Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.

An aircraft having a fuselage with one or more wings coupled to the fuselage. A pair of booms are attached to the one or more wings. Each boom has a front end coupled with a front propulsion system and a rear end coupled with a rear propulsion system. Each front propulsion system includes a front motor coupled with a foldable front propeller in a tractor configuration. Each rear propulsion system includes a rear motor coupled with a foldable rear propeller in a pusher configuration.

An aircraft having a fuselage with one or more wings coupled to the fuselage. A pair of booms are attached to the one or more wings. Each boom has a front end coupled with a front propulsion system and a rear end coupled with a rear propulsion system. Each front propulsion system includes a front motor coupled with a foldable front propeller in a tractor configuration. Each rear propulsion system includes a rear motor coupled with a foldable rear propeller in a pusher configuration.

A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

Disclosed here are systems for detachable airframe components including detachable nose cones, propeller assemblies and motors. In some example embodiments, the assemblies include a nose cone with a connection receiver, a motor assembly with a rotatable section, where the rotatable section includes torque arms configured to secure with the nose cone connection receiver, and a propeller assembly, configured to connect to the nose cone.

Disclosed here are systems for detachable airframe components including detachable nose cones, propeller assemblies and motors. In some example embodiments, the assemblies include a nose cone with a connection receiver, a motor assembly with a rotatable section, where the rotatable section includes torque arms configured to secure with the nose cone connection receiver, and a propeller assembly, configured to connect to the nose cone.

Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.

Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.

A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

A foldable propeller assembly for an aerial vehicle is disclosed herein. The foldable propeller assembly comprises a propeller blade arranged pivotably about a pivot axis and a first hub element arranged stationary relative to the pivot axis. The propeller blade or the first hub element comprises at least two openings provided about the pivot axis, each opening is configured for interlocking with a raised portion provided on the other one of the propeller blade and the first hub element. The at least two openings extend further about the pivot axis than the raised portion such that the propeller blade has limited play about the pivot axis when an opening is interlocking with the raised portion. A biasing element is arranged about the pivot axis and configured for biasing the propeller blade and the first hub element towards each other in an axial direction along the pivot axis.