Mission-adaptable aerial vehicle and methods for in-field assembly and use
Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.
1. A method for facilitating in-field assembly of a mission-adaptable aerial vehicle, the method comprising:
providing a user interface via a software application on a mobile device associated with a a user, wherein the user interface includes a display screen presenting details of an aircraft a and a list of available sections and/or components associated with the aircraft of the mission-adaptable aerial vehicle;
receiving an input from the user interface associated with a selection of at least one or some of the available sections and/or components to include in an assembly of the mission-adaptable aerial vehicle;
producing one or more assembly protocols including instructions to assemble the mission-adaptable aerial vehicle for an in-field assembly procedure; and
generating, in real-time of the in-field assembly procedure, a modification scheme to cause a change in the instructions based on a determined change in one or more of flight dynamics, flight stability, or flight control of the mission-adaptable aerial vehicle.
2. The method of claim 1 , wherein the determined change includes one or more of: an environmental factor including a temperature, pressure, or weather forecast or measurement; a mission factor including a target location, a launch location, a trajectory parameter, or an altitude parameter; or a temporal factor including a time window of assembly or a time window of a mission.
3. The method of claim 1 , wherein the instructions include information on how the user modifies elements, including at least one of wing placement, a control surface sizing, a powerplant output or thrust, or one or more parameters to accommodate a change in a weight, a a fuselage length, an added or reduced drag, and/or a powerplant.
4. The method of claim 1 , wherein the user interface includes a touchscreen interface to allow the input to include one or more of a tap, a drag, or a dropdown.
5. The method of claim 1 , wherein the mission-adaptable aerial vehicle comprises:
a fuselage assembly comprising one or more fuselage sections;
a wing assembly attachable to the fuselage assembly, the wing assembly including one or more wing sections;
a nose cone assembly attachable to the fuselage assembly, the nose cone assembly including one or more nose cone sections;
a tail assembly attachable to the fuselage assembly, the tail assembly including one or more tail sections;
a propulsion unit at least partially contained in at least one of the tail assembly or the fuselage assembly and configured to drive flight of the mission-adaptable aerial vehicle; and
an electronics unit comprising a wireless transceiver device.
6. The method of claim 5 , wherein the generated modification scheme causes a change in the instructions to a number of fuselage sections for the fuselage assembly based on the determined change in one or more of the flight dynamics, the flight stability, or the flight control of the mission-adaptable aerial vehicle.
7. The method of claim 5 , wherein the generated modification scheme causes a change in the instructions to a number of wing sections for the wing assembly based on the determined change in one or more of the flight dynamics, the flight stability, or the flight control of the mission-adaptable aerial vehicle.
8. The method of claim 5 , wherein the generated modification scheme causes a change in the instructions to a number of tail sections for the tail assembly based on the determined change in one or more of the flight dynamics, the flight stability, or the flight control of the mission-adaptable aerial vehicle.
9. The method of claim 5 , wherein at least one fuselage section of the fuselage assembly and at least one tail section of the tail assembly each comprise a body portion having a curved wall and either (i) one or more protrusion structures integrally part of and spanning from the curved wall or (ii) one or more slots disposed in a portion of the curved wall, wherein the one or more protrusion structures is integrally formed of a same material structure as the curved wall of the at least one fuselage section or the at least one tail section, and wherein the portion having the one or more slots is formed of a same material structure of the curved wall as the other one of the at least one fuselage section or the at least one tail section.
10. The method of claim 9 , wherein one or both of (i) the one or more protrusion structures and (ii) the one or more slots includes one or more holes to align with corresponding one or more holes of the other of the of (i) the one or more protrusion structures or (ii) the one or more slots.
11. The method of claim 9 , wherein one or both of (i) the one or more protrusion structures and (ii) the one or more slots includes one or more projections to align with corresponding one or more holes of the other of the of (i) the one or more protrusion structures or (ii) the one or more slots.
12. The method of claim 1 , wherein the one or more assembly protocols include instructions to 3D-print the mission-adaptable aerial vehicle for the in-field assembly procedure.
13. The method of claim 1 , wherein the in-field assembly procedure allows for an in-the-field change to one or more components of the mission-adaptable aerial vehicle at a location where the mission-adaptable aerial vehicle is to take off.