RESUMEN

A group of researchers, mosquito and coastal managers, and consultants joined together to explore issues of concern to coastal and mosquito management in mangrove forests. At a 1-day workshop in Florida, participants identified issues that are important for their roles. The issues were subsequently compiled into a matrix and the participants were asked to individually assess the importance and urgency of each. The most important issues for everyone included habitat responses to management, community attitude, public education, interaction between agencies, local connectivity, sea-level rise (SLR) loss of wetlands, and conservation. Most urgent were public education, conservation easements, local connectivity, SLR, loss of wetland, restoration, and conservation. There were differing viewpoints among the roles that appeared to be related to responsibility for and ability to influence on-ground outcomes. This is reflected in mosquito and coastal managers who viewed issues broadly and ascribed higher levels of importance and urgency to them than did researchers and consultants. We concluded that collaboration is a key issue. Barriers to collaboration include knowledge differences between agencies. Facilitators of collaboration include interaction, trust, and shared goals.

Asunto(s)

RESUMEN

The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days.