Astra Space

[Steven Pietrobon]

Funny looking second stage. Looks like a toroidal fuel tank below the LOX tank. Can't tell if its pressure or pump fed.

[brussell]

I think that's made up. That wasn't an Astra rendering.

[Kosmos2001]

The rocket looks great. I hope they make it.

[john smith 19]

Hopefully enough to improve the model of the fairing.

Most or all shot by John Kraus.

That payload fairing looks odd.  Like an umbrella of fabric stretched over a set of ribs.

Which sounds pretty implausible.

Still tremendously exciting as a shot at "responsive space" on a commercial basis. Really looking forward to the launch.

[HeartofGold2030]

Funny looking second stage. Looks like a toroidal fuel tank below the LOX tank. Can't tell if its pressure or pump fed.

It’s almost definitely just a placeholder unless the maker has inside sources, which I highly doubt. Personally, I think it looks more like a solid-fuel kickstage (e.g. Star 48). A small solid-fuel upper stage would be an interesting attempt to keep costs down, at the expense of efficiency. Furthermore, such a setup would be similar to the early American rockets of the 1950s.

[illectro]

Given that we see the bulkheads for the second stage in their factory they're probably not building solid motors, they don't really have the facilities for that. Also the MLI seen on the top of the second stage might be taken to suggest cryogenic propellants. So I still think the most likely option is a Kerolox second stage.

[gmbnz]

A small solid-fuel upper stage would be an interesting attempt to keep costs down, at the expense of efficiency.

And at the expense of accuracy - which for smallsats and constellation building is pretty important.

Given that we see the bulkheads for the second stage in their factory they're probably not building solid motors, they don't really have the facilities for that. Also the MLI seen on the top of the second stage might be taken to suggest cryogenic propellants. So I still think the most likely option is a Kerolox second stage.

Performance-wise too if they're not completely optimising their rocket (eg the fairing carbon fibre decision) I can't imagine a solid having enough mojo to lift their claimed 100kg to SSO.

[LH2NHI]

You can see the second stage in the newly released video.



I guess these tanks are arranged one above the other (like Masten's XOMBIE).

[Comga]

You can see the second stage in the newly released video.



I guess these tanks are arranged one above the other (like Masten's XOMBIE).

Do you mean the stacked spheres towards the back of the room at ~20 seconds?

[john smith 19]

You can see the second stage in the newly released video.

I guess these tanks are arranged one above the other (like Masten's XOMBIE).

Welcome to the site.

Interesting idea. Spheres are the minimum area for maximum volume and mass is more critical for the US. I think people have talked about a kerolox US but its so small I think boiloff would be a serious issue without substantial insulation.  It's the obvious choice for reasonably simple, pretty good performance, although it does need an ignition system.

For minimum complexity, safe handling I thing you could be looking at peroxide with a catalyst pack although that sacrifices performance.

If they are willing to risk the complexity and speculation is correct they could be running with battery powered pumps. Li⁺ battery performance has shown a year on year increase of about 10% so what would borderline for this size a few years ago (when RocketLab started) could be quite viable by now.

Exciting times.

[illectro]

Anyone want to make a guess as to why the launch cube needs gaseous CH4? Given the plumbing inside the launch system I suspect it's part of engine ignition with burners inside the engine combustion chambers, but the old images showing the previous launch tests don't include this.

[FutureSpaceTourist]

https://twitter.com/djsnm/status/1234154850247512065

I think the latest Astra video might have given us a few sightings of the second stage:

twitter.com/djsnm/status/1234157224739491840

Assuming that this can't be much bigger than 1m in diameter, and assuming they're sticking to LOX/kerosene that could contain 600kg of oxygen in a sphere, and ~230kg of kerosene.
For spherical fuel tanks the fuel tank is 80% of the radius of the LOX tank.

https://twitter.com/djsnm/status/1234160362502545413

We can see the plumbing for second stage propellent entering the side of the fairing, and we know the second stage extends up inside this so It's probably something like this.

Edit to add:

https://twitter.com/djsnm/status/1234162335930937344

But the main thing is the using spherical tanks limits the mass of propellent available. So assuming a 100kg stage, 100kg payload and 830kg of propellant that's a wet dry ratio of ~5 which puts it in the right ball park to boost to orbital velocity with >300s of ISP

[jcm]

Has anyone geolocated LP-3B yet?  I assume there is also an LP-3A, is that where the second launch will be from?
Maybe those who are there like John know which way they turn on the road there, or even have a map they can share?
The googleearth image is from 2019 so: the known locations of LP1 and LP2 are marked.  Site C is present but undeveloped in the 2006
image; Site A was added between 2006 and 2010 -  probably support stuff for the Minotaur IV;  Site B/B1/B2 is new since 2010 and is my best guessf for LP-3A/LP-3B.

 

[AnalogMan]

Came across some recent documents outlining plans for the Spaceport produced by Alaska Aerospace (they operate the spaceport).  They are part of the 2020 - 2030 Master plan for future developments (still a work in progress, these drafts are dated January 9, 2020).  Attached are two figures for the Commercial Launch Area (Area 3) showing Pads A thru D and alternative locations for a further Pad E which may be of interest.

Also attached are Chapters 4 and 5 of the Master Plan which has more details.

[Ben]

More recent satellite imagery. JCM, have you tried getting an education account with Planet?

[LH2NHI]

It is very interesting. Feb 28, 2020 video showed a distant view, so I compared it with the plan and satellite photos. The first launch uses PadB.

[LH2NHI]

By the way, according to the link below, the launch capability of ASTRA's Rocket 3.0 is 25 kg for 500 km SSO.
https://spaceflightnow.com/2020/02/24/fresh-out-of-stealth-mode-astra-gearing-up-for-orbital-launch-from-alaska/

Also, according to the link below, Rocket4.0's capacity is 50kg for SSO.
https://spacenews.com/astra-emphasizes-rapid-iteration-in-its-quest-for-low-cost-rapid-launch/

The ASTRA website accepts reservations for 150kg SSO payloads, but how do they improve the rocket?
Larger upper stage (with another container shippment)?

[edkyle99]

By the way, according to the link below, the launch capability of ASTRA's Rocket 3.0 is 25 kg for 500 km SSO.
https://spaceflightnow.com/2020/02/24/fresh-out-of-stealth-mode-astra-gearing-up-for-orbital-launch-from-alaska/

Also, according to the link below, Rocket4.0's capacity is 50kg for SSO.
https://spacenews.com/astra-emphasizes-rapid-iteration-in-its-quest-for-low-cost-rapid-launch/

The ASTRA website accepts reservations for 150kg SSO payloads, but how do they improve the rocket?
Larger upper stage (with another container shippment)?

Possibilities include removal of test instrumentation, second stage restart at first apogee, and more thrust/propellant.  My guess is that second stage restart is a likely means of bumping up sun synchronous payload.

 - Ed Kyle

[Kryten]

By the way, according to the link below, the launch capability of ASTRA's Rocket 3.0 is 25 kg for 500 km SSO.
https://spaceflightnow.com/2020/02/24/fresh-out-of-stealth-mode-astra-gearing-up-for-orbital-launch-from-alaska/

Also, according to the link below, Rocket4.0's capacity is 50kg for SSO.
https://spacenews.com/astra-emphasizes-rapid-iteration-in-its-quest-for-low-cost-rapid-launch/

The ASTRA website accepts reservations for 150kg SSO payloads, but how do they improve the rocket?
Larger upper stage (with another container shippment)?

They've been willing to do major design changes so far, Rocket 3.0 has engines twice the thrust of 2.0 and has to be four-odd times the size of Rocket 1.0.

[LH2NHI]

By the way, according to the link below, the launch capability of ASTRA's Rocket 3.0 is 25 kg for 500 km SSO.
https://spaceflightnow.com/2020/02/24/fresh-out-of-stealth-mode-astra-gearing-up-for-orbital-launch-from-alaska/

Also, according to the link below, Rocket4.0's capacity is 50kg for SSO.
https://spacenews.com/astra-emphasizes-rapid-iteration-in-its-quest-for-low-cost-rapid-launch/

The ASTRA website accepts reservations for 150kg SSO payloads, but how do they improve the rocket?
Larger upper stage (with another container shippment)?

They've been willing to do major design changes so far, Rocket 3.0 has engines twice the thrust of 2.0 and has to be four-odd times the size of Rocket 1.0.

Yes, I think major design change is necessary to reach 150 kg capacity as you mentiond.
ASTRA rockets are made using traditional manufacturing methods, so they may be larger than Electron to achieve the same capabilities......