Development of a Rotary Fluid Transfer Coupling and Support Mechanism for Space Station

A design has been developed for a rotary fluid coupling to transfer coolant fluids (primarily anhydrous ammonia) across rotating joints of the Space Station. Development testing using three conceptual designs yielded data which were used to establish the design of a multipass fluid coupling capable of handling three fluid circuits. In addition, a mechanism to support the fluid coupling and allow an astronaut to replace the coupling quickly and easily has been designed. INTRODUCTION A permanent manned Space Station, as currently envisioned, will be gravity gradient stabilized and incorporate rotating solar arrays and thermal radiator panels. The rotation of the solar arrays and radiators will provide much more efficient thermal and power systems, thereby reducing overall size, weight, and cost of the systems. The rotation requirement calls for the development of structural, fluid, and electrical systems to provide for the transfer of loads, thermal control fluids (heat), and power across the rotation joints. As part of the advance development effort, an investigation was begun which would lead to the design of a rotary fluid coupling which a11ows 360 ° rotation and meet the severe design requirements of the Space Station. The primary objectives of the development program were to demonstrate the design feasibility and to evaluate the particular design concepts proposed for a 360 ° continuous rotation joint. These objectives included the identification of manufacturing or assembly methods, identification of candidate materials and investigation of compatibility, selection of seals, determination of leakage rates, determination of drive power requirements, and lifetime assessment. A set of design requirements was assembled based on the expected mission of the Space Station. Included in this set was a lifetime goal of 20 years of continuous rotation in orbit with little or no maintenance. The design rotation rate was one revolution per orbit period, or about 0.01RPM. *NASA Langley Research Center, Hampton, VA **PRC KENTRON, Inc. Hampton, VA PReCeDING PAG_ _LANK NOT FILMED 355 https://ntrs.nasa.gov/search.jsp?R=19880012109 2018-03-09T13:12:32+00:00Z