| 摘要 |
<p>The invention relates to the field of inertial satellite navigation of different objects. According to the inventive method, the coordinates and/or the speed of an object (1) in a basic coordinate system (3) and in a reference coordinate system (2), related to the object, are measured at moments of time t(i) - t(i+1). Such measurements are made by means of 'Glonass' and/or 'Navstar' global satellite systems. In the portions (t(i) - t(i+1)) of the trajectory of the object, a vector of the acceleration thereof is measured in the system (2), which allows for measurement of the indicated coordinates and/or of the speed. Such coordinates and speed are determined by similarity in the systems (2) and (3) at the moments t(j) and t(j+1) in the portion (t(j) - t(j+1)) which is not parallel to the portion of trajectory where the measurement has been made. On the basis of such data, vectors corresponding to displacements L(i) and L(j) and/or to the increase Δ V(i), Δ V(j) of the speed of the object (1) in the coordinate systems (2) and (3) are determined for at least two portions of the trajectory. Said vectors are used to determine the desired matrix of transfer between the coordinate systems (2) and (3). When necessary, the object (1) is maneuvered to obtain non parallel portions of the trajectory. The invention allows for higher precision and for better all-weather use of the method.</p> |
