Patent
Redundant system for the indication of heading and attitude in an aircraft
Reads0
Chats0
TLDR
In this paper, a method and an arrangement for synthetically calculating redundant attitude and redundant heading by means of existing data in an aircraft is presented, in one embodiment the aircraft is available and in another embodiment the heading is calculated from a magnetic heading sensor.Abstract:
A method and an arrangement for synthetically calculating redundant attitude and redundant heading by means of existing data in an aircraft. In one embodiment the heading of the aircraft is available and in another embodiment the heading is calculated from a magnetic heading sensor. When the heading is available (redundant heading) attitude is calculated by weighting together the signals from and angular rate gyros (2) in the aircraft's flight control system, information from air data (altitude, speed, angle of attack) as well as information about heading (redundant heading). When the heading is not available, attitude and heading are calculated in one embodiment with the aid of Kalman filters (11, 22) by weighting together the signals from the angular rate gyros in the aircraft's control system, information from air data (altitude, speed, angle of attack and sideslip angle) as well as information from a magnetic heading detector existing in the aircraft.read more
Citations
More filters
Patent
Magnetically stabilized forward observation platform
Randy Louis Wells,Rusty Allen Anderson,E. Pinczewski Ii Eugene,Robert Edward Oakley,Ralph Francis Gesin,Ruben Rojas +5 more
TL;DR: In this paper, a system and method for determining a position of a remote object comprising inertial sensors and three axis magnetic sensor, together with a target sighting device aligned with the observation platform to determine a target line of sight and a target range finder, is presented.
Patent
Inertial/magnetic measurement device
TL;DR: In this article, a system and method for onboard optimal estimation of heading, pitch, and roll through real-time measurement of magnetic field, acceleration and angular motion in three dimensions is presented.
Patent
Self-calibration for an inertial instrument based on real time bias estimator
TL;DR: In this paper, a bias estimator calculates the first and second bias correction signals based on first-and second measurements made during respective first- and second time intervals where a sign of one of the bias error signals changes from one state to another state during the first time interval to the second time interval.
Patent
Systems and methods for attitude fault detection based on air data and aircraft control settings
TL;DR: In this paper, a sensor monitor for an aircraft attitude measurement system comprises an aircraft model configured to model a plurality of states, including at least an aircraft altitude state, an aircraft velocity state, a sink rate error state, and a wind velocity state; and a residual evaluator configured to input residual error values generated by the propagator-estimator.
Patent
Systems and methods of redundancy for aircraft inertial signal data
Mark T. Manfred,Thomas A. Ryno +1 more
TL;DR: An aircraft inertial system comprises at least two inertial reference units (IRUs) that provide a first set of inertial signal data for an aircraft and at least attitude heading reference systems (AHRS) that provides a second set of the inertial data for the aircraft as discussed by the authors.
References
More filters
Patent
Integrated redundant reference system for the flight control and for generating heading and attitude informations
Uwe Krogmann,Juergen Bessel +1 more
TL;DR: In this paper, a plurality of two-axis rate gyros are arranged in relation to an aircraft-fixed coordinate system such that they redundantly supply angular rate information and correspondingly redundant acceleration information.
Patent
Strap-down attitude and heading reference system
TL;DR: In this article, a vehicle's position and attitude with respect to the earth is estimated continuously by integrating the outputs of translational and rotational accelerometers that are attached to the vehicle.
Patent
Aircraft piloting aid system using a head-up display
Jean-Luc Sicre,Patrice Guillard +1 more
TL;DR: In this paper, an aircraft piloting aid system mainly used during take-off and landing under adverse visibility conditions is disclosed, where a non-inertial attitude heading reference system (AHRS) combined with a compass is used and data therefrom is periodically corrected in order to display attitude symbols by means of corrected data rather than raw data from the AHRS.
Patent
Synthesized attitude and heading inertial reference
TL;DR: In this paper, an inertial reference system for determining the attitude and rate of change of attitude of a vehicle such as an aircraft is described, and the information provided by the eliminated fiber-optic gyroscope is synthesized from the output of the remaining fiber-ogroscope and the output from the low-cost reference IMU.