There were some things about the terminal descent on the last mission that kind of spooked a lot of people. One of the things suggested as a result of this was to add a capability to the LM guidance and control system which would assist the crew during the last 100 feet or so of the descent. Specifically, fix the PGNCS so that it will provide an automatic nulling of the horizontal velocity while the crew controls the descent rate with the ROD switch. This memo is to inform you that we are adding this capability to the system for the next flight - Apollo 13 - and to describe briefly just what it is we are doing.

A modification is being made to P66 which will eliminate P65 or, if you like, replace it with a similar but superior capability. We are retaining the current P66 mode of operation exactly but are adding the following feature to it. If the crew switches from “Attitude Hold” to “Auto” the PGNCS will null horizontal velocity to zero - both fore/aft and lateral. It does this, of course, just as the crew would in the manual mode by controlling the spacecraft attitude. There is no restriction for switching back and forth between “Attitude Hold” and “Auto” in P66 as often as the crew desires.

It is anticipated that the crew would fly the descent to an altitude of about 100 feet exactly as has been done on both previous missions - that is, they will exit P64 and go into P66 (Att. Hold) and manually control rate of descent and attitude to place the spacecraft over the desired touchdown point with small horizontal velocity remaining (say about 3 fps and certainly not more than 10 fps). At this point they can switch to Auto which would cause the PGNCS to take over attitude control to get and maintain the horizontal velocity as near zero as it is able, leaving the crew free to monitor their systems, watch out the windows, control the rate of descent, etc. MIT also fixed the system so that the attitude errors are always displayed on the FDAI “error” needles in P66 so the crew will know what the PGNCS plans to do when they enable it.

Since there is no programmed constraint keeping the crew from switching to Auto when the horizontal velocities are quite large, spacecraft attitude limits have been programmed to insure that the LM does not suddenly pitch or yaw to an extreme attitude in an attempt to kill off these velocities, if the crew were to select Auto under those conditions. This limit is in erasable memory and is currently set at 20°.

An associated feature we are implementing is the inhibiting of the landing radar data at about the same point in order to insure that spurious velocity data does not cause undesirable attitude or translational transients.

Since there is no apparent reason P65 would ever be preferred to the new Auto P66, the PGNCS logic is being fixed so that if the P64 target conditions are met prior to the crew taking over in P66, the automatic program switching from P64 will be to P66 Auto rather than P65. Thus, with this change and the one previously implemented so that the PGNCS ignores the throttle mode switch position, we have essentially eliminated both P65 and P67, and have remaining two modes of operation in P66. Most experts involved seem to feel that if we had been clairvoyant the programs would have been implemented this way in the first place.

One final word, this program change was not seriously considered until December 12 at which time a group of us got together here and pinned down specific functional requirements which we then discussed over the phone with MIT’s Russ Larson and Allan Klumpp. It was interesting to note that they had also thought about this and had arrived at almost exactly the same conclusions. At our request they set about implementing this change in an orderly but expeditious way, resulting in an offline assembly delivered to MSC at the break of dawn on December 23. Gene Cernan and Pete Conrad exercised it in the LMS that day and proclaimed it to be outstanding. Jim Lovell has also played with it at the Cape and is said to have expressed his pleasure and burning desire for it. MIT, in the meantime, has completed their detailed reverification of the program. GAC’s Clint Tillman has also exercised it on their simulator and John Norton has reviewed the actual coding and I am told declared it to be a work of art. In other words, although we are messing with absolutely the most critical part of the most critical phase of the mission, we are confident that the change has been made correctly and are releasing the tape to Raytheon to make the new Module 5 rope to be delivered to KSC before CDDT.

Although I’m certain there are others, I personally know that a large dose of special credit should go to Allan Klumpp and Tom Price for getting this job done so well and so quickly!

Terms & Abbreviations


Countdown Demonstration Test.


Flight Director Attitude Indicator. An instrument in the CM used to keep track of the orientation of the spacecraft. Commonly referred to as the "8-ball".


Kennedy Space Center.


Lunar Module. Earlier it was known as the Lunar Excursion Module and abbreviated “LEM.” Even after the name change, it continued to be pronounced “lem.”


Massachussets Institute of Technology. In these memos, MIT is shorthand for the MIT Instrumentation Laboratory, created and led by avionics pioneer Charles Stark Draper. It is now known as the Charles Stark Draper Laboratory and became independent of MIT in 1973.


Manned Spacecraft Center. Now known as Johnson Space Center.


LGC Approach Phase program.


LGC Landing Phase (Auto).


LGC Landing Phase (ROD) program.


LGC Landing Phase (Manual) program.


Primary Guidance, Navigation and Control System (pronounced “pings”). The inertial guidance system in both the Command Module and the Lunar Module.


Rate of Descent. The guidance computer controlled the rate at which the lunar module descended and held it steady while landing. The ROD switch allowed the pilot to increase or decrease this rate by clicking the switch up (to decrease it) or down (to increase it).