The Experts below are selected from a list of 2910 Experts worldwide ranked by ideXlab platform
Hitoshi Kuninaka - One of the best experts on this subject based on the ideXlab platform.
-
microwave discharge Ion Engines onboard hayabusa asteroid explorer
Journal of the Surface Science Society of Japan, 2012Co-Authors: Hitoshi KuninakaAbstract:The Hayabusa spacecraft rendezvoused with the asteroid Itokawa in 2005 after the powered flight in the deep space by the μl0 cathode‐less electron cyclotron resonance Ion Engines. Though the spacecraft was seriously damaged after the successful soft‐landing and lift‐off, the xenon cold gas jets from the Ion Engines rescued it. New attitude stabilizatIon method using a single reactIon wheel, the Ion beam jets, and the photon pressure was established and enabled the homeward journey from April 2007 aiming the Earth return on 2010. The total accumulated operatIonal time of the Ion Engines reaches 31,400 hours at the end of 2007. One of four thrusters achieved 13,400‐hour space operatIon.
-
discussIon on performance history and operatIons of hayabusa Ion Engines
Transactions of The Japan Society for Aeronautical and Space Sciences Space Technology Japan, 2012Co-Authors: Kazutaka Nishiyama, Hitoshi KuninakaAbstract:The μ10 cathode-less electron cyclotron resonance Ion Engines, have propelled the Hayabusa asteroid explorer for seven years since its launch in May 2003. The spacecraft was focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. The final stage of the return cruise and the subsequent trajectory correctIon maneuvers have been accomplished by using a special combined operatIon of neutralizer A and Ion source B after the exhaustIon of the other neutralizers' lives by the autumn of 2009. The total duratIon of the powered spaceflight was 25,590 h, which provided a delta-V of approximately 2.2 km/s and a total impulse of 1 MN·s. The degradatIon trends of the thruster performances have been investigated. It seems that the main cause of the degradatIon was the decrease in effective microwave power input to the discharge plasma induced by the increase in the transmissIon loss of the microwave feed system, and not due to the increase in the gas leakage through the accelerator grid apertures enlarged by erosIon. UnintentIonal engine stop events have been summarized and analyzed. Most of them occurred due to the limit check errors of the backward microwave powers. Such errors can be decreased by carefully monitoring the trend change in microwave backward power as a functIon of xenon flow rate in future missIons.
-
hayabusa s way back to earth by microwave discharge Ion Engines
46th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2010Co-Authors: Kazutaka Nishiyama, Hitoshi Kuninaka, Yukio Shimizu, Junichiro Kawaguchi, Satoshi Hosoda, Hiroyuki Koizumi, Ikkoh Funaki, Michael Bodendorfer, Daisuke NakataAbstract:The cathode-less electron cyclotron resonance Ion Engines, μ10, propelled the Hayabusa asteroid explorer, launched in May 2003, which is focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. It rendezvoused with the asteroid Itokawa after a two year deep space flight with a delta-V of 1.4 km/s, 22 kg of xenon propellant consumptIon and 25800 hours of total accumulated operatIonal time of all the four Ion Engines added up. Though it succeeded in landing on the asteroid on November 2005, the spacecraft was seriously damaged. This delayed the Earth return in 2010 from the original plan in 2007. ReconstructIon on the operatIonal scheme using remaining functIons and newly uploaded control logic made Hayabusa leave for Earth in April 2007. After a coasting period of 2008, the Ion propulsIon was reignited in February 2009. Although most of the neutralizers were degraded and unable to be used by fall of 2009, a combinatIon of an Ion source and its neighboring neutralizer has been successfully operated for the last 3230 hours including a series of final trajectory correctIon maneuvers. Before reentry, the total accumulated operatIonal time reached 39637 hours consuming a total of 47 kg Xenon propellant. Total duratIon of powered spaceflight is 25590 hours which provided a delta-V of 2.2 km/s and a total impulse of 1 MN·s, approximately. Finally, the spacecraft returned to Earth. Its reentry capsule, which may contain samples from asteroid Itokawa, was retrieved from the Australian outback according to plan .
-
antenna design method for low power miniaturized microwave discharge Ion Engines
Journal of The Japan Society for Aeronautical and Space Sciences, 2009Co-Authors: Hiroyuki Koizumi, Hitoshi KuninakaAbstract:In this study, we succeeded to develop a very low power miniaturized Ion engine powered by microwave discharge. The accomplished performance was Ion productIon cost of 240W/A and propellant utilizatIon efficiency of 39% by input microwave power 1.0W and mass flow rate of 0.15sccm. In order to realize this very low power operatIon, we have proposed an antenna design method for miniaturized microwave Ion Engines. The effectiveness of this method was verified by plasma observatIon inside the discharge chamber and Ion beam extractIon characteristics of the engine. Based on this method, antenna of the engine was designed and improved. As a result we have achieved to our goal.
-
lineup of microwave discharge Ion Engines μ series
한국추진공학회 학술대회논문집, 2008Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroshi Hayashi, Hiroyuki KoizumiAbstract:Institute of Space and Astronautical Science of Japan Aerospace ExploratIon Agency (ISAS/JAXA) successfully developed and operated the microwave discharge Ion Engines onboard Hayabusa asteroid explorer. The μ10 Ion Engines feature the cathode-less plasma generatIon in both the Ion generators and neutralizers with the results of long life and high reliability in space. Based on the space achievements of μ10 Ion Engines with 8mN thrust, 3,000sec Isp and 350W consumptIon power, several programs are currently under developments: μ20, μ10HIsp and μ1. The first is a 20-cm diameter microwave discharge Ion engine, aiming to achieve 30mN/kW in the thrust-to-power ratio for the asteroid sample return missIon larger than Hayabusa. The second is a high Isp versIon of μ10, and exhausts the plasma beam over 10,000sec Isp using 15kV acceleratIon voltage for deep space missIons to such as Jupiter and Mercury. The third is μ1 to be adapted to small satellites for drag-free.
Kazutaka Nishiyama - One of the best experts on this subject based on the ideXlab platform.
-
discussIon on performance history and operatIons of hayabusa Ion Engines
Transactions of The Japan Society for Aeronautical and Space Sciences Space Technology Japan, 2012Co-Authors: Kazutaka Nishiyama, Hitoshi KuninakaAbstract:The μ10 cathode-less electron cyclotron resonance Ion Engines, have propelled the Hayabusa asteroid explorer for seven years since its launch in May 2003. The spacecraft was focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. The final stage of the return cruise and the subsequent trajectory correctIon maneuvers have been accomplished by using a special combined operatIon of neutralizer A and Ion source B after the exhaustIon of the other neutralizers' lives by the autumn of 2009. The total duratIon of the powered spaceflight was 25,590 h, which provided a delta-V of approximately 2.2 km/s and a total impulse of 1 MN·s. The degradatIon trends of the thruster performances have been investigated. It seems that the main cause of the degradatIon was the decrease in effective microwave power input to the discharge plasma induced by the increase in the transmissIon loss of the microwave feed system, and not due to the increase in the gas leakage through the accelerator grid apertures enlarged by erosIon. UnintentIonal engine stop events have been summarized and analyzed. Most of them occurred due to the limit check errors of the backward microwave powers. Such errors can be decreased by carefully monitoring the trend change in microwave backward power as a functIon of xenon flow rate in future missIons.
-
hayabusa s way back to earth by microwave discharge Ion Engines
46th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2010Co-Authors: Kazutaka Nishiyama, Hitoshi Kuninaka, Yukio Shimizu, Junichiro Kawaguchi, Satoshi Hosoda, Hiroyuki Koizumi, Ikkoh Funaki, Michael Bodendorfer, Daisuke NakataAbstract:The cathode-less electron cyclotron resonance Ion Engines, μ10, propelled the Hayabusa asteroid explorer, launched in May 2003, which is focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. It rendezvoused with the asteroid Itokawa after a two year deep space flight with a delta-V of 1.4 km/s, 22 kg of xenon propellant consumptIon and 25800 hours of total accumulated operatIonal time of all the four Ion Engines added up. Though it succeeded in landing on the asteroid on November 2005, the spacecraft was seriously damaged. This delayed the Earth return in 2010 from the original plan in 2007. ReconstructIon on the operatIonal scheme using remaining functIons and newly uploaded control logic made Hayabusa leave for Earth in April 2007. After a coasting period of 2008, the Ion propulsIon was reignited in February 2009. Although most of the neutralizers were degraded and unable to be used by fall of 2009, a combinatIon of an Ion source and its neighboring neutralizer has been successfully operated for the last 3230 hours including a series of final trajectory correctIon maneuvers. Before reentry, the total accumulated operatIonal time reached 39637 hours consuming a total of 47 kg Xenon propellant. Total duratIon of powered spaceflight is 25590 hours which provided a delta-V of 2.2 km/s and a total impulse of 1 MN·s, approximately. Finally, the spacecraft returned to Earth. Its reentry capsule, which may contain samples from asteroid Itokawa, was retrieved from the Australian outback according to plan .
-
lineup of microwave discharge Ion Engines μ series
한국추진공학회 학술대회논문집, 2008Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroshi Hayashi, Hiroyuki KoizumiAbstract:Institute of Space and Astronautical Science of Japan Aerospace ExploratIon Agency (ISAS/JAXA) successfully developed and operated the microwave discharge Ion Engines onboard Hayabusa asteroid explorer. The μ10 Ion Engines feature the cathode-less plasma generatIon in both the Ion generators and neutralizers with the results of long life and high reliability in space. Based on the space achievements of μ10 Ion Engines with 8mN thrust, 3,000sec Isp and 350W consumptIon power, several programs are currently under developments: μ20, μ10HIsp and μ1. The first is a 20-cm diameter microwave discharge Ion engine, aiming to achieve 30mN/kW in the thrust-to-power ratio for the asteroid sample return missIon larger than Hayabusa. The second is a high Isp versIon of μ10, and exhausts the plasma beam over 10,000sec Isp using 15kV acceleratIon voltage for deep space missIons to such as Jupiter and Mercury. The third is μ1 to be adapted to small satellites for drag-free.
-
status of microwave discharge Ion Engines on hayabusa spacecraft
43rd AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroyuki Koizumi, Ju Ichiro N KawaguchiAbstract:[Abstract] The μ10 cathode-less electron cyclotron resonance Ion Engines made the Hayabusa spacecraft rendezvous with the asteroid Itokawa in 2005. Though the spacecraft was seriously damaged after the successful soft-landing and lift-off, the xenon cold gas jets from the Ion Engines rescued the Hayabusa. New attitude stabilizatIon method using a single reactIon wheel, the Ion beam jets, and the solar pressure was established and enabled the homeward journey aiming the Earth return on 2010. The total accumulated operatIonal time of the Ion Engines reaches 28,000 hours at the end of May 2007.
-
powered flight of electron cyclotron resonance Ion Engines on hayabusa explorer
Journal of Propulsion and Power, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Yukio Shimizu, Tetsuya Yamada, Junichiro KawaguchiAbstract:The electron cyclotron resonance Ion engine has long life and high reliability because of electrodeless plasma generatIon in both the Ion generator and the neutralizer. Four μ10s, each generating a thrust of 8 mN, specific impulse of 3200 s, and consuming 350 W of electric power, propelled the Hayabusa asteroid explorer launched on May 2003. After vacuum exposure and several baking runs to reduce residual gas, the Ion engine system established continuous acceleratIon. Electric propelled delta-V Earth gravity assist, a new orbit change scheme that uses electric propulsIon with a high specific impulse was applied to change from a terrestrial orbit to an asteroid-based orbit. In 2005, Hayabusa, using solar electric propulsIon, managed to successfully cover the solar distance between 0.86 and 1.7 AU. It rendezvoused with, landed on, and lifted off from the asteroid Itokawa. During the 2-year flight, the Ion engine system generated a delta-V of 1400 m/s while consuming 22 kg of xenon propellant and operating for 25,800 h.
Junichiro Kawaguchi - One of the best experts on this subject based on the ideXlab platform.
-
IKAROS, a Solar Sail Demonstrator and Its ApplicatIon to Trojan Asteroid ExploratIon
2012Co-Authors: Ryu Funase, Hirotaka Sawada, Junichiro Kawaguchi, Osamu Mori, Yuichi TsudaAbstract:Solar power sail is a deep space probe to be powered by hybrid propulsIon of solar photon acceleratIon and Ion Engines to explore outer planetary regIon of the Solar System without relying on nuclear technology. The Japan Aerospace ExploratIon Agency (JAXA) launched the world's first deep space solar sail demonstratIon spacecraft "IKAROS" (Interplanetary Kite-craft Accelerated by RadiatIon Of the Sun) on May 21, 2010. IKAROS succeeded in deploying a 20m-span solar sail on June 9 and demonstrated several key technologies for solar sail utilizing the deep space flight environment. JAXA is currently studying an outer solar system exploratIon missIon using the demonstrated solar power sail technology. The missIon plans to fly for Jupiter, where the spacecraft drops a tiny Jovian probe and performs a swing-by for a Trojan asteroid. Current scenario consists of the rendezvous with one of the Trojan asteroids that are at the Lagrange points L4/L5 associated with Sun-Jupiter system. About as large as 50m sail should be deployed for this missIon according to preliminary missIon analysis and related research is intensively being carried out in JAXA. JAXA plans to initiate the project in a few years and looks at the launch around 2020. © 2012 by JAXA.
-
hayabusa s way back to earth by microwave discharge Ion Engines
46th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2010Co-Authors: Kazutaka Nishiyama, Hitoshi Kuninaka, Yukio Shimizu, Junichiro Kawaguchi, Satoshi Hosoda, Hiroyuki Koizumi, Ikkoh Funaki, Michael Bodendorfer, Daisuke NakataAbstract:The cathode-less electron cyclotron resonance Ion Engines, μ10, propelled the Hayabusa asteroid explorer, launched in May 2003, which is focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. It rendezvoused with the asteroid Itokawa after a two year deep space flight with a delta-V of 1.4 km/s, 22 kg of xenon propellant consumptIon and 25800 hours of total accumulated operatIonal time of all the four Ion Engines added up. Though it succeeded in landing on the asteroid on November 2005, the spacecraft was seriously damaged. This delayed the Earth return in 2010 from the original plan in 2007. ReconstructIon on the operatIonal scheme using remaining functIons and newly uploaded control logic made Hayabusa leave for Earth in April 2007. After a coasting period of 2008, the Ion propulsIon was reignited in February 2009. Although most of the neutralizers were degraded and unable to be used by fall of 2009, a combinatIon of an Ion source and its neighboring neutralizer has been successfully operated for the last 3230 hours including a series of final trajectory correctIon maneuvers. Before reentry, the total accumulated operatIonal time reached 39637 hours consuming a total of 47 kg Xenon propellant. Total duratIon of powered spaceflight is 25590 hours which provided a delta-V of 2.2 km/s and a total impulse of 1 MN·s, approximately. Finally, the spacecraft returned to Earth. Its reentry capsule, which may contain samples from asteroid Itokawa, was retrieved from the Australian outback according to plan .
-
attitude control flight experience coping with solar radiatIon and Ion Engines leak thrust in hayabusa muses c
Proceedings of the 20th International Symposium on Space Flight Dynamics, 2007Co-Authors: Junichiro Kawaguchi, Takashi Kominato, Kenichi ShirakawaAbstract:The paper presents the attitude reorientatIon taking the advantage of solar radiatIon pressure without use of any fuel aboard. The strategy had been adopted to make Hayabusa spacecraft keep pointed toward the Sun for several months, while spinning. The paper adds the above mentIoned results reported in Sedona this February showing another challenge of combining Ion Engines propulsIon tactically balanced with the solar radiatIon torque with no spin motIon. The operatIon has been performed since this March for a half year successfully. The flight results are presented with the estimated solar array panel diffusIon coefficient and the Ion engine's swirl torque.
-
powered flight of electron cyclotron resonance Ion Engines on hayabusa explorer
Journal of Propulsion and Power, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Yukio Shimizu, Tetsuya Yamada, Junichiro KawaguchiAbstract:The electron cyclotron resonance Ion engine has long life and high reliability because of electrodeless plasma generatIon in both the Ion generator and the neutralizer. Four μ10s, each generating a thrust of 8 mN, specific impulse of 3200 s, and consuming 350 W of electric power, propelled the Hayabusa asteroid explorer launched on May 2003. After vacuum exposure and several baking runs to reduce residual gas, the Ion engine system established continuous acceleratIon. Electric propelled delta-V Earth gravity assist, a new orbit change scheme that uses electric propulsIon with a high specific impulse was applied to change from a terrestrial orbit to an asteroid-based orbit. In 2005, Hayabusa, using solar electric propulsIon, managed to successfully cover the solar distance between 0.86 and 1.7 AU. It rendezvoused with, landed on, and lifted off from the asteroid Itokawa. During the 2-year flight, the Ion engine system generated a delta-V of 1400 m/s while consuming 22 kg of xenon propellant and operating for 25,800 h.
Yukio Shimizu - One of the best experts on this subject based on the ideXlab platform.
-
hayabusa s way back to earth by microwave discharge Ion Engines
46th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2010Co-Authors: Kazutaka Nishiyama, Hitoshi Kuninaka, Yukio Shimizu, Junichiro Kawaguchi, Satoshi Hosoda, Hiroyuki Koizumi, Ikkoh Funaki, Michael Bodendorfer, Daisuke NakataAbstract:The cathode-less electron cyclotron resonance Ion Engines, μ10, propelled the Hayabusa asteroid explorer, launched in May 2003, which is focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. It rendezvoused with the asteroid Itokawa after a two year deep space flight with a delta-V of 1.4 km/s, 22 kg of xenon propellant consumptIon and 25800 hours of total accumulated operatIonal time of all the four Ion Engines added up. Though it succeeded in landing on the asteroid on November 2005, the spacecraft was seriously damaged. This delayed the Earth return in 2010 from the original plan in 2007. ReconstructIon on the operatIonal scheme using remaining functIons and newly uploaded control logic made Hayabusa leave for Earth in April 2007. After a coasting period of 2008, the Ion propulsIon was reignited in February 2009. Although most of the neutralizers were degraded and unable to be used by fall of 2009, a combinatIon of an Ion source and its neighboring neutralizer has been successfully operated for the last 3230 hours including a series of final trajectory correctIon maneuvers. Before reentry, the total accumulated operatIonal time reached 39637 hours consuming a total of 47 kg Xenon propellant. Total duratIon of powered spaceflight is 25590 hours which provided a delta-V of 2.2 km/s and a total impulse of 1 MN·s, approximately. Finally, the spacecraft returned to Earth. Its reentry capsule, which may contain samples from asteroid Itokawa, was retrieved from the Australian outback according to plan .
-
lineup of microwave discharge Ion Engines μ series
한국추진공학회 학술대회논문집, 2008Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroshi Hayashi, Hiroyuki KoizumiAbstract:Institute of Space and Astronautical Science of Japan Aerospace ExploratIon Agency (ISAS/JAXA) successfully developed and operated the microwave discharge Ion Engines onboard Hayabusa asteroid explorer. The μ10 Ion Engines feature the cathode-less plasma generatIon in both the Ion generators and neutralizers with the results of long life and high reliability in space. Based on the space achievements of μ10 Ion Engines with 8mN thrust, 3,000sec Isp and 350W consumptIon power, several programs are currently under developments: μ20, μ10HIsp and μ1. The first is a 20-cm diameter microwave discharge Ion engine, aiming to achieve 30mN/kW in the thrust-to-power ratio for the asteroid sample return missIon larger than Hayabusa. The second is a high Isp versIon of μ10, and exhausts the plasma beam over 10,000sec Isp using 15kV acceleratIon voltage for deep space missIons to such as Jupiter and Mercury. The third is μ1 to be adapted to small satellites for drag-free.
-
status of microwave discharge Ion Engines on hayabusa spacecraft
43rd AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroyuki Koizumi, Ju Ichiro N KawaguchiAbstract:[Abstract] The μ10 cathode-less electron cyclotron resonance Ion Engines made the Hayabusa spacecraft rendezvous with the asteroid Itokawa in 2005. Though the spacecraft was seriously damaged after the successful soft-landing and lift-off, the xenon cold gas jets from the Ion Engines rescued the Hayabusa. New attitude stabilizatIon method using a single reactIon wheel, the Ion beam jets, and the solar pressure was established and enabled the homeward journey aiming the Earth return on 2010. The total accumulated operatIonal time of the Ion Engines reaches 28,000 hours at the end of May 2007.
-
powered flight of electron cyclotron resonance Ion Engines on hayabusa explorer
Journal of Propulsion and Power, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Yukio Shimizu, Tetsuya Yamada, Junichiro KawaguchiAbstract:The electron cyclotron resonance Ion engine has long life and high reliability because of electrodeless plasma generatIon in both the Ion generator and the neutralizer. Four μ10s, each generating a thrust of 8 mN, specific impulse of 3200 s, and consuming 350 W of electric power, propelled the Hayabusa asteroid explorer launched on May 2003. After vacuum exposure and several baking runs to reduce residual gas, the Ion engine system established continuous acceleratIon. Electric propelled delta-V Earth gravity assist, a new orbit change scheme that uses electric propulsIon with a high specific impulse was applied to change from a terrestrial orbit to an asteroid-based orbit. In 2005, Hayabusa, using solar electric propulsIon, managed to successfully cover the solar distance between 0.86 and 1.7 AU. It rendezvoused with, landed on, and lifted off from the asteroid Itokawa. During the 2-year flight, the Ion engine system generated a delta-V of 1400 m/s while consuming 22 kg of xenon propellant and operating for 25,800 h.
-
assessment of plasma interactIons and flight status of the hayabusa asteroid explorer propelled by microwave discharge Ion Engines
IEEE Transactions on Plasma Science, 2006Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Yukio Shimizu, Tetsuya Yamada, Ju Ichiro N KawaguchiAbstract:Microwave discharge Ion Engines "mu10" are dedicated to the main propulsIon on the HAYABUSA asteroid explorer. In a development program, various tests and assessments were conducted on the Ion Engines and the spacecraft. They include endurance tests, an electromagnetic interference susceptibility test, an interference test between the plasma and communicatIon microwave, a beam exhaust test on the spacecraft, assessments on the plasma interference with a solar array, and so on. The spacecraft was launched in deep space by the M-V rocket in May 2003. After vacuum exposure and several runs of baking for reductIon of residual gas, the Ion engine system established continuous acceleratIon of the spacecraft toward the asteroid ITOKAWA. The spacecraft passed through a perihelIon of 0.86 astronomical unit (AU) in February 2004 and an aphelIon of 1.7 AU in February 2005, becoming the first solar electric propulsIon system to travel this far toward and away from the Sun. The HAYABUSA succeeded in rendezvousing with the target asteroid in September 2005
Hiroyuki Koizumi - One of the best experts on this subject based on the ideXlab platform.
-
hayabusa s way back to earth by microwave discharge Ion Engines
46th AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2010Co-Authors: Kazutaka Nishiyama, Hitoshi Kuninaka, Yukio Shimizu, Junichiro Kawaguchi, Satoshi Hosoda, Hiroyuki Koizumi, Ikkoh Funaki, Michael Bodendorfer, Daisuke NakataAbstract:The cathode-less electron cyclotron resonance Ion Engines, μ10, propelled the Hayabusa asteroid explorer, launched in May 2003, which is focused on demonstrating the technology needed for a sample return from an asteroid, using electric propulsIon, optical navigatIon, material sampling in a zero gravity field, and direct re-entry from a heliocentric orbit. It rendezvoused with the asteroid Itokawa after a two year deep space flight with a delta-V of 1.4 km/s, 22 kg of xenon propellant consumptIon and 25800 hours of total accumulated operatIonal time of all the four Ion Engines added up. Though it succeeded in landing on the asteroid on November 2005, the spacecraft was seriously damaged. This delayed the Earth return in 2010 from the original plan in 2007. ReconstructIon on the operatIonal scheme using remaining functIons and newly uploaded control logic made Hayabusa leave for Earth in April 2007. After a coasting period of 2008, the Ion propulsIon was reignited in February 2009. Although most of the neutralizers were degraded and unable to be used by fall of 2009, a combinatIon of an Ion source and its neighboring neutralizer has been successfully operated for the last 3230 hours including a series of final trajectory correctIon maneuvers. Before reentry, the total accumulated operatIonal time reached 39637 hours consuming a total of 47 kg Xenon propellant. Total duratIon of powered spaceflight is 25590 hours which provided a delta-V of 2.2 km/s and a total impulse of 1 MN·s, approximately. Finally, the spacecraft returned to Earth. Its reentry capsule, which may contain samples from asteroid Itokawa, was retrieved from the Australian outback according to plan .
-
antenna design method for low power miniaturized microwave discharge Ion Engines
Journal of The Japan Society for Aeronautical and Space Sciences, 2009Co-Authors: Hiroyuki Koizumi, Hitoshi KuninakaAbstract:In this study, we succeeded to develop a very low power miniaturized Ion engine powered by microwave discharge. The accomplished performance was Ion productIon cost of 240W/A and propellant utilizatIon efficiency of 39% by input microwave power 1.0W and mass flow rate of 0.15sccm. In order to realize this very low power operatIon, we have proposed an antenna design method for miniaturized microwave Ion Engines. The effectiveness of this method was verified by plasma observatIon inside the discharge chamber and Ion beam extractIon characteristics of the engine. Based on this method, antenna of the engine was designed and improved. As a result we have achieved to our goal.
-
lineup of microwave discharge Ion Engines μ series
한국추진공학회 학술대회논문집, 2008Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroshi Hayashi, Hiroyuki KoizumiAbstract:Institute of Space and Astronautical Science of Japan Aerospace ExploratIon Agency (ISAS/JAXA) successfully developed and operated the microwave discharge Ion Engines onboard Hayabusa asteroid explorer. The μ10 Ion Engines feature the cathode-less plasma generatIon in both the Ion generators and neutralizers with the results of long life and high reliability in space. Based on the space achievements of μ10 Ion Engines with 8mN thrust, 3,000sec Isp and 350W consumptIon power, several programs are currently under developments: μ20, μ10HIsp and μ1. The first is a 20-cm diameter microwave discharge Ion engine, aiming to achieve 30mN/kW in the thrust-to-power ratio for the asteroid sample return missIon larger than Hayabusa. The second is a high Isp versIon of μ10, and exhausts the plasma beam over 10,000sec Isp using 15kV acceleratIon voltage for deep space missIons to such as Jupiter and Mercury. The third is μ1 to be adapted to small satellites for drag-free.
-
status of microwave discharge Ion Engines on hayabusa spacecraft
43rd AIAA ASME SAE ASEE Joint Propulsion Conference & Exhibit, 2007Co-Authors: Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroyuki Koizumi, Ju Ichiro N KawaguchiAbstract:[Abstract] The μ10 cathode-less electron cyclotron resonance Ion Engines made the Hayabusa spacecraft rendezvous with the asteroid Itokawa in 2005. Though the spacecraft was seriously damaged after the successful soft-landing and lift-off, the xenon cold gas jets from the Ion Engines rescued the Hayabusa. New attitude stabilizatIon method using a single reactIon wheel, the Ion beam jets, and the solar pressure was established and enabled the homeward journey aiming the Earth return on 2010. The total accumulated operatIonal time of the Ion Engines reaches 28,000 hours at the end of May 2007.
