1971 (8th) Vol. 1 Technology Today And The Space Congress® Proceedings Tomorrow Apr 1st, 8:00 AM Skylab Facilities and Operations Robert B. Krause Chief, Skylab Ground Systems Branch, Apollo- Skylab Programs Office, John. F Kennedy Space Center, NASA Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Krause, Robert B., "Skylab Facilities and Operations" (1971). The Space Congress® Proceedings. 1. https://commons.erau.edu/space-congress-proceedings/proceedings-1971-8th/session-11/1 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. SKYLAB FACILITIES AND OPERATIONS Robert B. Krause Chief, Skylab Ground Systems Branch Apollo- Skylab Programs Office John F, Kennedy Space Center, NASA Kennedy Space Center, Florida ABSTRACT The purpose of this paper is to outline the essen­ demonstrated by previous manned missions and tial objectives and elements of the Skylab Pro­ we expect to capitalize on this prior experience gram and to describe the impact of the Program during the Skylab Program. Infra-red photo­ on the Kennedy Space Center. The operational graphs taken by the Apollo 9 astronauts were test flows and the required facility modifications used by scientists at the U. S. Geological Center to support Skylab checkout and launch require­ at Menlo Park, California, to observe the St. ments will be highlighted. Andreas Fault. These observations indicated a pressure buildup which forecast the imminence of a major earthquake in this area. This earth­ INTRODUCTION quake activity occured during the Apollo 14 mission in the California Imperial Valley. The Skylab Program, using basic hardware de­ veloped to support the Apollo manned lunar Further, Skylab represents an effective and landing, supplemented by several new flight economical approach to the development of a hardware modules, represents the next major basis for potential future space programs. These step in the orderly progression of manned space include a long duration earth orbital space station, flight. The Program has a number of basic ob­ with the capability of operation of up to two years jectives. or longer, and manned planetary exploration. The information we gather in Skylab will serve First is the conduct of long duration space flights as a firm base upon which the future space sys­ of man and systems. These flights will demon­ tems can be developed. strate the unique capabilities of man to both function in a space environment for extended The Kennedy Space Center is cast in its tradi­ periods of up to 56 days and to contribute mater­ tional role - being charged with the responsibility ially to mission success. Further, it will allow to conduct prelaunch checkout and launch opera­ us to establish a habitable space workshop and tions for the Skylab missions. Accomplishment verify our ability to conduct experiments within of this task also requires modification of KSC that structure. We plan to conduct a number of checkout and launch facilities previously utilized biomedical and behavioral experiments to deter­ to support Apollo manned launches. The design, mine the effects of long duration space flight on development and incorporation of the required the crew so that a logical basis can be established modifications to meet the peculiar Skylab Pro­ for increasing crew orbital stay time. gram requirements is also a KSC responsibility. Secondly, we will conduct scientific investigations The remainder of this paper will briefly outline in earth orbit using the Apollo Telescope Mount the essential elements of the unique Skylab flight to observe the sun. Such observations can be hardware and will highlight the KSC operational much more accurately obtained outside the re­ test flows, describing the processing of each strictive atmosphere of the earth, module through the checkout areas of the Opera­ tions and Checkout Building and Launch Complex Thirdly, a number of specific applications in 39. Particular emphasis will be placed on the earth orbit will be explored. Meteorlogical and * major modifications required which include the earth resources experiments will be conducted ATM clean room, the pedestal on the Launch and communications methods and equipment will Umbilical Tower to enable the Saturn IB/CSM be exercised and evaluated. The value of earth vehicle to be launched from LC-39, and new ac­ observation from space has already been partially cess and service arms to meet peculiar program 11-41 requirements. Of particular note is the fact that intervals from the SL-2 launch. These missions the inherent capabilities of Launch Complex 39 are open ended and planned to last 56 days. These to absorb new program requirements are being missions will reactive the workshop and reper- fully exploited at minimum cost in support of form medical, technical, scientific, earth re­ Skylab Program needs. This theme will be sources, and solar astronomy experiments. A stressed throughout this paper. mission profile of the entire sequence of Skylab missions is shown in Figure 1. SKYLAB MISSION PROFILE SKYLAB UNIQUE MISSION HARDWARE The Skylab Program consists of four launches, one unmanned and three manned, to conduct three To accomplish the Skylab Program objectives, a interrelated missions. The first mission, SL-1/ number of new hardware flight modules have been SL-2 will consist of two launches approximately developed. The essential elements of each are one day apart. The SL-1 vehicle configuration briefly described below. consists of a two stage Saturn V launch vehicle - the S-IC and S-II stages - and the Saturn Work­ shop (SWS) comprised of a modified S-IVB ORBITAL WORKSHOP (OWS) Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Tele­ The OWS is a modified S-IVB stage that is ground scope Mount (ATM), and Instrument Unit (IU). outfitted to provide a habitable environment for After launch from LC-39 Pad A, the workshop extended crew operations. The LH2 tank is will be placed in a nominal 235 nautical mile al­ divided into two floors by open aluminum grid titude by the two launch vehicle, the ATM structures compartmented to provide space for deployed to its orbital configuration and the or- crew habitation and operational activities. See assembly stabilized in the proper attitude. Figure 2. The crew quarters are divided into four areas, as shown in Figure 3: sleep com­ The of the assembly will be verified by partment, waste management compartment, ground command telemetry data prior to the wardroom, and experiment compartment. A launch of the CSM mission, SL-2, from side hatch into the wardroom is provided for ac­ LC-39 Pad B, The launch vehicle is a standard cess into the OWS during ground checkout. Saturn IB, consisting of the S-IB and S-IVB stage and Instrument Unit, similar to that used Astronaut mobility/stability aids are required to on Apollo 7 to place the first manned Apollo assist the astronauts in performing tasks as­ spacecraft in earth orbit. The SL-2 vehicle sociated with activation, crew habitation, ex­ be launched approximately one day after the perimentation, and deactivation. These aids are SL-1 launch. The CSM will rendezvous and of two basic types: fixed and portable. Fixed the orbital assembly. Following astronaut aids include handrails, tether attach the crew will transfer into the OWS, devices, and the central handrail. They are per­ the OWS life support systems and place manently installed in locations throughout the the in a quiescent, minimum energy de- LH2 tank where it is expected that heavy traffic for the duration of this initial or task loading will occur. Portable astronaut operations period. aids include handholds, tether attach brackets and foot restraints. SL-1/SL-2 will be primarily directed toward the accomplishment of a series A meteoroid shield is designed as a structurally- of medical related to the extension integrated part of the OWS and protects the cylin­ of manned space!light. Secondary emphasis drical portion of the tank. After deployment, will be on. solar astronomy, earth resources, the shield does not extend more than 6 inches and technical experiments. This mission is radially from the outer surface of the LH2 tank. open but is to last 28 days begin- Deployment is accomplished during orbit by a with the launch of the SL-2 CSM. At the signal from the IU. of period, the will be pre­ pared for an during which it A Solar Array System (SAS) is provided as a will be in a semiactive condition. The crew source of power during orbital operations. will transfer to the CSM, from the or­ Routing of this power is accomplished via the bital assembly, deorbit return to earth. Airlock Module power distribution system. The SL-3 and SL-4 will perform at and six 11-42 AIRLOCK MODULE (AM) provides for the following: The AM provides the major work area and sup­ a. Installation and removal of experiment film port equipment required to activate and operate cassettes during orbital operations (by of the OWS. The AM includes a fixed airlock shroud EVA); (FAS) and an ATM Deployment Assembly. In­ tegration of the AM structure within the cluster b. Remote-controlled protective covers for the provides for: a pressurized interconnecting experiments and for the pointing optics at the passageway between the MDA and the OWS; sup­ sun end of the experiment canister. These port for intervehicular activity (IVA) and extra­ covers can be controlled from the ATM control vehicular activity (EVA) via the AM airlock; and display panel located in the MDA; structural support for the MDA; the supply, dis­ tribution and control of the cluster atmosphere, c.