The Apollo LM had a radar altimeter which was particularly critical in the final stages of landing. It could be set to two different pitch angles, either aimed backwards by 24º to be used during the earlier part of descent when the LM was pitched far back, or aimed directly downwards for the final approach.

As the LM pitched and rolled during its final descent maneuvers, the radar beam would unavoidably be swept around the lunar terrain. This would yield two sources of error: the height difference between the beam contact point and the terrain directly under the LM, and the off-angle "cosine factor" (the radar beam would be the hypotenuse of a right triangle with the altitude as the adjacent side, getting longer as the spacecraft attitude departed further from the vertical).

Obviously the varying terrain couldn't really be accounted for (or could it?) but the LM guidance system would be aware of its pitch and roll attitude relative to the local vertical, so it could factor out the cosine for a better estimate of the correct altitude.

The LM generally wouldn't pitch or roll beyond 20º in the terminal phase of flight, so the cosine error would be no more than 13% (at 20º pitch and 20º roll) and usually much less, probably around 3.5% when the commander took manual control.

Were the altitude figures presented to the crew by the instruments in the LM corrected for the LM's attitude?

† The guidance computer did include a very crude, low resolution 2-D representation of a cross section of terrain at the expected landing site, which could conceivably be used for correcting altitude for terrain in the downrange direction, but would be useless at best in the crossrange direction.

  • $\begingroup$ I am wondering if there is a possibility the answer is both "no" and "yes" , i.e. a possibility that procedures could have changed between the missions. $\endgroup$ – Sergiy Lenzion Feb 6 at 6:38

Yes and No. The altitude data presented on the altitude indicator (tapemeter) depends on the mode select switch setting.

MODEL SEL switch

LGD RADAR: Radar altitude, altitude rate... are displayed.

PGNS: LGC-computed altitude, altitude rate... are displayed.

AGS: AGS-computed altitude, altitude rate... are displayed.

Source: LM Apollo Operations Handbook Volume I, page 3-22

So with the switch in the LDG RADAR position the data comes directly from the landing radar, as Organic Marble described, which doesn't account for the attitude of the LM. In the AGS position the data would come from the backup computer in the LM, which doesn't even have an interface with the LR. So there the altitude is purely determined from the state vector, which is getting updated with accelerometer data.

But in the PGNS position, which was the nominal position for the switch during the descent (see e.g. Apollo 12 LM Timeline Book page 5), the data comes from the Apollo Guidance Computer, which does incorporate LR data into its state vector calculations. In that process the attitude of the LM and the position of the landing radar (position 1 or 2) is accounted for. The displayed altitude is then derived from the state vector. (Source: Guidance System Operations Plan for Luminary 1E, Guidance Equations figure and page 5.3-72)

To answer your secondary question, starting with Apollo 14 (see Luminary Memo #147 ) the AGC had the ability to account for a simple terrain profile ahead of the landing site. In terms of altitude this means that the displayed number (in PGNS mode) would be altitude above the landing site and not the current altitude (with or without accounting for the pitch or roll angle).

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  • $\begingroup$ AFAIK everything you say is correct. I just took the question literally "does the radar altimeter account for pointing angle" , not the state vector. You've answered the bolded part better. Nice answer, +1 $\endgroup$ – Organic Marble Feb 6 at 13:54
  • $\begingroup$ True, I mainly looked at the bolded part which is slightly different from the title of the question. $\endgroup$ – indy91 Feb 6 at 14:08
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    $\begingroup$ This would be a definitive answer for me if it included a citation for the statement "in that process the attitude of the LM and the position of the landing radar (position 1 or 2) is accounted for." (@OrganicMarble, I've updated the title to better align with my actual question.) $\endgroup$ – Russell Borogove Feb 6 at 15:39
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    $\begingroup$ I see that the terrain model is locked out once P66 is entered, so at least that’s one thing I don’t need to worry about :) $\endgroup$ – Russell Borogove Feb 6 at 21:00
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    $\begingroup$ @RussellBorogove I added a source for the calculations that are done to incorporate the LR measurements into the state vector. $\endgroup$ – indy91 Feb 7 at 10:38


The "LM altitude" computed from the Landing Radar slant range is only corrected for the altimeter beam angles, not the vehicle attitude angles.

enter image description here

The altimeter beam angles are used by the LGC in the computation of LM altitude from LR slant range output.

Source: LMA790-3 -LM APOLLO OPERATIONS HANDBOOK pp. 2.2-25 and 2.2-26

On Figure 2.2-9 you can see the altitude going straight to the crew displays from the Electronics Assembly. There is no input into this processing for the vehicle attitude. It comes only from the radar.

enter image description here

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  • $\begingroup$ I'm not convinced. The document consistently talks about "slant range" as the value supplied by the landing radar, and about "altitude" being displayed. $\endgroup$ – JCRM Feb 7 at 13:59
  • $\begingroup$ If you can supply a reference showing that the vehicle attitude is used in calculating the altitude displayed in the LANDING RADAR switch position, you could 'not convince' me as well. $\endgroup$ – Organic Marble Feb 7 at 14:33
  • $\begingroup$ If you could provide a reference which states the display marked "altitude/rendevous range" actually shows the slant range, I'll up vote this answer. $\endgroup$ – JCRM Feb 7 at 16:03

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