Patent ID: 7333030
Filing Date: 2008-02-19
Classification: G01C,G01S,G05D

Abstract:
1. The method for preventing an aircraft from penetrating into a dangerous trailing vortex area of a vortex generator where: information on the aircraft configuration, position, and orientation with respect to the inertial frame is received at the current time; information on the vortex generator position, geometrical and weight characteristics, as well as on the generator motion parameters with respect to the inertial frame is received at the current time; information on the vortex generator position and motion parameters in the inertial frame is saved; information on ambient parameters in the region of the aircraft and vortex generator collocation is received at the current time; the generator vortex trajectory in the form of the set of the generator vorticity region center trajectories in the inertial frame, as well as the generator vortex intensity are determined at the current time; information on the generator vortex trajectory points in the form of the set of the generator vorticity region center trajectories in the inertial frame, as well as on the generator vortex intensity is saved; the delay time within which the aircraft has a possibility of a flight evasive maneuver providing evasion of the aircraft from the generator vortex danger area after the signal warning against the possibility of wake encounter has been received is selected; the delay distance, which equals to the distance covered by the aircraft during the delay time is calculated, the control plane located in front of the aircraft perpendicular to its flight direction at the delay distance is modeled, and the forecasted time necessary for the aircraft to gain the control plane in the inertial frame is determined; the geometrical characteristics of the generator wake vortex danger areas in the form of the set of the danger areas of the generator vorticity regions are determined at the forecasted time; the generator wake vortex path in the form of the set of the generator vorticity region centers with respect to the inertial frame and the intensity of the wake vortices are determined at the forecasted time; the coordinates of the intersection point of the generator wake vortex trajectory and the above control plane are determined at the forecasted time of the aircraft flight through it; the wake vortex danger area in the form of the set of the generator vorticity danger areas, where the entering aircraft can have the flight parameters exceeding the admissible limits is formed around the above intersection point; the area of the aircraft forecasted positions at the forecasted time of the aircraft intersection with the above control plane is formed with due regard to the flight regulations is formed in the above control plane; the alert area is formed around the region of the aircraft forecasted positions; the information on the entrance of the wake danger areas into the alert area is provided to the user; the coordinates of the points of the area of the aircraft forecasted positions, of the alert area and of the wake vortex danger areas in the aircraft frame are determined; the distance from the alert area to the danger area of wake vortices in the control plane is calculated; the distance from the area of the aircraft forecasted positions to the danger area of wake vortices is calculated; indication for the user of the nulling of the distance from the warning area to the danger area of the generator wake vortices is performed; emergency indication for the user of the nulling of the distance from the area of the aircraft forecasted positions to the danger area of the generator wake vortices is performed.