Space based laser missions have gained their popularity in areas such as: communication, power
beaming, ranging, altimetry, and Light Detection and Ranging. The capabilities of 1.0 micron lasers
offer a host of improvements in the knowledge gaps that exist and help promote our understanding
of our Earth and lunar environments as well as planetary and space science applications. Some past
and present National Aeronautics and Space Administration missions that have been developed for
increasing our universal knowledge of such environments and applications include: The Shuttle
Laser Altimeter, Mars Orbiter Laser Altimeter, Geoscience Laser Altimeter System, Mercury Laser
Altimeter, Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observation, and Lunar Orbiter
Laser Altimeter.
The effort of contamination control depends on the specific performance goals, instrument designs,
and planned operating scenarios of such missions. Trace amounts of contamination have been
shown to greatly reduce the performance of 1.0 micron space based laser systems. In addition, the
type of contamination plays an important role in the degree of degradation and helps to define the
"contamination sensitivity" of the mission. A space based laser mission is considered highly
contamination sensitive and therefore requires an unprecedented contamination control effort.
During Kennedy Space Center processing of the Hubble Space Telescope First Servicing Mission, critical optical components were integrated in a Class 100,000 (M 6.5 at 0.5 micrometers and 5.0 micrometers , per Fed-Std 209E) cleanroom. A Class 10,000 (M 5.5) environment was mandated by the 400B (per Mil-Std 1246B) surface cleanliness requirement of the Scientific Instruments. To maintain a Class M 5.5 environment, a contamination control plan was implemented which addressed personnel constraints, operations, and site management. This plan limited personnel access, imposed strict gowning requirements, and increased cleanroom janitorial operations, prohibited operations known to generate contamination while sensitive hardware was exposed to the environment, and controlled roadwork, insecticide spraying, and similar activities. Facility preparations included a ceiling to floor cleaning, sealing of vents and doors, and revising the garment change room entry patterns. The cleanroom was successfully run below Class 5000 while the instruments were present; certain operations, however, were observed to cause local contamination levels to increase above Class M 5.5.
Contamination witness plates were flown on STS-51 as part of a NASA Extravehicular Activity (EVA) Flight Test Experiment to quantify and identify particulate contamination generated in the Orbiter crew compartment which has the potential to contaminate the Extravehicular Mobility Units (EMUs) and transfer from the EMUs to mission critical hardware during EVAs. Particles, larger than 100 microns, were found on both witness plates, indicating transfer from the EMUs during EVAs. For missions such as the Hubble Space Telescope First Servicing Mission, where contamination critical optical elements were exposed during EVAs, the potential for particulate transfer from the crew compartment to these optical elements and the Hubble Space Telescope was evaluated.
The Hubble Space Telescope is the first spacecraft designed from its conception to allow for Scientific Instrument upgrading and subsystem maintenance by using the Shuttle. Regular and contingency servicing missions preserve and broaden the scientific objectives of the HST through on-orbit maintenance. To achieve mission success for the Hubble Space Telescope First Servicing Mission, a contamination control methodology was developed and instituted by ensure that scientific instrument performance was not degraded or compromised during fabrication, build-up, ground integration and test activities, on-orbit servicing including Extravehicular Activities, or through on-orbit operational activities. The cleanliness methodology considered the effects of outgassing and surface contaminants on the degradation of the sensitive components. Through plans and procedures for handling sensitive components and the development of a detailed contamination budget extending from Goddard Space Flight Center processing through launch, the preservation of the science capabilities (as affected by contamination) was achieved.
For spacecraft hardware that is contamination sensitive, it is necessary to protect the hardware from inadvertent contamination from external environments. In the case of the Hubble Space Telescope First Servicing Mission hardware, contamination due to particles or non-volatile residue depositions could cause severe degradation in optical performance. Once a hardware component is vacuum baked and certified `clean' from the outgassing perspective, it must be protected from surface contaminants. Surface contaminants such as particles and non-volatile residue will cause light scattering and ultraviolet absorptance on critical optical components. One method of protecting the hardware from contamination effects is to institute the use of protective bags. Bagging of flight hardware is most efficient during the phases that include storage, integration and test, and transportation. For bags to provide an effective barrier and minimize depositions from the environment, the bags must meet several requirements to preclude the bag material itself from becoming a source of contamination to the hardware. These requirements must satisfy cleanliness specifications, in addition to strict safety standards for spacecraft and launch facilities. During the launch site processing of the HST FSM hardware, an innovative design for a protective bag was created to facilitate removal during integration into the payload bay. The protective bag design incorporated a `ripcord' method for removal to minimize contamination on the FSM hardware from Canister handling, facility fall-out, Payload Ground Handling Mechanism transfer, and personnel induced contamination. In addition to cleanliness requirements, the `ripcord' design was required due to accessibility limitations while processed in the Payload Changeout Room.
KEYWORDS: Molecules, Contamination, Temperature metrology, Contamination control, Space operations, Receivers, Solids, Adsorption, Data centers, Control systems
The transport of molecules, under vacuum conditions, from a source surface to a receiving surface is of major concern from the perspective of spacecraft contamination control. The transport phenomena involved is a complex mechanism comprising the physical characteristics of each surface, the properties of contaminant species participating, and the temperatures of both surfaces. Because of both the complex nature and the limited data available to describe such a phenomena, contamination modeling usually requires that a highly simplified engineering approach be undertaken. One area where this is particularly true is in the representation of the surface accommodation of incident molecules. When a molecule in the gas phase collides with the surface of a receiver it can either "stick" to that surface or be scattered away. Molecules accommodated by this surface become thermally equilibrated to the receiver temperature while the material that is not accommodated retains its original energy and undergoes specular reflection. The ratio of this thermally accommodated mass to the total incident mass is known as the "accommodation" or "sticking" coefficient. Most of the current theory and experimental work performed to date has been restricted to the accommodation coefficients of the rare gases in contact with metal surfaces3'10"1. UnfortUnately, the results generated by these studies cannot be made very useful to spacecraft contamination engineers who are predominantly interested in environments where contaminants are typically limited only to water and long-chain hydrocarbons. Because of this deficiency most current spacecraft contamination analyses are forced to rely on general mathematical expressions that consider the sticking coefficient to be only a direct function of the temperature gradient between the emitting and receiving surfaces. The major shortcoming of the simplified method presently in use is that it may provide an inadequate representation of the actual molecular transport occurring between surfaces. The purpose of this paper is, therefore, to study the nature of the transport mechanisms involved in the adsorption of high molecular weight gases on typical spacecraft surfaces, the overall concept of the sticking coefficient, and the quantitative and qualitative theory involved. In addition, this paper will examine some of the existing molecular accommodation data as it relates to spacecraft applications, as well as present new experimental data gathered by the Contamination Control Section of the Goddard Space Flight Center (GSFC). All this information will then be correlated and used to verify the accuracy of the most common sticking coefficient equations in use by contamination analyses.
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