Rockwell Collins, Inc.

Maxime M Gariel

Vladislav Gavrilets

Joshua R Bertram

Bryan M Krawiec

Ramachandra J Sattigeri

Robert M Caplinger

Sami S Mina

Systems and methods configured to adaptively control input sequences that are used to conduct qualification tests of simulators are disclosed. An input sequence may be adaptively controlled by: providing the input sequence to a simulator configured to simulate operations of a device; comparing output of the simulator to a set of recorded operation data obtained from the device; adaptively modifying the input sequence within specified bounds to produce a modified version of the input sequence to reduce one or more differences that exist between the output of the simulator and the set of recorded operation data; and providing the modified version of the input sequence to the simulator to simulate operations of the device.

Adaptive control for simulator input generation

A relative positioning system is described. At least one emitter is attached to a first object, where each of the at least one emitters includes: an electromagnetic radiation source configured to generate electromagnetic radiation over a band of wavelengths, and a prism arranged to refract and disperse the electromagnetic radiation from the electromagnetic radiation source according to the wavelength of the electromagnetic radiation. At least one electromagnetic radiation detector is attached to a second object arranged to detect the wavelengths of some of the electromagnetic radiation refracted and dispersed by a respective prism. At least one processor is configured to determine the relative position of the first object and the second object based on the detected wavelengths by the at least one electromagnetic radiation detector.

Prismatic relative positioning system

An avionics computing device of an aircraft including a rotor may include a non-transitory computer-readable medium and a processor communicatively coupled to the non-transitory computer-readable medium. Upon an occurrence of a condition indicative of a requirement to perform an autorotation maneuver, the processor may be configured to generate autorotation guidance commands based on a generated feasible three-dimensional autorotation trajectory. The generated feasible three-dimensional autorotation trajectory may be for the autorotation maneuver of an aircraft including a rotor. The generated autorotation guidance commands may be configured to guide a pilot of the aircraft to perform the autorotation maneuver of the aircraft along the generated feasible three-dimensional autorotation trajectory. The processor may further be configured to output data associated with the generated autorotation guidance commands to an input/output device for presentation to the pilot.

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Sterling, VA, United States of America

Maxime M Gariel