Agreed Gaseous H2 would be a good choice, though I don't know the specific
problem they were trying to solve.
I also remember hearing references to gaseous Methane (as well as the
helium reference). In the end, I'm not sure which gas they chose.
Anthony Cesaroni could provide some enlightenment. Alas he is no long on
the list...
Brian Feeney
President CEO - CTO
Alaia Design Group
alaiadesign@xxxxxxxxx
On Tue, Jan 5, 2021 at 6:44 PM roxanna Mason <rocketmaster.ken@xxxxxxxxx>
wrote:
GH2 would be a better choice lighter too and has been done,at EdwardsAFB,
on solid rocket motors to boost ISP but they used LH2 of course.
K
On Tue, Jan 5, 2021 at 3:16 PM Brian Feeney <alaiadesign@xxxxxxxxx> wrote:
I would agree that the CG has shifted, unless this was their intention to
scarf the nozzle from the beginning with the low wing design.
The only thing that comes to mind are the high pressure helium (other
gas?) pressure vessels that are placed in the leading edge of the wing.
I believe these were added after the fact to provide helium gas injection
into the hybrid engine to deal with some bombustion anomalies. If this is
the case it would have been an unplanned added weight.
Cheers Brian
-----------------
Brian Feeney
President CEO - CTO
Alaia Design Group
alaiadesign@xxxxxxxxx
On Tue, Jan 5, 2021 at 5:17 PM Michael Kelly <dmarc-noreply@xxxxxxxxxxxxx>
wrote:
Does anyone know why VG has scarfed the SpaceShip 2 nozzle fairly
dramatically? I've seen it in videos from two different flights, so
it isn't a one-off. The only explanation I can imagine is that the CG of
SS2 has shifted (it would be lower than originally designed). It's
puzzling that VG would accept the performance loss associated with
scarfing, rather than reworking the CNT to slightly angle the full nozzle.
Forgive me if this has been asked and answered; I somehow unsubscribed
to arocket for a time, and may have missed it.