PRELAUNCH CHECKOUT

The uprated Saturn I launch vehicle -- first stage (S-IB), second stage (S-IVB), and instrument unit (IU) -- arrived at Cape Kennedy in January and February. They were erected inside the Complex 34 service structure in March.

The Apollo spacecraft,command module, service module and lunar module adapter, arrived at the NASA Kennedy Space Center in April. The command module underwent extensive environmental control system checks and was taken to the pyrotechnic installation building where it was mated with the launch escape system.

After receiving and inspection, the service module was taken to Complex 16 on Cape Kennedy for checks of its secondary propulsion system. Then it was returned to the Kennedy Space Center for fuel cell installation and tests in an altitude chamber which simulates the near-vacuum of space.

The lunar module adapter and the service module were mated near the end of June. Mate of the Apollo modules with the launch vehicle was accomplished in early July.

Tests of the integrated launch vehicle and spacecraft followed at Complex 34. A full-scale countdown demonstration was conducted by the launch team about three weeks before the schedul-ed launch date. During the demonstration, actual countdown was followed to ignition and liftoff. This included loading the launch vehicle with cryogenic propellants -- liquid oxygen and liquid hydrogen.

As in previous Uprated Saturn I flights, much of the checkout of both launch vehicle and spacecraft was accomplished through the use of computers. Launch vehicle automatic checkout -- already used to a great extent in Apollo spacecraft tests -- will be progressive with each succeeding flight.

The Saturn V launch vehicle, for the most part, will signify the ultimate in automatic checkout when most of its preparation is accomplished through the use of computers. Two RCA 110-A computers, one located at the base of the launch pad and one in the launch control center are used for checkout of the Saturn.

Spacecraft computer checkout uses a system called ACE/SC(acceptance checkout equipment for spacecraft). The ACE system provides reliable, instantaneous, accurate checkout of the systems with computers, display consoles and recording equipment.

ACE, also used at spacecraft contractor plants and at NASA's Manned Spacecraft Center, Houston, is manufactured by General Electric, Apollo Support Department, Daytona Beach, Fla.

While automatic checkout of the various systems of the spacecraft and the launch vehicle are being carried out independently at the Kennedy Space Center and on the launch complex at Cape Kennedy interface instrumentation joins the two systems for a picture of the overall prelaunch preparation.

APOLLO SPACECRAFT

The spacecraft consists of two modules which are fastened together in tandem, the Apollo command and service modules. The launch escape system is atop the command module. An adapter section is located between the service module and the launch vehicle which will house the lunar module on future Apollo flights.

Command Module

Although this is an unmanned mission, the instruments and equipment in the command module will be fully operational, with the exception of a few astronaut-oriented displays. It consists of a pressurized compartment of aluminum honeycomb and an outer heat shield of stainless steel honeycomb.

Shape:	Conical (cone)
Height:	11.5 feet
Diameter at base:	13 feet
Launch weight:	11,900 (including RCS propellants)
Outer Structure:	Stainless steel brazed honeycomb bonded between aluminum alloy sheets. An ablative material which varies from 1/2 inch to 2-1/2 inches is applied to entire outer surface.
Inner compartment:	Aluminum honeycomb bonded between aluminum alloy sheets. Thickness ranges from 1-1/2 inches at base to 3/4 inch at forward bulkhead.
Insulation:	A two-layer micro-quartz fiber insulation 1/2 inch-thick separates the walls of the inner and outer structures.
Electrical:	Six silver oxide-zinc batteries with a capacity of 40 ampere hours provide entry, post landing and pyrotechnics energy.

Service Module

The service module is an unpressurized cylindrical shell which houses the main propulsion engine, propellant tanks, electrical power system, reaction control engines and portion of the environmental control system in a six pie- shaped section. Three fuel cells, each with the capability of producing 1,420 watts, will fly on this mission.

Shape:	Cylinder
Height:	24.6 feet (including main propulsion engine
Diameter:	13 feet
Launch weight:	9,800 pounds (structure) 23,000 pounds (propellants) 32,800 Total
Structure:	Aluminum honeycomb panels one inch thick bolted to slx solid aluminum field beams that are chemically milled to within .007 inches (seven thousandths).
Electrical power:	The electrical energy source for the spacecraft throughout the mission until the command module separates from the service module is provided by the three fuel cells.

Spacecraft Lunar Module Adapter

This adapter joins the service module and the S-IVB instrument unit. In future flights it will house the lunar module, but on this flight an aluminum alloy bracing is included in its place. The adapter is 28 feet high and tapers from 22 feet at the instrument unit end to 13 feet where it attaches to the service module. It weighs 3,700 pounds. It consists of four aluminum honeycomb panels attached by hinges to the lower end of the adapter. The panels may be separated by explosive charges and opened petal-like to expose the lunar module preparatory to CSM lunar module docking on future flights.