Mitigation of multipacting, enhanced by gas condensation on the high power input coupler of a superconducting RF module, by comprehensive warm aging

2017 ◽  
Vol 872 ◽  
pp. 150-159 ◽  
Author(s):  
Chaoen Wang ◽  
Lung-Hai Chang ◽  
Mei-Hsia Chang ◽  
Ling-Jhen Chen ◽  
Fu-Tsai Chung ◽  
...  
Keyword(s):  
High Power ◽  
Power Input ◽  
Input Coupler ◽  
Gas Condensation ◽  
Superconducting Rf ◽  
Rf Module

Fabrication of the high power input coupler for BEPCII superconducting cavities

2008 ◽  
Vol 32 (11) ◽  
pp. 931-933 ◽  
Author(s):  
Huang Tong-Ming ◽  
Ma Qiang ◽  
Pan Wei-Min ◽  
Wang Guang-Wei
Keyword(s):  
High Power ◽  
Power Input ◽  
Input Coupler ◽  
Superconducting Cavities

Calculation of the external quality factor of the high power input coupler for the BEPCII superconducting cavity

2008 ◽  
Vol 32 (1) ◽  
pp. 72-74 ◽  
Author(s):  
Huang Tong-Ming ◽  
Pan Wei-Min ◽  
Wang Guang-Wei ◽  
T Furuya ◽  
S Mitsunobu
Keyword(s):  
Quality Factor ◽  
High Power ◽  
Power Input ◽  
Superconducting Cavity ◽  
External Quality ◽  
Input Coupler

805 MHz High Power Input Coupler for SRF Cavity in a RIA Cryomodule

2005 ◽  
Vol 15 (2) ◽  
pp. 1307-1310
Author(s):  
Q.-S. Shu ◽  
J. Susta ◽  
G. Cheng ◽  
T.L. Grimm ◽  
J. Popielarski ◽  
...  
Keyword(s):  
High Power ◽  
Power Input ◽  
Input Coupler ◽  
Srf Cavity

A review of high-power magnetoplasmodynamic electric propulsion designs and studies of RSC Energia

2020 ◽  
pp. 112-133
Author(s):  
Victor V. SINYAVSKIY
Keyword(s):  
Service Life ◽  
Electric Power ◽  
High Power ◽  
Electric Propulsion ◽  
Nuclear Power ◽  
Materials Science ◽  
Low Voltage ◽  
Power Input ◽  
Design Bureau ◽  
Rocket Propulsion

At the initiative of S.P.Korolev, in 1959, Special Design Bureau No.1 (now RSC Energia) established the High-temperature Power Engineering and Electric Propulsion Center which was tasked with development of nuclear electric propulsion for heavy interplanetary vehicles. Selected as the source of electric power was a nuclear power unit based on a thermionic converter reactor, and selected as the engine was a stationary low-voltage magnetoplasmodynamic (MPD) high-power (0.5–1.0 MW) thruster which had thousands of hours of service life. The paper presents the results of extensive efforts in research, development, design, materials science experiments, and tests on the MPD-thruster, including the results of development and 500-hours life tests of an MPD-thruster with a 500-600 kW electric power input that used lithium propellant. The world’s first lithium 17 kW MPD-thruster was built and successfully tested in space. The paper points out that to this day nobody has surpassed the then achievements of RSC Energia neither in thruster output during long steady-state operation, nor in performance and service life. Key words: Martian expeditionary vehicle, nuclear electric rocket propulsion system, electric rocket thruster, magnetoplasmodynamic thruster, lithium, cathode, anode, barium, electric propulsion tests in space.

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