Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
Research Unit IV, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
EBARA CORPORATION
EBARA CORPORATION
EBARA CORPORATION
EBARA CORPORATION
EBARA CORPORATION
EBARA CORPORATION
The rocket engine of the propellant supply system based on the electric pump is simplified as with the expander cycle system. In the engine system using the electric pump, in addition to the combustor, the motor, the battery, and the inverter are the heat sources. In particular, it is assumed that a motor, which becomes a heat source by electromagnetic loss, uses a propellant or helium as a coolant. The propellant that has been heated by the cooling of the motor is returned to the pump or discharged. This process affects pump efficiency. In this report, we describe concepts for evaluating the feasibility of the electric pump system from the viewpoint of cooling and the basic model constructed.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
ロケットエンジン推進剤供給電動ポンプの成立性に向けた検討
AA1830028000.pdf
(1.53MB)
