|
RD-0410 (РД-0410, GRAU index: 11B91) was a Soviet nuclear thermal rocket engine developed from 1965 through the 1980s using liquid hydrogen propellant. The engine was ground-tested at the Semipalatinsk Test Site,〔(【引用サイトリンク】publisher=KBKhA - Chemical Automatics Design Bureau )〕 and its use was incorporated in the Kurchatov Mars 1994 manned mission proposal.〔 This engine had slightly higher performance (exhaust temperature and specific impulse) over NERVA (the U.S. nuclear thermal rocket engine project), but much less thrust: only 35.2 kN compared to 333.6 kN of NERVA. The design of the reactor core included thermal insulation between uranium carbide/tungsten carbide fuel and the zirconium hydride moderator. This solution allowed for a very compact reactor core design. Hydrogen flow cooled the moderator first allowing to keep very low neutron energy and high fission cross-section, then it was heated by the direct contact to the fuel rods. To prevent the chemical reaction between carbide and hydrogen, about 1 percent of heptane was added to the hydrogen after the moderator passage. The hydrogen boost turbopump was designed by KBKhA in Voronezh. ==See also== * Nuclear Thermal Rocket * NERVA, the American project for nuclear thermal propulsion 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「RD-0410」の詳細全文を読む スポンサード リンク
|