Post by gonetoplaid on Aug 19, 2009 21:26:03 GMT -4
From this link:
www.hq.nasa.gov/office/pao/History/SP-4009/v3o.htm
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December 9-16
Preliminary results of the "fire-till-touchdown" study by Grumman indicated that this maneuver was not feasible. The engine might be exploded by driving the shock wave into the nozzles. The base heatshield temperature would exceed 1,789K (5,000 degrees F), which was high enough to melt portions of the structure, possibly causing destruction of the foot pads. The allowable pressure on the nonstructural elements of the base heatshield would be exceeded; and the descent engine flow field would tend to cause a "POGO" effect which would cause landing instability and could prevent engine cutoff.
As an outgrowth of the study, the landing probes would have to be made longer (137.1 to 187.9 cm [54 to 74 in] with automatic cutoff, 228.6 to 304.8 cm [90 to 120 in] with manual cutoff). The probe switches would be moved from the tip of the probe to the base, which was objectionable from the standpoint of a possible false reading due to probe dynamics.
MSC, "ASPO Weekly Management Report, December 16-23, 1965."
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Well, knowing that the length from edge-to-edge of the footpads for opposite landing gear legs is 31 feet, I examined the Eagle LM in photo AS11-44-6598 and calculated that the length of the landing probes is 5.5 feet or roughly 66 inches. That seems to be right in the middle of the recommended probe length for using automatic engine cutoff.
My question is, does anybody know "for sure" whether the LM's used auto engine cutoff on probe surface contact or did the astronauts have to manually kill the engine within 0.7 seconds of getting the blue contact light? Some stuff that I have read says that ideally the engine had to be killed within 0.4 seconds.
I ask because some sources say that engine cutoff was automatic yet other sources say that engine cutoff was manually executed.
www.hq.nasa.gov/office/pao/History/SP-4009/v3o.htm
****************
December 9-16
Preliminary results of the "fire-till-touchdown" study by Grumman indicated that this maneuver was not feasible. The engine might be exploded by driving the shock wave into the nozzles. The base heatshield temperature would exceed 1,789K (5,000 degrees F), which was high enough to melt portions of the structure, possibly causing destruction of the foot pads. The allowable pressure on the nonstructural elements of the base heatshield would be exceeded; and the descent engine flow field would tend to cause a "POGO" effect which would cause landing instability and could prevent engine cutoff.
As an outgrowth of the study, the landing probes would have to be made longer (137.1 to 187.9 cm [54 to 74 in] with automatic cutoff, 228.6 to 304.8 cm [90 to 120 in] with manual cutoff). The probe switches would be moved from the tip of the probe to the base, which was objectionable from the standpoint of a possible false reading due to probe dynamics.
MSC, "ASPO Weekly Management Report, December 16-23, 1965."
****************
Well, knowing that the length from edge-to-edge of the footpads for opposite landing gear legs is 31 feet, I examined the Eagle LM in photo AS11-44-6598 and calculated that the length of the landing probes is 5.5 feet or roughly 66 inches. That seems to be right in the middle of the recommended probe length for using automatic engine cutoff.
My question is, does anybody know "for sure" whether the LM's used auto engine cutoff on probe surface contact or did the astronauts have to manually kill the engine within 0.7 seconds of getting the blue contact light? Some stuff that I have read says that ideally the engine had to be killed within 0.4 seconds.
I ask because some sources say that engine cutoff was automatic yet other sources say that engine cutoff was manually executed.