Hybrid electric aircraft propulsion system

Abstract

An aircraft comprising a hybrid electric aircraft propulsion system. The system comprises a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location. The system also comprises a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.

1 . An aircraft comprising a hybrid electric propulsion system, the system comprising:
 a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location; and   a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.   
     
     
         2 . The aircraft of  claim 1 , wherein the first location and the third location are adjacent, and the second location and the fourth location are adjacent. 
     
     
         3 . The aircraft of  claim 1 , wherein the first location and the fourth location are adjacent, and the second location and the third location are adjacent. 
     
     
         4 . The aircraft of  claim 1 , wherein the first sub-assembly is mounted cross-wing to the aircraft, and the second sub-assembly is mounted cross-wing to the aircraft. 
     
     
         5 . The aircraft of  claim 1 , wherein:
 the first electric propulsor assembly comprises a first electric motor, a third rotating structure coupled to the first electric motor, and a first motor inverter coupled between a direct current (DC) power source and the first electric motor; and   the second electric propulsor assembly comprises a second electric motor, a fourth rotating structure coupled to the second electric motor, and a second motor inverter coupled between the DC power source and the second electric motor.   
     
     
         6 . The aircraft of  claim 5 , wherein:
 the first electric propulsor assembly further comprises a third electric motor and a fifth rotating structure coupled to the third electric motor; and   the second electric propulsor assembly further comprises a fourth electric motor and a sixth rotating structure coupled to the fourth electric motor.   
     
     
         7 . The aircraft of  claim 6 , wherein:
 the first electric propulsor assembly further comprises a third motor inverter coupled to the third electric motor; and   the second electric propulsor assembly further comprises a fourth motor inverter coupled to the fourth electric motor.   
     
     
         8 . A method for controlling yaw of an aircraft, the method comprising:
 operating an aircraft having a hybrid electric propulsion system;   detecting a fault to a first sub-assembly of the hybrid electric propulsion system, the first sub-assembly having a first electric propulsor assembly attached to the aircraft at a first location and a first thermal propulsor assembly attached to the aircraft at a second location;   in response to detecting the fault:
 shutting down the first electric propulsor assembly and the first thermal propulsor assembly; 
 operating the aircraft with a second sub-assembly of the hybrid electric propulsion system, the second sub-assembly having a second electric propulsor assembly attached to the aircraft at a third location and a second thermal propulsor assembly attached to the aircraft at a fourth location; and 
 controlling yaw of the aircraft with the second electric propulsor assembly and the second thermal propulsor assembly. 
   
     
     
         9 . The method of  claim 8 , wherein the first location and the third location are adjacent, and the second location and the fourth location are adjacent. 
     
     
         10 . The method of  claim 8 , wherein the first location and the fourth location are adjacent, and the second location and the third location are adjacent. 
     
     
         11 . The method of  claim 8 , wherein the first sub-assembly is mounted cross-wing to the aircraft, and the second sub-assembly is mounted cross-wing to the aircraft. 
     
     
         12 . The method of  claim 8 , wherein the first thermal propulsor assembly comprises a first thermal engine, a first generator and a first rotating propulsor, and wherein the second thermal propulsor assembly comprises a second thermal engine, a second generator and a second rotating propulsor. 
     
     
         13 . The method of  claim 12 , wherein:
 the first electric propulsor assembly comprises a first electric motor, a third rotating structure coupled to the first electric motor, and a first motor inverter coupled between a direct current (DC) power source and the first electric motor; and   the second electric propulsor assembly comprises a second electric motor, a fourth rotating structure coupled to the second electric motor, and a second motor inverter coupled between the DC power source and the second electric motor.   
     
     
         14 . A hybrid electric aircraft propulsion system comprising:
 a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attachable to an aircraft at a first location and the first thermal propulsor assembly attachable to the aircraft at a second location; and   a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attachable to the aircraft at a third location and the second thermal propulsor assembly attachable to the aircraft at a fourth location.   
     
     
         15 . The system of  claim 14 , wherein:
 the first electric propulsor assembly comprises a first electric motor, a third rotating structure coupled to the first electric motor, and a first motor inverter coupled between a direct current (DC) power source and the first electric motor; and   the second electric propulsor assembly comprises a second electric motor, a fourth rotating structure coupled to the second electric motor, and a second motor inverter coupled between the DC power source and the second electric motor.   
     
     
         16 . The system of  claim 15 , wherein:
 the first electric propulsor assembly further comprises a third electric motor and a fifth rotating structure coupled to the third electric motor; and   the second electric propulsor assembly further comprises a fourth electric motor and a sixth rotating structure coupled to the fourth electric motor.   
     
     
         17 . The system of  claim 16 , wherein:
 the first electric propulsor assembly further comprises a third motor inverter coupled to the third electric motor; and   the second electric propulsor assembly further comprises a fourth motor inverter coupled to the fourth electric motor.   
     
     
         18 . The system of  claim 17 , wherein:
 the first motor inverter is selectively connected to the first electric motor and the third electric motor, and the third motor inverter is selectively connected to the first electric motor and the third electric motor; and   the second motor inverter is selectively connected to the second electric motor and the fourth electric motor, and the fourth motor inverter is selectively connected to the second electric motor and the fourth electric motor.   
     
     
         19 . The system of  claim 17 , wherein:
 the first generator comprises a first generator stator connected to the first electric motor and a second generator stator connected to the third electric motor; and   the second generator comprises a third generator stator connected to the second electric motor and a fourth generator stator connected to the fourth electric motor.   
     
     
         20 . The system of  claim 19 , wherein:
 the first electric motor comprises a first motor stator connected to the first generator stator and a second motor stator connected to the first motor inverter;   the second electric motor comprises a third motor stator connected to the third generator stator and a fourth motor stator connected to the second motor inverter;   the third electric motor comprises a fifth motor stator connected to the second generator stator and a sixth motor stator connected to the third motor inverter; and   the fourth electric motor comprises a seventh motor stator connected to the fourth generator stator and an eighth motor stator connected to the fourth motor inverter.