Patent
Systems and methods of redundancy for aircraft inertial signal data
Mark T. Manfred,Thomas A. Ryno +1 more
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TLDR
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.Abstract:
An aircraft inertial system comprises at least two inertial reference units (IRU) that provide a first set of inertial signal data for an aircraft and at least two attitude heading reference systems (AHRS) that provide a second set of the inertial signal data for the aircraft At least one primary flight display receives the first and the second sets of the inertial signal data, and a standby flight display receives at least the second set of the inertial signal data from at least one of the AHRS When a single fault condition occurs, the primary flight display continues to operate with fail-operational redundancy from at least three independent sources of the inertial signal data comprising one or more IRU and AHRS combinations The standby flight display will operate using a different source of the inertial signal data than the source of the inertial signal data for the primary flight displayread more
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Patent
Systems and methods for providing aircraft heading information
Mark T. Manfred,Thomas A. Ryno +1 more
TL;DR: In this article, an attitude heading reference device consisting of at least one interface for receiving heading information from one or more IRUs, at least a set of gyroscopes and accelerometers, and a memory device for storing data representing heading information received via the at least 1 interface is presented.
Patent
System and method for isolating attitude failures in aircraft
TL;DR: In this paper, the attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying an attitude solution; an attitude integrity system generating attitude integrity (AI) solution calculated from measurements from attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems.
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TL;DR: In this article, the authors describe a device aboard an aircraft comprising output means (3) configured to restore information relating to the aircraft status from aircraft systems (7a-7c), the device including a module (5, 5a) providing interface between output means and aircraft systems.
Patent
Navigation data sharing system and navigation instrument
TL;DR: In this article, a navigation system includes two or more navigation instruments connected with a network, and a representative sensor selecting module for selecting the sensor to be used based on the representative sensor selection related information received from the navigation instrument that functions as the mother unit.
Patent
Systems and methods for producing two independent dissimilar attitude solutions, two independent dissimilar inertial solutions or both from one improved navigation device
TL;DR: In this paper, the authors present a system and methods for producing two independent dissimilar attitude solutions from one improved navigation device, or both from a single improved navigation system, using an attitude heading and reference unit.
References
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Patent
Airborne surveillance method and system
TL;DR: In this paper, an airborne surveillance method and system uses a phase comparison direction finding antenna (20), other data including Mode C transponder (60) generated altitude information of the target aircraft in addition to a variety of other factors to determine target aircraft position.
Journal ArticleDOI
A Low-Cost, Redundant Inertial Measurement Unit for Unmanned Air Vehicles:
TL;DR: The development of a low-cost, redundant, strapdown inertial measurement unit (IMU), which comprises four ceramic vibrating structure gyroscopes and four QLC 400 accelerometers configured on a truncated tetrahedron design, is discussed.
Patent
Micro inertial measurement unit
Hiram McCall,Ching-Fang Lin +1 more
TL;DR: In this article, a micro inertial measurement unit was adapted to apply to output signals proportional to rotation and translational motion of a carrier, respectively from angular rate sensors and acceleration sensors, and the processing method utilizes a feed-forward open-loop signal processing scheme to obtain highly accurate motion measurements.
Patent
Low cost flight instrumentation system
TL;DR: In this paper, a device for providing flight condition information and a method of displaying such information is presented, which can be either a primary or a backup system, depending on the pilot's cognitive workload.
Patent
Method, apparatus and computer program product for estimating airplane attitude with reduced sensor set
TL;DR: In this article, an apparatus, method and computer program product useful for supplying the pilot of an aircraft with aircraft attitude information in the event of full or partial failure of the gyroscopic system normally used to supply such data.