other contains the transmitter system. The orbiter would orientate itself into a sun-pointing configuration, after which the lids on both GAS CAPs would open and the subsatellite deployed. (Figure 6.2-1) When the subsatellite had reached a safe distance, it would inflate or unfurl, if required. The transmitter in the other GAS CAP would track the target and power would be transmitted to it as required, and for as long as the target was in range. If the deployment rate of the subsatellite could be kept as low as 5 cm/s, and the experiment was conducted for 100 meters, then the duration of the experiment would be about 30 minutes. As with the Eureca mission, a CCD camera could be located in the GAS can to observe the deployment However, more likely, such a mission would be observed with the Orbiter’s CCTV cameras and by the crew. If the target subsatellite was equipped with an array of lights (also like Eureca) then, this would be a very “visible” experiment. Discussion & Potential Problems While there are a number of advantages to the use of a GAS CAP, a number of problems must be overcome. Perhaps the most prevalent are the problems associated with the power supply and thermal control. NASA provides a list of preferred battery options and, even though they do not preclude the use of high energy lithium-based batteries, NASA warns strongly against their use in GAS canisters by stating that, [37] Many of the new “high power” batteries have exhibited hazards such as high operating temperatures and rupture of cases; in particular, we recommend against the use of Lithium cells in GAS pay loads. Lithium batteries are very difficult to certify for manned space flight use. Using lithium batteries in your payload will increase the time it takes to process your payload, and you will be charged for this increased workload.
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