Flight Plan Summary

Following Is a brief summary of tasks to be accomplished in Apollo 9 on a day-to-day schedule. Apollo 9 work days are not on a 24-hour basis but rather on a variable mission phase and crew activity basis. Rest periods are scheduled at Irregular intervals between mission phases•

Launch Day (0-19 hours elapsed time):

* CSM systems checkout following insertion into 103 nm orbit

* Preparations for transposition, docking and LM ejection

* CSM separation, transposition and docking with lunar module

* LM pressurizatlon to equal of CSM

* LM ejection from spacecraft/lM adapter

* Spacecraft evasive maneuver to observe S-IVB restart

* Docked posigrade service propulsion system burn raises apogee to 128 nm

* Daylight star check and sextant calibration

Second day (19-40 hours GET):

* Second SPS docked burn tests digital autopilot stability at 40 per cent of full amplitude gimbal stroke posigrade, raises apogee to 192 nm

* Third SPS docked bum tests digital autopilot stability at full stroke; although mostly out-of-plane, burn raises apogee to 270 nm

* Fourth docked SPS burn, out-of-plane; orbit remains 115*270 nm

* Commander and IM pilot transfer to LM

* IM systems checkout

* 1« alignment optical telescope daylight star visibility check

* IM S-Band steerable antenna check more-

LM platform alignment with combination of known CSM attitudes and voiced data from ground

LM RCS engines hot firing

Docked 1/4 descent engine burn: out of plane, no orbit change

LM crew transfer baok into command module

Fifth SPS docked burn circularizes orbit to 133 nm

Commander and LM pilot transfer to LM and begin preparations for EVA

CSM and £M depressurized and hatches opened

LM pilot leave» through IM front hatch, mounts oamera; command module pilot mounts camera on command module open hatoh

LM pilot carries out two-hour EVA In transfer to command module and back to IM for period in "golden slippers" on IM porch; tests IM TV camera

IM pilot enters LM, closes hatch; IM and command module re^pressurized; LM crew returns to command module

Commander and IM pilot transfer to IM and prepare for un-docking

IM checkout simulating preparations for lunar landing descent IM rendezvous radar self-test

IM/CSM separation, command module pilot inspects and photographs 114 landing gear

IM rendezvous radar lock-on with CSM transponder

Descent engine phasing burn places LM in 119x145 nm orbit for rendezvous radial separation

IM descent engine posigrade bum inserts IM into 142x144 nm orbit for coelliptic rendezvous maneuver

IM RCQ retrograde burn and staging of LM descent stage; IM ascent stage now in 120x139 nm orbit

LM ascent engine coelliptic burn places IM in 119x121 nm orbit; IM orbit now constant about 10 nm below CSM

LM HCS terminal phase Initiation burn along line of sight toward CSM, followed by midcourse correction burns

Rendezvous and docking

Hi crew transfer to command module

IM jettisoned and ascent engine ground «-commanded for burn to depletion

Sixth day (114-139 GET): Sixth SPS burn lowers CSM perigee to 95 nm

Seventh day (139-162 GET): landmark tracking over U.S. and South Atlantic

Eighth day (162-185 GET): Seventh SPS burn raises apogee to 210 nm

Ninth day (185-208 GET)s No major mission activities planned

Tenth day (208-231 GET): No major mission activities planned

Eleventh day (231 OET to splashdown): Entry preparations SPS fps retrograde deorbit burn CM/SM separation, entry and splashdown.

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