Conceptual study of manned space transportation vehicle using laser thruster in combination with the H-II rocket

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.

► Manned Space Transportation Vehicle (MSTV) using laser thruster is investigated. ► MSTV that carries both laser device and power supply on board is found to be feasible. ► MSTV is propelled by laser thruster using water as propellant. ► MSTV is launched and put into LEO 200 km with H-II Rocket. ► Orbital transfer is performed to arrive at ISS of LEO 400 km by laser thruster.