Aircraft propulsion assembly
In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.
1. A propulsion assembly for an aircraft comprising:
a nacelle;
at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel;
an engine disposed within the nacelle operable to run on the liquid fuel;
a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine;
a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system;
a proprotor mechanically coupled to the rotor hub and operable to rotate therewith; and
a thrust vectoring system including a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis and wherein the engine, the drive system, the rotor hub and the proprotor are mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.
2. The propulsion assembly as recited in claim 1 wherein the engine further comprises a rotary engine.
3. The propulsion assembly as recited in claim 1 wherein the drive system provides a reduction between revolutions of the engine and revolutions of the rotor hub.
4. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of proprotor blades.
5. The propulsion assembly as recited in claim 1 wherein the proprotor further comprises a plurality of folding proprotor blades.
6. The propulsion assembly as recited in claim 1 wherein the thrust vector has a maximum pitch angle of about twenty degrees.
7. The propulsion assembly as recited in claim 1 further comprising an electronics node operable to control operations of the propulsion assembly.
8. The propulsion assembly as recited in claim 7 wherein the electronics node further comprises controllers operable to send commands to the engine.
9. The propulsion assembly as recited in claim 7 wherein the electronics node further comprises sensors operable to monitor parameters associated with the at least one self-contained fuel tank, the engine and the drive system.
10. An aircraft, comprising:
an airframe;
a distributed propulsion system including a plurality of propulsion assembles securably attached to the airframe, the propulsion assembles each comprising:
a nacelle;
at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel;
an engine disposed within the nacelle operable to run on the liquid fuel;
a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine;
a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system;
a proprotor mechanically coupled to the rotor hub and operable to rotate therewith; and
a thrust vectoring system including a pivoting plate, a rotary actuator operable to rotate the pivoting plate about a propulsion assembly centerline axis and a linear actuator operable to pivot the pivoting plate about a pivot axis that is normal to the propulsion assembly centerline axis and wherein the engine, the drive system, the rotor hub and the proprotor are mounted on the pivoting plate such that operation of the pivoting plate enables resolution of a thrust vector within a thrust vector cone.
11. The aircraft as recited in claim 10 wherein the thrust vector has a maximum pitch angle of about twenty degrees.
12. The aircraft as recited in claim 10 wherein each of the propulsion assemblies further comprises an electronics node including controllers operable to send commands to the engine and sensors operable to monitor parameters associated with the at least one self-contained fuel tank, the engine and the drive system.
13. The aircraft as recited in claim 10 wherein, for each propulsion assembly, the engine further comprises a rotary engine.
14. The aircraft as recited in claim 10 wherein, for each propulsion assembly, the drive system provides a reduction between revolutions of the engine and revolutions of the rotor hub.
15. The aircraft as recited in claim 10 wherein, for each propulsion assembly, the proprotor further comprises a plurality of proprotor blades.
16. The aircraft as recited in claim 10 wherein, for each propulsion assembly, the proprotor further comprises a plurality of folding proprotor blades.