Impact of Geoid Improvement on Ocean Mass and Heat Transport Estimates

One long-standing difficulty in estimating the large-scale ocean circulation is the inability to observe absolute current velocities. Both conventional hydrographic measurements and altimetric measurements provide observations of currents relative to an unknown velocity at a reference depth in the case of hydrographic data, and relative to mean currents calculated over some averaging period in the case of altimetric data. Space gravity missions together with altimetric observations have the potential to overcome this difficulty by providing absolute estimates of the velocity of surface oceanic currents. The absolute surface velocity estimates will in turn provide the reference level velocities that are necessary to compute absolute velocities at any depth level from hydrographic data. Several studies have been carried out to quantify the improvements expected from ongoing and future space gravity missions. The results of these studies in terms of volume flux estimates (transport of water masses) and heat flux estimates (transport of heat by the ocean) are reviewed in this paper. The studies are based on ocean inverse modeling techniques that derive impact estimates solely from the geoid error budgets of forthcoming space gravity missions. Despite some differences in the assumptions made, the inverse modeling calculations all point to significant improvements in estimates of oceanic fluxes. These improvements, measured in terms of reductions of uncertainties, are expected to be as large as a factor of 2. New developments in autonomous ocean observing systems will complement the developments expected from space gravity missions. The synergies of in situ and satellite observing systems are considered in the conclusion of this paper. This revised version was published online in August 2006 with corrections to the Cover Date.     

Apogee manoeuvre with a restartable liquid bipropellant motor

Unified Propulsion Systems present perceptible advantages for geostationary spacecrafts design: mass savings, as the ergols tanks are the same for the apogee motor and for the Attitude and Orbit Control System, higher performance, as specific impulse of bi-ergols motors is higher than the one of solid propellant motors and higher operational flexibility as the fuel amount can be adapted to the real flight conditions and as biliquid motors are restartable. On the other hand, the use of these propulsion systems for geostationary spacecrafts sets quite new mission analysis problems: the “predictability” of each delivered Delta-V is rather coarse (the corresponding uncertainty is about 4% for the existing motors). Also, only midlevel thrusters (about 400N) are available and so the finite burn losses associated with long burns arcs have to be minimized. This paper surveys the problems resulting from these new operational constraints and deals successively with the following items: optimal splitting up of the apogee manoeuvre, taking into account the possible dispersions on each Delta-V and the on-station longitude acquisition; minimization of the finite burn losses; adaptation of the apogee manoeuvre to the initial orbit parameters corresponding to the first North-South station-keeping cycle. The operation procedures derived from this survey will be used for the future launch of the ARABSAT spacecraft and for the following spacecrafts of the SPACEBUS family.