Patent ID: 8000848
Filing Date: 2011-08-16
Classification: G01C,G01S,G05D,G08G

Abstract:
1. An integrated system for aircraft vortex safety, comprising: an informational subsystem of an aircraft parameters capable of receiving, saving and providing the user with information on the aircraft configuration, position, flight velocity, and attitude; an informational subsystem of vortex generators capable of receiving, saving and providing the user with information from different available sources on vortex generator configuration, position, flight velocity, and attitude for all vortex generators located in the aircraft vicinity; an informational subsystem of ambient parameters capable of receiving, saving and providing the user with information on ambient conditions in the aircraft vicinity at current and forecasted time moments; a subsystem warning the user against a risk of the aircraft encounter with vortex generator wake vortices at the forecasted time; a user subsystem capable of receiving, saving and providing the user with information from other subsystems and forming an instructive signal for the aircraft evasion maneuver ensuring aircraft evasion from a vortex generator danger areas during a chosen danger criterion by the user delay time after the user receives the warning signal about a risk of the aircraft encounter with vortex generator wake vortices at the forecasted time; a communication subsystem ensuring integration of the subsystems into a united complex, and said informational subsystem of the aircraft parameters ensures receipt, processing, saving, and transmitting information to the warning subsystem at least on the aircraft configuration, coordinates and attitude in the inertial frame, on the aircraft velocity and angular rate components in the aircraft frame; said informational subsystem of vortex generators ensures receipt, processing, saving, and transmitting information to the user at least on the vortex generator types, coordinates and attitude, velocity and angular rate components in the inertial frame; said informational subsystem of ambient parameters ensures receipt, processing, saving, and transmitting information to the user at least on a wind velocity components in the inertial frame at different attitudes in the region of the wake vortex presence, as well as on an ambient turbulence; said warning subsystem informing the user on a possibility of the aircraft encountering with the vortex generator danger areas performs at least calculation of the vortex generator wake vortex position, and intensity, and danger areas, the area of the aircraft forecasted positions at the forecasted time and directs to the user subsystem information on a possibility of the aircraft encountering with the vortex generator wake vortex danger areas at the forecasted time; and said user subsystem receives, processes, saves and indicates the information from the warning subsystem at least on a nulling of the distance from the area of the aircraft forecasted positions to the vortex generator wake vortex danger area at the forecasted time and forms a signal indicating the change of the aircraft position providing the increase of the above mentioned distance; wherein said warning subsystem informing the user on the possibility of the aircraft encountering with the vortex generator wake vortex danger areas at the forecasted time includes a system comprising: an aircraft parameters tracker capable of receiving information on the aircraft configuration, position, coordinates, and attitude in the inertial frame at the current time; a vortex generator tracker capable of receiving information on the vortex generator position, geometrical and weight characteristics, as well as on the motion parameters in the inertial frame at the current time; a memory unit capable of saving information on the vortex generator position and motion parameters in the inertial frame; an ambient parameters detector capable of receiving information on the environmental parameters in the space of the collocation of the aircraft and vortex generator at the current time; a wake vortex tracker capable of determining the vortex generator wake vortices in the form of a set of the voracity center paths in the inertial frame; a memory device capable of storing information on the vortex generator wake vortex path point coordinates in the form of the set of the vorticity region centers and wake vortex intensity in the inertial frame; a device for selection of a delay time capable of calculating the time period within which the aircraft has at least a possibility of a flight evasive maneuver providing evasion of the aircraft from the generator wake danger area after the signal warning against the possibility of wake encounter has been received; a device for simulation of a control plane capable of calculating the delay distance, which equals to the distance covered by the aircraft during the delay time, modeling the control plane situated in front of the aircraft perpendicular to its flight direction at the delay distance, and determining the forecasted time necessary for the aircraft to gain the control plane in the inertial frame; a device for determination of the danger area parameters capable of determining 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 at the forecasted time; a forecasting device capable of determining the generator wake path in the form of the set of the generator vorticity region centers with respect to the inertial frame and of the intensity of the generator wake vortices at the forecasted time; a device for calculation of the intersection points capable of determining the coordinates of the intersection points of a generator wake vortex trajectory and the control plane at the forecasted time of the aircraft flight through it; an areas and regions forming device capable of forming around the intersection point of the wake vortex path and the control plane of the wake vortex danger area in the form of a set of the generator voracity danger areas, where the entering aircraft may have a flight parameter exceeding the admissible limits, forming in the control plane of the area of the aircraft forecasted positions at the forecasted time of the aircraft intersection with the control plane with due regard to flight regulations, forming around the region of the aircraft forecasted positions of an alert area, the information on the entrance of the wake danger areas into the warning area will be provided to the user; a transformation unit capable of calculating the coordinates of the area of the aircraft forecasted positions, of the warning area and of the wake vortex danger area in the aircraft frame; a first intersection conditional test unit capable of calculating the distance from the alert area to the wake vortex danger area and marking its nulling; a second intersection conditional test unit capable of calculating the distance from the area of the aircraft forecasted positions to the wake vortex danger area and marking its nulling; a first indication unit capable of forming and transmitting the nulling signal for the distance from the area of the aircraft forecasted positions to the vortex generator wake vortex danger area; and a second indication unit capable of indicating the nulling of the distance from the warning area to the to the vortex generator wake vortex danger area.