Peters, T. V.Briz Valero, José FranciscoEscorial Olmos, DiegoLappas, V.Jakowski, P.Gray, IainTsourdos, AntoniosSchaub, H.Biesbroek, R.2018-03-222018-03-222018-03-12Peters TV, Valero JF, Lappas V, et al., Attitude control analysis of tethered de-orbiting. Acta Astronautica, Volume 146, May 2018, pp. 316-3310094-5765https://doi.org/10.1016/j.actaastro.2018.03.016https://dspace.lib.cranfield.ac.uk/handle/1826/13111The increase of satellites and rocket upper stages in low earth orbit (LEO) has also increased substantially the danger of collisions in space. Studies have shown that the problem will continue to grow unless a number of debris are removed every year. A typical active debris removal (ADR) mission scenario includes launching an active spacecraft (chaser) which will rendezvous with the inactive target (debris), capture the debris and eventually deorbit both satellites. Many concepts for the capture of the debris while keeping a connection via a tether, between the target and chaser have been investigated, including harpoons, nets, grapples and robotic arms. The paper provides an analysis on the attitude control behaviour for a tethered de-orbiting mission based on the ESA e.Deorbit reference mission, where Envisat is the debris target to be captured by a chaser using a net which is connected to the chaser with a tether. The paper provides novel insight on the feasibility of tethered de-orbiting for the various mission phases such as stabilization after capture, de-orbit burn (plus stabilization), stabilization during atmospheric pass, highlighting the importance of various critical mission parameters such as the tether material. It is shown that the selection of the appropriate tether material while using simple controllers can reduce the effort needed for tethered deorbiting and can safely control the attitude of the debris/chaser connected with a tether, without the danger of a collision.enAttribution-NonCommercial-NoDerivatives 4.0 InternationalArticle19835566