Iru position updating crippledating com
A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position.
Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform.
In a typical radar tracking system, pulses are transmitted through an antenna at a predetermined repetition rate toward a target and the pulses are reflected from the target back to the antenna.
The time of reception and the doppler shift of the pulses, together with the pointing angles of the airborne antenna, the time history of angular orientation and of the velocity vector of the skin tracking aircraft or missile are processed by a signal processor to generate signals that represent range, radial velocity or range rate, and the elevation and azimuth angles to the target.
The Gulf of Mexico, where single long-range navigation system (S-LRNS) RNP 10 is authorized; i.e., the Houston oceanic control area (CTA)/flight information region (FIR) and the portion of the Miami CTA/FIR overlying the Gulf of Mexico, Monterrey CTA, and Merida High CTA within the Mexico FIR/upper control area (UTA).
A section of the operators application for RNP 10 authorization.
The equipment suffixes contained in the attached table are for use only in FAA Flight Plan (FAA Form 7233-1).An inertial navigation system (INS) is a navigation aid that uses a computer, motion sensors (accelerometers) and rotation sensors (gyroscopes) to continuously calculate via dead reckoning the position, orientation, and velocity (direction and speed of movement) of a moving object without the need for external references.It is used on vehicles such as ships, aircraft, submarines, guided missiles, and spacecraft.The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies.This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.