An aircraft, comprising: a fuselage; counter-rotating and co-axially disposed and vertically stacked first and second rotor hubs (12, 13) coupled to the fuselage, wherein each rotor hub (12, 13) comprises a driven portion (12A, 13A) coupled to a driven blade (14A, 16A) and a non-driven portion (12B, 13B) coupled to at least one non-driven blade (14B, 16B), wherein the driven portions (12A, 13A) are driven in rotation by direct coupling to a driveshaft (50, 64) of their respective rotor hub (12, 13), and wherein the non-driven blades (14B, 16B) are configured for free rotation until entrained in rotation by the driven portions (12A, 13A), the vertically-stacked first and second rotor hubs being configured to extend vertically in relation to the fuselage to enable the driven blades and the non-driven blades to selectively assume a deployed configuration in which they are configured to provide lift for the aircraft, the vertically-stacked first and second rotor hubs being further configured to retract vertically in relation to the fuselage to enable the driven blades and the non-driven blades to selectively assume a stowed configuration in which the driven blades and the non-driven blades at least partially overlap each other and do not provide substantial lift for the aircraft; and at least one wing coupled to the fuselage, configured to provide lift for the aircraft at least when the vertically-stacked first and second rotor hubs are vertically retracted and the driven blades and non-driven blades are in the stowed configuration, wherein the driven and non-driven blades are selectively configured to assume, at least during sustained flight of the aircraft, the deployed configuration and the stowed configuration and wherein each of the at least one wing is foldable around a swivel, wherein each rotor hub (12, 13) has an associated upper: swashplate coupled to the driven portion (12A, 13A) and to the non-driven portion (12B, 13B) and configured to selectively assume deployed and stowed configurations and to cause the driven and non-driven blades to change their pitch, and wherein each upper swashplate comprises a first portion coupled to the driven portion (12A, 13A) and a second portion coupled to the non-driven portion(12B, 13B). a fuselage; counter-rotating and co-axially disposed and vertically stacked first and second rotor hubs (12, 13) coupled to the fuselage, wherein each rotor hub (12, 13) comprises a driven portion (12A, 13A) coupled to a driven blade (14A, 16A) and a non-driven portion (12B, 13B) coupled to at least one non-driven blade (14B, 16B), wherein the driven portions (12A, 13A) are driven in rotation by direct coupling to a driveshaft (50, 64) of their respective rotor hub (12, 13), and wherein the non-driven blades (14B, 16B) are configured for free rotation until entrained in rotation by the driven portions (12A, 13A), the vertically-stacked first and second rotor hubs being configured to extend vertically in relation to the fuselage to enable the driven blades and the non-driven blades to selectively assume a deployed configuration in which they are configured to provide lift for the aircraft, the vertically-stacked first and second rotor hubs being further configured to retract vertically in relation to the fuselage to enable the driven blades and the non-driven blades to selectively assume a stowed configuration in which the driven blades and the non-driven blades at least partially overlap each other and do not provide substantial lift for the aircraft; and at least one wing coupled to the fuselage, configured to provide lift for the aircraft at least when the vertically-stacked first and second rotor hubs are vertically retracted and the driven blades and non-driven blades are in the stowed configuration, wherein the driven and non-driven blades are selectively configured to assume, at least during sustained flight of the aircraft, the deployed configuration and the stowed configuration and wherein each of the at least one wing is foldable around a swivel, wherein each rotor hub (12, 13) has an associated upper: swashplate coupled to the driven portion (12A, 13A) and to the non-driven portion (12B, 13B) and configured to selectively assume deployed and stowed configurations and to cause the driven and non-driven blades to change their pitch, and wherein each upper swashplate comprises a first portion coupled to the driven portion (12A, 13A) and a second portion coupled to the non-driven portion(12B, 13B).