Abstract: An airfoil performance monitor comprising a housing mounted on a low pressure face of an airfoil, and defining pitot and static pressure orifices; an airspeed-dependent sensor that senses airflow impinging on the pitot orifices and generates a digital airflow signal indicative of turbulence of the airflow; and a controller that derives a turbulence intensity ratio by filtering turbulence values calculated from the digital airflow signal.

Abstract: There is described a method for generating a parameter for airfoil performance monitoring, the method comprising: receiving at least a first signal indicative of a first airflow parameter measured at one of an aft position and a side-facing position of a sensor mast mounted to an airfoil and at least a second signal indicative of a second airflow parameter measured at a fore position of the sensor mast; generating a turbulence intensity ratio for each one of the first airflow parameter and the second airflow parameter; and combining the turbulence intensity ratio of the first airflow parameter and the turbulence intensity ratio of the second airflow parameter to generate a combined turbulence intensity ratio for airfoil performance monitoring.

Abstract: A method and a system for providing a sighting reticle oriented to aim at a target from a vehicle within an environment of the target are described. The method improves the situational awareness of the operator regardless of the orientation and motion of the aiming instrument. The method comprises providing a graphical image representing the environment seen from the vehicle when aiming at the target; determining a state of the vehicle with respect to a spatial reference point; overlaying the sighting reticle onto the graphical image, the sighting reticle indicating the target on the graphical image with respect to the spatial reference point, the sighting reticle comprising a marking defining the spatial reference point; positioning the sighting reticle to orient the marking based on the state of the vehicle; and displaying on a display device the sighting reticle positioned on the graphical image to enable aiming at the target.

Abstract: A method and apparatus is disclosed for displaying a dynamic parameter, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing to said scale in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Abstract: A method and apparatus are disclosed for estimating a position of a target of interest using a plurality of position detection sensors wherein for at least one of the sensors, a corresponding time-variant detection probability profile is combined with the detection status received from the sensor and further wherein each of the corresponding detection probability profiles is combined to generate a global detection probability profile, wherein the combining comprises probabilistically adding a first given probability profile in the case where a first given corresponding indication comprises a target detection and probabilistically subtracting a second given probability profile in the case where a corresponding second given indication comprises a target non-detection and wherein the position of the target is estimated using the highest probability region(s) of the generated global detection probability profile.

Abstract: The airspeed over an external surface of the aircraft is sensed at a predetermined location spaced from the surface, signals are produced representative of average airspeed and of airspeed fluctuations caused by air turbulence, and the signals are also used to produce a signal representative of the ratio of the airspeed fluctuations to the average airspeed.

Abstract: The approaching stall of an aircraft wing is predicted using an inherent characteristic of the airflow as the stall is approached. The airspeed over the wing is sensed at a predetermined location spaced above the top surface of the wing, input signals are produced representative of airspeed fluctuations caused by air turbulence, input signals are used to produce a signal representative of the ratio of the airspeed fluctuations to the average airspeed, and the ratio signal produces a signal indicating imminent stalling.