Honeywell International Inc.

Sperry Rand Corporation

Honeywell G.m.b.h.

James S Johnson

Harmohan N Singh

Christopher John Shehi

Kimberly TenPasBell

David R Brickner

Reginald Crocker

Gene A Albrecht

A high integrity navigation system and method are provided. The method comprises performing a cyclic redundancy check (CRC) of a desired flight path of an aircraft, for example an approach to an airport, and comparing the CRC with a stored CRC performed on the identified flight path. If the comparison exceeds a first threshold, a first alert is provided wherein the pilot is to perform a published missed approach. A second alert, also requiring a missed approach, is provided when one or more comparisons are performed of a sensor position of the aircraft with the high integrity flight path; a defined flight path with the high integrity flight path; and the sensor position with an aircraft position determined by a flight management system, and thresholds are exceeded.

Aircraft system and method for improving navigation performance

In accordance with various embodiments, there are systems and methods for predicting end of life of a Li-ion battery. The method can include at least one of partially charging and partially discharging a battery, measuring an open circuit voltage of the battery before and after at least one of partial charging and partial discharging, and determining a state of charge value of the battery corresponding to the open circuit voltage measured before and after at least one of partial charging and partial discharging. The method can also include correlating at least one of a charge energy and a discharge energy with a change in the state of charge value and extrapolating to get a full battery capacity, tracking the full battery capacity as a function of time, and performing trend analysis of the full battery capacity over time to predict the battery's end of life.

Lithium-ion battery prognostic testing and process

An aircraft heading correction system utilizing the horizontal field strength of the earth's magnetic field to determine the tangent of the dip angle generally associated with a given field strength. The tangent of the dip angle is then used to generate a signal which corrects the flux valve heading during accelerated flight.

Magnetic flux detector correction system

An automatic rate range switching and control system adapts the full range of an analog output signal of a gyroscopic rate sensor to a range consistent with the precision conversion thereof into a digitally compatible signal. In a digital strapped down inertial reference system, for example, a plurality of strapped down, force-rebalanced rate sensors is used to sense aircraft body rates, wherein each gyro pick off signal is fed back to the gyro torquer in a manner to maintain the pick off signal essentially null, the torquer current signal thus being proportional to the sensed aricraft rate. The full range of the gyro's rate sensing capability may extend from zero to several hundred degrees per second. However, with the present invention, the switching and conversion of the analog rate signal into a digitally compatible signal is necessary only over a limited range. The current switching is accomplished by means of a rate tracing gate voltage rate switch for protecting the switching devices from destructively high switching voltages.

Gyroscope rate range switching and control system

An improved second order gyroscopic attitude and heading reference system including separate variable time constant accelerometer integrators for independently controlling the velocity error signals associated with respective east and north acceleration signals to provide velocity damped output signals so that a high acceleration input signal of dubious accuracy will have minimal precessional authority while a lower acceleration input signal of greater accuracy will retain nominal control.

Growing community of inventors

Phoenix, AZ, United States of America

James S Johnson