Thanks for that. The propellant mass values for the stages are given here,
but not the Isp values or dry mass values:
http://spaceflight101.com/japan-ss-520-5-launch-success/
Bob Clark
On Sun, Feb 18, 2018 at 12:41 PM, Ed LeBouthillier <codemonky@xxxxxxxxxxxxx>
wrote:
On Sun, 2018-02-18 at 10:38 -0500, Robert Clark wrote:
Trying to find the specs on the stages of the rocket such as thrust,
Isp,
mass ratio if anyone knows those. Some reports give the max payload
to
orbit as 4 kg. Then scaling it down to a 1 kg payload, perhaps a 650
kg
rocket could launch a 1U cubesat to orbit. This would be in the size
range
a university team could produce of a APCP propellant rocket.
I've got my first-cut approximations. What I have so far is attached.
There are big gaps in the details that I'm working on identifying.
Some of the values are pretty certain because there are technical specs
on the 1st stage motor available. The upper stages are still mysteries
in many of their details.
However, I've also written to JAXA to get official specs and I will
improve the results once I get feedback.
Cheers,
Ed L