FUSELAGE SPINE WITH MODULAR SECTIONS AND AERO SHELL

1 . A system comprising:

a spine spanning from a tail portion to a nose portion of an aircraft, wherein the spine is configured to provide rigidity to the aircraft; and

one or more modules configured to be detachably attached to the spine, wherein the one or more modules are configured to be movable on the spine to obtain a desired center of gravity for the aircraft.

2 . The system of claim 1 , further comprising one or more spines spanning from the tail portion to the nose portion of the aircraft,

wherein the two or more spines are configured to be located at both sides of the aircraft.

3 . The system of claim 1 , wherein a position of each module of the one or more modules is configured to be movable on the spine to obtain a desired center of gravity for the aircraft.

4 . The system of claim 1 , further comprising: an active slid,

wherein the active slid is configured to receive a module arrangement instruction,

wherein the active slid is configured to automatically move each module of the one or more modules along the spine based on the received module arrangement instruction.

5 . The system of claim 4 , further comprising: a computing device including a processor,

wherein the processor is configured to receive weight information of each module of the one or more modules; and

wherein the processor is configured to generate the module arrangement instruction by calculating positions of the one or more modules to have a desired center of gravity for the aircraft based on the weight information.

6 . The system of claim 5 , wherein the one or more modules include the computing device.

7 . The system of claim 1 , wherein the one or more modules are configured to be detachably attached to the spine using at least one of: a sliding mechanism, an interlocking mechanism, screws, clamps, glue, and adhesive.

8 . The system of claim 1 , further comprising: a shell configured to cover the one or more modules,

wherein the shell is configured to provide access to the one or more modules disposed within the shell.

9 . The system of claim 8 , wherein the rigidity of the shell is less than the rigidity of the spine.

10 . The system of claim 8 , wherein the shell comprises a releasable closure mechanism, the releasable closure mechanism comprising:

an opening configured to be formed in a line shape along at least a portion of the shell; and

a closure configured to be formed along the opening, the closure configured to close the opening; and

wherein the releasable closure mechanism is configured to provide access to the one or more modules disposed within the shell.

11 . The system of claim 8 , wherein the releasable closure mechanism comprises at least one of: a zipper and a hook and loop fastener.

12 . The system of claim 11 , wherein the zipper is configured to be formed along a longitudinal direction of the shell.

13 . The system of claim 1 , wherein the nose portion of the aircraft is configured to receive a first end of the shell; and

wherein a rear portion of the aircraft is configured to receive a second end of the shell, wherein the first end is distal from the second end.

14 . The system of claim 1 , wherein positions of the one or more modules is configured to be adjusted based on different desired flight missions for the aircraft.

15 . The system of claim 1 , wherein the one or more modules include at least one of: a payload module, a power source module, a motor controller module, an avionics module, and a computing module.

16 . A method comprising:

determining one or more modules needed for a flight plan of an aircraft;

detachably attaching the one or more modules to a spine of the aircraft; and

adjusting positions of the one or more modules to obtain a desired center of gravity for the aircraft.

17 . The system of claim 16 , wherein adjusting the positions of the one or more modules comprises:

receiving, by a processor in communication with the one or more modules and an active slid, weight information of each module of the one or more modules;

generating, by the processor, a module arrangement instruction by calculating positions of the one or more modules to have the desired center of gravity based on the weight information;

receiving, by the active slid, the module arrangement instruction from the processor; and

automatically moving, by the active slid, each module of the one or more modules along the spine based on the received module arrangement instruction.

18 . The system of claim 17 , wherein adjusting positions of the one or more modules is configured to be performed for flight conditions, and

wherein adjusting positions of the one or more modules is configured to be performed while the aircraft is in operation.

19 . A method comprising:

securing at least one of: a power source and a payload to a spine of an aircraft;

positioning a shell over the at least one of: the power source and the payload; and

closing the shell to secure the shell between a nose portion and a rear portion of the aircraft.

20 . The method of claim 19 , wherein closing the shell is configured to be performed by closing a releasable closure mechanism, and

wherein the releasable closure mechanism comprises at least one of: a zipper and a hook and loop fastener.