FIELD: physics, navigation.
SUBSTANCE: invention relates to satellite navigation and passive radar. The disclosed method of locating an aircraft is characterised by ground-based stationary navigation receivers receiving direct beams of repeating radio signal transmissions emitted by navigation satellites, from which coordinates of the navigation receivers on the ground are calculated and refined; using a group of spaced-apart navigation receivers with predetermined dislocation coordinates, which transmit information received from navigation satellites to a computer for calculating the coordinates of the aircraft; the aircraft is detected using at least two navigation satellites visible to the receivers and at least two corresponding navigation receivers upon detecting a radio shadow represented by abrupt weakening of the radio signal from the first navigation satellite or complete loss thereof at the corresponding first navigation receiver and simultaneously from the second navigation satellite at the second navigation receiver; wherein the computer records the time of detecting the radio shadow by the first and second navigation receivers, using a preceding radio shadow, the full radio signal respectively from the first and second navigation satellites, containing the accurate universal time of atomic clocks at each navigation satellite, and an accurate range-finding code, which enables to filter out adverse reflected radio signals corresponding to abrupt increase in range for the corresponding navigation satellite and navigation receiver pair; for said recorded time of detecting a radio shadow, coordinates of the first and second navigation satellites are recorded, as well as known constant coordinates of the first and second navigation receivers confirmed by each reception of a radio signal from the navigation satellite; the first and navigation satellites and navigation receivers used can be any of a system of a navigation satellite and a group of navigation receivers; two lines in space are therefore recorded at said moment in time, one of which passes through the obtained coordinates of the first navigation satellite and known coordinates of the first navigation receiver, and the second passes through the obtained coordinates of the second navigation satellite and known coordinates of the second navigation receiver; the coordinates of the point of intersection of said two lines are determined, said coordinates being the coordinates of the detected aircraft at the corresponding detected moment in time; further, coordinates of the aircraft at other moments in time are determined similarly and tracked, thereby forming a path.
EFFECT: broader functional capabilities.
1 dwg
