SPACE LAUNCH REPORT Japan Kagoshima Smallsat Launchers Flight History by Variant/Year (1966-Present) L(F) = Number of Launches(Number of Failures) L4S/M4S M-3 M-5 Epsilon SS-520 Year L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ 1960 - - - - - - - 1961 - - - - - - - 1962 - - - - - - - 1963 - - - - - - - 1964 - - - - - - - 1965 - - - - - - - 1966 2(2) - - - - - - 1967 1(1) - - - - - - 1968 - - - - - - - 1969 1(1) - - - - - - 1970 2(1) - - - - - - 1971 2(0) - - - - - - 1972 1(0) - - - - - - 1973 - - - - - - - 1974 - 1(0) - - - - - 1975 - 1(0) - - - - - 1976 - 1(1) - - - - - 1977 - 1(0) - - - - - 1978 - 2(0) - - - - - 1979 - 1(0) - - - - - 1980 - 1(0) - - - - - 1981 - 1(0) - - - - - 1982 - - - - - - - 1983 - 1(0) - - - - - 1984 - 1(0) - - - - - 1985 - 2(0) - - - - - 1986 - - - - - - - 1987 - 1(0) - - - - - 1988 - - - - - - - 1989 - 1(0) - - - - - 1990 - 1(0) - - - - - 1991 - 1(0) - - - - - 1992 - - - - - - - 1993 - 1(0) - - - - - 1994 - - - - - - 1995 - 1(1) - - - - 1996 - - - - - - 1997 - - 1(0) - - - 1998 - - 1(0) - - - 1999 - - - - - - 2000 - - 1(1) - - - - 2001 - - - - - - - 2002 - - - - - - - 2003 - - 1(0) - - - - 2004 - - - - - - - 2005 - - 1(0) - - - - 2006 - - 2(0) - - - - 2007 - - - - - - - 2008 - - - - - - - 2009 - - - - - 2010 - - - - - - - 2011 - - - - - - - 2012 - - - - - - - 2013 - - - 1(0) - 2014 - - - - - 2015 - - - - - - 2016 - - - 1(0)# - - 2017 - - - - 1(1) - 2018 - - - 1(0)# 1(0) - 2019 - - - 1(0)# - - 2020 - - - - - - 2021 - - - 1(0)# - - 2022 - - - 1(1)# - - 2023 - - - - - ------------------------------------------------------------------ L4S/M4S M-3 M-5 Epsilon SS-520 Year L(F) L(F) L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ Total 9(5) 19(2) 7(1) 6(1) 2(1) ------------------------------------------------------------------ Footnotes: # Enhanced Epsilon with heavier, wider second stage and other improvements. EPSILON ORBITAL SPACE LAUNCH LOG DATE VEHICLE ID PAYLOAD MASS(t) SITE* ORBIT* ------------------------------------------------------------------ 09/14/13 Epsilon E-01 Sprint A 0.35 KA M5 LEO 12/20/16 Enh Epsilon E-02 ERG 0.365 KA M5 EEO 01/17/18 Enh Epsilon E-03 ASNARO 2 0.57 KA M5 SSO 01/18/19 Enh Epsilon E-04 RAPIS+usats 0.386 KA M5 SSO 11/09/21 Enh Epsilon E-05 RAISE 2 + usats 0.337 KA M5 SSO 10/12/22 Enh Epsilon E-06 RAISE 3 0.11 KA M5 [FTO] ------------------------------------------------------------------ [E-01, E-03 through E-06] Used CLPS 4th Stage [E-02] First Enhanced Epsilon. To 219 x 33,200 km x 31.4 deg orbit. [E-06] Problem during Stg 2 coast. RSO just before planned S3 ignition. Site Code: KA = Kagoshima, Japan TA = Tanageshima, Japan YO = Yoshinobu Launch Pad M5 = M5 Launch Pad Orbit Code: EEO/M = Molynia (12-hr) Elliptical Earth Orbit FTO = Failed to Orbit FSO = Failed Suborbital GTO = Geosynchronous Transfer Orbit GTO+ = Supersynchronous or High Perigee Transfer Orbit GTO- = Subsynchronous Transfer Orbit GTOi = Inclined GTO GEO = Geosynchronous Orbit HCO = Heliocentric (solar) Orbit HTO = High Earth Transfer Orbit LEO = Low Earth Orbit LEO/S = Sun Synchronous Low Earth Orbit LEO/P = Polar Low Earth Orbit MEO = Medium Earth Orbit MTO = Medium Earth Transfer Orbit SUB = Suborbital xxx Epsilon Vehicle Configurations ------------------------------------------------------------------ Payload Configuration Liftoff GLOW (tonnes) Height (tonnes) [1] 250x500km (meters) x 30 deg [2] 500 km x 30 deg [3] 500 km x 98.6 deg [4] 200x33,100 km x 31 deg ================================================================== Epsilon 1.20 t [1] SRB-A+M-34c+KM-V2b+PLF 24 m 91 t Epsilon CLPS 0.70 t [2] Epsilon+PLF 24 m 91 t 0.45 t [3] Enh Epsilon 1.50 t [1] SRB-A+M-35+KM-V2c+PLF 26 m 95.4 t Enh Epsion CLPS 0.59 t [3] Enh Epsion+CLPS 26 m 95.4 t 0.365 t [4] ================================================================== * GEO: Geosynchronous Earth Orbit Epsilon Vehicle Components ------------------------------------------------------------------ Stg 1 Stg 2 Stg 2 Stg 3 Stg 3 Stg 4 (SRB-A) (M-34c) (M-35) (KM-V2b) (KM-V2c) (CLPS) ================================================================== Diameter (m) 2.5 m 2.2 m 2.5 m 1.45 m 1.45 m 1.2 m Length (m) 13.27 m 3.6 m 5.17 m 1.75 m 2.25 m 1.2 m 13.97 m# Incl I/S Incl I/S Mp (tonnes) 66 t 10.8 t 15.0 t 2.5 t 2.5 t 0.120 t 0.145 t# Mb/o (tonnes) 9.3 t 0.8 t 2.2 t 0.5 t 0.8 t 0.180 t 0.155 t# GLOW (tonnes) 75.5 t 11.6 t 17.2 t 3.0 t 3.3 t 0.3 t 75.3 t# Engine SRB-A M-34c M-35 KM-V2b KM-V2c Engine Mfgr Nissan Fuel HTPB HTPB HTPB HTPB HTPB N2H4 Oxidizer T(SL t) 219.24 t T(Vac t) 161.12 t 38.46 t 45.38 t 8.29 t 10.16 t 0.041 t ISP (SL sec) ISP (Vac sec) 283.6 s 299.9 s 295 s 301.7 s 299 s 215 s Tburn (sec) 109 s 104.7 s 129 s 91.1 s 89 s No. Engines 1 1 1 1 1 1 ================================================================== * Original PLF Enclosed Stg 2, 3, and when present 4 Enhanced Epsilon PLF only Encloses Stg 3 and when present 4 PLF is 2.5 meters x 9.19 meters and weighes about 0.8 tonnes. # Enh = Enhanced CLPS = Compact Liquid Propulsion System SPACE LAUNCH REPORT Epsilon History by: Ed Kyle, Last Update: October 12, 2022 After phasing out the M-5 (or M-V) launch vehicle in 2006, the Japan Aerospace Exploration Agency (JAXA) began development of a smaller solid propellant launch vehicle named "Epsilon" that it hoped would cost less to fly than M-5 had cost. Epsilon would continue the long-running tradition of smaller, lower cost "Mu" series orbital launchers that the Institute of Space and Astronautical Sciences (ISAS) had managed. Formerly independant ISAS became the Space Science Research Disvision of JAXA on October 1,2003. Epsilon used three solid motors and an optional "Compact Liquid Propulsion System" (CLPS) fourth stage. The first stage was a modified SRB-A motor, weighing 74.4 tonnes and similar to the 230 tonne thrust monolithic boosters used by JAXA's H-2A and H-2B launch vehicles. The second stage was a 11.6 tonne M-34c motor, a modified version of the M-5 rocket's third stage that uses an extendible nozzle. A small KM-V-2b solid motor, derived from the M-5 fourth stage motor and weighing 3 tonnes will served as the third stage. The three motors burned for 120, 104.7 and 91.1 seconds, respectfully. A 2.5 meter diameter payload fairing enclosed the payload and the third and fourth (CLPS) stages (when used). CLPS could provide orbit trimming and raising manuevers. With CLPS, Epsilon could lift 700 kg to a 500 km x 30 deg orbit, or 450 km to a 500 km sun synchronous orbit. Without CLPS, Epsilon could boost 1.2 tonnes into a 250 x 500 km x 30 deg orbit. Epsilon was designed to simplify launch check out procedures. It performed its own self-tests using its on-board computer, which was able to be monitored and controlled via. standard network connections from anywhere, making the launch control system independant of launch site. Use of the monolithic SRB-A first stage motor eliminated the need to stack motor segments, as was required for the M-5 first stage. Epsilon weighed only 91 tonnes at liftoff, compared to 140 tonnes for M-5. It was also less capable, but smaller payloads meant smaller budgets. Epsilon was meant to cost one-third as much as M-5. The 2006 goal was to cut costs from $60 million to $20 million per flight. Epsilon Inaugural Success Japan's new Epsilon launch vehicle scored an inaugural success on September 14, 2013 when it boosted Sprint-A (Spectroscopic Planet Observatory for Recognition of Interaction of Atmosphere) into orbit from the Uchinoura Space Center, Kagoshima on the island of Kyushu. The 348 kg orbiting telescope was aimed toward a 950 x 1,150 km x 31 deg. orbit. Sprint-A will study ineractions of the solar wind with the atmospheres and magnetoshpheres of Mars, Venus, and Jupiter at extreme ultraviolet wavelengths. On this flight, the first stage burned for 112 seconds, the second stage for 102 seconds, and the third stage for 89 seconds. The vehicle coasted for 53 seconds between the first and second stage burn and for 361 seconds between the second and third stage burn. Epsilon coasted for another 140 seconds after third stage burnout before the hydrazine fueled "Post Boost Stage" (PBS) separated and ignited. On this flight, the PBS performed a nearly 11 minute long initial burn and a 6.5 minute long second burn that were separated by a 23 minute long coast. Sprint-A separated 61 minutes 39 seconds after liftoff. Once on orbit, Sprint-A was given the nickname "Hisaki", which means "beyond the sun" in Japanese. The success followed an August 27 last second aborted attempt that was found to have been caused by latent sensor signal delays that spoofed the ground launch launch control program. Epsilon was designed to reduce the cost of scientific satellite launches compared to its M-V predecessor. Japan Aerospace Exploration Agency (JAXA) began development of "Epsilon" in 2006 to continue the long-running tradition of smaller, lower cost "Mu" series orbital launchers that the Institute of Space and Astronautical Sciences (ISAS) had managed. Formerly independant ISAS became the Space Science Research Disvision of JAXA on October 1,2003. Epsilon uses three solid motors and an optional "Post Boost Stage" (PBS), or "Compact Liquid Propulsion System" (CLPS) fourth stage. The first stage is a modified SRB-A motor, weighing 74.4 tonnes and similar to the 230 tonne thrust monolithic boosters used by JAXA's H-2A and H-2B launch vehicles. The second stage is an 11.6 tonne M-34c motor, a modified version of the M-5 rocket's third stage that uses an extendible nozzle. A small KM-V-2b solid motor, derived from the M-5 fourth stage motor and weighing 3 tonnes serves as the third stage. Epsilon weighs 91 tonnes at liftoff. A 2.5 meter diameter payload fairing enclosed Sprint-A and the third and fourth stages. The PBS provides orbit trimming and raising manuevers on some missions. With CLPS, Epsilon can lift 700 kg to a 500 km x 30 deg orbit, or 450 km to a 500 km sun synchronous orbit. Without CLPS, Epsilon can boost 1.2 tonnes into a 250 x 500 km x 30 deg orbit. Enhanced Epsilon Enhanced Epsilon uses improved second and third stages and a stretched payload fairing. Enhanced Epsilon is designed to haul about 30% more payload mass to low earth orbit. The rocket's second stage carries more propellant and is no longer enclosed within the fairing. The third stage also carries more propellant. Both solid upper stages use fixed, rather than extendible, nozzles, with appropriately stretched interstage sections. The changes make Enhanced Epsilon stand two meters taller and weigh 4.4 tonnes more than the original prototype Epsilon Launch Vehicle. Epsilon F6 Failure During the Enhanced Epsilon F6 flight, the second stage RCS had an attitude control problem. From the two RCS systems in the 2nd stage, pressure on the +Y manifold did not reach high enough pressure. Second stage attitude control is actuated by the TVC to steer the main motor and RCS, which is a set of eight pressure-fed hypergolic thrusters activated by pyrovalves on the second stage. When the 2nd stage is firing, the TVC provides pitch and yaw control, while the RCS provides roll control During coasts, the RCS controls all three axes. During the F6 flight, the attitude immediately went out of bounds on yaw after burnout, reaching up to 21 deg after a minute (nominal is up to 0.91 deg, 3 sigma). After that, the +Y RCS returned to nominal operation to stabilized the 21 deg error, but it did not restore the LV back to a nominal orientation. JAXA narrowed the cause of the RCS failure to a blockage of the diaphragm at the helium tank outlet. The diaphragm joint between the helium side & the hydrazine side may have been damaged during tank assembly, allowing hydrazine to leak into the helium side and blocked the hydrazine outlet. The blockage would cause the complete failure of 1 of 2 sides of RCS thrusters on the 2nd stage motor and loss of attitude control. This tank was pressure tested prior to integration onto the stage but the possible leak was not found in pre-flight testing. Other possible failure scenarios such as the diaphragm being broken or slipped out of joint were simulated & dismissed. JAXA & IHI were considering whether to modify these tanks or to use alternatives from H-2A for the next enhanced "Epsilon-S" for Flight 7. References Epsilon Launch Vehicle brochure, JAXA, 2012 "System Design of Enhanced Epsilon Launch Vehicle", Takayuki IMOTO, Sengen Jonathan's Space Report Launch Vehicle Database "http://www.planet4589.org/space/lvdb/index.html" Encylopedia Astronautica "http://www.astronautix.com/" Gunter's Space Page "http://www.skyrocket.de/space" Last Update 12/31/2023 by Ed Kyle