Weight-shifting coaxial helicopter

1. An unmanned helicopter comprising:

a propulsion system comprising:

a first rotor assembly comprising a first motor coupled to a first rotor, the first rotor comprising a plurality of first fixed-pitch blades; and

a second rotor assembly comprising a second motor coupled to a second rotor, the second rotor comprising a plurality of second fixed-pitch blades, the second rotor being coaxial to the first rotor, the second rotor configured to be counter-rotating to the first rotor;

a fuselage comprising:

a power source; and

a controller; and

a housing for securing a gimbal assembly, the gimbal assembly comprising:

a first gimbal motor configured to control pitch of the unmanned helicopter; and

a second gimbal motor configured to control roll of the unmanned helicopter;

wherein:

the housing comprises a first portion and a second portion, the first portion being coupled to the propulsion system and the second portion being coupled to the fuselage; and

the housing separates the first gimbal motor from the second gimbal motor;

wherein the controller is communicably coupled to the first and second gimbal motors and is configured to provide instructions to the first and second gimbal motors in order to weight-shift the fuselage of the unmanned helicopter, thereby controlling pitch and roll movements of the unmanned helicopter.

2. The unmanned helicopter of claim 1 , wherein the fuselage comprises a tubular body formed from a plurality of separable modular components arranged in a stacked assembly.

3. The unmanned helicopter of claim 2 , wherein one of the plurality of separable modular components comprises:

a payload module; or

a landing module configured to support the unmanned helicopter in a generally vertical orientation.

4. The unmanned helicopter of claim 3 , wherein the payload module comprises a camera system.

5. The unmanned helicopter of claim 1 , wherein each of the plurality of first and second fixed-pitch blades is coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot into a position parallel to the fuselage.

6. The unmanned helicopter of claim 5 , wherein centrifugal force is used to pivot the plurality of first and second fixed-pitch blades into a position that is perpendicular to the fuselage.

7. The unmanned helicopter of claim 1 , wherein the first rotor assembly is coupled to the gimbal assembly using a fixed, non-rotating shaft that passes through the second motor assembly.

8. The unmanned helicopter of claim 1 , wherein the unmanned helicopter further comprises a wing, the wing coupled to an exterior portion of the fuselage, the wing configured to increase the unmanned helicopter's speed of travel or flight duration.

9. The unmanned helicopter of claim 3 , wherein the landing module comprises one of:

a self-balancing module comprising an elastic polymeric base;

a magnetic base module comprising one of a material that produces a magnetic field or material that is attracted to a magnetic field, the magnetic base module configured to couple to a surface comprising one of a material that produces a magnetic field or material that is attracted to a magnetic field;

a grapple module comprising a clasp, the clasp configured to enclose around a cable, thereby allowing the unmanned helicopter to hang in suspension from the cable;

a spike module comprising an elongated piece of material terminating in a point, the spike module configured to pierce through a landing surface;

a float module configured to have buoyant properties, thereby allowing the unmanned helicopter to float upon contact with a liquid surface;

a cup holder module configured to couple with a landing container, the container having a funnel shape;

a folding legs module comprising at least two landing legs, the landing legs configured to pivot from a position that is parallel to the fuselage to a position that stabilizes the unmanned helicopter in an upright position;

a vacuum module comprising a deformable material having a concave shape, the vacuum module configured to couple to a surface using the force of air pressure; or

a self-balancing wheel module comprising one or more wheels.

10. The unmanned helicopter of claim 1 , wherein the amount of first fixed-pitch blades is different than the amount of second fixed-pitch blades.

11. The unmanned helicopter of claim 1 , wherein the angle of the first fixed-pitch blades is different than the angle of the second fixed-pitch blades.

12. A helicopter comprising:

a propulsion system comprising:

a first rotor assembly comprising a first motor coupled to a first rotor; and

a second rotor assembly comprising a second motor coupled to a second rotor, the second rotor being coaxial to the first rotor, the second rotor configured to be counter-rotating to the first rotor;

a housing for securing a gimbal assembly and for coupling a fuselage of the helicopter to the propulsion system, wherein:

the housing comprises a first portion and a second portion;

the first portion is coupled to the second rotor assembly and the second portion is coupled to the fuselage;

the housing separates the first gimbal motor form the second gimbal motor; and

a controller communicably coupled to the gimbal assembly and configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

13. The helicopter of claim 12 , wherein the first rotor assembly is coupled to the gimbal assembly using a fixed, non-rotating shaft that passes through the second motor assembly.

14. The helicopter of claim 12 , wherein the first rotor assembly further comprises a plurality of first fixed-pitch blades and the second rotor assembly further comprises a plurality of second fixed-pitch blades, the plurality of first and second fixed-pitch blades being coupled to a hub of its respective rotor via a hinge mechanism configured to allow each of the fixed-pitch blades to pivot.

15. A helicopter comprising:

a gimbal assembly;

a first rotor assembly mechanically coupled to the gimbal assembly, the first rotor assembly comprising a first rotor;

a second rotor assembly mechanically coupled to the gimbal assembly, the second rotor assembly comprising a second rotor configured to be counter-rotating to the first rotor;

a fuselage mechanically coupled to the gimbal assembly by a housing; and

a controller configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter; wherein:

the housing comprises a first portion and a second portion, the first portion being coupled to the second rotor assembly and the second portion being coupled to the fuselage; and

the housing separates the first gimbal motor from the second gimbal motor.

16. The helicopter of claim 15 , wherein the first rotor assembly is coupled to the gimbal assembly using a fixed, non-rotating shaft that passes through the second motor assembly.

17. The helicopter of claim 15 , wherein the helicopter further comprises a wing, the wing coupled to an exterior portion of the fuselage, the wing configured to increase the helicopter's speed of travel or flight duration.

18. The helicopter of claim 15 , wherein the first rotor assembly further comprises a plurality of first fixed-pitch blades and the second rotor assembly further comprises a plurality of second fixed-pitch blades, the amount of first fixed-pitch blades being different than the amount of second fixed-pitch blades.

19. The helicopter of claim 15 , wherein the fuselage comprises a tubular body formed from a plurality of separable modular components arranged in a stacked assembly, the plurality of separable modular components comprising:

a payload module; or

a landing module configured to support the helicopter in a generally vertical orientation.

20. The helicopter of claim 19 , wherein the landing module comprises one of:

a self-balancing module comprising an elastic polymeric base;

a magnetic base module comprising one of a material that produces a magnetic field or material that is attracted to a magnetic field, the magnetic base module configured to couple to a surface comprising one of a material that produces a magnetic field or material that is attracted to a magnetic field;

a grapple module comprising a clasp, the clasp configured to enclose around a cable, thereby allowing the helicopter to hang in suspension from the cable;

a spike module comprising an elongated piece of material terminating in a point, the spike module configured to pierce through a landing surface;

a float module configured to have buoyant properties, thereby allowing the helicopter to float upon contact with a liquid surface;

a cup holder module configured to couple with a landing container, the container having a funnel shape;

a folding legs module comprising at least two landing legs, the landing legs configured to pivot from a position that is parallel to the fuselage to a position that stabilizes the helicopter in an upright position;

a vacuum module comprising a deformable material having a concave shape, the vacuum module configured to couple to a surface using the force of air pressure; or

a self-balancing wheel module comprising one or more wheels.