Proximity operations refers to all activities outside the Space Station which take place within a 1-km radius. Since there will be a large number of different operations involving manned and unmanned vehicles, single- and multiperson crews, automated and manually controlled flight, a wide variety of cargo, and construction/repair activities, accurate and continuous human monitoring of these operations from a specially designed control station on Space Station will be required. Total situational awareness will be required. This paper presents numerous human factors design guidelines and related background information for control windows which will support proximity operations. Separate sections deal with natural and artificial illumination geometry; all basic rendezvous vector approaches; window field-of-view requirements; window size; shape and placement criteria; window optical characteristics as they relate to human perception; maintenance and protection issues; and a comprehensive review of windows installed on U.S. and U.S.S.R. manned vehicles.

Space station proximity operations windows: Human factors design guidelines

The aim of this work is to improve current knowledge of micrometeoroids and orbital debris in low Earth orbit using space detection experiments. In 1990 and 1993, a series of samples exposed to the space environment for several years aboard the NASA Long Duration Exposure Facility and the Mir Orbital Station were retrieved. The samples were scanned to examine crater/perforationmorphologyand size distributions. The predicted  ux on both experiments also wasmodeledusingKessler’s debris andGrun’s meteoroid distributions.To interpret the  ux observed by the experiments, impact equations were needed to convert observed crater dimensions to impacting particle dimensions. Simulation experiments carried out in the laboratory showed that the Cour-Palais empirical equation was suitable. Further experiments demonstrated the in uence of impact angle upon crater morphology. The results of the simulations together with the  ux distribution on the Mir experiment indicated that secondary impacting might have occurred. Even without secondary impacts, the  ux on Mir was signi cantly higher than model predictions.

Low-Earth-Orbit Micrometeoroid and Debris Investigations

The need for lunar surface power is expected to grow to megawatt levels, which is in line with NASA's objective of building a long-term human presence on the moon that can house more than 100 people. As humanity seeks to establish a long-term presence on the moon and construct lunar habitats or bases, the importance of efficient and dependable power transmission on the moon becomes crucial. Power lines of varied lengths and power transfer capacities are needed for a lunar-based power system to link the various power generation, energy storage, and load facilities dispersed over the lunar surface. Developing power lines with high power density, while considering weight, volume, safety, cost-effectiveness, and reliability in the harsh lunar environment, poses a significant challenge. Three potential locations for power lines on the lunar surface can be considered: above the surface, on the surface, or below the surface. The extreme lunar environment, characterized by factors such as temperature variation, micrometeoroid bombardment, and ionizing radiation, limits the effectiveness of the first two methods for power transfer on the moon. Underground deployment offers both safety and convenience. Using the COMSOL Multiphysics software, this work proposes a novel method for designing and assessing affordable bipolar HVDC cables for power transmission below the lunar surface with an emphasis on its electrical insulation difficulties. At a voltage level of up to ±10 kV, the cables are intended to transfer power at two different levels: medium power (500 kW), and high power (1 MW). These specially designed cables offer a viable solution for power transmission on the moon, as they are capable of functioning effectively in harsh lunar conditions.

High Power Density, Cost-Effective HVDC Cables for Power Transmission on the Moon

On retrieval from Low Earth Orbit (LEO), the solar arrays from the European Retrievable Carrier(EuReCa) and one solararray wing of the Hubble Space Telescope (HST) were inspected for micrometeoroid and space debris impact damage. 703and 814 impact sites respectively were analysed in detail. Interpretation of particle parameters from this large data set canyield a useful measurement of the micrometeoroid and debris flux in LEO. Due to similar orbital parameters, this thenprovides a flux measurement complimentary to those measured by the 'flmeband Capture Cell Experiment (TiCCE) of theEuReCa spacecraft and detectors and exposed surfaces on the Long Duration Exposure Facility (LDEF).To allow comparison of data from the space retrieved solar cells to previous data, solar cell material, glass and aluminiumtargets were impacted for inter-calibration using the University of Kent's Light Gas Gun (LGG). An average of 20 impactsites on each target material per shot were measured. It was decided to consider only non-perforations of the 150 micronthick CMX cover glass, common to both EuReCa and HST solar cells. Trends in crater morphology of the laboratoryimpacts are discussed and compared to those from space impacts. The effects of impact angle and crater scaling with

detectors in low earth orbit

Hypervelocity impact in metals, glass and composites

The Apollo window meteoroid experiment is described which uses the Apollo command module heat shield window surfaces to obtain information about the flux of meteoroids with masses of 10 to the minus 7th power g and less; to examine the residue and the morphology of the craters produced by these meteoroid; to obtain information regarding the dynamic and physical properties of the meteoroids; and to discover possible correlations with the lunar-rock-crater studies. Photographs are included.

Apollo window meteoroid experiment

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Apollo window meteoroid experiment