An aircraft having a fuselage extending in a longitudinal direction from a nose to a tail, a nose wheel located at the nose, a tail support located at the tail, and a main wheel assembly located between the nose wheel and the tail support in the longitudinal direction. The main wheel assembly is positioned such that the aircraft is operable to selectively land in a first operating mode in which the main wheel assembly and the nose wheel support both the aircraft during the landing process, and the tail support does not support the aircraft during the landing process, and a second operating mode in which the main wheel assembly and the tail support both support the aircraft during the landing process. A method for operating the aircraft, an aircraft with a movable wheel assembly, and a movable wheel assembly are also provided.

An aircraft having a fuselage extending in a longitudinal direction from a nose to a tail, a nose wheel located at the nose, a tail support located at the tail, and a main wheel assembly located between the nose wheel and the tail support in the longitudinal direction. The main wheel assembly is positioned such that the aircraft is operable to selectively land in a first operating mode in which the main wheel assembly and the nose wheel support both the aircraft during the landing process, and the tail support does not support the aircraft during the landing process, and a second operating mode in which the main wheel assembly and the tail support both support the aircraft during the landing process. A method for operating the aircraft, an aircraft with a movable wheel assembly, and a movable wheel assembly are also provided.

An aircraft having a fuselage extending in a longitudinal direction from a nose to a tail, and a main wheel assembly having a first main wheel spaced in a transverse direction from a second main wheel, the transverse direction being perpendicular to the longitudinal direction. One or more pivots connect the main wheel assembly to the fuselage. The one or more pivots have a rotation axis extending in the transverse direction such that the main wheel assembly is pivotable relative to the fuselage between a first fixed position with the first main wheel and the second main wheel in a first longitudinal position behind a center of gravity of the aircraft, and a second fixed position with the first main wheel and the second main wheel in a second longitudinal position behind the center of gravity of the aircraft. One or more extendable struts are operatively connected between the main wheel assembly and fuselage, and operable to move the main wheel assembly between the first fixed position and the second fixed position.

An aircraft having a fuselage extending in a longitudinal direction from a nose to a tail, and a main wheel assembly having a first main wheel spaced in a transverse direction from a second main wheel, the transverse direction being perpendicular to the longitudinal direction. One or more pivots connect the main wheel assembly to the fuselage. The one or more pivots have a rotation axis extending in the transverse direction such that the main wheel assembly is pivotable relative to the fuselage between a first fixed position with the first main wheel and the second main wheel in a first longitudinal position behind a center of gravity of the aircraft, and a second fixed position with the first main wheel and the second main wheel in a second longitudinal position behind the center of gravity of the aircraft. One or more extendable struts are operatively connected between the main wheel assembly and fuselage, and operable to move the main wheel assembly between the first fixed position and the second fixed position.

Various implementations directed to composite skid member with varying cross-sections are provided. In one implementation, an aircraft landing gear assembly may include two composite skid members configured to contact the ground, where each composite skid member includes a first cross-section and a second cross-section, and where the first cross-section is different than the second cross-section. The aircraft landing gear assembly may also include two cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two composite skid members.

Various implementations directed to composite skid member with varying cross-sections are provided. In one implementation, an aircraft landing gear assembly may include two composite skid members configured to contact the ground, where each composite skid member includes a first cross-section and a second cross-section, and where the first cross-section is different than the second cross-section. The aircraft landing gear assembly may also include two cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two composite skid members.

Various implementations directed to composite skid members are provided. In one implementation, an aircraft landing gear assembly may include two skid members configured to contact the ground, where each skid member includes composite material manufactured using a pultrusion process. The aircraft landing gear assembly may also include a plurality of cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two skid members.

Various implementations directed to composite skid members are provided. In one implementation, an aircraft landing gear assembly may include two skid members configured to contact the ground, where each skid member includes composite material manufactured using a pultrusion process. The aircraft landing gear assembly may also include a plurality of cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two skid members.

A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.

A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.