Method for calibrating inertial navigation instruments of aircraft
Номер патента: CA2104716A1
Опубликовано: 24-09-1994
Автор(ы): John W. Diesel
Принадлежит: Litton Systems Inc
Опубликовано: 24-09-1994
Автор(ы): John W. Diesel
Принадлежит: Litton Systems Inc
Реферат: A method and apparatus for minimizing the effect of lateral velocity transients upon an aircraft inertial instrument calibration process of the type in which cross-track velocity is measured and utilized to correct for the east component of gyro bias error. A "cross-track position" value is obtained by integration of the cross-track velocity. A Kalman filter calculates a plurality of gain values corresponding to measurements of crab angle, lever arm, north and east velocity, heading angle and rate of change of heading angle and those gain values are applied to the cross-track position value to obtain error values for each of such parameters. The calculated error values are then employed as corrections to, or calibrations of, the inertial instrument outputs.
A method for initial alignment of an inertial navigation apparatus
Номер патента: US20180274940A1. Автор: Xuefeng SHEN,Qiang Ren,Jiejun Wang,Lilong WEI,Guiyan CUI. Владелец: SHANGHAI HUACE NAVIGATION TECHNOLOGY LTD. Дата публикации: 2018-09-27.