Apollo Saturn Bedienungsanleitung PDF herunterladen (Seite 28)

CUIDANOE AND CONTROL SYSTEM (G&C)

• F_,nction and Description

J e G&C system provides the following basic functions during flight:

I. Stable positioning of the vehicle to the commanded position with a

minimum amount of sloshin_ and bending.

2. A first stage tilt attitude program which gives a near zero lift tra-

jectory through the atmosphere.

3. Steering commands during S-Ii and S-IVB burns which guide the vehic, e to

a predetermi,led set of end conditions while maintaining a minimum propellant

trajectory for ea_Lh orbiL i.,b_rtlon.

4. The proper vehicle position during earth orbit.

5. Guidance during the second S-IVB burn, placing the vehicle in the proper

waiting orbit.

G&C Hardware

The Stabilized Platform (ST-12_:) is a three gimbal configuration with gas

bearing gyros and accelerometers mom_ted on the stable element. Gimbal angles

are measured by redundant resolvers and inertial velocit_ is obtained from inte-

grating accelerometers.

The Launch Vehicle Data Adapter (LVDA) is an input-output device for the

Launch Vehicle Digital Computer (LVDC). The LVDA/LVDC components are digital

devices which operate in con_unctlo_, uo carry out the flight program. The flight

program performs the following functions: (i) processes the inputs from the

StT-124M, (2) performs navigation calculations, (3) provides the first stage tilt '_

program, (4) calculates IGM steering commands, (5) calculates attitude errors,

(6) issues launch vehicle sequencing signals.

The Control/Eds Rate Gyro Package contains nine rate gyros (triple redundant

in three axes). Their outputs go the Control Signal Processor (CSP) where they

are voted and sent to the Flight Control Computer (FCC) Eor damping vehicle

angular motion.

The FCC is an analog device which receives attitude error signals from the

LVDA/LVDC and vehicle angular rate signal s from the CSP. These sig_als are

filtered and scaled, then sent as commands to the S-IC, S-II, and S-IVB engine

actuators and to the Auxiliary Propulsion System (APS) Control Relay Packages.

The Control Relay Packages accept FCC commands and relay these commands to

operate propellant valves in the APS. During spacecraft control of the launch

vehicle, the FCC receives attitude error signals from the Command Module Compu-

ter or the Astronaut hand co_troller.

The Switch Selectors in each stage are used to control the inflight se-

quencing as commanded from the LVDA/LVDC.

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Apollo Saturn Bedienungsanleitung Seite 28