[AR] Re: [AR] Re: [AR] Re: “Transitioning space propulsion to a nitrous-based industry standard”
- From: Ben Brockert <wikkit@xxxxxxxxx>
- To: arocket@xxxxxxxxxxxxx
- Date: Wed, 5 Apr 2023 11:01:53 +0200
Setting that aside, bear in mind that torch igniters don't necessarily
have to add a lot of complexity or delay. The Apollo SM/LM RCS engines
used a "preigniter" scheme, with the plumbing arranged so that propellant
flow through the main valves reached the preigniter chamber first, so it
would light (hypergolically) and pressurize the main chamber before flow
reached the main injector, minimizing (hypergolic) ignition delays there.
You could presumably do the same thing with a spark-ignited torch, so it
would still need the spark system but wouldn't have its own valves etc.
This is reportedly how the RCS worked on DC-X, a spark torch igniter
and main chamber on the same valves. I haven't seen much documentation
on it, just heard about it from someone who worked on it.
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