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Some information to JAXA's
Solid Rocket Booster (SRB-A and SRB-3)
Norbert Brügge, Germany
Upload: 30.06.22020
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SRB-A is a series of Japanese solid-fueled rocket booster manufactured
by IHI Corporation for use on the H-IIA, H-IIB, and Epsilon rockets.
SRB-A is 2.5 meters in diameter, and 15.17 or 15.10 meters in length.
Its casing is a carbon-fiber-reinforced polymer filament wound composite.
Two-axis attitude control is provided by electrically-actuated thrust
vectoring. The SRB-3
with the same diameter is 14.60 m long due to the shortened tip and will
developed for the H-3 rocket (and Epsilon-S). |
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SRB-A
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SRB-3 nozzle
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SRB-A
The original SRB-A was developed for the H-IIA rocket, and was used on
its first 6 flights. It was derived from the SRB used on H-II. During
the sixth launch of an H-IIA, one of the boosters failed to separate due
to a leak of hot gasses eroding the detachment points, causing the rocket
to fail to reach orbit.
SRB-A2
SRB-A2 was a planned upgrade, intended to replace SRB-A on H-IIA. Following
the 2003 failure, it was cancelled and its design improvements were merged
into the SRB-A Improved.
SRB-A Improved
An improved version of SRB-A was developed following the 2003 incident.
The nozzle was changed from a conical to a bell shape, to reduce thermal
loading and erosion. Its thrust was also reduced slightly, and its burn
time lengthed, to further decrease heating. This version was flown on
the seventh through the thirteenth H-IIA. However, the nozzle erosion
problem was still not fully solved, leading to the development of the
SRB-A3.
SRB-A3
SRB-A3 is the current version, redesigned to provide higher performance
and improve reliability. It is available in two variants, one producing
high thrust at a short duration burn, and the other with a longer duration
lower thrust burn. It has been used on all H-IIA flights past the thirteenth
mission, as well as the H-IIB and as the first stage of ASR-Epsilon.
Source: Wikipedia |
However, according to a table published
by JAXA, there are obviously further modifications in which thrust and burn
time are varied. According to my calculations, the following overview is obtained:
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Type
|
Vehicle |
Propellant
|
Max thrust (kN) |
Aver. Thrust (kN) |
Isp (sec) |
Pressure |
Duration
|
Total vac Imp. |
Used
on vehicle
|
|
t |
s.l. |
vac |
s.l. |
vac |
s.l. /vac |
MPa |
sec |
MN*sec
|
|
SRB-A
|
J-1 (2) |
65 |
2,098.6 |
2,260.0 |
1,657.4 |
1,784.9 |
260
/ 280 |
|
100 |
178.48 |
not realized
|
|
H-IIA |
65 |
2,098.6 |
2,260.0 |
1,657.4 |
1,784.9 |
260 /
280 |
11.8 |
100 |
178.48 |
F01 to F06
|
|
SRB-A2
|
H-IIA |
65 |
1,959.2 |
2,110.0 |
1,453.9 |
1,565.8 |
260 / 280 |
|
114 |
178.48 |
not used
|
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SRB-A
improved
|
H-IIA |
66 |
2,084.7 |
2,245.0 |
1,314.7 |
1,415.9 |
260 /
280 |
|
128 |
181.23 |
F07
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|
66 |
2,122.3 |
2,285.0 |
1,407.7 |
1,515.5 |
261 /
281 |
|
120 |
183.56 |
?
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SRB-A3
|
H-IIA |
65 |
2,271.5 |
2,445.0 |
1,670.1 |
1,797.5 |
262 /
282 |
|
100 |
179.76 |
F14
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|
66 |
2,102.9 |
2,262.5 |
1,421.7 |
1,529.8 |
263.6 /
283.6 |
11.1 |
120 |
183.56 |
F15, F17
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|
64.9 |
2,324.2 |
2,500.5 |
1,711.7 |
1,841.6 |
263.6 /
283.6 |
11.8 |
98 |
180.50 |
F18
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|
66 |
2,142.5 |
2,305.0 |
1,421.7 |
1,529.8 |
263.6 /
283.6 |
|
120 |
183.56 |
F21
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H-IIB
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66 |
2,142,5 |
2,305.0 |
1.496.4 |
1,610.1 |
263.6 /
283.6 |
11.1 |
116 |
183.56 |
3040: F01 to F09
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Epsilon |
66 |
2,142.5 |
2,305.0 |
1,523.3 |
1,639.0 |
263.6 /
283.6 |
|
112 |
183.56 |
F01
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Epsilon-2 |
66 |
2,184.3 |
2,350.0 |
1,579.6 |
1,699.7 |
263.6 /
283.6 |
|
108 |
183.56 |
F02 to F04
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SRB-3
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H-3 |
66.8 |
2,233.5 |
2,402.6 |
1,647.0 |
1,771.7 |
264 / 284 |
|
105 |
186.04 |
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Red colored =official source; Average thrust calculation
on base duration
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SRB-A full thrust sequences in tests
(PM, EM, QM)
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SRB-A QM3
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First SRB-A nozzle
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The following SRB nozzles (SRB-A.imp./-A3
and -3)
are slightly bell-shaped and shorter.
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SRB3-OM2
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