Un-manned aerial vehicle having adjustable wing module, tail, and landing gear

A method of configuring an aircraft, the method comprising:

• positioning a payload within a fuselage module, the fuselage module comprising a first adjustable coupling disposed on an upper surface and a main landing gear coupled to the fuselage module;
• determining a desired distance between a center of gravity of the aircraft and an aerodynamic center of the aircraft;
• determining a first desired location of a wing module relative to the fuselage module so as to maintain the desired distance, the wing module comprising a second adjustable coupling disposed on a lower aspect thereof, wherein the first adjustable coupling and the second adjustable coupling are configured to selectively intermesh with each other and configured to adjust the wing module relative to the fuselage module at discrete step-wise intervals;
• selectively intermeshing the first adjustable coupling with the second adjustable coupling so as to connect the wing module to the fuselage module at the first desired location;
• decoupling the main landing gear from the fuselage module;
• recoupling the main landing gear to the fuselage module at a second desired location so as to maintain the desired distance;
• and
• connecting a tail module to the wing module.

A method of configuring an aircraft, the method comprising:

• selecting a desired location of a center of gravity of the aircraft and a desired distance between an aerodynamic center of the aircraft and the desired location of the center of gravity of the aircraft;
• positioning a payload within a fuselage module so as to maintain the desired location of the center of gravity of the aircraft, the fuselage module comprising a first adjustable coupling disposed on an upper surface thereof and a main landing gear coupled to the fuselage module;
• decoupling the main landing gear from the fuselage module;
• recoupling the main landing gear to the fuselage module at a first desired location so as to maintain the desired location of the center of gravity of the aircraft;
• determining a second desired location of a wing module relative to the fuselage module so as to maintain the desired location of the center of gravity of the aircraft and the desired distance between the location of the aerodynamic center of the aircraft and the desired location of the center of gravity of the aircraft, the wing module comprising a second adjustable coupling disposed on a lower aspect thereof, wherein the first adjustable coupling and the second adjustable coupling are configured to selectively intermesh with each other and configured to adjust the wing module relative to the fuselage module at discrete step-wise intervals;
• selectively intermeshing the first adjustable coupling with the second adjustable coupling so as to connect the wing module to the fuselage module at the second desired location;
• determining a third desired location of a tail module relative to the wing module so as to maintain the desired distance between the location of the aerodynamic center of the aircraft and the desired location of the center of gravity of the aircraft;
• and
• connecting the tail module to the wing module at the third desired location.