Helicopter

• US 9,456,185 B2
• Filed: 08/26/2010
• Issued: 09/27/2016
• Est. Priority Date: 08/26/2009
• Status: Active Grant

• Current Assignee: Geotech Environmental Equipment, Inc.
• Original Assignee: Geotech Environmental Equipment, Inc.
• Inventors: Oakley, John Robert, Heath, David Scott
• Primary Examiner(s): Ellis, Christopher P
• Assistant Examiner(s): WONG, JESSICA BOWEN
• Application Number:
  US12/805,971
• Publication Number:
  US 20110301784A1
• Time in Patent Office: 2,224 Days
• Field of Search: 244/17.11, 244/17.19, 244/17.21, 244/17.25, 244/189, 244/190, 446/37, 701/3, 701/11
• US Class Current: 1/1
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/17 Helicopters flying platforms B64U10/13
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• 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 50/19 using electrically powered motors
• 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 1/0858 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 reduced scale industrial helicopter, with an integrated automatic flight control system, that includes core autopilot functions, GPS management, and full-function navigation systems. The autopilot technology includes rapid launch capability, real-time in-flight switching between one or more of a) remote control, b) autopilot-directed, c) ground station controlled, and d) home modes, and is upgradeable. The helicopter is used for high or low altitude surveillance, and can handle various payloads, including photographic missions. The helicopter may include onboard batteries and/or a unique battery unit disposed beneath the helicopter, and includes autonomous features such as automatic takeoff, automatic landing, safety return to home base, and predetermined mission plans.

Claims

1. A reduced scale helicopter comprising:

a chassis having two hinged side panels and a bottom panel;

a main rotor mounted on a rotor shaft disposed within said chassis;

a rotor head assembly mounted on said rotor shaft and including a plurality of main rotor blades;

a swash plate disposed on said rotor shaft, and connected to said rotor blades via a plurality of pushrods;

a plurality of control arms which connect said swash plate to said rotor shaft;

a plurality of connectors which connect said swash plate to an electrical panel which controls movements of the helicopter, said electrical panel being electrically connected to a plurality of indicators which show a user a flight status of the helicopter;

a tail rotor assembly comprising a removable, hollow tail boom removably secured to and extending rearward from said chassis, a tail rotor disposed on one end of the removable, hollow tail boom and mounted on a tail rotor shaft which is rotatably disposed within the removable, hollow tail boom, a tail motor for driving the tail rotor and which is mounted on the removable, hollow tail boom, a tail speed controller for the tail motor, and a tail gyrometer connected to the tail speed controller and having a quick release connection via quick release connector leads to a programming interface which is disposed on said chassis, the tail gyrometer being controlled using the programming interface;

a plurality of battery shelves disposed on each of said hinged side panels of said chassis;

a plurality of batteries disposed on each of said plurality of battery shelves;

a landing gear disposed under said bottom panel of said chassis; and

an autopilot disposed within and mounted to said chassis by a plurality of boards secured by vibration mounts, said autopilot being electrically connected to said electrical panel;

wherein said autopilot receives wireless instructions, for helicopter control.

2. The helicopter according to claim 1, further comprising:

a gear disposed on said rotor shaft and connected to a plurality of gears in a main motor, to spin said rotor shaft and said main rotor.

3. The helicopter according to claim 1, further comprising:

an auxiliary battery disposed at a tail portion proximate to said tail boom.

4. The helicopter according to claim 1, further comprising:

a plurality of connectors which connect said batteries to said electrical panel.

5. The helicopter according to claim 2, further comprising:

a main motor speed controller connected to said batteries, which conditions a power from said batteries and acts as an adjustable speed regulator for said main motor.

6. The helicopter according to claim 1, further comprising:

a magnetometer disposed on a supporting holder on said tail boom; and

a global positioning system (GPS) connected to said magnetometer;

wherein said GPS provides real-time positional information to said autopilot.

9. The helicopter according to claim 1, further comprising a payload connected to said chassis, wherein said payload is mounted at one of a front of the helicopter forward of said chassis, under said bottom panel of said chassis, or mounted hanging below the helicopter.

10. The helicopter according to claim 9, wherein said payload is mounted to the front of the helicopter and is a camera assembly.

11. The helicopter according to claim 10, wherein said camera assembly comprises:

two horizontal elements extended forward from and connected to the two hinged side panels, respectively, of the chassis;

a plate connecting the two horizontal elements for stabilization;

two vertical parallel plates extending downward from said two horizontal elements, and connected together by said plate; and

a camera, gimbal-mounted to said plate.

12. The helicopter according to claim 11, further comprising:

a wireless video transmitter, connected to said camera, which sends video and still photographs to one of a wireless transmitter/receiver at a ground station unit, or a wireless transmitter/receiver hand-held remote control unit.

13. The helicopter according to claim 11, wherein said camera is controlled by a wireless transmitter/receiver hand-held remote control unit.

14. The helicopter according to claim 1, wherein said plurality of boards comprises two horizontal boards located at a top and a bottom of a vertical board to which said electrical panel is mounted, said two horizontal boards being connected to said chassis by attachment mechanisms, said two horizontal boards and vibrations mounts which provide shock and vibration isolation in three axes, to said electrical panel.

15. The helicopter according to claim 6, wherein said autopilot is connected to said GPS, and receives satellite information that said autopilot uses to identify locations in latitude, longitude, altitude and velocity.

19. The helicopter according to claim 1, further comprising:

a payload connected to said chassis;

wherein said autopilot receives wireless instructions, for helicopter control, from at least one of a first wireless communication transmitter/receiver disposed on 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 on the helicopter, that transmits and receives wireless instructions from a hand-held remote control unit; and

wherein said hand-held remote control unit includes;

a plurality of antennae for receipt of a video transmission from said payload from said second wireless communication transmitter/receiver;

a wireless video receiver/transmitter disposed in a housing for receiving said video transmission from said payload from said second wireless communication transmitter/receiver;

an LCD screen which displays said video transmission;

a remote control assembly, including a plurality of joy sticks, for control of the helicopter and said payload; and

a battery assembly which powers said hand-held remote control unit.

20. The helicopter assembly according to claim 19, wherein said ground station unit comprises:

a plurality of antennae for receipt of a video transmission from said payload from said first wireless communication transmitter/receiver;

a wireless video receiver/transmitter disposed in a housing for receiving said video transmission from said payload from said first wireless communication transmitter/receiver;

an LCD screen which displays said video transmission;

a battery assembly which powers said ground station unit;

a portable DVR;

an antenna/patch panel; and

a computer having a processor and memory, which runs a software program specific to helicopter control.

21. The helicopter assembly according to claim 19, wherein said payload is a camera, and said video transmission includes photographs.

22. The helicopter assembly according to claim 19, further comprising:

a second wireless communication data link which transmits and receives flight instructions to and from the helicopter for operation of said payload.

23. The helicopter according to claim 1, wherein said chassis is made of carbon fiber.

28. The helicopter assembly according to claim 20, wherein said payload is a camera, and said video transmission includes photographs.

29. The helicopter assembly according to claim 20, further comprising:

a second wireless communication data link which transmits and receives flight instructions to and from the helicopter for operation of said payload.

30. The helicopter according to claim 1, further comprising:

a battery recharge unit disposed under said chassis of the helicopter.

31. The helicopter according to claim 1, wherein said vibration mounts comprise interchangeable vibration mounts, said interchangeable vibration mounts including mounts having different shock absorption rates to allow for low-high vibrations.

7. A reduced scale helicopter comprising:

a chassis;

a main rotor mounted on a rotor shaft disposed within said chassis;

a rotor head assembly mounted on said rotor shaft and including a plurality of main rotor blades;

a power source disposed on said chassis;

a landing gear disposed under said chassis; and

an autopilot disposed within and mounted to said chassis said autopilot being electrically connected to an electrical panel, and said autopilot receiving wireless instructions for helicopter control; and

a liquid crystal display (LCD) screen mounted in said chassis, and connected to said electrical panel and said autopilot, to display a status of the reduced scale helicopter to a user located externally of the reduced scale helicopter, wherein said LCD screen displays two or more of a plurality of error codes including a status of said autopilot, a status of satellite reception and grade of satellite reception from a global positioning system (GPS), a percentage of power used by said power source and remaining power available, an overall health of helicopter operating systems, revolutions per minute (RPM) of the main rotor, or a stability status of the reduced scale helicopter; and

a plurality of light-emitting diodes (LEDs) disposed next to said LCD screen and being electrically connected to said electrical panel, wherein at least one LED indicates to a user located externally of the reduced scale helicopter that an error has occurred, and wherein at least one other LED indicates to a user located externally of the reduced scale helicopter that all systems are operating properly and that the reduced scale helicopter is safe to fly.

8. The helicopter according to claim 7, further comprising:

a flight data card removably mounted in said chassis and connected to said electrical panel, said LCD screen, and said autopilot, which records data collected from each flight of the helicopter.

16. The helicopter according to claim 7, wherein said power source comprises a battery unit disposed under a bottom portion of said chassis and connected thereto.

17. The helicopter according to claim 16, further comprising:

a battery rail system disposed on a top of said battery unit;

a chassis rail system disposed under said bottom portion of said chassis, which corresponds to said battery rail system and slidingly engages therewith; and

a handle disposed at one end of said battery unit, which allows the user to slide said battery unit into a locking position and to pull and release said battery unit from said helicopter.

25. The helicopter according to claim 7, wherein said chassis is made of carbon fiber.

26. The helicopter according to claim 17, further comprising:

a keyed locking mechanism disposed on said battery unit for locking said battery unit to said chassis.

18. A reduced scale helicopter comprising:

a chassis;

a main rotor mounted on a rotor shaft disposed within said chassis;

a rotor head assembly mounted on said rotor shaft and including a plurality of main rotor blades;

a landing gear disposed under said bottom panel of said chassis;

an autopilot disposed within and mounted to said chassis, said autopilot being electrically connected to an electrical panel;

a slide lock battery unit disposed under a bottom portion of said chassis; and

a connecting mechanism for connecting said slide lock battery unit to said bottom portion of said chassis, wherein said connecting mechanism comprises;

a battery rail system disposed on a top of said slide lock battery unit;

a chassis rail system disposed under said bottom portion of said chassis and having terminals, which corresponds to said battery rail system and slidingly engages therewith; and

a handle disposed at one end of said slide lock battery unit, which allows the user to slide said slide lock battery unit into a locking position and to pull and release said slide lock battery unit from said helicopter, such that during mounting the slide lock battery unit is placed into the chassis rail system, and slid into place along the chassis rail system, until the slide lock battery unit connects with the terminals of the chassis rail system.

24. The helicopter according to claim 18, wherein said chassis is made of carbon fiber.

27. The helicopter according to claim 18, further comprising:

a keyed locking mechanism disposed on said slide lock battery unit for locking said slide lock battery unit to said chassis.