Abstract: Systems and methods to determine navigation states of a platform are disclosed. An example system includes a first processing node to determine a first aeroelastic navigation state of a platform at a first structural location of the platform with respect to a first aeroelasticity reference, a second processing node to determine a second aeroelastic navigation state of the platform at a second structural location of the platform with respect to the first aeroelasticity reference or a second aeroelasticity reference, and a storage device to store a platform navigation state based on at least one of the first or second aeroelastic navigation states.

Abstract: A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.

Abstract: A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.

Abstract: A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.

Abstract: Systems and methods to determine navigation states of a platform are disclosed. An example system includes a first processing node to determine a first aeroelastic navigation state of a platform at a first structural location of the platform with respect to a first aeroelasticity reference, a second processing node to determine a second aeroelastic navigation state of the platform at a second structural location of the platform with respect to the first aeroelasticity reference or a second aeroelasticity reference, and a storage device to store a platform navigation state based on at least one of the first or second aeroelastic navigation states.

Abstract: Systems and methods for autonomous underwater navigation are disclosed. In one embodiment, a system for autonomous underwater navigation comprises an underwater communication network, at least one master controller node coupled to the underwater communication network, at least one network docking node coupled to the underwater communication network, and at least one submersible vehicle for underwater mapping at least a portion of a floor of a body of water. The submersible vehicle comprises a geolocation module to establish a geographic reference for at least one location in the underwater geographic region and an image collection module to collect images of an underwater geographic region proximate the geographic reference.

Abstract: A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.

Abstract: Systems and methods for aeroelasticity measurement and vehicle structural health analysis and monitoring are disclosed. In one embodiment, a computer based system to monitor structural integrity of an aircraft comprises a processor and a memory module coupled to the processor and comprising logic instructions stored on a computer readable medium which, when executed by the processor, configures the processor to receive a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation, store the plurality of aeroelasticity measurements and associated flight parameters in a persistent storage medium, and generate an alert when one or more aeroelasticity parameters exceeds a threshold. In some embodiments, the system may be implemented in a computing system or as logic instructions recorded on a computer readable medium.

Abstract: Techniques for removing time tag jitter and crossover distortion from a measurement system are described. A period or clock drift estimate is generated for each sensor, and the estimates are used to remove time tag jitter and detect and remove crossover distortion. This crossover distortion condition is common to measurement systems required to acquire and accurately time tag data from multiple sensors where the sensors produce data at an asynchronous periodic rate which may result in a distortion in time tag accuracy. These techniques are germane to aircraft and other systems that require precisely time correlated measurements from multiple sensors hosted by a data control system, and can obviate the use of real time operating systems and specialized hardware for this purpose.

Abstract: Techniques for removing time tag jitter and crossover distortion from a measurement system are described. A period or clock drift estimate is generated for each sensor, and the estimates are used to remove time tag jitter and detect and remove crossover distortion. This crossover distortion condition is common to measurement systems required to acquire and accurately time tag data from multiple sensors where the sensors produce data at an asynchronous periodic rate which may result in a distortion in time tag accuracy. These techniques are germane to aircraft and other systems that require precisely time correlated measurements from multiple sensors hosted by a data control system, and can obviate the use of real time operating systems and specialized hardware for this purpose.

Abstract: An active wing and lift surface control system for an aircraft is described. The wing and lift surface control system includes an aeroelasticity measurement system configured to provide at least one of real time wing twist measurements and real time measurements of aircraft body bending, at least one actuator mechanically coupled to a control surface of the aircraft, and a control system communicatively coupled to the aeroelasticity measurement system and to the at least one actuator. The control system is operable to receive the measurements from the aeroelasticity measurement system and generate control signals, based on the real time measurements, to operate the at least one actuator to adjust a drag associated with one or more of the wing and the aircraft body.

Abstract: An aircraft aeroelasticity measurement system according to the invention can be used to perform in-flight wing twist measurements of an aircraft or any moving vehicle or structure on which its sensors can be mounted. The system includes a centralized processing unit, a reference navigation unit mounted in the aircraft body, a plurality of measurement navigation units mounted in the aircraft wings, and a global positioning system (“GPS”) receiver that generates GPS data for enhancing the accuracy of the navigation data. The system collects navigation data from the reference navigation unit and the measurement navigation units, generates navigation solutions from the navigation data, and performs a stochastic alignment and flexure estimation procedure to generate a corrected measurement solution that indicates the aeroelasticity of the aircraft. Wing twist and wing deflection information can be derived from the corrected measurement solution.