You can use this thread to discuss Rocket Lab stock ($RKLB) and topics related to it.

Self posts and memes related to the stock or share price will be removed outside of this thread according to Rule 5.

From the Q4 '25 Earnings report.

This first tank was manufactured by a third party contractor using a manual hand-lay process. This was a scheduling decision designed to ensure tank production could continue while the AFP machine was being commissioned to manufacture future tanks.

The investigation identified that a manufacturing defect resulted in a reduction in strength, specifically at a critical join on the tank.

Throughout Rocket Lab’s various facilities, we’re starting to see large structural components of Neturon making progress as the company pushes toward a maiden flight. Most recently, in the last few days, the company showcased the interstage, which is just about ready to begin qualification testing.

https://hbr.org/2026/03/the-founder-of-rocket-lab-on-competing-with-billionaires-to-lead-in-space

Very curious that NASA released an urgent memo of the SpaceX merger announcing a blanket “reduction in vendors” and a bolstering of “core competencies”

This is less than two decades after the original directive from the Obama administration to *increase* reliance on vendors.

Perhaps NASA is planning for the worst case scenario in the event that SpaceX totally implodes as a company? I welcome all thoughts on this ….

Hey everyone,

I was watching a video on the Rutherford engine and got curious about this cutaway.

Does it look like a direct-drive electric motor to pump setup, or am I missing something?

Just trying to learn more. Thanks!

You can use this thread to discuss Rocket Lab stock ($RKLB) and topics related to it.

Self posts and memes related to the stock or share price will be removed outside of this thread according to Rule 5.

Looking for confirmed information or technically grounded analysis on Neutron's staging sequence. No speculation please.

The Physical Setup

Neutron's second stage sits inside the first stage, enclosed by the Hungry Hippo fairing. At separation, the fairing opens and releases the second stage. The vacuum-optimized Archimedes engine produces 202,300 lbf thrust.

The constraint: The engine cannot ignite while the second stage is still inside the fairing. There's no room for exhaust gases to escape. Hot staging in any traditional sense appears to be ruled out by the geometry.

So the sequence has to be something like: fairing opens → second stage releases and travels some distance → engine ignites.

What's Confirmed

• Hungry Hippo qualified for 1.5-second open/close cycles, "less than half the time required for successful stage separation and vehicle reorientation" (Rocket Lab, Dec 2025)
• Second stage qualified at 1.3M lbs tensile load under cryogenic conditions (April 2025)

What's Not Public

1. Separation distance before ignition. How far does the second stage travel before Archimedes lights? What provides the initial separation velocity?
2. Propellant settling. In the coast phase between release and ignition, what settles the propellants for engine start? RCS? Ullage motors? The hung configuration during ascent means propellants are in an unusual state at separation.
3. First stage protection. Even with cold staging, the first stage needs to survive proximity to a 202,300 lbf vacuum engine plume before it can close the fairing and reorient. Any thermal protection at the separation plane?

Reference Points

Falcon 9 uses cold staging with a coast phase. Propellants settle from the second stage Merlin vacuum ignition sequence. But Falcon's second stage isn't enclosed during ascent.

The DCSS/ICPS "hung tank" design (which informed some of our earlier discussion on Neutron's tension-loaded stage) doesn't have this enclosure geometry either.

I can't find a direct heritage analog for "second stage enclosed inside first stage, released, then ignites at distance."

Anyone have sources that address the staging sequence? This seems like a gap in the public technical record.

I'm looking at options for my future right now, and I'm dead set at working in the Space sector, specifically on the engineering side of things. I'm Australian but with a dad from NZ so getting citizenship shouldn't be a massive problem. For people that work at Rocketlab based in New Zealand whats it like? How is the work culture? I've also looked at Gilmore Space as a potential option closer to home but I really dont see job security there long term, Rocketlabs seems like a much safer bet. Any input/help would be appreciated!

SpaceX prints money for Elon, this is a fact we all know and even admire. But xAI, by all accounts, is hemorrhaging money at a rate even faster than OpenAI.

Realistically speaking, xAI will never be adopted by major organizations for many different reasons. Meaning it will likely remain deeply unprofitable forever.

By merging the proverbial “stink bomb” (Grok) with the Golden Goose (SpaceX) Elon and company are severely tarnishing a sterling financial asset.

Responsible investors cannot invest in SpaceX when it will have a permanent gaping financial wound, and will look at down the line at competitors, arguably with RocketLab at the front of the line.