CSM WITH EXPERIMENT CARRIER A study was recently completed to define a hardware configuration and to develop an approach for integrating 23 NASA-designated experiments into AAP mission 1A (AAP-1A). The objectives of the experiments and mission operations are 1. To perform an early evaluation of the operational feasibility of selected earth resources, bioscientific, meteorology, and astronomy experiments; 2. To verify the enhancement of experiments by the presence of man for monitoring, controlling, and interpreting data obained on orbit; 3. To obtain operating experience with available hardware; 4. To extend experiment and mission coverage to 50° latitude. The recommended carrier configuration shown here consists of a welded aluminum truncated cone enclosure 84 inches in diameter at the experiment mounting end and 110 inches long overall. A truss, which supports the cone in the spacecraft lunar module adapter (SLA) at the lunar module (LM) hard points, provides structural support for subsystems and all experiments not requiring in-flight access or pressurization. Carrier experiments are provided power from seven silver-zinc batteries; a data system using one S-band and three VHF transmitters provides for handling experiment data and subsystem housekeeping data; and an active/passive thermal control system with Freon 21 coolant and truss-mounted radiators provides temperature control. A command service module (CSM) guidance and navigation system back-up for local vertical control is provided by a horizon-scanner and gyrocompass attitude reference system mounted on the carrier. An AAP-1A baseline mission, developed with NASA/MSC coordination, identifies an average of six daytime passes over the continental United States each 24 hours at 140 nautical miles altitude and 50° inclination. Launch at 1000 eastern standard time optimizes daytime coverage over the continental United States and permits daytime recovery in the primary Atlantic Ocean recovery area at the conclusion of a 14-day mission based on an April 1, 1969, launch. (See fig. 5.) The second AAP mission planned consists of a dual launch (AAP1/AAP-2). One of these is a manned launch of a CSM; the other is an unmanned launch of an Orbital Workshop/Airlock Module/Multiple Docking Adapter. These space vehicles will rendezvous in space and dock as shown in figure 6. The nominal orbit will be circular at an altitude of 260 nautical miles, with an inclination of 2812°. The crew will activate the AM, pressurize the OWS, and build the two-floor laboratory or workshop from the materials stored in the AM. At the end of their 28-day mission the crew will leave the workshop in orbital storage with its unused expendable supplies and return to earth in the Command Module. The first floor of the workshop thus created will be devoted to living quarters for the astronaut crew and the second floor will be devoted to a laboratory and maintenance area equipped to carry out various experiments and maintenance functions. Attached to the airlock will be a docking adapter which provides for docking five vehicles or equipment modules. CLUSTER CONFIGURATION-56-DAY MISSION On the second dual launch for Apollo Applications, a manned Command-Service Module and supplies will be flown into orbit. This spacecraft would then link up with an LM/ATM launched separately. The LM/ATM would be carrying telescopes and other instruments for observation of the sun during the peak of the sunspot cycle beginning in early 1969. An embryonic space station would be created by linking up the hardware launched for the second dual mission with the workshop left in orbit from the first dual mission, as shown in figure 7. The single space station created combines the hardware elements and supplies from the four separate launches. Later we expect that other experiments will be carried up to this cluster of equipment. We will reuse the solar telescope and we also will be trying out other experiments. In particular, the duration of the crew's exposure to the space environment will be increased, first to 4 months, then to 8 months and, later, if all goes well, we should be able to have men in orbit continuously. LM/ATM (FREE FLIGHT CONFIGURATION) The Lunar Module (LM) portion of the LM/ATM shown in figure 8, consists of a modified Apollo LM ascent stage. The ascent stage contains the crew envelope portion of the Apollo LM and thus provides a pressurized compartment in which the crew can control 89-149 0-68- -17 |