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As the vehicle rises from the launch pad, a yaw maneuver is executed to tnsure

that the vehicle does not collide with the tower in the event of h_.gh wind$ or a

single engine failure. Once tower clearance has been accomplished, a p_tch and

roll maneuver is initiated to achieve proper flight attitude and a flight azimuth

• o_ientation of between 72 and 108 degrees.

A successful boost sequence, as illustrated in Figure 3, will _nsert the

°" S-IVB/IU/SC into n 100 NNI circular earth parking orbit.

Coast in Earth Parkin_ Orbit (EPO). The vehicle will coast in earth park-

ing orbit while space vehicle subsystems checkout is performed. Preparation for

• translunar injection takes place during this period, The reignition time and

' orbital position of the S-IVB injection burn will depend on lunar declination and

upon the injection window opportunity to be selected. The first injection opportunity

occurs midway through the second parking orbit revolution while the second opportunity

occurs midway through the third revolution.

Translunar injection, Followlng the selection of one of the _wo injection

opportunities described above, the S-IVB stage relgnltes to provide translunar

injection. The nominal injection provides a free return trajectory to earth If the

deboost to the lunar parking orbit is not initiated.

Translunar Coast. _nortly after traaslunar injection, the Transposition,

Docking, and Extraction (TDbE) of the Command and Service Module (CSH) and the

Lunar Hodule (124)will take place. To initiate this maneuver, the CSbl,assisted

by the service module's reaction control system, will separate from the S-IVB.

Spacecraft Lunar-Module Adapter (SLA) panels are then Jettisoned =o expose the

docklngmechanlsm of the lunar module. Following separation, the CSM will trans-

late approximately 50 feet, pitch 180 degrees, roll 60 degrees and move to docking

interface with the lunar module. As soon as the crew has c_pleted verification

that docking latches are engaged, and that CSM/LH tunnel pressure has been equalized,

the LM/SLA attach points are severed and the I_ is extracted and moved approximately

I00 ft. from the S-IVB. During translunar coast ( _pproximately 75 hours), mid-

course corrections are made if required.

S-IVB "Slingshot". In order to minimize the probability of spacecraft

and latmch vehicie collision, and to avert S-IVB earth or lunar impact, a S-IVB

"slingshot" procedure is executed. To initiate this maneuver, the launch vehicle

(S-IVB/IU/SLA) will move to a predetermined attitude and execute a retrograde

dump of residual propellants_ T_is will reduce vehicle velocity by approximately

115 feet per second. Following retrograde propellant dumping, the S-IVB is

"safed" by dumping the remaining propellants and gas from gas bottles through

•. the latch-open, nonpropulslye vents. This velocity change in the S-IVB will per-

turb the S-IVB trajectory so that the vehicle will be influenced by the moon's

gravitational fleld. This Influence will increase velocity sufficiently _o as

. to place the S-IVB/IU/SLA in solar orbit

•

Lunar Orbit Insertion. Prior to lunar o_bit insertion, the crew will

check the LM for operational readiness and return to the CSH• If all conditions

are "go", the Service Module (SN) propulsion system will be used to deboost the

CSH/LM into a moon orbit ranging from 60 to ]70 NMI above the moon's surface•

Two orbits later, approximately four hours, the astronauts will circularize the

• orbit at 60 NMI.

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Apollo Saturn Manual do Utilizador Página 8

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