In two previous papers we presented the LARES 2 space experiment aimed at a very accurate test of framedragging and at other tests of fundamental physics and measurements of space geodesy and geodynamics. We presented the error sources of the LARES 2 experiment, its error budget and Monte Carlo simulations and covariance analyses confirming an accuracy of a few parts in one thousand in the test of frame-dragging. Here we discuss the impact of the orbital perturbation known as the de Sitter effect, or geodetic precession, in the error budget of the LARES 2 frame-dragging experiment. We show that the uncertainty in the de Sitter effect has a negligible impact in the final error budget because of the very accurate results now available for the test of the de Sitter precession and because of its very nature. The total error budget in the LARES 2 test of frame-dragging remains at a level of the order of 0.2%, as determined in the first two papers of this series.
LARES 2 and an introduction to the de Sitter effectThe LARES 2-LAGEOS space experiment is designed to achieve a new, accurate measurement of the General Relativistic frame-dragging due to the rotation of the Earth. Analytical estimates, covariance studies, and Monte Carlo simulations concur that the expected error level in this effect is of order 0.2%, as shown in Refs. [1,2].The two LAGEOS (Laser GEOdynamics Satellite) and the two LARES (Laser RElativity Satellite) are laser-ranged satellites. Satellite Laser Ranging (SLR) is the most accurate technique for measuring distances to the Moon [3] and to artificial satellites such as the LAGEOS and LARES satellites a e-mail: ignazio.ciufolini@gmail.com [4][5][6]. Short-duration laser pulses are emitted, with different elevations, from lasers on the Earth towards a satellite and then reflected back to the emitting laser-ranging stations by the retro-reflectors on the satellite. The tracking data collected by the SLR network are analysed, organized and distributed by the International Laser Ranging Service (ILRS) [7]. By measuring the total round-trip travel time we are today able to determine the instantaneous distance of a retro-reflector on the LAGEOS and LARES satellites with a precision of a few millimetres [8]. Then, using orbital estimators, such as GEODYN, EPOSOC and UTOPIA, the orbit of the satellite is reconstructed and its six Keplerian orbital elements are determined with extremely high accuracy. For example the longitude of the ascending node can be determined with an uncertainty of a fraction of milliarcsecond that, over a long period of time, allows for extremely high accuracy in the measurement of the total nodal precession of a laser-ranged satellite. The LAGEOS satellites (LAGEOS and LAGEOS 2) [4] are spherical, made of heavy brass and aluminium, with a radius of 300 mm and about 406 kg in weight, completely passive and covered with retro-reflectors. LAGEOS and LAGEOS 2 have an essentially identical structure but they have different orbits. The semimajor axis of LAGEOS is a = 12270 km, t...