Aircraft including a plurality of novel elements and a method of assembling and forming the same
A modular aircraft includes a plurality of structural elements. The structural elements include a pod module assembly, a wing assembly, and a chassis module. The pod module assembly is configured to be selectively attached to and detached from at least one of the chassis module and the wing module when the aircraft is not in flight. The pod module assembly is configured to transport at least one of a passenger and cargo.
1 . An aircraft including a plurality of structural elements, the structural elements comprising:
a chassis module configured with one or more longitudinal elements, wherein the one or more longitudinal elements are configured to maintain longitudinal orientation during vertical and horizontal flight;
one or more wings configured to attach to the chassis module;
a programmable controller including instructions for operating an adjustment system;
a pod module assembly being configured to be selectively attached to and detached from the chassis module and when attached to the chassis module said adjustment system executing recorded instructions for adjusting a center of gravity of the aircraft by moving said pod module along the one or more longitudinal elements of the chassis module;
wherein the pod module assembly is configured to transport at least one of a passenger and cargo;
wherein the pod module assembly is configured for operation as a vehicle when detached from the chassis module; and
wherein the chassis module is comprised of one or more mechanical stops along the at least one longitudinal element of the one or more longitudinal elements to lock the pod module assembly in place.
2 . The aircraft, as set forth in claim 1 , wherein operation as a vehicle includes attaching the pod module vehicle to at least one of a ground vehicle, a watercraft, and an aerial vehicle.
3 . The aircraft, as set forth in claim 1 , further comprising a controller in operative communication with the adjustment mechanism;
wherein the controller is configured to transmit a signal to the adjustment mechanism to vary the center of gravity of the aircraft.
4 . The aircraft of claim 1 , wherein the chassis module is configured with one or more tracks along the one or more longitudinal elements.
5 . The aircraft of claim 1 , wherein an energy module is translatable longitudinally along the chassis module to adjust the center of gravity of the aircraft.
6 . The aircraft of claim 1 , wherein the pod module assembly is comprised of a roll cage.
7 . The aircraft of claim 1 , wherein the pod module assembly is translatable longitudinally along the chassis module to adjust center of gravity of the aircraft.
8 . The aircraft of claim 1 , further comprised of a quick connect system, for connecting the pod module assembly to the chassis module.
9 . The aircraft of claim 8 , wherein the quick connect system is comprised of an electromagnetic connection.
10 . The aircraft of claim 8 , wherein the quick connect system is comprised of a mechanical connection.
11 . The aircraft of claim 1 , wherein at least one wing of the one or more wings attaches to the chassis module via a hinge assembly for transitioning between vertical and horizontal flight.
12 . The aircraft of claim 1 , wherein at least one wing of the one or more wings is rotatable.
13 . The aircraft of claim 12 , wherein at least one wing of the one or more wings rotates about a central transverse axis relative to the chassis module.
14 . The aircraft of claim 1 , wherein at least one wing of the one or more wings is configured to carry at least one battery module.
15 . The aircraft of claim 14 , wherein the at least one battery module is configured to move through a low friction interface within the at least one of the one or more wings.