METHOD OF DETERMINING NAVIGATION PARAMETERS OF OBJECT AND STRAPDOWN INERTIAL NAVIGATION SYSTEM FOR IMPLEMENTATION OF METHOD

FIELD: measurement technology.SUBSTANCE: invention relates to the field of navigational measurements and can be used to determine the flight and navigation parameters of aircraft or ground vehicles, for example, an aircraft or a vehicle. Method for determining the pilot and navigation parameters by the strapdown inertial navigation system (SINS) is that they compensate for errors in the unit of the main sensing elements (MSE), which is part of the "traditional" SINS structure. Compensation is made by averaging and taking into account the measurements of three additional gyroblocks and accelerometer blocks consisting of "n" gyroscopic absolute angular velocity sensors and "n" accelerometers respectively. In this case, the sensitivity axis of the main sensor coincides with the common sensitivity axis of the corresponding measuring block and averaging the total set of measurements. Correction of the main sensors of the MSE for more accurate information from the corresponding "averaged" blocks is made with an evaluation and subsequent consideration of the observed components of the mathematical model of MSE errors with the Kalman filtering procedure. To increase the accuracy of the Kalman measurements, a constant switching of these units is made with a technically permissible frequency. Thus, the device is an inertial-gyroscopic multisystem containing a calculator, a block of main navigation sensing elements, in addition to these three gyroblocks, three blocks of accelerometers.EFFECT: significant increase in the accuracy of determining the flight and navigation parameters of the carrier in the autonomous mode of operation of the inertial navigation system (INS) when using small-size navigation sensing elements.2 cl, 4 dwg Изобретение относится к области навигационных измерений и может быть использовано для определения пилотажных и навигационных параметров авиационных или наземных носителей, например летательного аппарата или автомобиля. Способ определения пилотажных и навигационных параметров бесплатформенной инерциальной навигационной системой (БИНС) заключается в том, что осуществляют компенсацию погрешностей блока основных чувствительных элементов (БЧЭ), входящего в «традиционный» состав БИНС. Компенсация производится за счет усреднения и учета измерений трех дополнительных гироблоков и блоков акселерометров, состоящих из "n" гироскопических датчиков абсолютных угловых скоростей и "n" акселерометров соответственно. При этом ось чувствительности основного д