FLOWN APOLLO 11 CSM MANEUVER CARD.
SOME OF NEIL ARMSTRONG'S MOST EXTENSIVE FLIGHT NOTES, INCLUDING ALDRIN'S ACTUAL BURN DATA FOR MCC-5.
Flown Apollo 11 CSM Updates Checklist, P(Program) 30 data grid, a single sheet printed recto and verso. NASA/MSC, April 5, 1969, updated July 10, 1969. 5½ x 8 inches. Extensive notations by all three Apollo 11 crewmen. With a Typed Letter Signed by BUZZ ALDRIN.
FLOWN APOLLO 11 CSM P(Program) 30 SHEET, ONE OF ONLY TWO USED BY ARMSTRONG DURING THE MISSION.
During this period of the mission, the Apollo 11 crew had just successfully entered orbit of the Moon. Neil Armstrong recorded the TEI4 data information during the early parts of the second lunar orbit. The reverse side data was recorded by Mike Collins during the fourth lunar orbit. The MCC (Mid Course Correction) 5 burn data was recorded by Buzz Aldrin just after the TransEarth Injection during their return home to Earth. This single P-30 sheet contains some of the most critical flight maneuver data recorded during the entire flight and is the only one with data recorded by all three Apollo 11 crew members.
BUZZ ALDRIN'S signed provenance letter reads: "The data card which accompanies this letter is from the Apollo 11 CSM Updates, Part No. SKB32100080-330, S/N 1001, a manual flown in the Command Module Columbia during the first lunar landing mission during July 16 to 24, 1969. It is a P30 maneuver card that is in a column and grid format for recording data to perform spacecraft engine burns.
This card has data that Neil Armstrong recorded for the TEI 4 (Transearth Injection) lunar orbit number 4 as read to him from Mission Control at about 79 hours into our mission. Neil logged 11 data entries including the purpose - 'TEI 4,' our spacecraft weight (WT) of '38320' pounds, engine trim angles of '-0.55' and '+0.60,' the actual time for the burn in hhh mm ss.ss - '084:30:27.49,' the change in velocity (deltas Vx, Vy, and Vz) of '+3138.0, +0347.5, -0103.2.' The P value of '034' is the angle for the IMU (Inertial Measurement Unit) for the maneuver. Neil then wrote: '2 Jet, 16 sec.' which meant we would use just 2 of the reaction control engines for 16 seconds to set the proper ullage for our main propellant tanks. Neil also wrote the purpose for the pad 'Undocked NO LOI 2.' TEI 4 was a contingency burn to return home, if required, if we did not have a LOI (Lunar Orbit Insertion) number 2 burn. We could then undock and perform this TEI burn to return home. This pad update was actually the second one we recorded for TEI 4. During the LOI 1 burn, we used a bit more propellant that expected, thus we needed updated figures for the contingency TEI 4 burn.
On the other side of this card, there is an identical P30 grid which has three different burn pads. Mike Collins recorded the first entry in pencil for TEI 11 around 83 hours and 30 minutes into the mission. Neil and I were in the LM completing communication checks at that time. Mike logged the following starting with PURPOSE all the way through to the R, P, and Y blocks: 'TEI 11, SPS/G&N, 37200, -0.60, +0.47, 098, 05, 24.22, +4144.8, +0371.9, -0242.2, N/A, 020, N/A.' Mike then wrote: '2 jet :16, use B & D, Undocked, present CSM WT (weight) 37,002 #.' This pad was for a contingency return home that could be done during lunar orbit 11 and we planned to use 2 reaction control jets (B and D) for 16 seconds for the needed ullage.
Mike then wrote the TEI 30 pad at the right side margin based on our own spacecraft navigational data. The PURPOSE through to the R, P, and Y blocks recorded information was: '30, SPS/G&N, 36639, -0.72, +0.51, 135, 24, 40.00, +3217.8, +0603.6, -0130.4, 0 (then lined out), 064, (then another line out).' His last entry on the right margin was 'LOI REFSMMAT' which was the basis of this data.
The actual implemented burn on this side was the MidCourse Correction burn number 5 which occurred at 150 hours 29 minutes into the mission. This was sent to me at around 148 hours 45 minutes. I logged over 20 values which included the purpose and propulsion/guidance - 'MCC 5, RCS/G&N,' our spacecraft weight (WT) of '26025' pounds, engine trim angles were not needed, the scheduled time for the burn in hhh:mm:ss.ss - '150:29:54.53,' the change in velocity (deltas Vx, Vy, and Vz) of '-0004.8, +0000.1.' The R, P, and Y values of '075, 159, 328,' for the angles used by the IMU (Inertial Measurement Unit). We did not need HA (Apogee) but HP (Perigee) was '+0023.0.' Total velocity (delta VT) was '0004.8,' Burn Time (BT) in minutes and seconds of '0:11' and our premaneuver setting (delta VC) was '0004.8.' The next 3 values of '03, 090.8, 38.2' were star, shaft, and trunnion settings for the sextant. Additionally I recorded Lat and Long values of '+11.02, -172.04' with a Range To GO of '1180.3' and Inertial Velocity (V10) of '36275' with an end of mission Ground Elapsed Time (GET) of '195:03:33' in hhh:mm:ss.
Then I wrote the flight notes of: 'D & Vega' for stars Deneb and Vega, with an alignment of '007, 144, 068.' The '4 Q' meant we would use only the 4 reaction control engines for the course correction. The burn was successful which enabled us to splashdown very close to the USS Hornet, our prime recovery ship.
I have written 'Carried to the Moon on Apollo XI' and signed my name on the TEI-4 side of the card. This page has been in my private collection since my return from the Moon in July 1969."
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