[AR] Re: Successful Launch Of SS-520
- From: Ed LeBouthillier <codemonky@xxxxxxxxxxxxx>
- To: arocket@xxxxxxxxxxxxx, arocket@xxxxxxxxxxxxx
- Date: Mon, 19 Feb 2018 12:49:09 -0700 (GMT-07:00)
Bob Clark said:
Thanks for that. The propellant mass values for the stages are given here,
but not the Isp values or dry mass values:
The values for the 1st and 3rd stages have references (with fudge factor for
average Isp for the first stage: 266 s vac). The 2nd stage, I assumed the same
Isp as the 3rd stage. I'm still researching for more details for the each of
the stages.
For the SS-520 first stage, I used the values available for the S-520 stages
(from which the SS-520 first stage was developed). The Lambda (body:propellant
ratio) is from the S-520 with tail fins. Contact me if you want the references.
But there's still a lot of variability possible: the delta V for each of the
stages is guessed and the Lambda for upper stages is guessed. But, the numbers
work pretty closely to all currently available published figures.
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