Apollo Saturn Bedienungsanleitung PDF herunterladen (Seite 31)

EMERGENCY DETECTION SYSTEM |

The Emergency Detection System (EDS) is designed to sense and react to

emergency situations resulting from launch vehicle malfuDctions which may arise

during the mission. Crew safety and protection is the primary function of the

EDS. Triple redundant sensors and majority voting logic are used in the auto-

matic abort system. Dual redundancy is used for most of the manual a_ort sen-

sors. The redundancy in the sensing systems is designed to protect against "

inadvertent aborts. I

Automatic Aborts - During most of the S-IC flight, the EDS provides the

c_pabi!!ty of au_omat_e_11y ah_rring the m_ssion. The automatic abort system

is enablcd at liftoff and disabled by the crew at approximately 2 minutes or by "

the IU switch selector prior to S-IC inboard engine cutoff. The system re-

sponds to failuze modes that lead to rapid vehicle breakup. The parameters and

the associated limits monitored for an automatic abort are:

_ 1." Simultaneous loss of thrust on two or more S-IC engines

2. Vehicle rates in excess of ±4°/sec in pitch or yaw; or ±20°/sec in roll

3. S/C to IU breakup.

Manual Aborts - After the automatic abort mode is disabled, aborts may be

initiated manually by the astronauts. Manual aborts are initiated based on at

least two separate and distinct indications. The indications may be a combina-

tion of EDS sensor displays, physiological indications, and ground information

to the astronauts. EDS displays for the crew consist of light and meters which

; indicate loss of thrust of each engine, staging sequences, launch vehicle attitude

reference failure, angle of attack, tank ullage pressures, spacecralt attitude

error and angular rates. The manual abort overrate limits are:

1. Pitch and Yaw - L.O. to S-IC/S-II Staging - ± lO°/sec

- S-IC/S-II Staging to S-IVB C.O - _9°/sec

2; Roll - L.O. to S-IVB C.O. - ±20°/see

Aborts occurring during the launch phase will be performed by using either

the Launch Escape System (LES) or the Service Propulsion System (SPS). The

LES is used to propel the CM a safe distance from the launch vehicle and to

ensure a water landing. Aborts prior to 30 seconds of flight do not terminate

S-IC thrust in order to protect the launch area. The SPS aborts utilize the

Service Module SPS engine to propel the CSM away from the launch vehicle, and

to maneuver to a planned landing area or boost into a contingency orbit.

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Apollo Saturn Bedienungsanleitung Seite 31