Title:
CALIBRATION METHOD FOR INTERNAL NAVIGATION INSTRUMENT OF AIR CRAFT
Document Type and Number:
Japanese Patent JP3447772
Kind Code:
B2
Abstract:
PURPOSE: To calibrate and precisely initialize a navigation device by measuring speeds of north and east directions, an air craft orientation, and variation rate thereof, obtaining a diagonal aviation angle and a lever arm, obtaining these Kalman gain values, multiplying the respective Kalman gain values by an intersection aviation trace position integrating the intersection track speed.
CONSTITUTION: An inertial reference device 14 measures speeds VN and VE of the north and east directions, an aircraft orientation, and variation rate Ψthereof and calculates a speed meter calculation transient 15 from that value, a intersection aircraft orientation speed VC, and an aircraft speed VH. Integrators 18 and 20 outputs a diagonal aviation angle β and an arm RL, respectively, an insertion aviation trace speed is obtained from these values, the speeds VH and VC, and the variation rate ΨH of the aircraft orientation using deviation nodes 30 and 34 and is integrated by means of an integrator 36. The Kalman gain values generated by a Kalman filter 22 input by VE, VN, ΨH, β, and RL are integrated with a position PCT by means of a multiplier 24, the respective values are input to an aircraft computer, and error correction is performed.
Inventors:
Joan W. Diesel
Application Number:
JP22115793A
Publication Date:
September 16, 2003
Filing Date:
September 06, 1993
Export Citation:
Assignee:
Riton Systems, Inc.
International Classes:
G01C19/00; G01C21/16; G01C25/00; (IPC1-7): G01C19/00; G01C21/16
Domestic Patent References:
| JP551295A | ||||
| JP5254463A |
Attorney, Agent or Firm:
Masao Okabe (4 others)