Automated configuration of mission specific aircraft
Systems and methods for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. A method includes receiving mission parameters including flight parameters and payload parameters; configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations; determining thrust requirements based upon the mission parameters; configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting inboard propulsion assemblies operable for coupling to the inboard nacelle stations of the first and second wings and selecting outboard propulsion assemblies operable for coupling to the outboard nacelle stations of the first and second wings.
1. A method for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the method comprising:
receiving mission parameters including flight parameters and payload parameters;
configuring an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations;
determining thrust requirements based upon the mission parameters; and
configuring a two-dimensional distributed thrust array based upon the thrust requirements including selecting a plurality of inboard propulsion assemblies having a first thrust type operable for coupling to the first and second inboard nacelle stations of the first and second wings and selecting a plurality of outboard propulsion assemblies having a second thrust type operable for coupling to the first and second outboard nacelle stations of the first and second wings, the first thrust type being different from the second thrust type.
2. The method as recited in claim 1 wherein receiving mission parameters including flight parameters and payload parameters further comprises receiving mission flight speed parameters.
3. The method as recited in claim 1 wherein receiving mission parameters including flight parameters and payload parameters further comprises receiving mission endurance parameters.
4. The method as recited in claim 1 wherein receiving mission parameters including flight parameters and payload parameters further comprises receiving payload weight parameters.
5. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting outboard propulsion assemblies that are thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
6. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting outboard propulsion assemblies that are unidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
7. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting outboard propulsion assemblies that are omnidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
8. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting outboard propulsion assemblies that are omnidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies that are unidirectional thrust vectoring propulsion assemblies.
9. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting inboard propulsion assemblies that are longitudinal thrust vectoring propulsion assemblies and outboard propulsion assemblies that are lateral thrust vectoring propulsion assemblies.
10. The method as recited in claim 1 wherein configuring the two-dimensional distributed thrust array based upon the thrust requirements further comprises selecting outboard propulsion assemblies that are longitudinal thrust vectoring propulsion assemblies and inboard propulsion assemblies that are lateral thrust vectoring propulsion assemblies.
11. A system for automated configuration of mission specific aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the system comprising:
an aircraft configuration computing system having logic stored within a non-transitory computer readable medium, the logic executable by a processor, wherein the computing system is configured to:
receive mission parameters including flight parameters and payload parameters;
configure an airframe based upon the mission parameters including selecting a flight control system, first and second wings and first and second pylons operable for coupling between the first and second wings, the first and second wings each having first and second inboard nacelle stations and first and second outboard nacelle stations;
determine thrust requirements based upon the mission parameters; and
configure a two-dimensional distributed thrust array based upon the thrust requirements including selecting a plurality of inboard propulsion assemblies having a first thrust type operable for coupling to the first and second inboard nacelle stations of the first and second wings and selecting a plurality of outboard propulsion assemblies having a second thrust type operable for coupling to the first and second outboard nacelle stations of the first and second wings, the first thrust type being different from the second thrust type.
12. The system as recited in claim 11 wherein the computing system is configured to receive mission flight speed parameters.
13. The system as recited in claim 11 wherein the computing system is configured to receive mission flight endurance parameters.
14. The system as recited in claim 11 wherein the computing system is configured to receive payload weight parameters.
15. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select outboard propulsion assemblies that are thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
16. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select outboard propulsion assemblies that are unidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
17. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select outboard propulsion assemblies that are omnidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies are non thrust vectoring propulsion assemblies.
18. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select outboard propulsion assemblies that are omnidirectional thrust vectoring propulsion assemblies and inboard propulsion assemblies that are unidirectional thrust vectoring propulsion assemblies.
19. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select inboard propulsion assemblies that are longitudinal thrust vectoring propulsion assemblies and outboard propulsion assemblies that are lateral thrust vectoring propulsion assemblies.
20. The system as recited in claim 11 wherein, based upon the thrust requirements, the computing system is configured to select outboard propulsion assemblies that are longitudinal thrust vectoring propulsion assemblies and inboard propulsion assemblies that are lateral thrust vectoring propulsion assemblies.