Drag and energy accommodation coefficients during sunspot maximum

Thermospheric Density and Wind Determination from Satellite Dynamics

“…Figure 3.9 demonstrated the importance of the choice of the value of the energy accommodation coefficient for the calculation of the aerodynamic force coefficient. Pardini et al [2010] have published on this issue, based on earlier work by Moe et al [1995]. Other recent works of relevance to this topic are the analyses of drag on spherical satellites by Bowman and Moe [2005], Moe and Bowman [2005] and Bowman and Hrncir [2007].…”

Satellite drag effects due to uplifted oxygen neutrals during super magnetic storms

“…The drag coefficients C D and C Di have been discussed theoretically and calculated from empirical observations of satellite deceleration and other data by many authors (Chopra, 1961;Cook, 1965Cook, , 1966Fournier, 1970;Gaposchkin and Coster, 1988;Moe and Moe, 2005;Moe et al, 1998;Pardini et al, 2010;Li, 2011). The information on the gas-surface interaction on the surface of the satellite and contamination of the satellite surface due to the absorbed atomic oxygen is essential to accurately determine the drag coefficients (Chopra, 1961;Cook, 1965Cook, , 1966Pardini et al, 2010). Various studies (Chopra, 1961;Cook, 1965Cook, , 1966Pardini et al, 2010) show that, for spherically or cylindrically shaped satellites, the neutral drag coefficient C D varies from ∼ 2.0 to 2.8 between altitudes of z = ∼ 200 to 800 km with a most commonly used value of C D = 2.…”

“…The area-to-mass ratio of the satellite, A/M, can have values of ∼ 0.038-0.285 cm 2 g −1 , which obviously varies from satellite to satellite. A typical value of a satellite payload is A/M = 0.1 cm 2 g −1 (Gaposchkin and Coster, 1988;Pardini et al, 2010), which we will use in our following calculations. A typical value for the LEO satellite speed with respect to the atmosphere is V s ∼ 7.5 km s −1 .…”

“…Drag force per unit mass on a satellite moving through the Earth's atmosphere is given by (Chopra, 1961;Gaposchkin and Coster, 1988;Moe and Moe, 2005;Pardini et al, 2010;Li, 2011)…”

“…The information on the gas-surface interaction on the surface of the satellite and contamination of the satellite surface due to the absorbed atomic oxygen is essential to accurately determine the drag coefficients (Chopra, 1961;Cook, 1965Cook, , 1966Pardini et al, 2010). Various studies (Chopra, 1961;Cook, 1965Cook, , 1966Pardini et al, 2010) show that, for spherically or cylindrically shaped satellites, the neutral drag coefficient C D varies from ∼ 2.0 to 2.8 between altitudes of z = ∼ 200 to 800 km with a most commonly used value of C D = 2. In contrast the Coulomb drag coefficient C Di varies widely with altitude, e.g.…”