H3 (rocket)

Last updated

Sources: Japanese Cabinet [23]

H3
H3 rocket model in Kakamigahara Aerospace Science Museum November 8, 2019 02.jpg
A model of the H3 Launch Vehicle
Function Medium-lift launch vehicle
Manufacturer Mitsubishi Heavy Industries
Country of originJapan
Cost per launchUS$50 million (H3-30S) [1]
Size
Height63 m (207 ft) [2]
Diameter5.27 m (17.3 ft) [2]
Mass574,000 kg (1,265,000 lb) for H3-24L [3]
Stages2
Capacity
Payload to SSO
Mass4,000 kg (8,800 lb) for H3-30 [2]
Flight No.Date and time (UTC)VersionLaunch sitePayload(s)Launch outcome
TF17 March 2023,
01:37:55 [24]
H3-22S [25] Tanegashima, LA-Y2 ALOS-3 Failure
TF217 February 2024,
00:22:55 [26]
H3-22S Tanegashima, LA-Y2 Vehicle Evaluation Payload (with rideshares: CE-SAT-1E / TIRSAT) [27] Success
F31 July 2024,
03:06:42 [28]
H3-22S Tanegashima, LA-Y2 ALOS-4 Success [29]
F44 November 2024, 06:48H3-22S Tanegashima, LA-Y2 DSN-3 (Kirameki 3)Success

Future launches

Date and time (UTC)VersionPayload(s)
1 February 2025 [30] H3-22S
F5
QZS-6
JFY2025 (TBD) [31] H3-30S
F6
Vehicle Evaluation Payload (with rideshares: PETREL / STARS-X / VERTECS / HORN L / HORN R / BRO-x)
September 2025 [32] H3-24W
F7
HTV-X1
JFY2025 (TBD)H3-22S
F8
QZS-5
JFY2025 (TBD)H3-22S
F9
QZS-7
JFY2025 (TBD)H3-24L
F10
ETS-IX
JFY2026 (TBD)H3-24W HTV-X2
2026 (TBD)H3-24L MMX
JFY2026 (TBD)H3-24W HTV-X3
JFY2026 (TBD)H3 IGS-Optical Diversification 1
2026–28 (TBD)H3 LUPEX
JFY2027 (TBD)H3 IGS-Optical 9
JFY2027 (TBD)H3 IGS-Optical Diversification 2
2027 (TBD)H3JDRS-2
2027 (TBD)H3 ALOS-3 Successor
2027 (TBD)H3 Eutelsat (TBD) [33]
March 2028H3 MBR Explorer
JFY2028 (TBD)H3 Himawari 10
2028 (TBD)H3 ALOS-4 Successor
JFY2029 (TBD)H3 IGS-Radar Diversification 1
JFY2029 (TBD)H3 IGS-Optical 10
JFY2030 (TBD)H3 IGS-Radar Diversification 2
JFY2031 (TBD)H3 IGS-Radar 9
JFY2032 (TBD)H3 IGS-Optical Diversification Successor
JFY2032 (TBD)H3 LiteBIRD
JFY2033 (TBD)H3 IGS-Radar 10
JFY2033 (TBD)H3 IGS-Optical 11
(TBD)H3 Inmarsat (satellite TBD) [34]

TF1

The first launch attempt on 17 February 2023 was aborted just before the SRB-3 boosters ignition, although the main engines were successfully ignited. [35] [36] [37]

On the second launch attempt for the H3 Launch Vehicle on 7 March the vehicle launched at 1:37:55 AM UTC (Universal Time Coordinated). Shortly after the SRB-3 boosters separated from the rocket around two minutes into the flight, the rocket appeared to lose control and begin to tumble based on the views from the ground camera; however, based on subsequent analysis, this appears to be part of a planned dogleg maneuver in order to achieve sun-synchronous orbit and not in fact a loss of control. [38] Approximately five minutes and twenty-seven seconds after launch, the second stage engine failed to ignite. After continuing to be unable to confirm second stage engine ignition, and with the velocity of the rocket continuing to fall, JAXA sent a self-destruct command to the rocket at around L+ 00:14:50 because there was "no possibility of achieving the mission". The payload onboard was the ALOS-3 satellite, which was also destroyed with the launch vehicle on the moment of self-destruct. [39] [40] [41] [42] [43] [44] [45] [46] [47]

TF2

On 17 February 2024, JAXA finally successfully launched the second testing rocket which has the same configuration as the first one, H3-22S, and the second stage reached the desired orbit. [48]

Notes

  1. A Japanese Fiscal Year starts in April of the year and ends in March of the next year. For this case, it denotes launch will occur no earlier than 1 April 2021, and no later than 31 March 2022.

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The LE-5 liquid rocket engine and its derivative models were developed in Japan to meet the need for an upper stage propulsion system for the H-I and H-II series of launch vehicles. It is a bipropellant design, using LH2 and LOX. Primary design and production work was carried out by Mitsubishi Heavy Industries. In terms of liquid rockets, it is a fairly small engine, both in size and thrust output, being in the 89 kN (20,000 lbf) and the more recent models the 130 kN (30,000 lbf) thrust class. The motor is capable of multiple restarts, due to a spark ignition system as opposed to the single use pyrotechnic or hypergolic igniters commonly used on some contemporary engines. Though rated for up to 16 starts and 40+ minutes of firing time, on the H-II the engine is considered expendable, being used for one flight and jettisoned. It is sometimes started only once for a nine-minute burn, but in missions to GTO the engine is often fired a second time to inject the payload into the higher orbit after a temporary low Earth orbit has been established.

<span class="mw-page-title-main">N-I (rocket)</span> Booster

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The LE-9 is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in an expander bleed cycle. Two or three will be used to power the core stage of the H3 launch vehicle.

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The Innovative Satellite Technology Demonstration Program is a series of spacecraft missions for testing technology and ideas put forward by universities and private companies. The program demonstrates various experimental devices and technology in space by providing flight opportunities. It is managed by the JAXA Research and Development Directorate. According to JAXA, the goal of this program is to test high risk, innovative technology that will lead to the space industry gaining competitiveness in the international field.

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