In-flight operation of the Hayabusa2 ion engine system on its way to rendezvous with asteroid 162173 Ryugu
In-flight operation of the Hayabusa2 ion engine system on its way to rendezvous with asteroid 162173 Ryugu
复制标题
Hayabusa2 离子发动机系统在前往与小行星 162173 Ryugu 交会途中的飞行中运行
DOI:
10.1016/j.actaastro.2019.10.005
复制
发表时间:
2020
影响因子:
3.5
通讯作者:
H. Kuninaka
中科院分区:
文献类型:
--
作者:
K. Nishiyama;S. Hosoda;R. Tsukizaki;H. Kuninaka
Japan's second asteroid explorer Hayabusa2 was successfully launched on Dec 3, 2014, to return a sample from asteroid 162173 Ryugu by 2020. Four xenon ion thrusters based on electron cyclotron resonance discharge propelled the spacecraft for 547 h during its first year in space. Hayabusa2 completed an Earth gravity assist on Dec 3, 2015, followed by 798 and 2593 h of ion thruster operation, called the first and second transfer phases of delta-v, respectively. The third transfer phase of delta-v was conducted from Jan 10, 2018, to Jun 6, 2018, in which the final 2475-h ion thruster operation was executed before the rendezvous with Ryugu. The cumulative operating times for the four ion thrusters are 6,450, 11, 5,193, and 6418 h. This paper summarizes the 6515-h powered flight by the ion engine system, which produced 1015 m/s delta-v, in terms of thruster performance change, roll torques generated by various combinations of ion thrusters, and spacecraft surface erosion history measured by two quartz crystal microbalances located near the thrusters. In parallel with the space flight operation, an engineering model of the microwave discharge neutralizer has been under long-duration testing on the ground since 2012. It has accumulated 55,170 h of diode-mode operation as of Mar 15, 2019.
DOI:
10.2514/6.2010-6862
发表时间:
2010-07
期刊:
--
影响因子:
--
作者:
K. Nishiyama;S. Hosoda;H. Koizumi;Y. Shimizu;I. Funaki;H. Kuninaka;M. Bodendorfer;J. Kawaguchi;D. Nakata
通讯作者:
K. Nishiyama;S. Hosoda;H. Koizumi;Y. Shimizu;I. Funaki;H. Kuninaka;M. Bodendorfer;J. Kawaguchi;D. Nakata