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This part of the manual presents methods for arriving at a solution to the problem of spacecraft inflight equipment environmental control. The temperature aspect of this problem may be defined as the maintenance of a proper balance and integration of the following thermal loads: equipment-generated, personnel-generated, and transmission through external boundary.

It is therefore imperative to develop a safe, effective method of microbial control. Spacecraft application dictates a more stringent set of requirements for biocide selection than is usually necessary for terrestrial situations. ...Toxicity of the biocide is the driving factor for disinfectant choice in spacecraft. This concern greatly reduces the number and types of chemical agents that can be used as disinfectants. ...Furthermore, the chemical and toxicological properties of these biocides and others are considered in relation to disinfection of spacecraft and allied hardware.

Water is an important commodity during spaceflight. The Shuttle-Orbiter produces water on-orbit as a direct result of electricity generation. Hydrogen/oxygen fuel cells provide ample water for drinking, food rehydration and hygiene purposes. During the Shuttle-Mir program, water was transferred between the orbiter and the Mir space station to provide crewmembers with drinking water and water to be used for electrolysis for oxygen production. Due to the incompatibility of Russian and U.S. drinking water biocides (silver versus iodine), methods and hardware were developed to remove iodine and allow for the addition of silver biocide and minerals. At the completion of the Mir program, 5,800 kilograms of water had been transferred from the Orbiter to Mir. A refined version of the hardware used during the Mir program is now under flight development and certification for operations on board the International Space Station (ISS).

The ROSETTA mission is a European Space Agency spacecraft which will rendezvous with the comet Wirtanen. The spacecraft will deploy a Surface Science Package (SSP) to land on the comet. ...Thus, the heater power demand at 5.25 AU has to be low, when the spacecraft is in Deep Space Hibernation mode. Prior to the comet rendezvous, the spacecraft is woken up. ...With a fully operational payload, the ROSETTA spacecraft establishes an orbit around comet Wirtanen. The spacecraft follows the comet during its approach to the sun.

However, this technology has been slow to achieve full maturity and operational status for spacecraft use. This paper describes the efforts to advance spacecraft cryogenic refrigerators beyond the technology development demonstration level. ...The requirement for a reliable long-life refrigerator to cool spacecraft payloads to cryogenic temperatures dates to the very beginning of the era of space flight. ...The development of spacecraft cryocooler technology has been funded on a more or less continuous basis for over 30 years.

Future long-duration manned space missions will require efficient methods for maintenance of viable atmosphere in spacecraft crew cabins. Life Systems, working with NASA, has been developing an integrated regenerative Air Revitalization System (ARS) for removal of carbon dioxide and water vapor and replenishment of oxygen and nitrogen for spacecraft atmosphere. ...Life Systems, working with NASA, has been developing an integrated regenerative Air Revitalization System (ARS) for removal of carbon dioxide and water vapor and replenishment of oxygen and nitrogen for spacecraft atmosphere. A one-person-capacity experimental ARS (ARX-1) has recently been developed and tested.

(ADA) is developing a handheld fine water mist fire extinguisher for use on manned spacecraft and in future planetary habitats. This design employs only water and nitrogen as suppression agents to allow local refill and reuse. ...Continued development will result in prototype hardware suitable for use on future manned spacecraft.

Cost effective design does not allow for rejection of spacecraft hardware because it cannot be inspected adequately. An actual example of an uninspectable part is presented together with its impact.

NASA's Earth Observing System (EOS) Program will place a series of unmanned polar-orbiting spacecraft in low-earth orbit to support a variety of scientific and Earth-observing missions. The EOS AM spacecraft has a requirement for an advanced heat transportation system for thermal energy. ...The EOS AM spacecraft has a requirement for an advanced heat transportation system for thermal energy. A Capillary Pumped Heat Transportation System (CPHTS) using Capillary Pumped Loop (CPL) technology was selected to accommodate the instruments requiring advanced heat transport.

This paper describes modeling results for the on-orbit thermal response of spacecraft propellant used for orbit stationkeeping. The specific objectives of the work are to improve analytical models of a transient thermal Propellant Gauging System (PGS) in use on communications satellites.

Heat dissipated in conduction cooled spacecraft components must be transported across the component base plate/spacecraft mounting plate interface preparatory to final radiation to the space sink.

The cruise period from launch until Saturn arrival takes the spacecraft through a wide range of solar/thermal environments (0.67 astronomical units [AU] to 10 AU). ...The off-sun exposure flight experience with interplanetary spacecraft at relatively close heliocentric distance is very limited. Cassini's ability to perform off-sun maneuvers relies heavily on the large thermal capacitance of the spacecraft's central body and the relatively short off-sun durations required for these maneuvers. ...Cassini's ability to perform off-sun maneuvers relies heavily on the large thermal capacitance of the spacecraft's central body and the relatively short off-sun durations required for these maneuvers.

Two-phase heat transport systems are currently considered for the thermal management of future large power spacecraft. The monitoring of the quality, being the relative vapour mass content, of the two-phase mixture at various locations in the system, is valuable - possibly indispensable - for the proper operation of such a system. ...Only a few concepts turn out to be suitable for spacecraft applications. Promising concepts are based on the capacitance, sonic velocity and index of refraction.

Not only the detectors are cooled, but also major subsystems and systems of the spacecraft’s. The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. ...The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. ...The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. Each test requires temperature lower than 20 [K], in volumes ranging from 1 [m3] to 60 [m3], cooling down several kilograms to more than one ton, and withstanding heat load up to 150 [W] in stabilization.

The dynamic testing of the QuikSCAT spacecraft is discussed as an example of a successful combined loads, workmanship, and model validation test program.

Multilayer Insulation (MLI) is used for thermal control of spacecraft (S/C). Built-in discontinuities degrade the performance of MLI blankets. In this paper the blanket properties are considered by defining an effective emissivity for the MLI covered S/C surface.

Research was initiated due to increased concern over trace contaminant gas build-up in an enclosed atmosphere of a spacecraft for long duration space flights. A gas mixture simulating conditions on long duration space missions must be created in order to test trace contaminant control hardware. ...This contaminant model gas mixture can be used to test trace contaminant control hardware for an enclosed spacecraft environment.

Vapor Compression Distillation technology has proved its readiness as a spacecraft wastewater processor as evidenced by selection of this technology for the Urine Processor Assembly aboard Space Station Freedom.

An aqueous phase catalytic oxidation system (APCOS) was designed, tested and delivered to NASA/Johnson Space Center (JSC). The APCOS removes residual organic impurities in reclaimed water to a level acceptable for potable use and to provide disinfection. The reactor, which contains a heterogeneous catalyst consisting of a noble metal on an inert support medium, operates at 120 - 150 °C and at fluid pressures of several atmospheres to maintain an aqueous liquid phase. Pressurized gaseous oxygen, used as the oxidant, is directly injected into the liquid phase. A description of the subsystems process hardware is presented. The APCOS was demonstrated to mineralize organic impurities at concentrations of 100 mg/L total organic carbon (TOC) to < .5 mg/L (<500 μg/L TOC). In addition, disinfection features were demonstrated with microbial challenge tests.

An update of a Two-Phase Thermal Management System concept is presented including hardware status for flight prototypic components, modeling techniques, and terrestrial test results for both preprototype and some prototypic hardware. A test plan for a microgravity test on a KC 135 is discussed.