INTEGRATED INERTIAL-SATELLITE ORIENTATION AND NAVIGATION SYSTEM FOR OBJECTS MOVING ON BALLISTIC TRAJECTORY WITH ROTATION AROUND LONGITUDINAL AXIS

FIELD: physics; navigation. ^ SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay. ^ EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity. ^ 6 dwg Изобретение относится к области навигационного приборост