50
51
53
52
55
56
54
57
58
59
60
61
62
64
63
65
67
66
69
68
71
72
70
73
74
75
76
79
77
78
81
80
83
82
85
84
86
87
88
89
90
91
92
93
95
94
96
97
99
98
01
00
02
03
04
05
06
07
09
08
11
10
13
12
15
14
17
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24
H-II (H-II, H-IIS, H-IIA, H-2B) - Vehicle use: Satellite, HTV on H-IIB
Japanese orbital launch vehicle. The original H-II version was cancelled after failures and replaced by the redesigned H-IIA, which launches commercial satellites to orbit, and H-IIB, which launches the H-II Transfer Vehicle (HTV) Kounutori that carries cargo to the ISS. H-II vehicles are two-stage rockets which use liquid oxygen and liquid hydrogen as propellant and strap-on solid rocket boosters (SRBs) powered by polibutadiene. H-IIA uses one engine for the first stage and two strap-on SRBs, while H-IIB uses two engines in the first stage and four strap-on SRBs.
source: http://global.jaxa.jp/projects/rockets/
Variant
All variants
H-II
H-IIS
H-IIA
H-IIB
Launches
59
6
1
43
9
Failures
3
1
1
1
0
Realized
0.95
0.83
0.00
0.98
1.00
Predicted
0.93
0.75
0.33
0.96
0.91
2/21/1998 - H-II
PREMATURE SECOND STAGE SHUTDOWN
6th H-II launch
The second stage burn cut off 44 seconds into a scheduled 3 minute 12 second burn. The early stage two shutdown resulted in the payload (COMETS satellite) being placed in a much lower orbit than the planned geostationary transfer orbit. The satellite on-board propulsion system was able to raise the orbit to a more useful, but limited-use orbit. The failure was attributed to a hot combustion gas leak in the second stage LE-5A engine combustion chamber. Enhancements were made to the second stage engine (LE-5B) and engine brazed joint inspection processes.
SOURCES:
H-IIA rocket engine development
11/15/1999 - H-II
CATASTROPHIC FIRST STAGE ENGINE FAILURE
7th H-II launch
first and only H-IIS launch
The launch vehicle began experiencing first stage engine problems approximately four minutes into flight, which led to ground control issuing a self-destruct command approximately eight minutes into flight, destroying the launch vehicle and payload (MTSAT). The LE-7 first stage engine hydrogen turbo pump blades failed due to high cycle fatigue, which was accelerated due to low inlet pressures operating conditions during flight. Flow-induced vibration and flaws on the surface of the blades may have also contributed to turbo pump blade failure. Enhancements were made to the first stage engine (LE-7A) and verification testing to mitigate recurrence on subsequent flights.
SOURCES:
HIIA rocket engine development
SUPPLEMENTAL MATERIALS:
H-II 008: MTSAT launch failure; final H-II launch (15.11.99) (F)
11/29/2003 - H-IIA
BOOSTER SEPARATION FAILURE
13th H-II launch
6th H-IIA launch
A hot gas leak from one of the two solid rocket boosters (SRB-A) damaged the booster separation system, resulting in a failure to separate and jettison the affected booster following burn out. As a result of this separation failure, the H-IIA launch vehicle failed to achieve sufficient velocity and altitude and was consequently destroyed by a destruction command from the ground at 13:43:53. A design deficiency in the recently redesigned SRB-A booster resulted in excessive localized nozzle erosion and burn-through, which was determined to be the cause of the accident. Enhancements to the SRB-A booster design were implemented on subsequent launches.
SOURCES:
JAXA article on H-IIA F6 failure
Space Activities Commission investigation report (online source, Japanese text)
0.83
0.75
0.83
0.80
0.82
0.77
0.86
0.83
0.71
0.67
0.85
0.82
0.77
0.73
1.00
0.75
0.75
0.70
0.71
0.67
0.79
0.75
0.77
0.73
1.00
0.83
1.00
0.80
0.94
0.92
0.95
0.93
0.94
0.93
0.94
0.93
0.91
0.89
0.93
0.91
0.90
0.87
0.94
0.92
0.90
0.88
0.93
0.91
0.88
0.86
0.88
0.85
1.00
0.86
Realized Rate
Predicted Rate