A vehicle can be configured to include a body having a body bottom conjoined with a body sidewall and a body top forming a body cavity. The body top includes a body top opening and the body sidewall includes a body sidewall opening. The vehicle can include a payload housing having a payload bottom conjoined with a payload housing sidewall and a payload housing top forming a payload housing cavity, wherein the payload housing cavity is configured to hold at least one operating module for the vehicle. The vehicle can include at least one arm. The vehicle can include at least one interlocking arrangement of the body top opening or body side wall configured to removably secure the payload housing and the at least one arm to the body. Each of the body, the payload housing, and the at least one arm can be structured with additive manufactured material.

An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

A rotary wing aircraft with a fuselage that comprises an upper primary skin and an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises a firewall arrangement that defines a fire proof separation at least between at least one aircraft engine and an aircraft interior region, wherein the firewall arrangement comprises at least one funnel-shaped lower firewall that is arranged between the at least one aircraft engine and the upper primary skin of the fuselage, wherein the at least one funnel-shaped lower firewall converges from an outer perimeter to at least one inner collecting point, and wherein the outer perimeter is spaced apart from the upper primary skin of the fuselage.

A rotary wing aircraft with a fuselage that comprises an upper primary skin and an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises a firewall arrangement that defines a fire proof separation at least between at least one aircraft engine and an aircraft interior region, wherein the firewall arrangement comprises at least one funnel-shaped lower firewall that is arranged between the at least one aircraft engine and the upper primary skin of the fuselage, wherein the at least one funnel-shaped lower firewall converges from an outer perimeter to at least one inner collecting point, and wherein the outer perimeter is spaced apart from the upper primary skin of the fuselage.

An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

An aircraft includes fuselage, a seat, and battery compartment. Fuselage extends along a longitudinal axis. Seat is configured to support a passenger. The battery compartment that includes a battery configured to provide power to propel the aircraft. The battery compartment, including the battery, is located laterally adjacent to the seat along the longitudinal axis.

An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.