The Design Characteristics of the HTV Propulsion Module

Paper number

IAC-05-C4.1.03

Author

Mr. Shinobu Matsuo, Mitsubishi Heavy Industries, Ltd., Japan

Coauthor

Mr. Yoichiro Miki, Mitsubishi Heavy Industries, Ltd., Japan

Coauthor

Mr. Takane Imada, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Shunichiro Nakai, IHI Aerospace Co, Ltd., Japan

Year

2005

Abstract

H-II Transfer Vehicle (HTV), which is a vehicle to transport the cargoes to the International Space Station (ISS), is now under developing. HTV is constructed by four modules which are Pressurized Logistic Carrier (PLC), Un-pressurized Logistic Carrier (ULC), Avionics Module (AM) and Propulsion Module (PM).
 HTV Propulsion Module (PM) generates the torque to control the HTV attitude and the thrust to perform the rendezvous with ISS and the re-entry maneuver. HTV PM has twenty-eight 110N class RCS thrusters and four 500N class main thrusters. Both thrusters are bipropellant thrusters using the Monomethylhydrazine (MMH) as the fuel and the Mixed Oxide of Nitrogen (MON3) as the oxidizer.
 This paper describes the outline and several characteristics of the HTV PM design, such as the human rated safety design, the wide range pulse mode operation and the estimation method of the propellant consumption. 

Abstract document

IAC-05-C4.1.03.pdf

Manuscript document

IAC-05-C4.1.03.pdf (🔒 authorized access only).

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