TW201527171A - Hybrid six rotors helicopter - Google Patents

Abstract

Disclosed is a hybrid six rotors helicopter, comprising a body, a control unit, six rotors, a power carrying seat, a fuel engine, a battery, a differential mechanism, a first propeller, a second propeller and a plurality of landing chassis, wherein the body appears to be a hexagon; the control unit is disposed on the body to receive signals and possesses abilities of logical operation and electronic control; the rotors are disposed at respective corners of the body and electrically connected to the control unit; the fuel engine and the battery are disposed on the power carrying seat; the fuel engine outputs rotational power, and the battery provides electrical power as the necessary electrical power when the rotors are rotated; the differential mechanism is connected to the fuel engine and comprises a first output end and a second output end capable of outputting opposite rotations; the first and second propellers are respectively connected with the first and second output ends for performing opposite rotations; and the landing chassis is connected between the differential mechanism and the body, so as to provided better endurance and carrying capability.

Description

Oil-electric composite six-rotor aircraft

The invention relates to aircraft, and more particularly to an oil-electric composite six-rotor aircraft.

According to the differences in power sources, the current common remote-controlled multi-rotor aircraft can be divided into two types: pure fuel as the power source and pure power as the power source.

Among them, the multi-rotor aircraft with pure fuel as the power source, although it can generate a large amount of power, but the fuel consumption is extremely dramatic, it is a considerable burden for the user to spend on fuel.

However, the multi-rotor aircraft with pure electric power as the power source mainly supplies electric power from the carried battery (currently using lithium polymer (Li-Po) batteries as the mainstream). Due to the large number of brushless motors required for multi-rotor aircraft, Therefore, the power consumption of the power is also considerable. In the current use of a 3S5200mAh lithium polymer (Li-Po) battery, the multi-rotor aircraft can only fly for about 7 minutes, but has insufficient endurance and is quite power-consuming. The problem, and this power consumption situation also relatively limits its load capacity.

Therefore, how can we provide both the endurance and the gravity? It is an urgent problem for the relevant industry.

In view of the shortcomings derived from the above-mentioned conventional aircraft, the inventor of the present invention has improved and innovated, and after years of painstaking research, he finally successfully developed and completed the fuel-electric composite six-rotor aircraft.

It is an object of the present invention to provide an oil-electric composite six-rotor aircraft that has better endurance.

A second object of the present invention is to provide an oil-electric composite six-rotor aircraft that has a large load capacity.

The oil-electric composite six-rotor aircraft capable of achieving the above object includes: a fuselage having a hexagonal shape; a control unit disposed on the body for receiving signals and having logic operation and electronic control capability; a six-rotor, Each is disposed at each corner of the fuselage and electrically connected to the control unit; a power carrier; a fuel engine is disposed on the power carrier, and uses the fuel as a fuel to output the rotational power a battery is disposed on the power carrier and electrically connected to the control unit and the rotors to provide power as a source of power required for the rotor to rotate; a differential mechanism is coupled to the fuel engine a first output end and a second output end capable of outputting opposite power directions; a first propeller coupled to the first output end of the differential mechanism for performing rotation along a direction of rotation; a second propeller coupled to the second output end of the differential mechanism for performing a rotation opposite to the first propeller; a plurality of landing gears coupled to the differential mechanism and the fuselage In order to achieve both endurance and load capacity.

1‧‧‧ body

11‧‧‧hex frame

12‧‧‧Main control board

13‧‧‧ Connecting rod

2‧‧‧Control unit

3‧‧‧Rotor

31‧‧‧Brushless motor

32‧‧‧Double blade paddle

41‧‧‧Power bearing

42‧‧‧fuel engine

43‧‧‧Generator

44‧‧‧Battery

5‧‧‧Differential mechanism

51‧‧‧ first output

52‧‧‧second output

61‧‧‧First propeller

62‧‧‧second propeller

7‧‧‧ landing gear

1 is a perspective exploded view of the hybrid electric six-rotor aircraft of the present invention; FIG. 2 is a perspective assembled view of the hybrid electric six-rotor aircraft; FIG. 3 is a side view of the hybrid electric six-rotor aircraft; A perspective view of a power carrier, a fuel engine, a generator, and the like of an electric composite six-rotor aircraft; FIG. 5 and FIG. 6 are perspective views of a differential mechanism, a first propeller, and a second propeller of the hybrid electric six-rotor aircraft; 7 to 9 are top views showing the operation of the hybrid electric six-rotor aircraft.

Referring to FIG. 1 to FIG. 3 , the hybrid electric six-rotor aircraft provided by the present invention mainly includes a fuselage 1, a control unit 2, a six-rotor 3, a power bearing base 41, a fuel engine 42, and a generator. 43. A battery 44, a differential mechanism 5, a first propeller 61, a second propeller 62, and a plurality of landing gears 7, wherein;

The fuselage 1 has a hexagonal shape and has a hexagonal frame 11, a main control board 12 and six connecting rods 13; the hexagonal frame 11 has an elongated hexagonal frame, and the main control board 12 is located at a central position of the hexagonal frame 11. Made of fiberglass material, the connecting rods 13 are aluminum tubes, respectively connected to the hexagonal frame The corners of the frame 11 are spaced between the main control panel 12 to reinforce the structural strength of the hexagonal frame 11.

The control unit 2 is disposed on the main control board 12 of the body 1, and has the capability of receiving signals for logical operation and electronic control, such as a combination of a central processing unit (CPU) and a circuit board.

The six rotors 3 each have a brushless motor 31 and a double blade paddle 32 coupled to the brushless motor 31 and driven by the brushless motor 31. The six rotor blades 3 are respectively disposed on the hexagon of the fuselage 1. The brushless motor 31 of each of the rotors 3 is electrically connected to the control unit 2 at each corner of the frame 11.

It is made of fiberglass material and is located below the main control board 12 of the fuselage 1.

As shown in FIG. 4, the fuel engine 42 is fixedly disposed on the power bearing base 41, and uses fuel as a fuel to output the rotational power.

The generator 43 is disposed on the power bearing base 41 and coupled to the fuel engine 42 to receive the power output from the fuel engine 42 and convert it into electric power for output.

The battery 44 is disposed on the power bearing base 41, and is electrically connected to the control unit 2 and the generator 43. The battery 44 can receive power output from the generator 43 for charging and output power to the control unit 2 to the battery. The rotor 3 is used as a power source for the rotation of the rotor 3. In the present embodiment, the battery 44 is a lithium polymer (Li-Po) battery.

As shown in FIG. 5 and FIG. 6, the differential mechanism 5 is connected to the fuel. The engine 42 is coupled to be driven by the rotational power of the fuel engine 42. The differential mechanism 5 has a first output end 51 and a second output end 52. The first and second output ends 51, 52 output opposite directions. Rotating power, when the fuel engine 42 outputs rotational power to the differential mechanism 5, the first output end 51 outputs the same direction of rotational power, and the second output 52 end outputs the reverse rotational power; That is, when the fuel engine 42 outputs the rotational power in the clockwise direction, the first output end 51 of the differential mechanism 5 will also output the rotational power in the clockwise direction, and the second output end 52 will output the counterclockwise direction. Rotational power; the differential mechanism 5 is composed of a plurality of bevel gears.

The first propeller 61 is coupled to the first output end 51 of the differential mechanism 5 to be rotated by the differential mechanism 5 for providing primary lift.

The second propeller 62 is coupled to the second output end 52 of the differential mechanism 5 to be rotated by the differential mechanism 5 to rotate opposite to the first propeller 61, in addition to providing the main In addition to lift, it has the effect of offsetting the counter-torque to prevent the aircraft from spinning.

The landing gears 7 are coupled to the connecting rod 13 of the fuselage 1 and the differential mechanism 5 for supporting the ground.

Therefore, the above is a description of the components of the hybrid electric six-rotor aircraft and the assembly manner thereof provided by a preferred embodiment of the present invention, and then the features of the present invention are as follows:

As shown in FIG. 2, FIG. 7 to FIG. 9, first, the control unit 2, Receiving a signal transmitted by the user (wireless transmission) to control the fuel engine 42 to operate, and the fuel engine 42 outputs rotational power to the differential mechanism 5 to drive the first and second propellers 61 and 62. The reverse rotation is to provide the main lift by the first and second propellers 61, 62, and the creation can be lifted up to a predetermined height for flight, and the control unit 2 simultaneously simultaneously charges the battery 44. The electric power is output to the brushless motor 31 of the rotor 3, so that the double-blade propeller 32 rotates by the brushless motor 31, and by controlling the rotation speed of the rotors 3, the effect of controlling the direction is achieved, and thus, The author of the oil-electric composite six-rotor aircraft can perform the functions of ascending, descending and flying in different directions.

Thereby, the power output by the fuel engine 42 is used as the main lift (first and second propellers) and the power source of the flight, and the battery 44 is used as a small part of the lift and the power of the control direction and attitude (rotor 3). The source can effectively increase the load capacity by the power of the fuel engine, and the power required by the rotor 3 is shared by the battery 44, thereby increasing the flight capacity of the flight. Moreover, since the generator 43 generates power when the fuel engine 42 is powered, it is converted into electric power to be recharged into the battery 44, and the power of the battery 44 can be ensured.

In addition, if the fuel engine 42 fails, the six rotors 3 that are powered by the battery 44 can also provide limited lift to make a forced landing to reduce the crash of the aircraft.

In addition, the present invention may further include a plurality of electronic differentials (not shown) electrically connected to the control unit 2 and the Between the rotors 3, the rotation speed of the rotors 3 is independently adjusted to control the flight in different directions.

Therefore, the present invention combines the fuel engine and the battery, and uses the power of the fuel engine as the power source for the main lift of the first and second propellers, and the power provided by the battery is used to provide the rotor power source for controlling the direction and posture. Designed in a composite form, it is a very convenient and practical design. By the design of the invention, the problem of insufficient endurance of the pure battery multi-rotor aircraft can be solved, that is, the endurance of the aircraft can be effectively increased.

Therefore, the present invention is applied to aerial photography, aerial photography, airborne security monitoring, aerial crime investigation, fire or fire detection, observation of forest fires, marine or air pollution detection, air quality monitoring, geographic information system (GIS). ) Aerial measurement, aerial advertising, scientific research (such as telemetry applications in geo-environmental measurement, regional high-air composition testing, etc.), mountain conservation, disaster response, traffic monitoring, and inspection of oil pipelines or transmission cables... , all have quite practical effects.

Furthermore, the present invention further includes a carrier device disposed on the body, a GPS navigation module, and an authentication unit; the carrier device is electrically connected to the control unit for fixing an item and can be performed The opening and closing action, when the carrying device is in the closing action, the item cannot be taken out from the carrying device, and the GPS navigation module is electrically connected to the control unit for receiving a positioning signal of a GPS satellite. To generate a coordinate of the location of the GPS navigation module, and according to the coordinates of the location of the GPS navigation module A navigation path is generated between the coordinate position of a destination, and the control unit performs flight control according to the navigation path, that is, the aircraft is moved from the coordinates of the location to the location coordinate of the destination along the navigation path, and the location of the destination is to be reached. At the coordinates, an object picker (who purchases the item) can confirm the identity through the authentication unit. "The identity confirmation action can be transmitted by an entity that issues the item (such as a merchant, shipping warehousing or shipping provider) (eg QR code, QR code) to the portable electronic device (such as smart phone) of the user, and then the QR code is read by the authentication unit (image capturing device), and the QR code built in the control unit The code decoding software performs decoding. After the confirmation is correct, the carrier device is driven to be switched from the closing action to the opening action, so that the object can be taken out by the object, and after the item is taken out into the carrying device, the control unit is Then controlling the carrying device to return to the closing action, and performing reverse flight along the original navigation path, or regenerating a navigation path by the GPS navigation module to fly back to the original Coordinate location (such as a store or warehouse shipments).

Therefore, the present invention is applied to the transportation of goods, and has the advantages of being fast, saving manpower, and the like.

The detailed description of the preferred embodiments of the present invention is intended to be limited to the scope of the invention, and is not intended to limit the scope of the invention. The patent scope of this case.

In summary, the case is not only innovative in terms of space type, but also can enhance the above-mentioned functions more than the conventional items, and should fully comply with the novelty and The progressive statutory invention patent requirements, 提出 apply in accordance with the law, and ask your bureau to approve the invention patent application, in order to invent invention, to the sense of virtue.

1‧‧‧ body

11‧‧‧hex frame

12‧‧‧Main control board

13‧‧‧ Connecting rod

2‧‧‧Control unit

3‧‧‧Rotor

31‧‧‧Brushless motor

32‧‧‧Double blade paddle

41‧‧‧Power bearing

42‧‧‧fuel engine

43‧‧‧Generator

44‧‧‧Battery

5‧‧‧Differential mechanism

51‧‧‧ first output

61‧‧‧First propeller

62‧‧‧second propeller

7‧‧‧ landing gear

Claims (9)

An oil-electric composite six-rotor aircraft includes: a fuselage having a hexagonal shape; a control unit disposed on the body for receiving signals and having logic operation and electronic control capability; the six rotors are respectively disposed on the At each corner of the fuselage, and electrically connected to the control unit; a power carrier; a fuel engine is disposed on the power carrier, using fuel as a fuel for the output of rotational power; a battery, The utility model is disposed on the power bearing base and electrically connected to the control unit and the rotors to provide power as a power source required for the rotation of the rotor; a differential mechanism is coupled to the fuel engine and has an output capable of outputting a first power output is coupled to the first output end and a second output end; a first propeller is coupled to the first output end of the differential mechanism for rotation along a direction of rotation; a second propeller is coupled to The second output end of the differential mechanism is coupled to rotate in a direction opposite to the first propeller; a plurality of landing gears are coupled between the differential mechanism and the fuselage. The hybrid electric six-rotor aircraft of claim 1, wherein the fuselage has a hexagonal frame, a main control panel and six connecting rods; The frame is a narrow hexagonal frame, and the main control board is located at a central position of the hexagonal frame, and the connecting rods are respectively connected between the corners of the hexagonal frame and the main control board; the control unit is disposed on the main control board The rotors are disposed at respective corners of the hexagonal frame, and the power carrier, the fuel engine, the differential mechanism, the first propeller, and the second propeller are located below the main control board, the landing gear It is connected between the connecting rod and the differential mechanism. The hybrid electric six-rotor aircraft of claim 1, wherein each of the rotors has a brushless motor and a double-bladed paddle coupled to the brushless motor and driven by the brushless motor; The brushless motor is electrically connected to the control unit. The fuel-electric composite six-rotor aircraft according to claim 1, further comprising a generator disposed on the power carrier and coupled to the fuel engine to be electrically connected to the battery to receive the fuel The power output by the engine is converted into electric power and output to the battery to charge the battery. The oil-electric composite six-rotor aircraft of claim 1, further comprising a plurality of electronic differentials electrically connected between the control unit and the rotors The rotational speed of each of the rotors is independently adjusted. The fuel-electric composite six-rotor aircraft of claim 1, further comprising a GPS navigation module electrically connected to the control unit and disposed on the body for generating a navigation path, the control Unit basis The navigation path performs flight control. The oil-electric composite six-rotor aircraft according to claim 6, further comprising a carrying device disposed on the body and electrically connected to the control unit for fixing an item and being capable of opening and closing The action is that when the carrying device is in the closing action, the item cannot be taken out from the carrying device, and when the carrying device is in the opening action, the item can be taken out from the carrying device. The fuel-electric composite six-rotor aircraft according to claim 7 further includes an authentication unit disposed on the body and electrically connected to the control unit as the article and a receiver. The identity confirmation interface between the authentication codes. The fuel-electric composite six-rotor aircraft according to claim 8, wherein the authentication unit is an image capturing device, the authentication code is a QR code, and the control unit has a QR code decoding software built therein.