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南理事長、武捨理事
南理事長が関係された論文２編（１編は武捨理事と共著）が、ヨーロッパで著名なジャーナル誌
Acta Astronautica
に査読審査の上で掲載される事が決定しました。おめでとうございます。
以下にアブストラクトを掲載します。
-----
title:Field propulsion systems for space travel
by :Yoshinari Minami, Takaaki Musha
paper link
a b s t r a c t
Field propulsion systems were proposed by many researchers to overcome the speed
limit of the conventional space propulsion system. Field propulsion system can be
propelled without mass expulsion; its propulsion principle can induce a propulsive
force (i.e., thrust) that arises from the interaction of the substantial physical structure.
This notion is based on the assumption that space as a vacuum possesses a substantial
physical structure. This evaluation examines the substantial physical structure regarding
the space–time from both General Relativity in the view of a macroscopic structure
and Quantum Field Theory in the view of a microscopic structure. Thus, several kinds of
field propulsion system can be proposed by making these choices considering the
structure of physical space.
-----
-----
title:Conceptual study of manned space transportation vehicle using laser thruster in combination with the H-II rocket
by :Yoshinari Minami, Shigeaki Uchida
paper link
a b s t r a c t
This paper describes the conceptual study of a Manned Space Transportation Vehicle
(MSTV) using a laser thruster in combination with the H-II Rocket. By combining the
use of a laser thruster and H-II Rocket, space trip to the International Space Station (ISS)
or a round trip mission around the moon can be performed. Once MSTV with one crew
achieves a circular orbit at an altitude of 200 km around the earth (parking orbit) by use
of H-II Rocket, MSTV will then put into a circular orbit into an altitude of 400 km (ISS
orbit) from 200 km circular orbit by use of the laser thruster. H-II Rocket has the
following launch capability with payloads for LEO (300 km): 10 t (H-II A Rocket), 16.5 t
(H-II B Rocket). Laser thruster using water propellant, power source for the laser, orbital
transfer calculations (to ISS or the Moon) and other practical aspects are examined.
-----
南理事長が関係された論文２編（１編は武捨理事と共著）が、ヨーロッパで著名なジャーナル誌
Acta Astronautica
に査読審査の上で掲載される事が決定しました。おめでとうございます。
以下にアブストラクトを掲載します。
-----
title:Field propulsion systems for space travel
by :Yoshinari Minami, Takaaki Musha
paper link
a b s t r a c t
Field propulsion systems were proposed by many researchers to overcome the speed
limit of the conventional space propulsion system. Field propulsion system can be
propelled without mass expulsion; its propulsion principle can induce a propulsive
force (i.e., thrust) that arises from the interaction of the substantial physical structure.
This notion is based on the assumption that space as a vacuum possesses a substantial
physical structure. This evaluation examines the substantial physical structure regarding
the space–time from both General Relativity in the view of a macroscopic structure
and Quantum Field Theory in the view of a microscopic structure. Thus, several kinds of
field propulsion system can be proposed by making these choices considering the
structure of physical space.
-----
-----
title:Conceptual study of manned space transportation vehicle using laser thruster in combination with the H-II rocket
by :Yoshinari Minami, Shigeaki Uchida
paper link
a b s t r a c t
This paper describes the conceptual study of a Manned Space Transportation Vehicle
(MSTV) using a laser thruster in combination with the H-II Rocket. By combining the
use of a laser thruster and H-II Rocket, space trip to the International Space Station (ISS)
or a round trip mission around the moon can be performed. Once MSTV with one crew
achieves a circular orbit at an altitude of 200 km around the earth (parking orbit) by use
of H-II Rocket, MSTV will then put into a circular orbit into an altitude of 400 km (ISS
orbit) from 200 km circular orbit by use of the laser thruster. H-II Rocket has the
following launch capability with payloads for LEO (300 km): 10 t (H-II A Rocket), 16.5 t
(H-II B Rocket). Laser thruster using water propellant, power source for the laser, orbital
transfer calculations (to ISS or the Moon) and other practical aspects are examined.
-----
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