redirect Mission]]. Work on the thruster did not stop following the mission cancellation in April 2017 because there is demand of such thrusters for a range of NASA, defense and commercial missions in deep space.<ref name='AEPS 2017'/><ref name="defunded"></ref><ref name='Rocketdyne 2016'/> Since May 2016,<ref>[https://ift.tt/2hzqo5z NASA Works to Improve Solar Electric Propulsion for Deep Space Exploration]. NASA News. April 19, 2016. Accessed 27 July 2018.</ref> further work on AEPS has been transitioned to [[Aerojet Rocketdyne]] via a competitive contract, that is currently designing and testing the engineering-model hardware.<ref name='AEPS 2017'/>
==Preliminary design==
{| class="wikitable floatright"
|-
! AEPS !! Performance<ref name='AEPS 2017'/>
|-
| Power requirement || 40 kW
|-
| Maximum [[specific impulse]] (''I<sub>sp</sub>'') || 2,600 s
|-
| [[Thrust]] || 589 [[Newton (unit)|mN]]
|-
| Distance range from Sun || 0.8 to 1.7 [[Astronomical unit|AU]]
|-
| Input voltage range || 95 - 140 V
|-
| System mass || 100 kg x 4 engines
|-
| [[Xenon]] propellant mass || 5,000 kg
|}
AEPS is based on the 12.5 kW development model thruster called 'Hall Effect Rocket with Magnetic Shielding' (HERMeS). The AEPS solar electric engine makes use of the [[Hall-effect thruster]] in which the [[propellant]] is ionized and accelerated by an [[electric field]] to produce [[thrust]]. Four identical 14 kW AEPS engines would consume most the 50 kW generated by [[Solar panels on spacecraft|solar panels]]. <ref name='AEPS 2017'/>
The engineering model is also undergoing various vibration tests, thruster dynamic and thermal environment tests.<ref name='AEPS 2017'/> AEPS is expected to accumulate about 5,000 hr by the end of the contract and the design aims to achieve a flight model that offers a half-life of at least 23,000 hours<ref name='AEPS 2017'/> and a full life of about 50,000 hours.<ref name='Rocketdyne 2016'>[https://ift.tt/2vfF2D8 Aerojet Rocketdyne Signs Contract to Develop Advanced Electric Propulsion System for NASA]. Aerojet Rocketdyne. Press release, 28 April 2016. Accessed: 27 July 2018.</ref>
The three main components of the AEPS propulsion engine are: a Hall thruster, Power Processor Unit (PPU), and the Xenon Flow Controller (XFC). The thrusters are throatable over an input power range of 6.67 - 40 kW with input voltages ranging from 95 to
140 V.<ref name='AEPS 2017'/> The estimated [[xenon]] propellant mass for the Lunar Gateway would be 5,000 kg.<ref name='AEPS 2017'/> The Preliminary Design Review took place in August 2017.<ref>[https://ift.tt/2OorcXN 13kW Advanced Electric Propulsion Flight System Development and Qualification]. (PDF). Jerry Jackson, May Allen, Roger Myers, Erich Soendker, Benjamin Welander, Artie Tolentino, Chris Sheehan, Joseph Cardin, John Steven Snyder, Richard R. Hofer, Todd Tofil1, Dan Herman, Sam Hablitze and Chyrl Yeatts. The 35th International Electric Propulsion Conference. Atlanta, Georgia, USA. October 8 – 12, 2017.</ref> It was concluded that "The Power Processing Unit successfully demonstrated stable operation of the propulsion system and responded appropriately to all of our planned contingency scenarios."<ref>[https://ift.tt/2vfF3aa Advanced Electric Propulsion System successfully tested at NASA's Glenn Research Center]. Jason Rhian, ''Spaceflight Insider''. 8 July 2017.</ref>
==References==
Liquid error: wrong number of arguments (1 for 2)
[[Category:Hall effect]]
[[Category:Ion engines]]
[[Category:Magnetic propulsion devices]]
[[Category:Spacecraft propulsion]]
July 28, 2018 at 08:29AM
