A compliant tail structure for a rotorcraft having rotating components and a fuselage. The tail structure includes a tail assembly having first and second oppositely disposed tail members. A tail joint connects the tail assembly to an aft portion of the fuselage. The tail joint includes at least four tail mounts configured to establish a nodding axis for the tail assembly. At least two of the tail mounts are resilient tail mounts that are configured to establish a nodding degree of freedom for the tail assembly relative to the fuselage about the nodding axis, thereby detuning dynamic fuselage responses from excitation frequencies generated by the rotating components.

An aircraft is equipped with a telescope built in the fuselage, with the initial angular mirror installed in the open part of the fuselage and the main mirror installed in the cylindrical part of the fuselage. The open part of the fuselage represents an open observation cavity with the base made of the bottom arc section of the fuselage rigidly connected with the nose of the aircraft. The main mirror is permanently fixed at the end of the cylindrical part of the fuselage at the tail. The initial angular mirror is rotary fixed to the nose. The axis of rotation of the initial angular mirror overlaps the longitudinal axis of the aircraft and the optical axis of the main mirror. The bottom arc section of the fuselage has a recess for observation of the earth, and the lifting surface is releasably fixed to the cylindrical part of the fuselage .

An aircraft is equipped with a telescope built in the fuselage, with the initial angular mirror installed in the open part of the fuselage and the main mirror installed in the cylindrical part of the fuselage. The open part of the fuselage represents an open observation cavity with the base made of the bottom arc section of the fuselage rigidly connected with the nose of the aircraft. The main mirror is permanently fixed at the end of the cylindrical part of the fuselage at the tail. The initial angular mirror is rotary fixed to the nose. The axis of rotation of the initial angular mirror overlaps the longitudinal axis of the aircraft and the optical axis of the main mirror. The bottom arc section of the fuselage has a recess for observation of the earth, and the lifting surface is releasably fixed to the cylindrical part of the fuselage .

A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).

An aerostructure assembly that includes an aerostructure (e.g., a resin pressure molded structure) and a coupling assembly is disclosed. The aerostructure includes an outer shell and a female receiver located within an interior of the outer shell. The coupling assembly includes a coupling and a beam that extends from this coupling. The beam is disposed within the female receiver, including where at least part of the coupling is positioned beyond an open end of the outer shell. The shape of the female receiver may retain the aerostructure to the beam in at least one direction/dimension. One or more fasteners may be utilized to attach the aerostructure to the beam. The coupling may be formed from one or more metals, and in any case, accommodates attachment of the aerostructure assembly to a flight vehicle.

Modular unmanned aerial vehicles (UAVs) are disclosed. A disclosed example UAV includes a fuselage that extends along a longitudinal axis, a wing support frame extending from the fuselage and along a wingspan of the UAV. The wing support frame includes distal ends to support a releasably couplable wing, the releasably couplable wing to extend along the wingspan when coupled to the wing support frame, and a motor boom that extends parallel to the longitudinal axis, the motor boom to support a motor that is oriented to generate lift for the UAV.

A modular unmanned aerial vehicle (UAV) connection system is disclosed. A disclosed example connection system for use with a UAV includes a tab extending from one of an aerodynamic body or a frame, and a slot to receive the tab, the slot positioned on another of the aerodynamic body or the frame, the tab to be inserted into the slot in a direction that is opposite to a direction of travel of the UAV.

A modular unmanned aerial vehicle (UAV) connection system is disclosed. A disclosed example connection system for use with a UAV includes a tab extending from one of an aerodynamic body or a frame, and a slot to receive the tab, the slot positioned on another of the aerodynamic body or the frame, the tab to be inserted into the slot in a direction that is opposite to a direction of travel of the UAV.

A wing assembly mount for mounting a wing to a fuselage of an aircraft. The wing assembly mount includes a spigot arrangement between a wing assembly and a fuselage assembly. The spigot arrangement is able to react a load between the wing assembly and the fuselage assembly.

A wing assembly mount for mounting a wing to a fuselage of an aircraft. The wing assembly mount includes a spigot arrangement between a wing assembly and a fuselage assembly. The spigot arrangement is able to react a load between the wing assembly and the fuselage assembly.