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Analysis has been performed for the overall spacecraft, the subsystems and some selected units. The thermal control system of the RADARSAT-1 has been examined for cases of both normal orbital conditions and abnormal thermal environments and operations.

Manned space systems have many requirements for the monitoring of vital life support systems such as the cabin air quality and the quality of the recycled water supply. Infrared spectroscopy probes the characteristic vibrational and rotational modes of chemical bonds in molecules to provide information about both the chemical composition and the bonding configuration of a sample. The significant advantage of the IR spectral technique is that it can be used with minimal consumables to simultaneously detect a large variety of chemical and biochemical species with high chemical specificity. To date, relatively large Fourier Transform (FT-IR) spectrometers employing variations of the Michelson interferometer have been successfully employed in space for various IR spectroscopy applications. However, FT-IR systems are mechanically complex, bulky (> 15 kg), and require considerable processing.

Manned space systems have many requirements for the monitoring of vital life support systems including quality of cabin air and the recycled water supply, as well as direct monitoring of vital indicators of astronaut health. Infrared (IR) spectroscopy is an attractive monitoring technique because it requires minimal consumables while providing relatively high chemical specificity for the detection of a wide variety of biochemicals using the characteristic vibrational modes of chemical bonds. For space-based systems, the important drivers are reliability, power consumption, mass and simplicity of operation. MPB has advanced its IOSPEC™ technology for miniature integrated IR spectrometers to provide performance comparable to large bench-top IR systems but in a compact and ruggedized footprint weighing under 2.5 kg.

This paper describes a new approach to spacecraft thermal control based on a passive thin-film smart radiator device (SRD) that employs a variable heat-transfer/emitter structure. ...As the spacecraft temperature increases above the selected transition temperature, the thermal emissivity of the SRD to dark space increases by a factor of 2.5 to 3.

The need for higher performance and long-life cryogenic cooling system, along with already stringent requirements for vibration, compactness, and mass, is self evident in spacecraft instruments especially for long space missions. It is therefore an object of this study to provide a system that has the potential to meet these challenges.

Large numbers of experimental and operational two-phase loops were successfully tested and used in several spacecraft in the past two decades. Novel technologies such as Advanced CPL-LHP, High Performance CPL, miniature LHPs, inversion (reversible, “Push-Pull") LHPs, ramified, multiple evaporator and condenser LHPs and CPLs, for complex thermal control systems are being proposed.

They are suitable for spacecraft thermal control where the mass, volume, and power budgets are very limited. The Canadian Space Agency is developing loop heat pipe hardware aimed at understanding the thermal performance of two-phase heat transfer devices and in developing numerical simulation techniques using thermo-hydraulic mathematical models, to enable development of novel thermal control technologies.

As the construction of an International Space Station approaches reality, the next phases in the exploration of Space will require long duration missions to the Moon, Mars, and beyond. The risk of traumatic injury and death will be an ever present factor in near space (within our solar system). Reviews of trauma deaths have consistently found that the greatest reduction in preventable death will occur by addressing definitive airway management, treatment of hemothorax and pneumothorax, and control of intra-abdominal hemorrhage. On a long duration space voyage realistic capabilities exist to potentially manage the first two injuries of this triad. The ability to manage a patient requiring operative control of an abdominal injury represents a quantum leap in commitment, but provides a new standard to target in surgical support of the ongoing exploration of space.

The System for Monitoring and Maintaining MRO Performance (SMP) is a new Canadian payload on board the ISS since February 2003. It is designed to investigate the effects of long-term space flight on Mobile Servicing System Robotics Operator (MRO) skill degradation and recovery. SMP consists of a Space Station Remote Manipulator System (SSRMS) simulator running on a laptop computer which takes its input from a pair of hand controllers. The first prototype of SMP simulates the capture of a payload that is hovering in space next to the ISS. This task has been identified as the most complex MRO hand controlled operation. The SMP also contains an innovative software module that automatically evaluates and quantifies the performance level of a particular operator. Based on that evaluation, the system can make a recommendation on whether or not the MRO needs additional training to reach a satisfactory skill level.

This paper describes the thermal design and analysis of the Electronic Unit (EU) of a Microgravity Vibration Isolation System (MVIS) that will ensure the active isolation of the European Space Agency's Fluid Science Laboratory (FSL) payload from vibration induced by the International Space Station (ISS) structure. The FSL is equipped with optical and electronic devices that are very sensitive to vibration, thermal distortion, temperature change and ElectroMagnetic Interference (EMI). The MVIS has to provide a vibration attenuation of -40dB within the range of 0.1-100Hz without inducing thermal or electromagnetic interferences. The sensitive FSL instruments are mounted in a floating structure called the Facility Core Element (FCE), whereas the rest of the FSL electronics, mechanics and cooling systems are fixed to the International Standard Payload Rack (ISPR).

This paper describes the thermal design, analysis and test of a Microgravity Vibration Isolation System (MVIS) that will ensure the active isolation of the European Space Agency’s Fluid Science Laboratory (FSL) payload from vibration induced by the International Space Station (ISS) structure. The FSL is equipped with optical and electronic devices that are very sensitive to vibration, thermal distortion, temperature change and Electro Magnetic Interference (EMI). The MVIS has to provide a vibration attenuation of −40dB within the range of 0.1–100Hz without inducing thermal or electromagnetic interferences. The sensitive FSL instruments are mounted in a floating structure called the Facility Core Element (FCE), whereas the rest of the FSL electronics, mechanics and cooling systems are fixed to the International Standard Payload Rack (ISPR).