Differential Drag-Based Reference Trajectories for Spacecraft Relative Maneuvering Using Density Forecast

David Pérez, Riccardo Bevilacqua
2016 Journal of Spacecraft and Rockets  
A bc = element of matrix A d to which a Dcrit is the most sensitive A d = stable linear reference state-space matrix A s = Schweighart and Sedwick model state-space matrix a Dcrit = magnitude of the differential drag acceleration ensuring stability a Drel = magnitude of the differential aerodynamic drag acceleration a Prelx , a Prely = differential accelerations caused by orbital perturbations excluding drag, along x and y directions of the local vertical/local horizontal frame C DC , C DT =
more » ... ser and target spacecraft's drag coefficients e = tracking error vector i t = target's initial orbit inclination J 2 = second-order harmonic of Earth gravitational potential field (Earth flattening) lb, ub = lower and upper bounds for the optimization m C , m T = chaser and target spacecraft's mass R e = Earth mean radius R t = position vector of the target in relation to the Earth S C , S T = chaser and target spacecraft's crosswind surface areâ u = on/off control signal V = Lyapunov function v s = spacecraft velocity vector magnitude with respect to the Earth's atmosphere x n = state-space vector of the nonlinear system including relative position and velocity between the spacecraft in the local vertical/local horizontal orbital frame x t = reference state-space vector in the local vertical/ local horizontal orbital frame δ Aop = modifications made to matrix A d for the optimized adaptation μ = Earth's gravitational parameter ρ = atmospheric density ω = magnitude of the orbital angular velocity of the target
doi:10.2514/1.a33332 fatcat:3qxzdiya2jflrdzt4mzxqwdat4