H — Japan, 1986 H-IIB The original H-I was built by Mitsubishi as a derivative of their N series rockets, which were licensed copies of Delta. The first H retained the Delta-based first stage but used an original upper stage which burned hydrogen (hence the use of the letter H) and could re-ignite in orbit. The successor H-II was an all-Japanese design. It was replaced with the cheaper and more reliable H-IIA in 2001, and in 2007 it was privatized, so Mitsubishi has full ownership. The H-IIB arrived in 2009, featuring a fatter first stage with two engines. This has mainly been used for space station service. The A remains in use for lighter loads. Japan had a lot of smaller rockets as they gradually built up their expertise, mostly named after letters of the Greek alphabet. Now those are all gone, except that they’ve gone back to that in naming the new Epsilon. One odd trait of these earlier rockets is that their lower stages were completely innocent of any form of active guidance. They were made this way so as to prove they would be useless as potential ICBMs. They had to be launched from a leaning tower to aim them toward orbit. The core stage of the H-II burns hydrogen (so the “H” name is more applicable than ever), and is augmented with either two or four stubby solid boosters, sometimes with smaller booster-ettes tucked in between. The H-IIB always uses four, as its whole point is for heavier lifting than the A. The second stage also burns hydrogen. The original H-I upper stage engine used a conventional gas generator cycle, but for the II they switched to an expander bleed cycle — the first engine with that cycle to enter service. (Blue Origin is also planning to use that cycle for their BE-3U upper stage engine on the New Glenn.) There were a couple of different plans to launch human beings on an H-IIA, with both capsule and spaceplane designs existing on paper, but none were built. H3 But first they developed an H-III, which keeps the wider tank diameter from the H-IIB. (They also developed the ability to say “H3” instead of using roman numerals.) For this they replaced the dual LE-7A hydrogen engine with either two or three new engines called LE-9. The old engine used staged combustion, but for the new one they are building the world’s biggest expander-cycle engine, apparently on the belief that higher reliability matters more than higher specific impulse. Even with just two engines, this will increase the stage’s thrust considerably. The LE-5B expander on the second stage is getting a small upgrade. The III has similar solid boosters to the ones the IIB used, with a touch more propellant. Otherwise, not much else has changed, so it doesn’t sound like the cost could be reduced all that much, but by adding up a lot of small savings they get a substantial overall improvement. They aimed for a cost of $40 million per launch, which is half of what the old rocket cost, and underprices the Falcon 9. As this neared readiness, the IIB was retired, while the IIA remained active. The H3 can have zero, two, or four solid boosters. When no strap-ons are used, they fit three LE-9 engines under it. This is apparently the preferred configuration for low orbit, with the boosters being added on mainly for geosynchronous and higher destinations, though the LEO capacity without them is only about six tons. (They don’t like to give payload specs for LEO at all, focusing on sun-synchronous and geostationary capacities. The first test was sun-sync, which involved a rather severe dogleg in the flight path to stay safely over the ocean.) When the strap-ons are used, two core engines are enough; adding a third turned out to have very little benefit. Unfortunately the first H3 launch failed. The complicated new first stage was fine; it was the relatively unchanged upper stage that failed to light up. And unfortunately, because of the long delay in getting off the ground, they put quite an expensive satellite onto the test flight. This led to a lot of public criticism and hand-wringing which will only further delay the second attempt. For the future they are considering a triple-core H3 Heavy that would be able to lift 28 tons. That would give this system a wide range of capacities comparable to that of the Angara. H-IIB: mass 531 t, diam 5.2 m (10.3 at base), thrust 8146 kN, imp 4.3 km/s, staged combustion (hydrogen) and solid fuel, payload 19 t (3.6%), cost $10M/t, record (including II and IIA) 58/0/3 through May 2023. [Show stages] Stage name Nissan L-178 L-17 Role (pos) count booster (S) ×4 core (1) upper (2) Diameter (m) 2.50 5.20 4.00 Liftoff mass (t) 77 203 20 Empty mass (t) 10.9 24.9 3.9 Fuel mass (t) ~20 ~26 ~2.7 Oxidizer mass (t) ~46 ~152 ~13.4 Fuel type HTPB hydrogen hydrogen Engine SRB-A3 LE-7A ×2 LE-5B-2 Power cycle solid staged expander Chamber pres. (bar) ? 127 38 Ox./fuel ratio 2.3? 5.90 5.00 Thrust, vac max (kN) 2305 2196 137 Thrust, SL initial (kN) 1615 1685 — Spec. imp, vac (km/s) 2.78 4.30 4.39 Total imp, vac (t·km/s) 734 770 74.2 H3-30 (no boosters): mass ~265 t (574 t with four boosters), diam 5.2 m (10.3 at base), thrust 4410 kN (11600 kN), imp 4.17 km/s, expander bleed (hydrogen), payload ~6 t (2.3%), cost $7M/t?, record 0/1/0 through May 2023.