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Development of the GX Launch Vehicle, New Medium Class Launch Vehicle of Japan

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Development of the GX Launch Vehicle, New Medium Class Launch Vehicle of Japan Vol. 43 No. 1 2010 Development of the GX Launch Vehicle, New Medium Class Launch Vehicle of Japan IZUMIYAMA Taku : Manager, Space Development Department, Aero-Engine & Space Operations SHISA Akira : Manager, Space Development Department, Aero-Engine & Space Operations KOBAYASHI Kenji : General Manager, Technology Division, Galaxy Express Corporation The GX launch vehicle is a medium class launch vehicle, objectives of which are to support launching demand for medium-size satellite flexibly, to be back-up for the national main space transportation system, and to establish LNG propulsion system technology. This paper describes outline of the GX program such as its configuration, program merits including establishment of the LNG propulsion system, the main characteristics and its performance, etc. The future development concept of the GX is also described. 1. Introduction Figure 2 shows the configuration of the GX launch vehicle. The GX launch vehicle adopts the first stage of Atlas V The GX launch vehicle is a Japanese medium class launch launch vehicles, which are the most-advanced launch vehicles vehicle developed for operations beginning in the middle developed in the United States and are highly evaluated of the 2010s to flexibly meet diverse future launching among all countries of the world for its high degree of demands for small-and medium-size satellites and to back reliability. The second stage of the GX launch vehicle is up the main national space transportation system. Figure 1 equipped with a LNG engine, which is developed in Japan shows the appearance of the GX launch vehicle. Its for practical application for the first time in the world. The second stage will be equipped with an engine burning GX launch vehicle is made of a combination of leading-edge liquefied natural gas (LNG) for which there are high launch vehicle technologies in Japan and the United States, expectations. By acquiring LNG engine technologies in and this project is becoming symbolic of the cooperation the process of development, Japan is expected to exhibit between Japan and the United States in space exploration. international advantages in the development of future space There are expectations for the GX launch vehicle to be transportation systems. launched in Japan sometime in the future. However, in This paper provides an outline of the GX project, such as order to perform a demonstration flight as soon as possible merits and specifications of the GX launch vehicle and also to put the GX launch vehicle into service, Japan and describes its future development concept. the United States are considering modifying and sharing 2. Outline of the GX launch vehicle a launch site on the West Coast of the United States (Vandenberg Air Force Base, hereinafter called VAFB) 2.1 Configuration of the GX launch vehicle currently used for launching the Atlas V launch vehicles. The GX launch vehicle is a two-stage liquid launch vehicle. Figure 3 shows the launch site candidate (VAFB) for a demonstration flight of the GX launch vehicle. 2.2 Merits of the GX launch vehicle With the configuration described in Section 2.1, the GX launch vehicle has several merits: acquiring LNG engine technology, backing up the main national space transportation system, utilizing ①the most-advanced technologies in the United② States, and flexible utilization of the launch site. ③ 2.2.1 Acquisition of LNG engine technologies④ Table 1 shows the merits of the LNG engine. With these merits, the LNG engine is attracting attention not only as an engine for launch vehicles, but also as an engine that can be mounted on spacecraft to the Moon and Mars. Future space transportation technologies will be acquired through the development of the GX launch vehicle. In the period from June to September 2009, a series of Fig. 1 Conceptual image of the GX launch vehicle engine firing tests were successfully conducted, including 37 Vol. 43 No. 1 2010 Payload fairing Second Spacecraft stage Payload adapter Forward adapter Adopted the highly reliable Atlas V Booster developed First stage in the United States First stage Second stage Developed and mounted Interstage the first LNG engine adapter in the world ©ULA Liquid oxygen tank RP-1 tank RD-180 engine Fig. 2 Major components of the GX launch vehicle Mobile Service Tower (MST) Table 1 Merits of LNG (methane) engine (for assembling a launch vehicle) Merits Description Unlike solid propellants, the combustion gas of this RP-1 propellant does not include chloride and causes no storage facility Environmentally- destruction of the ozone layer. friendly Among hydrocarbon fuels, methane (the major Liquid constituent of LNG) has the lowest molecular weight oxygen and imposes less of a burden on the environment. storage The cost per unit mass is about 1/250 of that of liquid Low cost facility hydrogen. LNG This fuel has a higher boiling point (about -160°C) storage and a higher density (0.43 g/cm3) compared to liquid facility hydrogen (with a boiling point of -253°C and a (new) Easy to handle density of 0.07 g/cm3). This fuel contributes to relaxing operating temperatures conditions and specifications of valves and other components, and reducing devices in size, resulting in easier production and testing. Due to the boiling point being higher than that of liquid ©ULA Storable for hydrogen, this fuel can be stored for a long time in space extended periods (Note) RP-1 : Kerosene as a fuel for launch vehicle engines with less vaporizing. Unlike hydrazine and other storable propellants, this Nontoxic fuel is not toxic and can be safely used for manned Fig. 3 Launch site candidate for demonstration flight missions. of the GX launch vehicle (VAFB) a test with a duration of 600 seconds, which is longer than considered to be important to have a backup vehicle that the actual operation time. This success assured technical uses a technology different from that used for the main feasibility of the LNG engine and led to a large step national space transportation system. forward for practical application of the GX launch vehicle. Figure 4 shows that the H-IIA launch vehicles are based 2.2.2 Backup for the main national space transportation on independent Japanese technologies originating from system the technologies used for US Delta launch vehicles. The Even 1 out of 20 highly reliable launch vehicles fail to GX launch vehicle was developed jointly by Japan and launch on average. If a launch vehicle fails to launch, it Lockheed Martin Corporation (currently, United Launch cannot be launched again until the cause of the failure Alliance, LLC. (ULA)) to follow in the footsteps of the is investigated and corrective measures are taken. This technologies used for Atlas and Titan launch vehicles. is to prevent the same failure from occurring not only in This means that the GX launch vehicle uses different launch vehicles of the same type, but also in those of other technologies from those used for H-IIA vehicles. types that use the same technology. For this reason, it is 38 Vol. 43 No. 1 2010 GX launch vehicle Atlas-Centaur Applied to (under launch vehicles launch vehicles development) (from 1963) Atlas launch Atlas family Atlas *2 vehicles ICBM Atlas V launch (from the 1950s) vehicles *1 Atlas launch (since 2002, GALEX vehicles (manned) currently (the 1960s) in service) Made into a manned vehicle © ULA Titan launch vehicles Applied to (1964 to 2005) Titan family *1 Titan launch vehicles Made into a manned vehicle Lockheed Martin Corporation ICBM ULA Titan launch vehicles ©ULA (manned) (the 1960s) Delta IV launch *1 vehicles Applied to Delta II launch vehicles (since 2002, Delta family Thor-Delta Thor launch vehicles (7000 series) currently launch vehicles IRBM (since 1990, in service) (from the 1960s) currently in service) Boeing Company © ULA ©ULA The 1950s 1960 to 1990 Since 1990 H-IIA launch vehicles (since 2001, currently in service) N and H series *2 launch vehicles (from 1975) JAXA © JAXA (Note) *1 : US *2 : Japan Fig. 4 Japan-U.S. launch vehicle lineage Figure 5 (1) shows that most failures were caused by propulsion systems. The GX launch vehicle equipped with Other the LNG engine uses different technologies from those used 3% Unknown 17% for H-IIA launch vehicles equipped with liquid hydrogen Electrical engines. 2% Due to the independence of these technologies, the GX Structural Propulsion 3% launch vehicles can play a role as a backup for H-IIA Separation 55% launch vehicles. 10% 2.2.3 Utilization of the latest technologies developed Avionics 10% in the United States Atlas launch vehicles have been operated since the earliest development stage of launch vehicles in the United States and Russia, and technical know-how has been accumulated Fig. 5 Launch vehicle subsystem failures (1980–1999) over its long history. With this background, the Atlas- Centaur series (operated since 1963), which are the original forms of the current Atlas launch vehicles, have the highest 80 continuous Atlas launch vehicles have been successfully degree of reliability (mean predicted probability of success launched since 1993, and they are evaluated as the most for next launch attempt) in the world. Figure 6 shows the reliable launch vehicles. reliabilities (mean predicted probabilities of success for Atlas V launch vehicles are the main national space next launch attempt) of major launch vehicles. More than transportation system that was developed by the U.S. Air 39 Vol. 43 No. 1 2010 1.00 0.90 0.80 Enlarged view 0.70 Continuous success of Atlas-Centaur vehicles 0.60 1.00 0.50 Atlas-Centaur vehicles 0.95 0.40 : All Delta vehicles 0.30 : All Ariane vehicles 0.90 : All Long March vehicles for next launch attempt launch next for 0.20 : All N and H series vehicles (Japan) All N and H series vehicles (Japan) : All Atlas vehicles success of probability predicted Mean Mean predicted probability of success for next launch attempt ( — ) — ( attempt launch next for success of probability predicted Mean 0.85 0.10 : Atlas-Centaur vehicles 01/2006 01/2008 01/2010 0.00 01/1955 01/1960 01/1965 01/1970 01/1975 01/1980 01/1985 01/1990 01/1995 01/2000 01/2005 01/2010 Month/Year Fig.
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