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Lunar information and navigation support system

DOI 10.18127/j19998465-201812-13


V.E. Chebotarev – Dr.Sc.(Eng.), Professor, Leading Design Engineer, JSC Academician M.F. Reshetnev «ISS» (Zheleznogorsk)

The general principles for information and navigation support provided by Lunar Information and Navigation Support System (LINSS) for limited user population have been defined: high availability, software maintenance, integration of navigation and communication functions at the level of user equipment and spacecraft (SC).
The overall principle of target lunar missions information and navigation have been defined: LINSS nadal and orbitals items, ground stations, global navigation satellite systems (GNSS) navigation field with different approach of solving this task in the interest of a space user and a nadal user.
For a nadal user the following LINSS orbit configuration is proposed: the number of spacecrafts is 8−9, the spacecrafts shall be uniformly distributed over two or three planes in near-circular polar orbits with more than semidiurnal orbits ensuring duplex communication and positioning in plane at a navigation center.
The user equipment provides relay of interrogation navigation signals, light signals radiation (reflection) and the data exchange, that is implementation of communication and navigation function simultaneously. Between the navigation sessions the user realizes the autonomous navigation mode applying celonavigation means and the inertial navigation system.
Selenodetic supporting of LINSS shall be preventive and include the architecture of triangulation selenodetic network points, deployment of multilevel constellation of spacecraft at different altitude: less than 200 km, around 800 km and more than 2760 km.
For a space user the following is proposed: at trajectories after lift-off from the Earth it is proposed to use ground information and navigation support facilities, including GNSS navigation field; close to the Moon it is proposed to navigate using the selenodetic points, duplex communication shall be done directly with ground stations; LINSS orbital means shall be used for duplex communication in the available areas.
The task of LINSS ephemeris and time reference support has been defined as follows: with a network of selenodetic points with passive retro-reflectors of satellite signals: RF and optical range (ephemeris support); using the GNSS navigation field (synchronization of time scales).

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