Hybrid rotary drone and method of use

A hybrid rotary aircraft includes a body having an inner area; a plurality of arms rigidly attached to and extending from the body; a plurality of rotor assemblies pivotally engaged with the plurality of arms; a first gas engine; and a first brushless electric generator rotatably attached to the first gas engine and conductively coupled to each of the brushless electric motors. The plurality of rotor assemblies each having a brushless electric motor; and a rotor blades rotatably attached to the brushless electric motor.

BACKGROUND

1. Field of the Invention

The present invention relates generally to rotary aircraft, and more specifically, to a hybrid drone and method of use.

2. Description of Related Art

Drones are well known in the art. For example,FIG. 1depicts an oblique view of a drone101having a body105with a plurality of rotary assemblies103secured thereto. One or more legs107extend from the lower portion of the body105and are configured to provide landing support. The batteries and control system (not shown) are disposed within body105and are configured to power and manipulate the rotor assemblies103.

One of the problems commonly associated with drone101is the weight of the batteries. Specifically, the drone is required to reduce the weight of the battery to provide adequate lift-to-weight ratio for flight. The limited battery size greatly reduces the hours of flight. It should be understood that as the size of the vehicle increases, the cost, volume, and weight of batteries become the limiting design challenge. The power density of typical batteries used in the multi-rotor electric aircraft is substantially less than that of convention gasoline or diesel.

Accordingly, although great strides have been made in the area of drones, many shortcomings remain.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

The system and method of use in accordance with the present application overcomes one or more of the above-discussed problems commonly associated with conventional rotary aircraft systems. Specifically, the present invention includes the feature of providing power to the rotary assemblies via a gas engine and a brushless electric generator. These and other unique features of the system and method of use are discussed below and illustrated in the accompanying drawings.

Referring now to the drawings wherein like reference characters identify corresponding or similar elements throughout the several views,FIGS. 2-5depict various views of a drone201in accordance with a preferred embodiment of the present application. It will be appreciated that drone201overcomes one or more of the above-listed problems commonly associated with conventional drones.

In the contemplated embodiment, drone201includes one or more of a body203with an inner area configured to carry a power assembly401therein. The body203is preferably contoured with a greater height at front surface205and gradually contours downwardly to a back surface. A plurality of arms209a,209b,209c, and209drigidly attach to body203in a fixed position and are adapted to carry respective rotor assemblies211a,211b,211c, and211dthat provide lift. Each rotor assembly includes brushless electric motors configured to rotate a rotor blade.

Referring specifically toFIG. 4, an oblique view of the power assembly401is shown having a gas tank403with air intake openings405,407in gaseous communication with respective exhaust ports of gas engines409,411. During use, the exhaust from the engines pass through an exhaust system217configured channel the gas to the rear back surface of the body. The gas engines409,411are rigidly attached to a frame and rotatably attached to respective brushless electric generators413,415configured to generate electrical power to power the 3-phrase brushless motors of the rotor assemblies. An electronic housing compartment417would be utilized to store the battery, the flight hardware, and the CPU. The on-board battery would be utilized to start the gas engine.

One of the unique features believed characteristic of the present invention is the reduced size of the battery pack. In lieu of providing electrical power to the motors via a battery, the present invention utilizes a gas engine to rotate and to produce power to the rotor assemblies via the generators. In the contemplated embodiment, the on-board battery only functions to start the engine and to power the electronics offline.

InFIG. 5, a simplified schematic501of the components of drone201are shown. The schematic501includes the electrical system511with an engine starter circuit500with an optional component package502.

In the exemplary embodiment, the gas engine505is in gaseous communication with a gas tank507and configured to rotate generator513, which in turn is conductively coupled to the brushless electric motor517via a rectifier515. The generator513is also conductively coupled to the battery509via an electronic speed control device504. Although shown with one generator, it should be understood that the system in contemplated utilizing redundant generators in the preferred embodiment.

A computer503is operably associated with the gas engine505, brushless electric generator513, the brushless electric motor517, and the other devices of drone201. The CPU503regulates the speed control506and speed control504via digital or analog control wires and is powered via the step down voltage device508and the battery509. An electronic speed control506is conductively coupled to the motor517and rectifier515. A plurality of rotors519are rotatably attached to motor517and are configured to provide lift. The CPU503is also in data communication with the flight hardware510and the engine throttle control512for manipulating engine power output. An optional package502is also contemplated and includes one or more lights514, payload516, and retractable landing gear518. These optional devices are controlled by computer503.

InFIG. 6, a simplified top view of an alternative embodiment of an aircraft601is shown. It should be appreciated that the features discussed herein can be interchanged between embodiments as necessary. In this embodiment, the aircraft601includes a body603with a plurality of arms605,607,609,611extending therefrom. The plurality of arms each include a wing613and a rotor assembly615. It should be appreciated that this configuration allows for the aircraft to fly via fixed wings and hover, takeoff, and land in the multi-rotor configuration. In some embodiments, the aircraft is further configured with an unmanned control system617thereby allowing for flight in a manned or unmanned fashion.

InFIG. 7, a schematic depicts an alternative power system in accordance with the present application. As shown, the system can include a gas tank701in fluid communication with one or more engines703coupled to a brushless generator705and a relay/switch707, all connected to a control circuit709. A BUS terminal711is coupled to one or more rectifiers713yet further coupled to one or more electric speed controls715, to one or more brushless electric motors717, to one or more propeller lifts719. This system is configured to rectify AC output to DC power. This system further includes an output voltage step down721which is electrically coupled to other components, such as a CPU723, flight hardware725, flight telemetry727, a battery729, lights731, sensors733, landing gear735, and a payload737.

InFIG. 8, another schematic depicts another alternative power system in accordance with the present application. As shown, the system can include a gas tank801in fluid communication with one or more engines803coupled to a brushless generator805and a relay/switch807, all connected to a control circuit809. In this embodiment, a BUS terminal811is coupled to one or more variable frequency drives813yet further coupled to one or more brushless electric motors817, to one or more propeller lifts819. In this embodiment, the one or more variable frequency drives are configured to receive AC power to control the one or more brushless electric motors. The system further includes a rectifier821coupled to an output voltage step down823which is electrically coupled to other components, such as a CPU825, flight hardware827, flight telemetry829, a battery831, lights833, sensors835, landing gear837, and a payload839.