Helicopter with multi-rotors and wireless capability

• US 8,774,982 B2
• Filed: 10/06/2011
• Issued: 07/08/2014
• Est. Priority Date: 08/26/2010
• Status: Expired due to Fees

• Current Assignee: Geotech Environmental Equipment, Inc.
• Original Assignee: Leptron Industrial Robotic Helicopters, Inc.
• Inventors: Oakley, John Robert, Heath, David Scott
• Primary Examiner(s): Jabr, Fadey
• Assistant Examiner(s): Soofi, Yazan A
• Application Number:
  US13/200,986
• Publication Number:
  US 20120083945A1
• Time in Patent Office: 1,006 Days
• Field of Search: 701/2, 244/17.23
• US Class Current: 701/2
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/87 Mounting of imaging devices, e.g. mounting of gimbals
• CPC Class Codes: B64U 20/96 using air
• CPC Class Codes: B64U 2101/00 UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 2201/104 using satellite radio beacon positioning systems, e.g. GPS
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/293 Foldable or collapsible rotors or rotor supports
• CPC Class Codes: G05D 1/0038 by providing the operator with simple or augmented images from one or more cameras located onboard the vehicle, e.g. tele-operation images analyzed by a computer and used for automatic navigation G05D1/0246
• CPC Class Codes: G05D 1/0088 characterized by the autonomous decision making process, e.g. artificial intelligence, predefined behaviours using knowledge based models G06N5/00
• CPC Class Codes: G05D 1/0202 specially adapted to aircraft
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft
• CPC Class Codes: H04N 7/185 : from a mobile camera, e.g. for remote control

Abstract

The present invention relates to a helicopter having a modular airframe, with multiple layers which can be connected easily, the layers which house the electronics (autopilot and navigation systems), batteries, and payload (including camera system) of the helicopter. The helicopter has four, six, and eight rotors, which can be easily changed via removing one module of the airframe. In one embodiment, the airframe has a vertical stacked appearance, and in another embodiment, a domed shape (where several of the layers are stacked internally). In one embodiment, there is a combination landing gear and camera mount. The helicopter allows for simple flight and usage by remote control, and non-remote control, users.

Claims

1. A helicopter comprising:

a central airframe having a plurality of modular components stacked in a vertical manner on each other;

a component connecting mechanism which connects each of said modular vertical components to each other;

a plurality of rotor assemblies extending from a plurality of arms connected to one of said plurality of modular components of said airframe, said rotor assemblies each having a rotor thereon with a plurality of rotor blades, said rotors each being mounted horizontally on an end of each of said plurality of arms, an arm connecting system comprising a plurality of connect/disconnect mechanisms disposed in one of said plurality of vertical layers of modular components and which allow each of said plurality of arms to be connected and disconnected to said central airframe, such that said rotors may be interchanged in number, wherein said rotors are interchanged in number by changing the one of said plurality of vertical layers of modular components with another of said plurality of vertical layers of modular components having disposed therein a different number of the plurality of connect/disconnect mechanisms;

a plurality of landing gear extending from said airframe; and

an autopilot disposed within said airframe;

wherein said autopilot receives wireless instructions for helicopter control, from at least one of a first wireless communication transmitter/receiver disposed in the airframe of the helicopter, said first wireless communication transmitter/receiver that transmits and receives wireless instructions from a ground station unit, or a second wireless transmitter/receiver disposed in the helicopter, that transmits and receives wireless instructions from a hand-held remote control unit.

2. The helicopter of claim 1, wherein said modular vertical components are provided in a plurality of vertical layers, each of which is removed from said central airframe via said component connecting mechanism.

3. The helicopter of claim 1, further comprising:

a global positioning satellite (GPS) receiver disposed in said airframe and connected to said autopilot.

4. The helicopter of claim 3, wherein said GPS receiver is connected to GPS antennae that receive satellite data, which data is sent in real-time to said autopilot to identify a location of the helicopter in latitude, longitude, altitude, velocity, and in real-time.

5. The helicopter of claim 1, wherein said autopilot uses a plurality of controller connecting mechanisms to connect to separate speed controllers of a plurality of motors, to maneuver the helicopter in any of X, Y or Z directions

6. The helicopter of claim 1, further comprising:

a third wireless transmitter/receiver connected to said autopilot which sends separate instructions to said autopilot for helicopter control.

7. The helicopter of claim 1, further comprising:

an electrical system which controls each of said rotors, and which is an adjustable speed regulator for said rotors.

8. The helicopter of claim7, further comprising:

a plurality of batteries connected to said airframe by a battery connecting mechanism, said plurality of batteries which are controlled by said electrical system, such that said plurality of batteries are not overcharged or stop expending energy before said plurality of batteries are discharged.

9. The helicopter of claim 8, further comprising:

a daylight-readable LCD screen connected via electrical wiring to said electrical panel and to said autopilot, which displays a status of the helicopter and error codes to a user.

10. The helicopter of claim 9, further comprising:

a data card which operates with said electrical system, said LCD screen, and said autopilot, to store autopilot data from a predetermined number of helicopter flights.

11. The helicopter of claim 1, further comprising:

a magnetometer which is connected to said GPS receiver, and allows for input of directional information to said autopilot based upon magnetic compass readings by said magnetometer.

12. The helicopter of claim 8, wherein said battery connecting mechanism for said batteries includes a slide and lock mechanism for each battery.

13. The helicopter of claim 8, wherein said battery connecting mechanism for said batteries includes a single slide-lock battery unit, supported by a rail system on said airframe and on said battery unit.

14. The helicopter of claim 5, wherein said rotors are each connected by each of said plurality of arms to a separate speed controller.

15. The helicopter of claim 1 wherein each of the plurality of connect/disconnect mechanisms comprises an arm connection mechanism which allows each of said plurality of arms with attached rotor assemblies, to be folded parallel with one another in a vertical direction.

16. The helicopter of claim 15, further comprising:

one of a spring or piston for each of said plurality of arms, which allows each of said plurality of arms to open into a flight position after launch.

17. The helicopter of claim 16, further comprising:

a rotor guard that connects to each of said plurality of arms and extends beyond a reach of each of said plurality of rotor blades.

18. The helicopter of claim 17, wherein said landing gear comprises a plurality of tubes, said plurality of tubes which are attached to said central airframe by a landing gear connecting mechanism;

and

wherein said landing gear are folded parallel to one another for launch, and can be released by said landing gear connecting mechanism into a landing position after launch.

19. The helicopter of claim 18, wherein the helicopter carries a payload.

20. The helicopter of claim 19, wherein said payload is disposed in a bottom layer of said plurality of layers of said modular components, on a plate which creates a shelf for said payload.

21. The helicopter of claim 19, wherein said payload is a hanging payload mounted below the central airframe of the helicopter.

22. The helicopter of claim 20, wherein said plate is connected to side plates having a gear system that is connected to a servo that allows for 0-180 degree tilting of said payload.

23. The helicopter of claim 19, further comprising wherein said payload is a camera.

24. The helicopter of claim 23, wherein said camera is remote controlled.

25. The helicopter of claim 20, further comprising:

an automated recharge mechanism for said payload, supported in a full connection unit on said bottom layer.

26. The helicopter of claim 25, wherein said airframe is comprised of one of PVC plastic, carbon fiber, or injection-molded plastic and resin.

27. The helicopter of claim 1, wherein said modular vertical components are provided in a plurality of layers assembled together in a vertical, circular stacked arrangement, and said plurality of layers are covered by a dome-shaped cover that secures to a bottom layer of said plurality of layers.

28. The helicopter of claim 27, further comprising:

an air cooling system disposed in said central airframe;

wherein said central airframe includes a central core stacked shelf system, with electronics disposed in an outer ring configuration around a fan of said air cooling system.

29. The helicopter of claim 1, wherein said hand-held remote control unit further comprises:

a video receiver/transmitter disposed in a primary housing, and

a plurality of antennae on said primary housing, for receipt of a video transmission broadcast by the helicopter; and

an LCD screen on a front side of said hand-held remote control unit.

30. The helicopter of claim 29, further comprising:

a portable 12 volt battery pack and integrated wiring disposed in said primary housing.

31. The helicopter of claim 30, further comprising:

a plurality of joy sticks disposed on the front side of said hand-held remote control unit, on either side of said LCD screen, for operation of the helicopter and its payload.

32. The helicopter of claim 29, wherein said ground station unit includes a rechargeable battery.

33. The helicopter of claim 32, wherein said ground station unit includes a portable DVR for each RCA channel;

and an additional high gain antenna/patch panel for additional gain.

34. The helicopter of claim 33, wherein said ground station unit utilizes both a remote control (R/C) and/or wireless-connected computer configured with a wireless RS232 port.