A fuselage arranged within a fuselage outer shell; at least one main rotor located on top of the fuselage; at least one engine provided for driving the at least one main rotor; and at least one energy source storage unit comprising at least one energy source configured to provide energy for powering the at least one engine for driving the at least one main rotor; wherein the at least one energy source storage unit is arranged outside the fuselage outer shell; and wherein the fuselage and the fuselage outer shell form in vicinity of the at least one energy source storage unit a crashable structure configured to be crashable in an emergency landing at least for limiting effects of impact on the at least one energy source storage unit.

An aircraft including first and second elements spaced apart from one another and at least one device for absorbing energy by compression, positioned between the first and second elements, including at least one module for absorbing energy by compression and at least one attachment system removably connecting each module for absorbing energy by compression to at least one of the first and second elements, at least one module for absorbing energy by compression including several first conduits oriented in a compression direction and being independent of the first and second elements.

Proposed is a structure. The structure includes a front body frame configured to surround a front surface of an airframe, a crash unit disposed at a front end of the body front frame, and a dash reinforcement assembly fastened to the front body frame and disposed on the rear surface of the crash unit.

An aircraft fuselage section extending along a longitudinal direction including: a fuselage structure comprising a plurality of frames; a floor connected to the fuselage structure; a cushioning element arranged on the floor, and a crash absorption assembly between the fuselage structure and the floor, wherein the crash absorption assembly includes first absorption elements and second absorption elements distributed along the longitudinal direction, wherein the first absorption elements and the second absorption elements are configured to dissipate and distribute energy; and wherein the first absorption elements are each arranged at a position corresponding to a frame of the fuselage structure and the second absorption elements are each arranged at a position between successive frames of the fuselage structure.

A collision load distribution structure of a fuselage includes a front unit configured to be located at front ends relative to wings attached to the fuselage, a rear unit configured to be located at rear ends relative to the wings attached to the fuselage, a support unit configured to be located between the front unit and the rear unit, and a wing unit. The support unit is configured to transfer loads applied to the fuselage in case of a crash of the fuselage. The wing unit is configured to be located in the support unit, and connected to the support unit so as to transfer the loads in case of the crash of the fuselage. Loads in a length direction of the fuselage are passed through to the front unit, and are distributed to the wing unit through the support unit.

The present disclosure provides a battery load support structure of a fuselage, the battery load support structure including a battery mount support formed in a longitudinal direction of a floor frame of the fuselage, a battery unit inputted into an opened lower side of the floor frame and fastened to the battery mount support, and a joint unit configured to support the battery mount support and connected to a plurality of framework members that constitutes the floor frame.

Proposed is a collision load distribution structure of a fuselage, wherein the structure includes a support unit positioned between a front unit and a rear unit of the fuselage and configured to allow a collision load of the fuselage to be transferred by being connected to the front unit and the rear unit, a wing unit positioned at the inside of the support unit and connected to the support unit to transfer the collision load of the fuselage, and a seat unit coupled to a connection frame mounted in a second-row passenger space of a floor frame constituting the front unit and fastened to a first rear frame extending in a height direction from the floor frame toward the support unit.

A detachable battery structure of a fuselage including a floor unit positioned on a fuselage, a battery unit fastened to the floor unit and configured to receive a load in the event of a frontal collision of the fuselage, a battery unit extension fastened to a window frame of the fuselage and configured to transmit the load to the battery unit in the event of the frontal collision of the fuselage, a crash unit positioned in front of the window frame, and a dash reinforcement assembly fastened to the window frame and positioned on a rear surface of the crash unit, wherein the dash reinforcement assembly moves backward in the event of the frontal collision of the fuselage so that the battery unit extension moves in a longitudinal direction, and the battery unit is configured to move backward to be detached from the floor unit.