Soft Landing Dynamics Study with Extension to Elevator Anchoring
- Paper number
IAC-08.D4.2.4
- Author
Prof. Radu Rugescu, Politechnic University of Bucharest, Romania
- Year
2008
- Abstract
Soft landing dynamics of tethered systems consisting of two different masses is investigated through an inverse dynamics method. The deployment and anchoring of the lower end of the space elevator cable is analyzed and re-entry dynamics and necessary initial conditions for a secure soft landing are discussed. The physical method is considered for center bodies without atmosphere (Moon and other satellites) and for planets with atmosphere (Earth, Mars). The efficiency of the system is compared with the gasdynamical or balloon soft landing solutions, in terms of the mass expense and system complexity. The technology for the cable deployment is considered as given at any desired size within a circular orbit for a twin tether system of different masses. Numerical simulation covers the descent trajectory of the landing mass and the post-landing evolution of the orbital mass after de-connection. Emphasize is put on dynamic loads within the cable during the eigen-descent phase and at the landing position regarding safe anchoring capabilities. The estimates are based on simplifying assumptions regarding the inertial behavior of the hyper-long cable.
- Abstract document
- Manuscript document
(absent)