Aircraft having a fault tolerant distributed propulsion system
In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.
1. An aircraft comprising:
a flying frame including an airframe;
a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies;
a flight control system operably associated with the distributed propulsion system; and
a pod assembly selectively attachable to the flying frame,
wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode;
wherein, the flight control system is operable to independently control the propulsion assemblies;
wherein, the flight control system is operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level;
wherein, responsive to a fault detected in a first propulsion assembly, the flight control system is configured to initiate a pod assembly jettison sequence; and
wherein, responsive to the pod assembly being jettisoned, the flight control system is configured to command the distributed propulsion system to land the aircraft proximate to the pod assembly.
2. The aircraft as recited in claim 1 wherein the flight control system further comprises a redundant flight control system.
3. The aircraft as recited in claim 1 wherein the flight control system further comprises a triply redundant flight control system.
4. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly.
5. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly and shuts down a second propulsion assembly.
6. The aircraft as recited in claim 5 wherein the second propulsion assembly is symmetrically disposed on the airframe relative to the first propulsion assembly.
7. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system adjusts collective pitch of at least a second propulsion assembly.
8. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system adjusts cyclic pitch of at least a second propulsion assembly.
9. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system adjusts rotor speed of at least a second propulsion assembly.
10. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system adjusts a thrust vector of at least a second propulsion assembly.
11. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system turns on at least a second propulsion assembly.
12. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system turns on a plurality of second propulsion assemblies.
13. The aircraft as recited in claim 1 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly, shuts down a symmetrically disposed second propulsion assembly and turns on a plurality of third propulsion assemblies.
14. An aircraft comprising:
a flying frame including an airframe;
a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies;
a flight control system operably associated with the distributed propulsion system; and
a pod assembly selectively attachable to the flying frame,
wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode;
wherein, the flight control system is operable to independently control the propulsion assemblies;
wherein, the flight control system is operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level;
wherein, responsive to a fault detected in a first propulsion assembly, the flight control system is configured to initiate a pod assembly jettison sequence; and
wherein, responsive to the pod assembly being jettisoned, the flight control system is configured to command the distributed propulsion system to perform an emergency landing remote from the pod assembly.
15. The aircraft as recited in claim 14 wherein the flight control system is selected from the group consisting of a redundant flight control system and a triply redundant flight control system.
16. The aircraft as recited in claim 14 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly.
17. The aircraft as recited in claim 14 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly and shuts down a second propulsion assembly.
18. The aircraft as recited in claim 14 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system adjusts at least one of a collective pitch of at least a second propulsion assembly, a cyclic pitch of at least the second propulsion assembly, a rotor speed of at least the second propulsion assembly or a thrust vector of at least the second propulsion assembly.
19. The aircraft as recited in claim 14 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system turns on at least a second propulsion assembly.
20. The aircraft as recited in claim 14 wherein, responsive to the fault detected in the first propulsion assembly, the flight control system shuts down the first propulsion assembly, shuts down a symmetrically disposed second propulsion assembly and turns on a plurality of third propulsion assemblies.