Hope Credit - NASDA Media Gallery

Like Europe, the National Space Development Agency had big plans to develop a large carrier rocket and manned 'H2 Orbiting Plane' (HOPE). Plans in 1986-87 were for a the final, manned follow-on version in the early 21st century. It would carry a crew of four astronauts. The HOPE development plan included OREX to demonstrate thermal protection and atmospheric re-entry systems; ALFLEX to test the HOPE-X low-speed aerodynamic and landing systems; and HYFLEX to demonstrate hypersonic flight. The end goal was a fully reusable aerospace plane / space transportation system.

A major difference between the European Hermes program and HOPE was that the Japanese favored a phased approach, first building a smaller unmanned version before doing a larger manned mini-shuttle. Thus, the early goal was to design a robotic spaceplane capable of transporting a few metric tons of unmanned cargo and experiments to the International Space Station. Another important mission would be to fly independent missions with microgravity experiments in the spacecraft's small cargo bay. The Japanese regarded a small H-2-launched orbital spaceplane as the logical first step towards ultimately developing a fully reusable 'aerospace plane.'

The Japanese originally planned to develop separate version for initial technology tests and Space Station resupply. However, in 1997 the National Space Development Agency decided that the $830 million Hope-X unmanned experimental spaceplane might be modified for operational resupply flights to ISS, rather than build separate vehicles for testing and operations. The additional cost might be $292 million vs. $2.9 million for the full-scale 22t HOPE follow-on project. Budget constraints later forced a $690 million reduction, to $4.22 billion, in the five-year spending period 1998-2002. In 1998 the Japanese slipped the first Hope-X launch by three years, to 2003. By this time NASDA had spent $305 million since the project was approved ten years earlier.

Article by Marcus Lindroos

Typical orbit: 407 km circular orbit, 51.6 deg inclination. Length: 16.50 m (54.10 ft). Maximum Diameter: 5.00 m (16.40 ft). Span: 12.00 m (39.00 ft). Mass: 13,000 kg (28,000 lb). Payload: 2,000 kg (4,400 lb). Main Engine Propellants: 1,000 kg (2,200 lb).