Nominal Eva Timeline

VIEW THRU OPTICAL CENTER OF TV LENS IN DIRECTION OF "Z"-PLANE

INTERSECTION OF "Z" PLANE AND LUNAR SURFACE

LUNAR SURFACE PHASE

TRAVERSE

DEPLOY PSEP

DEPLOY LRRR

TV CAMERA

.FOV

KEY:

SWC - SOLAR WIND COMPOSITION

LR3 - LASER RANGING RETRO REFLECTOR

PSE - PASSIVE SEISMIC EXPERIMENT

SWC POSITION ( FEW FEET FROM LM)

BULK SAMPLE

(NEAR MESA IN QUAD IV)

CONTINGENCY SAMPLE (NEAR LADDER)

BULK SAMPLE

(NEAR MESA IN QUAD IV)

CONTINGENCY SAMPLE (NEAR LADDER)

v DOCUMENTED SAMPLE ^ (WITHIN TOO FT. FROM LM)

LR 3 POSITION (70 FT. FROM LM)

PSE POSITION (80 FT. FROM LM)

Lunar Sample Collection

Equipment for collecting and stowing lunar surface samples Is housed in the modularized equipment stowage assembly (MESA) on the LM descent stage. The commander will unstow the equipment after adjusting to the lunar surface environment. '

Items stowed in the MESA are as follows:

* Black and white TV camera.

* Large scoop for collecting bulk and documented samples of loose lunar surface material.

* Extension handle that fits the large scoop, core tubes and hammer.

* Tongs for collecting samples of rock and for picking up dropped tools.

* Gnomon for vertical reference, color and dimension scale for lunar surface photography.

* Hammer for driving core tubes, chipping rock and for trenching (with extension handle attached).

* 35mm stereo camera.

* Two sample return containers (SRC) for returning up to 130 pounds of bulk and documented lunar samples. Items such as large and small sample bags, core tubes, gas analysis and lunar environment sample containers are stowed in the SRCs. Both containers are sealed after samples have been collected, documented and stowed, and the crew will hoist them into the ascent stage by means of an equipment conveyor for transfer into the command module and subsequent return to Earth for analysis in the Lunar Receiving Laboratory.

Additionally, a contingency lunar sample return container is stowed in the LM cabin for use by the commander during the early phases of his EVA. The device is a bag attached to an extending handle in which the commander will scoop up about one liter of lunar material. He then will jettison the handle and stow the contingency sample in his pressure suit pocket.

LM Ascent, Lunar Orbit Rendezvous

Following the 22-hour lunar stay time during which the commander and lunar module pilot will deploy the Early Apollo Scientific Experiments Package (EASEP), the Solar Wind Composition (SWC) experiment, and gather lunar soil samples, the LM ascent stage will lift off the lunar surface to begin the rendezvous sequence with the orbiting CSM. Ignition of the LM ascent engine will be at 124:23:21 for a 7 min 14 sec burn with a total velocity of 6,055 fps. Powered ascent Is in two phases: vertical ascent for terrain clearance and the orbital insertion phase. Pitchover along the desired launch azimuth begins as the vertical ascent rate reached 50 fps about 10 seconds after liftoff at about 250 feet in altitude. Insertion into a 9 x 45-nm lunar orbit will take place about 166 nm west of the landing site.

Following LM insertion into lunar orbit, the LM crew will compute onboard the four major maneuvers for rendezvous with the CSM which is about 255 nm ahead of the LM at this point. All maneuvers in the sequence will be made with the LM RCS thrusters. The premission rendezvous sequence maneuvers, times and velocities which likely will differ slightly in real time, are as follows:

LM ASCENT

Tks Lunar OrbiterNominal Timeline

VERTICAL RISE PHASE

END VERTICAL RISE

.ORBIT INSERTION â– PHASE

ASCENT BURN OUT COAST TO 44.07 N. Ml. APOLUNE f 59,927.5 FT

TOTAL ASCENT: BURN TIME = 7:14.65 MIN:SEC AV REQUIRED = 6,055.39 FPS PROPELLANT REQUIRED = 4,989.86 LB

INSERTION ORBIT PARAMETERS

ONBOARD DISPLAYS AT INSERTION

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