Multi-rotor rotorcraft

1. A multi-rotor rotorcraft, comprising:

a fuselage;

at least four rotor assemblies operatively supported by and spaced-around the fuselage, wherein each of the at least four rotor assemblies defines a spin volume and a spin diameter; and

at least one rotor guard that is fixed relative to the fuselage, that borders the spin volume of at least one of the at least four rotor assemblies, and that is configured to provide a visual indication of the spin volume of the at least one of the at least four rotor assemblies, wherein the at least one rotor guard comprises at least one combined rotor guard that at least partially borders the spin volume of more than one of the at least four rotor assemblies;

wherein the fuselage comprises an internal compartment and an access door having a door-width that provides selective access to the internal compartment;

wherein the at least four rotor assemblies comprise a first pair of rotor assemblies positioned on opposing sides of the access door; and

wherein a spacing between the spin volumes of the first pair of rotor assemblies is at least 100% of the door-width.

2. The multi-rotor rotorcraft of claim 1 ,

wherein the at least four rotor assemblies comprises six rotor assemblies; and

wherein the at least one combined rotor guard comprises two combined rotor guards, each bordering the spin volume of three of the six rotor assemblies.

3. The multi-rotor rotorcraft of claim 2 ,

wherein the six rotor assemblies comprise:

the first pair of rotor assemblies;

a second pair of rotor assemblies positioned on opposing lateral sides of the fuselage; and

a third pair of rotor assemblies positioned on the opposing lateral sides of the fuselage between the first pair and the second pair; and

wherein each of the two combined rotor guards borders more than 50% of circumferential perimeters of the spin volumes of respective rotor assemblies of the first pair and the second pair and less than 50% of a circumferential perimeter of the spin volume of the third pair.

4. The multi-rotor rotorcraft of claim 1 , wherein each of the at least one combined rotor guard borders at least 50% of a circumferential perimeter of the spin volume of an adjacent corresponding rotor assembly.

5. The multi-rotor rotorcraft of claim 1 , wherein a combined rotor guard of the at least one combined rotor guard borders a greater portion of a circumferential perimeter of an adjacent spin volume than of a circumferential perimeter of another adjacent spin volume.

6. The multi-rotor rotorcraft of claim 1 , wherein a combined rotor guard of the at least one combined rotor guard borders more than 50% of a circumferential perimeter of one adjacent spin volume and borders less than 50% of a circumferential perimeter of another adjacent spin volume.

7. The multi-rotor rotorcraft of claim 1 , wherein the at least one combined rotor guard comprises at least one segment that is non-parallel to a plane that is perpendicular to a spin axis of an adjacent one of the at least four rotor assemblies.

8. A multi-rotor rotorcraft, comprising:

a fuselage; and

at least four rotor assemblies operatively supported by and spaced-around the fuselage, wherein each of the at least four rotor assemblies defines a spin volume and a spin diameter;

wherein the fuselage comprises an internal compartment and an access door having a door- width that provides selective access to the internal compartment;

wherein the at least four rotor assemblies comprise a first pair of rotor assemblies positioned on opposing sides of the access door;

wherein a spacing between the spin volumes of the first pair of rotor assemblies is at least 100% of the door-width;

wherein the multi-rotor rotorcraft further comprises a first pair of elongate support arms, each interconnecting a respective one of the first pair of rotor assemblies to the fuselage;

wherein each elongate support arm of the first pair of elongate support arms extends along a respective curved path between the fuselage and the respective one of the first pair of rotor assemblies; and

wherein, when viewed from above, each respective curved path is concave away from the fuselage.

9. The multi-rotor rotorcraft of claim 8 , wherein the internal compartment is configured for transportation of at least one human passenger, and wherein the access door is sized for entry and exit of the at least one human passenger to and from the internal compartment.

10. The multi-rotor rotorcraft of claim 8 ,

wherein the at least four rotor assemblies further comprise a second pair of rotor assemblies positioned on opposing lateral sides of the fuselage;

wherein the multi-rotor rotorcraft further comprises a second pair of elongate support arms, each interconnecting a respective one of the second pair of rotor assemblies to the fuselage; and

wherein each elongate support arm of the second pair of elongate support arms extends along a respective curved path between the fuselage and the respective one of the second pair of rotor assemblies.

11. The multi-rotor rotorcraft of claim 10 , wherein, when viewed from above, each respective curved path is concave away from the fuselage.

12. The multi-rotor rotorcraft of claim 8 , further comprising a pair of aerodynamic structures extending from opposing lateral sides of the fuselage, wherein at least one rotor assembly of the at least four rotor assemblies is supported by each of the pair of aerodynamic structures.

13. The multi-rotor rotorcraft of claim 12 ,

wherein the at least four rotor assemblies further comprise:

a second pair of rotor assemblies positioned on the opposing lateral sides of the fuselage; and

a third pair of rotor assemblies positioned on the opposing lateral sides of the fuselage; and

wherein each of the third pair of rotor assemblies is supported by one of the pair of aerodynamic structures.

14. The multi-rotor rotorcraft of claim 13 , wherein the third pair of rotor assemblies is positioned between the first pair of rotor assemblies and the second pair of rotor assemblies.

15. The multi-rotor rotorcraft of claim 8 , wherein each rotor assembly of the at least four rotor assemblies comprises a pair of co-axial rotors.

16. A method of assembling the multi-rotor rotorcraft of claim 1 , the method comprising:

operatively coupling the at least four rotor assemblies to the fuselage; and

operatively mounting the at least one combined rotor guard that at least partially borders the spin volumes of more than one of the at least four rotor assemblies and that is fixed relative to the fuselage, wherein the at least one combined rotor guard is configured to provide visual indication of the spin volumes.

17. A method of enhancing operation of a multi-rotor vehicle, the method comprising:

utilizing at least two combined rotor guards, wherein each combined rotor guard borders spin volumes of more than one rotor assembly, wherein each combined rotor guard is fixed relative to a fuselage of the multi-rotor vehicle, and wherein the at least two combined rotor guards collectively border at least 50% of circumferential perimeters of spin volumes of all rotor assemblies of the multi-rotor vehicle;

wherein the fuselage comprises an internal compartment and an access door having a door-width that provides selective access to the internal compartment;

wherein the rotor assemblies comprise a first pair of rotor assemblies positioned on opposing sides of the access door; and

wherein a spacing between the spin volumes of the first pair of rotor assemblies is at least 100% of the door-width.

18. The method of claim 17 wherein the rotor assemblies are operatively supported by the fuselage, and wherein the internal compartment has a volume of at least 0.5 cubic meters for transporting cargo.

19. The multi-rotor rotorcraft of claim 8 , wherein the internal compartment is sized to selectively receive cargo, and wherein the access door is sized to permit loading and unloading of cargo into and from the internal compartment.

20. A multi-rotor rotorcraft, comprising:

a fuselage; and

at least four rotor assemblies operatively supported by and spaced-around the fuselage, wherein each of the at least four rotor assemblies defines a spin volume and a spin diameter;

wherein the fuselage comprises an internal compartment and an access door having a door-width that provides selective access to the internal compartment;

wherein the at least four rotor assemblies comprise a first pair of rotor assemblies positioned on opposing sides of the access door;

wherein the at least four rotor assemblies further comprise a second pair of rotor assemblies positioned on opposing lateral sides of the fuselage;

wherein the multi-rotor rotorcraft further comprises a second pair of elongate support arms, each interconnecting a respective one of the second pair of rotor assemblies to the fuselage;

wherein each elongate support arm of the second pair of elongate support arms extends along a respective curved path between the fuselage and the respective one of the second pair of rotor assemblies;

wherein the multi-rotor rotorcraft further comprises a first pair of elongate support arms, each interconnecting a respective one of the first pair of rotor assemblies to the fuselage; and

wherein each elongate support arm of the first pair of elongate support arms extends along a respective curved path between the fuselage and the respective one of the first pair of rotor assemblies.

21. A multi-rotor rotorcraft, comprising:

a fuselage;

at least four rotor assemblies operatively supported by and spaced-around the fuselage, wherein each of the at least four rotor assemblies defines a spin volume and a spin diameter; and

a pair of aerodynamic structures extending from opposing lateral sides of the fuselage, wherein at least one rotor assembly of the at least four rotor assemblies is supported by each of the pair of aerodynamic structures;

wherein the fuselage comprises an internal compartment and an access door having a door-width that provides selective access to the internal compartment;

wherein the at least four rotor assemblies comprise a first pair of rotor assemblies positioned on opposing sides of the access door;

wherein the at least four rotor assemblies further comprise:

a second pair of rotor assemblies positioned on the opposing lateral sides of the fuselage; and

a third pair of rotor assemblies positioned on the opposing lateral sides of the fuselage; and

wherein each of the third pair of rotor assemblies is supported by one of the pair of aerodynamic structures.