A method for iteratively estimating a wind speed at a wind turbine is disclosed, said wind turbine comprising a rotor carrying a set of wind turbine blades, each wind turbine blade having a variable pitch angle. A minimum tip speed ratio, λ.sub.min, is derived, based on an obtained pitch angle, θ. The minimum tip speed ratio, λ.sub.min, defines a limit between a stable and an unstable control region. An initial tip speed ratio, λ.sub.init>λ.sub.min, is selected, and an initial estimated wind speed, v.sub.init, is derived based on the initial tip speed ratio, λ.sub.int, and an obtained rotational speed, ω, of the rotor. An estimated wind speed, v.sub.est, is iteratively derived, based on the obtained rotational speed, ω, and the obtained pitch angle, ω, and using the derived initial estimated wind speed, v.sub.init, as a starting point. The iterative process converges fast and reliably.

A method for iteratively estimating a wind speed at a wind turbine is disclosed, said wind turbine comprising a rotor carrying a set of wind turbine blades, each wind turbine blade having a variable pitch angle. A minimum tip speed ratio, λ.sub.min, is derived, based on an obtained pitch angle, θ. The minimum tip speed ratio, λ.sub.min, defines a limit between a stable and an unstable control region. An initial tip speed ratio, λ.sub.init>λ.sub.min, is selected, and an initial estimated wind speed, v.sub.init, is derived based on the initial tip speed ratio, λ.sub.int, and an obtained rotational speed, ω, of the rotor. An estimated wind speed, v.sub.est, is iteratively derived, based on the obtained rotational speed, ω, and the obtained pitch angle, ω, and using the derived initial estimated wind speed, v.sub.init, as a starting point. The iterative process converges fast and reliably.

Measurement apparatuses and methods are disclosed for generating high-precision and—accuracy gas concentration maps that can be overlaid with 3D topographic images by rapidly scanning one or several modulated laser beams with a spatially-encoded transmitter over a scene to build-up imagery. Independent measurements of the topographic target distance and path-integrated gas concentration are combined to yield a map of the path-averaged concentration between the sensor and each point in the image. This type of image is particularly useful for finding localized regions of elevated (or anomalous) gas concentration making it ideal for large-area leak detection and quantification applications including: oil and gas pipeline monitoring, chemical processing facility monitoring, and environmental monitoring.

Measurement apparatuses and methods are disclosed for generating high-precision and—accuracy gas concentration maps that can be overlaid with 3D topographic images by rapidly scanning one or several modulated laser beams with a spatially-encoded transmitter over a scene to build-up imagery. Independent measurements of the topographic target distance and path-integrated gas concentration are combined to yield a map of the path-averaged concentration between the sensor and each point in the image. This type of image is particularly useful for finding localized regions of elevated (or anomalous) gas concentration making it ideal for large-area leak detection and quantification applications including: oil and gas pipeline monitoring, chemical processing facility monitoring, and environmental monitoring.

An airspeed estimation system of an aircraft includes an electronic airspeed rate modeler unit configured to output an estimated airspeed rate signal indicating an estimated airspeed rate of the aircraft. The estimated airspeed rate signal is based on a longitudinal body acceleration of the aircraft and at least one adaptive parametric airspeed model. The airspeed estimation system further includes an electronic airspeed estimator unit in signal communication with the airspeed rate modeler unit. The airspeed estimator unit is configured to determine an estimated airspeed of the aircraft based on the estimated airspeed rate signal.

An airspeed estimation system of an aircraft includes an electronic airspeed rate modeler unit configured to output an estimated airspeed rate signal indicating an estimated airspeed rate of the aircraft. The estimated airspeed rate signal is based on a longitudinal body acceleration of the aircraft and at least one adaptive parametric airspeed model. The airspeed estimation system further includes an electronic airspeed estimator unit in signal communication with the airspeed rate modeler unit. The airspeed estimator unit is configured to determine an estimated airspeed of the aircraft based on the estimated airspeed rate signal.

A fire detection and suppression system includes a system controller for determining an initial location of the fire based on fire location information from fire detectors, and then the system controller determines a final location of the fire based on fire location information taking into account spatial and/or angular relationships between the fire detectors and the initial location. The system controller determines a location of the fire and activates monitors to deploy suppressant based on a distance between each of the monitors and the location of the fire. The system controller controls the monitors based on how the suppressant is deployed onto the fire.

A fire detection and suppression system includes a system controller for determining an initial location of the fire based on fire location information from fire detectors, and then the system controller determines a final location of the fire based on fire location information taking into account spatial and/or angular relationships between the fire detectors and the initial location. The system controller determines a location of the fire and activates monitors to deploy suppressant based on a distance between each of the monitors and the location of the fire. The system controller controls the monitors based on how the suppressant is deployed onto the fire.

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, an apparatus for close formation flight, comprises a plurality of sensors for collecting measurements characterizing airflow near an aircraft. The plurality of sensors are attachable to at least one of a wing, fuselage, or tail of the aircraft, and the measurements provide information about airflow velocity in a direction transverse to a direction of the aircraft flight.

Disclosed is a gradient information acquisition method comprising: a speed measured value acquisition step in which a measured value of the speed of a rail vehicle is acquired; a speed calculation step in which a calculated value of the speed of said vehicle is found using an equation of movement including a parameter indicating the gradient of the path of travel of said rail vehicle; a parameter value acquisition step in which a parameter value is found of a function indicating said gradient, for which parameter the difference of said measured value of the speed and said calculated value of the speed is a minimum; and a gradient information acquisition step of finding the gradient of said path of travel, based on the parameter value of the function indicating said gradient that was acquired in said parameter value acquisition step.