FIELD: aircraft instrumentation engineering; navigation, sighting and pilotage equipment of flying vehicles.
SUBSTANCE: ground speed vector is determined by means of gyro inertial navigational system which is corrected according to data of multi-beam Doppler meter; direction cosines of adapter matrix from gyro inertial system to body-axis coordinate system are obtained by integration of adiabatic differential equations by data on absolute angular velocities of flying vehicle. Altitude and spatial orientation data are used for determination of those which are characterized by stable separation of reflected signal. Predicted closure rate is calculated for bean being switched for control of Doppler filter; error between measured predicted magnitudes of closure rate is used for forming next equation for components of vector of ground speed increments in body-axis coordinate system. System of three linear independent equations is solved, equations obtained before or after malfunctions inclusive. Calculated magnitudes of vector of ground speed increments are presented by components in gyro inertial coordinate system and static processing is performed; static estimations thus obtained are used for correction of inertial system. Drift angle is determined as angle between present magnitudes of three-dimensional vectors of air speed and ground speed of flying vehicle being measured.
EFFECT: enhanced accuracy and stability of determination of ground speed vector and drift angle.
1 dwg
