Dynamic aircraft threat controller manager apparatuses, methods and systems
The present invention transforms flight profile information, terrain, weather/atmospheric data and flight parameter data via system components into comprehensive hazard avoidance optimized flight plans. Comprehensive hazard avoidance includes synergistic comprehensive turbulence and airfoil-specific icing data. In one implementation, the system comprises a processor and a memory disposed in communication with the processor and storing processor-issuable instructions to receive anticipated flight plan parameter data, obtain weather data based on the flight plan parameter data, obtain atmospheric data based on the flight plan parameter data, and determine a plurality of four-dimensional grid points based on the flight plan parameter data. The system may then determine comprehensive hazards mappings. With (near) real-time comprehensive hazard information and/or predictive turbulence/icing forecast specific to airfoil type and/or profile parameters, the system may allow aircraft to avoid areas where comprehensive hazard is greater than a predetermined threshold and/or avoid areas where turbulence/icing may occur.
1. An aircraft comprising:
an airfoil;
an icing component for determining existing icing accumulation on the airfoil; and
a dynamic airfoil icing flight planning system for determining a first icing forecast, the first icing forecast being associated with a first flight plan,
wherein determining the first icing forecast comprises:
receiving a first set of parameter data, the first set of parameter data being associated with the first flight plan;
obtaining a first set of atmospheric data, the first set of atmospheric data being associated with the first set of parameter data;
determining a first set of grid points, each grid point of the first set of grid points being a four-dimensional grid point associated with the first flight plan; and
determining a first set of icing data, the first set of icing data being associated with the first set of grid points and being determined based on an airfoil type of the airfoil.
2. The aircraft of claim 1 , further comprising a computation fluid dynamics component for determining anticipated percent power increase required by the aircraft based on the first icing forecast.
3. The aircraft of claim 2 , wherein the dynamic airfoil icing flight planning system is configured to determine a second icing forecast, the second icing forecast being associated with a first alternative flight plan,
wherein determining the second icing forecast comprises:
receiving a second set of parameter data, the second set of parameter data being associated with the first alternative flight plan;
obtaining a second set of atmospheric data, the second set of atmospheric data being associated with the second set of parameter data;
determining a second set of grid points, each grid point of the second set of grid points being a four-dimensional grid point associated with the first alternative flight plan; and
determining a second set of icing data, the second set of icing data being associated with the second set of grid points and being determined based on the airfoil type of the airfoil.
4. The aircraft of claim 3 , further comprising a first sensor, at least some of the data of the first set of parameter data being obtained from the first sensor.
5. The aircraft of claim 1 , further comprising a first sensor, at least some of the data of the first set of parameter data being obtained from the first sensor.
6. An aircraft control system comprising:
a means of determining a first flight plan of a first aircraft; and
a dynamic airfoil icing flight planning system for determining a first icing forecast, the first icing forecast being associated with the first flight plan of the first aircraft,
wherein determining the first icing forecast comprises:
receiving a first set of parameter data, the first set of parameter data being associated with the first flight plan of the first aircraft;
obtaining a first set of atmospheric data, the first set of atmospheric data being associated with the first set of parameter data;
determining a first set of grid points, each grid point of the first set of grid points being a four-dimensional grid point associated with the first flight plan of the first aircraft; and
determining a first set of icing data, the first set of icing data being associated with the first set of grid points and being determined based on an airfoil type of the first aircraft.
7. The aircraft control system of claim 5 , further comprising a computation fluid dynamics component for determining anticipated percent power increase required by the first aircraft based on the first icing forecast.
8. The aircraft of claim 5 , wherein the dynamic airfoil icing flight planning system is configured to determine a second icing forecast, the second icing forecast being associated with a first flight plan of a second aircraft,
wherein determining the second icing forecast comprises:
receiving a second set of parameter data, the second set of parameter data being associated with the first flight plan of the second aircraft;
obtaining a second set of atmospheric data, the second set of atmospheric data being associated with the second set of parameter data;
determining a second set of grid points, each grid point of the second set of grid points being a four-dimensional grid point associated with the first flight plan of the second aircraft; and
determining a second set of icing data, the second set of icing data being associated with the second set of grid points and being determined based on an airfoil type of the second aircraft.
9. The aircraft control system of claim 8 , wherein the first aircraft comprises a first sensor, at least some of the data of the first set of parameter data being obtained from the first sensor.
10. The aircraft control system of claim 9 , wherein the first aircraft comprises an icing component for determining existing icing accumulation on an airfoil of the aircraft.
11. The aircraft control system of claim 6 , wherein the first aircraft comprises an icing component for determining existing icing accumulation on an airfoil of the aircraft.
12. The aircraft of claim 1 , wherein three of the four dimensions of each grid point of the first set of grid points represents a point in three-dimensional space, and wherein the fourth dimension of each grid point of the first set of grid points represents a point in time.
13. The aircraft of claim 3 , wherein three of the four dimensions of each grid point of the second set of grid points represents a point in three-dimensional space, and wherein the fourth dimension of each grid point of the second set of grid points represents a point in time.
14. The aircraft control system of claim 6 , wherein three of the four dimensions of each grid point of the first set of grid points represents a point in three-dimensional space, and wherein the fourth dimension of each grid point of the first set of grid points represents a point in time.
15. The aircraft of claim 8 , wherein three of the four dimensions of each grid point of the second set of grid points represents a point in three-dimensional space, and wherein the fourth dimension of each grid point of the second set of grid points represents a point in time.