ZERO Orbital Launcher | 60 kN Engine Static Firing Test (Regenerative Cooling)

A combustion test of a 60 kN class prototype engine for an orbital launcher “ZERO”.
Interstellar Technologies Inc. (IST) is developing the orbital launcher “ZERO”.
Test stand: Interstellar Technologies Inc., Hokkaido Space Port
Date: March 30th, 2020
Thrust: 60 kN class
Injector type: Pintle
Propellant: Methane / LOX (Liquid Oxygen)　*Compressed Natural Gas was used.
🄫Interstellar Technologies Inc.
This combustion test was conducted as part of a contracted development from the Japanese Ministry of Economy, Trade and Industry.
#インターステラテクノロジズ
#ロケット
#宇宙
#Interstellar
#Rocket

[@neo_corra]

0:27からがすげえｗｗｗ

[@EngineerM]

卒業したらこういう所で働きたい。

[@Anvilshock]

Beautiful!

[@marusakura938]

綺麗なショックダイヤモンド😃

[@user-ko7si3fh9r]

透明なまま推進力を維持している

[@viewchico]

Time- 30sec. it hit VTEC mode “blue star”

[@rokuroku3604]

IHIが開発していたLPGエンジンと構造は同じなのかな？再使用に適してるエンジンですね。

[@supertyfon1736]

I know rockets exceed 200 dB but i heard an air horn like sound before engine cutoff.

[@user-ir7ku4uc1x]

momoが12kNだけどそれ以上にやっぱ迫力すげえな

[@Hitodekawaii]

規制線とか張らないんですね

[@ultraryman]

倉庫ごと発射して欲しい…

[@user-wn1mf1me8s]

緑色の炎（銅の炎色反応）がなくなってる。進歩が早い

[@TihaTan3150]

ほんそれ…高い部品使うと無くなるんだろうけど…民需打ち上げだからなぁ

[@cf-105arrow9]

There is additional exhaust and flume on the main combustion chamber. What’s that? And what’s the purpose?

[@SciFiFactory]

My guess would be that it is the exhaust from the gas generator that runs the fuel pump. Edit: No, actually, that looks like water. So it could be to protect the floor from the heat.

[@TA-xw1lx]

I guess thats what "水冷"燃焼器 is. water cooling.

[@SciFiFactory]

@@TA-xw1lx they water cool the engine? Huh. I guess that makes sense for a step by step development.

[@user-yj6ne2uv6j]

メタン/LOX 60kN級ロケットエンジン試験（水冷燃焼器）Static fire test of 60 kN class engine for orbital launcher “ZERO” kzbin.info/www/bejne/a4C6imVnjLV_icU

[@StreuB1]

You have a low frequency combustion instability when you transition into full thrust mode. Likely flame front oscillation due to chamber volume (Vc) being too small or characteristic chamber length (Lc) being too short. Could be injector to propellant feedline coupling as well.... How was your pressure trace looking on the tanks vs feedline vs injector?

[@cody7374]

Its no doubt the LC, looks less than 5 inches. That is crazy short...

[@KT-ez7rv]

You are totally correct about the instabiliy, however the cause is not due to L*. It is caused by significant O/F off-target resulting in pintle momentum ratio off-design. (former designer)

[@StreuB1]

@@KT-ez7rv Ahhh ok. So the deviation in pintle momentum is causing a shift in the resultant impingement half angle causing "fluttering" of the impingement pattern? I could tell based on the plume that there was a definite oscillation in the flame front and attributed it to pulsation due to feedline coupling (affecting the impingement half angle) or the flame front "walking" up and down the chamber due to resonant reversion associated with L*. Wasn't thinking of O/F deviation causing it.

[@KT-ez7rv]

@@StreuB1 Surprised & happy to get a response. I have already left this project awhile ago, but this engine never reached the intended combustion pressure, due to test stand limitations (funding issues). You are totally right about pulsation. The feed line upstream pressure is insufficient to achieve enough deltaP for stable injector function, even with if you left out the O/F issue. As others have stated, this chamber also runs a dangerously low L*, with the length limited by cooling capacity. It was a purpose built independently cooled chamber to obtain cooling channel performance data using pressurized steam. At least the cooling calculations were right, but I doubt there will be further development in the near term as they are focusing their resources on the ballistic launch platform at the moment.

[@cikguninja8363]

Earth has been move an inch from the orbit

[@Mollusk_Mollusk]

0:13辺りのジェットの形好きだわぁ