NASA has lengthy and detailed and complete LM checklists on PDF that you can download. You have these, right ? I bet there are 1,000 pages of LM information in detail. They are very good.
Can you supply a link for the LM checklists mentioned above?
Quote from: dks13827 on 09/17/2014 01:14 amNASA has lengthy and detailed and complete LM checklists on PDF that you can download. You have these, right ? I bet there are 1,000 pages of LM information in detail. They are very good.Yes, I have these, LM handbooks, two part. Sorry, I didn't know what was all in there. It's 2000 pages of stuff.
One more question, it can go here. I read in flight plan that LM FDAI was R0 P0 Y0 at landing site. Does that mean that Roll, Pitch and Yaw were calculated in relation to Lunar horizon? So wherever they were, if R, P and Y were all zero it means they were looking perpendicular to Lunar gravity vector?
The question is, how thoroughly did the LEM pilots actually study those 2,000 pages before flying?
The mode is LVLH (Local Vertical Local Horizontal)
And if you could answer that question about circuit breakers on side panels - how were they activated - by pulling them or pushing them?
Out - open, in - closed.
How does thruster "flame" look like in vacuum? I know there can't be smoke, but I wonder can you see some fuel exiting thrust chamber or something?
If I recall correctly, shuttle used compressed gas for RCS, not real combustion in thrust chamber?
One more question. Does anybody know what was propellant consumption for DPS? I am digging through all those manuals and reports and I only found "Engine life - 910 seconds or 17 510 pounds of propellant". Does that mean for full throttle all time?
However, on the Apollo 17 ascent video (the only one where the LM's pitchover maneuver was captured),
In your LM simulator have you got the Rate of Descent switch ? Descent engine command override switch ? Those are 2 of the items of interest, you may find.
Well, according to Wikipedia, the maximum thrust was 10,125 lb and the specific impulse was 311 s. That implies a consumption rate at full throttle of 35.6 lb/s.
Quote from: Proponent on 12/22/2014 05:26 pmWell, according to Wikipedia, the maximum thrust was 10,125 lb and the specific impulse was 311 s. That implies a consumption rate at full throttle of 35.6 lb/s. I run this through my simulation and it is correct. Or 14.763kg/s on full throttle. I assumed that there is linear relationship between thrust and fuel consumption for given engine.
As an FYI, the LM DPS used a pintle system to adjust fuel and oxidizer flow into the combustion chamber to vary thrust, so throttling the engine up and down did directly impact the rate of depletion of the propellants. The original proposal for throttling the DPS used injection of helium into the propellant streams to dilute them and thereby reduce thrust, which would have had much less of an impact on depletion rates.