Multi-rotor aircraft and related systems and methods
An aircraft can include a frame and a plurality of electrical rotors coupled to the frame. The aircraft can further include a control system physically coupled to the frame and communicatively coupled with each of the plurality of electrical rotors. The control system can be configured to control a speed of each electrical rotor on an individual basis to control a direction of flight of the aircraft. The aircraft can further include an engine coupled to the frame, the engine being configured to combust a combustible fuel to generate thrust.
1. An aircraft comprising:
a frame;
a plurality of electrical rotors coupled to the frame;
a control system physically coupled to the frame and communicatively coupled with each of the plurality of electrical rotors, wherein the control system is configured to control a speed of each electrical rotor on an individual basis to control a direction of flight of the aircraft; and
an engine coupled to the frame, the engine being configured to combust a combustible fuel to generate:
thrust, and
electrical energy,
wherein the engine is pivotally coupled to the frame, and wherein the control system is configured to adjust an angle of the engine relative to the frame.
2. The aircraft of claim 1 , wherein each rotor is pivotally mounted to the frame and defines an axis of rotation, and wherein the control system is configured to adjust an angle of the axis of rotation of each rotor relative to the frame.
3. The aircraft of claim 1 , further comprising a plurality of wings coupled to the frame, wherein the control system is configured to rotate the wings relative to the frame.
4. The aircraft of claim 3 , wherein the plurality of wings comprise control surfaces, and wherein the control system is configured to control movement of the control surfaces.
5. The aircraft of claim 1 , further comprising a plurality of wings pivotally coupled to the frame, wherein the wings are free to rotate relative to the frame in response to airflow relative to the aircraft.
6. The aircraft of claim 1 , further comprising a plurality of wings coupled to a respective plurality of wing spars, and wherein each rotor is positioned on a respective one of the wing spars at a position that is distal to the wing that is coupled to that wing spar.
7. The aircraft of claim 1 , further comprising a fuel bladder physically coupled to the frame and fluidly coupled to the engine.
8. An aircraft comprising:
a frame;
a plurality of wings coupled to the frame;
a respective plurality of electrical rotors pivotally coupled to the frame at positions distal to the plurality of wings, each electrical rotor defining an axis of rotation that is adjustable relative to the frame;
a control system physically coupled to the frame and communicatively coupled with each of the plurality of electrical rotors; and
an engine coupled to the frame, the engine being configured to combust a combustible fuel to generate;
thrust, or
electrical energy,
wherein the engine is pivotally coupled to the frame, and wherein the control system is configured to adjust an angle of the engine relative to the frame.
9. The aircraft of claim 8 , wherein the control system is configured to control a speed of each electrical rotor on an individual basis to control a direction of flight of the aircraft.
10. The aircraft of claim 8 or 9 , wherein the control system is configured to adjust an angle of the axis of rotation of each rotor relative to the frame.
11. The aircraft of claim 8 or 10 , wherein the control system is configured to rotate the wings relative to the frame.
12. The aircraft of claim 11 , wherein the plurality of wings comprise control surfaces, and wherein the control system is configured to control movement of the control surfaces.
13. The aircraft of claim 8 or 10 , wherein the wings are free to rotate relative to the frame in response to airflow relative to the aircraft.
14. The aircraft of claim 8 or 10 , wherein the plurality of wings are coupled to a respective plurality of wing spars, and wherein each rotor is positioned on a respective one of the wing spars at a position that is distal to the wing that is coupled to that wing spar.
15. An aircraft comprising:
a frame;
a plurality of electrical rotors pivotally coupled to the frame;
a plurality of wings pivotally coupled to the frame, the plurality of wings being configured to rotate relative to the frame independently of the rotors; and
an engine coupled to the frame, the engine being configured to combust a combustible fuel to generate;
thrust, or
electrical energy; and
a control system physically coupled to the frame and communicatively coupled with each of the plurality of electrical rotors, each of the plurality of wings, and the engine to individually control angles of each electrical rotor, each wing, and the engine relative to the frame.
16. The aircraft of claim 15 , wherein the control system is configured to control a speed of each electrical rotor on an individual basis to control a direction of flight of the aircraft.
17. The aircraft of claim 15 , wherein the plurality of wings comprise control surfaces, and wherein the control system is configured to rotate the plurality of rotors, the plurality of wings, and the engine from a first orientation, in which the control system controls a speed of each electrical rotor on an individual basis to control flight of the aircraft, to a second orientation, in which the control system controls the control surfaces of the wings to control flight of the aircraft.