Tiltrotor propulsion system for an aircraft
An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a port forward propulsor and a starboard forward propulsor, each of which rotatable between a forward thrust position and a vertical thrust position and together defining a maximum forward thrust capability. The propulsion system also includes a port aft propulsor and a starboard aft propulsor, each of which also rotatable between a forward thrust position and a vertical thrust position, and together defining a maximum aft thrust capability. The maximum forward thrust capability is different than the maximum aft thrust capability to achieve certain efficiencies.
1. An aircraft comprising:
a fuselage extending between a forward end and an aft end;
a forward wing assembly attached to or formed integrally with the fuselage proximate the forward end of the fuselage;
an aft wing assembly attached to or formed integrally with the fuselage proximate the aft end of the fuselage; and
a propulsion system comprising
a port forward propulsor and a starboard forward propulsor, the port and starboard forward propulsors each attached to the forward wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position, the port and starboard forward propulsors together defining a maximum forward thrust capability; and
a port aft propulsor and a starboard aft propulsor, the port and starboard aft propulsors each attached to the aft wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position, the port and starboard aft propulsors together defining a maximum aft thrust capability, the maximum forward thrust capability being different than the maximum aft thrust capability, and wherein the maximum forward thrust capability is greater than the maximum aft thrust capability.
2. The aircraft of claim 1 , wherein the port and starboard aft propulsors each include a fan having a plurality of fan blades, wherein the plurality of fan blades are moveable to a stowed position when the port and starboard aft propulsors are rotated to the forward thrust position.
3. The aircraft of claim 1 , wherein the port and starboard forward propulsors each define a fan diameter, wherein the port and starboard aft propulsors each define a fan diameter, and wherein the fan diameter of the port and starboard aft propulsors is different than the fan diameter of the port and starboard forward propulsors.
4. The aircraft of claim 1 , wherein the aircraft defines a minimum necessary takeoff thrust, and wherein the maximum forward thrust capability in combination with the maximum aft thrust capability is greater than or equal to the minimum necessary takeoff thrust of the aircraft.
5. The aircraft of claim 1 , wherein the port and starboard forward propulsors are configured as electric fans, and wherein the port and starboard aft propulsors are also configured as electric fans.
6. The aircraft of claim 5 , wherein the propulsion system further comprises an electric power source located remotely from the port and starboard forward propulsors and from the port and starboard aft propulsors, wherein the electric power source is in electric communication with the port and starboard forward propulsors and the port and starboard aft propulsors.
7. The aircraft of claim 6 , wherein the electric power source powers the port and starboard forward propulsors and the port and starboard aft propulsors.
8. The aircraft of claim 6 , wherein the electric power source comprises a combustion engine and an electric generator, wherein the combustion engine powers the electric generator.
9. A propulsion system for an aircraft, the aircraft including a forward wing assembly and an aft wing assembly, the forward and aft wing assemblies each attached to or formed integrally with the fuselage, the propulsion system comprising:
a port forward propulsor and a starboard forward propulsor, the port and starboard forward propulsors each configured for attachment to the forward wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position, the port and starboard forward propulsors together defining a maximum forward thrust capability; and
a port aft propulsor and a starboard aft propulsor, the port and starboard aft propulsors each configured for attachment to the aft wing assembly on opposing sides of the fuselage and rotatable between a forward thrust position and a vertical thrust position, the port and starboard aft propulsors together defining a maximum aft thrust capability, the maximum forward thrust capability being different than the maximum aft thrust capability, and wherein the maximum forward thrust capability is greater than the maximum aft thrust capability.
10. The propulsion system of claim 9 , wherein the port and starboard aft propulsors each include a fan having a plurality of fan blades, wherein the plurality of fan blades are moveable to a stowed position when the port and starboard aft propulsors are rotated to the forward thrust position.
11. The propulsion system of claim 9 , wherein the port and starboard forward propulsors each define a fan diameter, wherein the port and starboard aft propulsors each define a fan diameter, and wherein the fan diameter of the port and starboard aft propulsors is different than the fan diameter of the port and starboard forward propulsors.
12. The propulsion system of claim 9 , wherein the aircraft defines a minimum necessary takeoff thrust, and wherein the maximum forward thrust capability in combination with the maximum aft thrust capability is greater than or equal to the minimum necessary takeoff thrust of the aircraft.
13. The propulsion system of claim 9 , wherein the port and starboard forward propulsors are configured as electric fans, and wherein the port and starboard aft propulsors are also configured as electric fans.
14. The propulsion system of claim 13 , wherein the propulsion system further comprises an electric power source located remotely from the port and starboard forward propulsors and from the port and starboard aft propulsors, wherein the electric power source powers the port and starboard forward propulsors and the port and starboard aft propulsors.