CN105711827A

CN105711827A - Oil and electricity hybrid power multi-rotor aircraft

Info

Publication number: CN105711827A
Application number: CN201610167358.2A
Authority: CN
Inventors: 刘海涛
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-03-23
Filing date: 2016-03-23
Publication date: 2016-06-29

Abstract

The invention provides an oil and electricity hybrid power multi-rotor aircraft which comprises an oil and electricity compound rotor assembly, an aircraft body bracket, a control cabinet, a battery pack, a fuel tank and an undercarriage. The oil and electricity compound rotor assembly is composed of engine rotors and motor rotors. The engine rotors provide main flying power for the aircraft, and the motor rotors flexibly adjust change of lift force of the oil and electricity compound rotor assembly. The oil and electricity hybrid power multi-rotor aircraft has the advantages that multiple fuel oil engines are adopted to serve as the main power, the time of endurance is long, and meanwhile the engine rotors are adopted to flexibly adjust the flight attitude. The engine rotors and the motor rotors can be controlled respectively and are standby power for one another, and the standby power can be adopted for safe landing when a fault occurs in the air.

Description

Oil-electricity hybrid power multi-rotor aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to an oil-electricity hybrid power multi-rotor aircraft.

Background

The multi-rotor aircraft is an aircraft with simple structure, flexible control and stable flight attitude. Generally, different types such as three-axis, four-axis, six-axis, eight-axis, etc. are common. Thanks to the development of micro-electromechanical and sensor technologies in recent years, the multi-rotor aircraft is widely applied to the fields of aeromodelling, aerial shooting platforms and the like. The multi-rotor aircraft senses the flight state through various sensors and sends a rotating speed instruction to the rotor motor through the microprocessor to adjust different flight attitudes of the aircraft.

At present, the state of the multi-rotor aircraft needs to be accurately sensed by various sensors to obtain stable flight attitude, and the microprocessor sends a rotating speed instruction to the rotor motor with high response speed to keep the stable flight state, so that the process needs rapid response of all parts to keep the stability of the aircraft. The sensor, the processor and the motor all need to be powered by batteries, and especially the power consumption of the motor for providing power is the largest. The battery-powered multi-rotor aircraft is limited in the current battery technology development level, the battery-powered multi-rotor aircraft is short in cruising time and small in load capacity, and the performance and application fields of the multi-rotor aircraft are greatly limited. In order to solve the disadvantage of short endurance time of multi-rotor aircraft, people consider using a fuel engine as power. However, the biggest disadvantage of the fuel engine is the slow response speed compared with the motor, which cannot meet the requirement of rapidly controlling the flight attitude of the multi-rotor aircraft. In addition, when a rotor of a multi-rotor aircraft fails, the general result is that the aircraft crashes, and if the goods on the aircraft are expensive and even passengers are carried on the aircraft, the loss cannot be recovered.

Patent 201410385532.1 proposes a hybrid fuel-electric hybrid multi-rotor aircraft. This solution uses an engine that transmits power to a plurality of main rotors via a transmission. The disadvantage of this solution is that 1 the engine is relatively high in failure rate, and once the engine fails, the main rotors lose power, resulting in a loss of main power to the aircraft, which is too risky for flight situations with high requirements on safety, such as manned aircraft. The inevitable efficiency loss caused by the transmission mechanism for transmitting the power of the engine to a plurality of main rotors is not as high as the efficiency of direct connection. 3 the complex transmission mechanism occupies the space of the machine body and improves the failure rate. 4 if the passenger-carrying use engine occupies the middle position of the fuselage, the arrangement of the cabin position is not facilitated, and the vibration influence is larger due to the noise which is closer to passengers. 5 the small number of engines in the case of a certain fuselage volume is not favorable for providing large power, and particularly, the urban passenger aircraft requires the smallest possible volume to provide enough power for flying.

Disclosure of Invention

The invention aims to provide a gasoline-electric hybrid power multi-rotor aircraft to achieve the effects of long endurance time, high load capacity, high response speed and high safety factor of the aircraft.

The invention provides a gasoline-electricity hybrid power multi-rotor aircraft, which comprises a gasoline-electricity composite rotor assembly, an aircraft body bracket, a control box, a battery box, an oil tank and an undercarriage, and is characterized in that: multiunit oil electricity composite rotor subassembly is installed in fuselage support outer end according to the vertical distribution of rotor rotation axis direction, oil electricity composite rotor subassembly includes at least one engine rotor and at least one motor rotor, and the engine rotor comprises engine and the rotor of connecting, and the motor rotor comprises motor and the rotor of connecting, and all rotors are connected according to rotor rotation axis direction with the axial or parallel axial.

Further, many rotor crafts of oil-electricity hybrid still include one or more gesture rotors, and every gesture rotor includes motor and the rotor of connecting, and rotor rotation axis direction horizontal installation is in the fuselage and the non-intersect of plumb line through the fuselage focus.

Further, many rotor crafts of oil-electricity hybrid still include a plurality of gesture rotors, and every gesture rotor includes motor and the rotor of connecting, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and the non-intersect of plumb line through the fuselage focus, has at least one gesture rotor rotation axis direction vertical installation in the fuselage and parallel with the plumb line through the fuselage focus.

Further, many rotor crafts of oil-electricity hybrid still include a plurality of gesture rotors, and every gesture rotor includes motor and the rotor of connecting, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and the non-intersect of plumb line through the fuselage focus, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and intersects with the plumb line through the fuselage focus.

Further, many rotor crafts of oil-electricity hybrid, multiunit engine rotor use every two to adopt the same opposite direction's of rotational speed engine to offset each other to fuselage moment of torsion for a set of. The multiunit motor rotor uses per two to offset each other to fuselage moment of torsion for a set of motor that adopts the same direction of rotational speed is opposite.

Compared with the prior art, the oil-electricity hybrid power multi-rotor aircraft has the following characteristics and advantages:

1. the oil-electricity hybrid power multi-rotor aircraft has the long endurance and the large load capacity of the multi-rotor aircraft powered by the engine, and also has the characteristics of quick response and flexible adjustment of the flight attitude of the multi-rotor aircraft powered by the motor.

2. The oil-electricity hybrid power multi-rotor aircraft adopts the engine and the motor as backup power for each other, can still keep control over the attitude of the aircraft body after partial or total failure of the engine and partial failure of the motor, and has higher safety coefficient.

3 the oil-electricity hybrid power multi-rotor aircraft adopts a plurality of engines to generate power, the engines belong to parts with higher failure rate relatively, when a plurality of engines are adopted, one engine breaks down, and the rest engines can continue to work, so that the oil-electricity hybrid power multi-rotor aircraft is safer than a scheme that one engine transmits power to a plurality of rotors through a transmission mechanism, and more weight and failure rate are brought by a complex transmission mechanism; the multiple engines are more favorable for bringing larger power in smaller volume; the plurality of engines are distributed at the outer end of the machine body, so that the manned cabin can be more conveniently arranged at the middle position of the machine body, and the influence of noise and vibration on passengers is reduced.

The features and advantages of the present invention will become more apparent from the detailed description of the invention when taken in conjunction with the drawings.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a perspective view of a hybrid electric-gasoline multi-rotor aircraft according to embodiment 1 of the present invention;

fig. 2 is a perspective view of a hybrid electric-oil multi-rotor aircraft according to embodiment 2 of the present invention;

wherein,

1. undercarriage, 2, oil tank, 3, group battery, 4, control box, 5, fuselage support, 6, the compound rotor subassembly of oil electricity, 61, motor rotor, 62, engine rotor, 7, the gesture rotor.

Detailed Description

The invention is described in detail below with reference to the drawings and the detailed description.

As shown in fig. 1, this embodiment 1 provides a many rotor crafts of oil-electricity hybrid, assembly connection has oil tank 2 on undercarriage 1, and assembly connection has battery box 3 on the oil tank, and assembly connection has control box 4 on the battery box, and assembly connection has fuselage support 5 on the battery box, and four oily electric composite rotor subassembly 6 are vertically installed in fuselage support 5 outside evenly distributed. Each oil-electric composite rotor assembly comprises a motor rotor 61 driven by a motor and an engine rotor 62 driven by an engine, wherein the motor rotor 61 and the engine rotor 62 are coaxially and fixedly connected. The engine of oil tank 2 and drive engine rotor 62 is connected through defeated oil pipe way, and group battery 3 is connected through the wire electricity with the motor of drive motor rotor 61, has realized possessing engine rotor 62 and motor rotor 61 simultaneously on the many rotor crafts of oil-electricity hybrid and has as power, has the performance of long duration and the heavy load capacity of engine power aircraft, has the quick response of motor power aircraft again and adjusts the characteristic of flight gesture in a flexible way. A control box 4 is assembled and connected above the battery pack 3, and the control box is electrically connected with the battery pack 3 and is in signal connection with a motor driving the motor rotor 61 and an engine driving the engine rotor 62. The rotating speed of the motor and the accelerator of the engine are controlled through the control box 4 so as to adjust the flight attitude of the oil-electricity hybrid power multi-rotor aircraft. The four engine rotors are responsible for the main power source of the aircraft, and have long endurance and large load capacity. But the response speed of the engine is slow, and the flight attitude can be only roughly adjusted. The precise adjustment of the flight attitude is carried out by the motor rotor wing with higher response speed. When one engine breaks down in flight, the opposite engine is immediately stopped, the motor rotors of the same group of two stopped engines can still well control the flight attitude, and the remaining two groups of engine rotors immediately enter an emergency high-speed flight mode to make up for the power loss and control the safe landing of the aircraft. All became invalid when the engine broke down in flight, four motor rotor states were good, and the aircraft was equivalent to traditional electronic four shaft air vehicle this moment, can control the aircraft safety and promptly land. When one motor fails and other parts are in good states, the failure motor can control the rotation of the machine body towards the motor, and the safe emergency landing is realized. In the same way, the two non-opposite motors fail simultaneously, and other parts have good states, so that the aircraft can still effectively control the flight attitude and safely and emergently land. Therefore, the oil-electricity hybrid power multi-rotor aircraft has high safety performance.

As shown in fig. 2, embodiment 2 provides an oil-electric hybrid multi-rotor aircraft, which only uses two oil-electric hybrid rotor assemblies, and has low cost and low failure rate. Two attitude rotors 7 are symmetrically and horizontally arranged on the fuselage support. The gravity center of the aircraft is arranged below the lower part and is distributed in a light-weight-up and heavy-weight-down manner. The direction of the two oil-electricity composite rotors 6 is taken as the advancing and retreating direction of the aircraft, the rotation of the fuselage in the vertical plane of the direction is defined as the pitching of the fuselage, and the rotation of the fuselage perpendicular to the vertical plane is defined as the rolling of the fuselage. The two oil-electricity composite rotor wing assemblies respectively adopt a positive propeller and a negative propeller, and when the aircraft is suspended, the two oil-electricity composite rotor wing assemblies have opposite rotating directions and same lifting force and mutually offset the torque of the aircraft body. When the rotation speed of one of the two oil-electricity composite rotor wing assemblies is increased and the rotation speed of the other one of the two oil-electricity composite rotor wing assemblies is reduced, the aircraft can pitch, and therefore a horizontal component force is generated to drive the aircraft to move forwards or backwards. However, this change in rotational speed produces a torque on the fuselage, causing the fuselage to rotate. At the moment, the control box senses the rotation through the sensor and sends out a command to enable the two attitude rotors 7 to generate pulling forces with the same size and opposite directions, and the torque generated by the two forces can offset the torque of the oil-electricity composite rotor assembly on the aircraft body, so that the aircraft can move forwards or backwards in a straight line. The pulling force of the two attitude rotors 7 is adjusted, but the two forces are kept to be the same but opposite in direction, so that the two attitude rotors generate different torques to realize the in-situ rotation function of the fuselage. The pulling force size of two gesture rotors 7 is adjusted, makes the size of two power different, but the moment of torsion that the difference of two power produced and the moment of torsion that oil-electricity compound rotor subassembly gave the fuselage keep balance, can realize the aircraft sideslip function. Because the aircraft is arranged to be light on top and heavy on bottom, like a pendulum, the roll control of the aircraft is automatically balanced through the action of gravity.

It is to be understood that the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and those skilled in the art may make modifications, alterations, additions or substitutions within the spirit and scope of the present invention.

Claims

1. The utility model provides a many rotor crafts of oil-electricity hybrid, includes oily electric composite rotor subassembly, fuselage support, control box, battery box, oil tank and undercarriage, its characterized in that: multiunit oil electricity composite rotor subassembly is installed in fuselage support outer end according to the vertical distribution of rotor rotation axis direction, oil electricity composite rotor subassembly includes at least one engine rotor and at least one motor rotor, and the engine rotor comprises engine and the rotor of connecting, and the motor rotor comprises motor and the rotor of connecting, and all rotors are connected according to rotor rotation axis direction with the axial or parallel axial.

2. The hybrid electric multi-rotor aircraft of claim 1, wherein: including one or more gesture rotors, every gesture rotor includes motor and the rotor of connecting, and rotor rotation axis direction horizontal installation is in the fuselage and the plumb line non-intersect through the fuselage focus.

3. The hybrid electric multi-rotor aircraft of claim 1, wherein: including a plurality of gesture rotors, every gesture rotor includes motor and the rotor of connecting, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and the plumb line non-intersect through the fuselage focus, has at least one gesture rotor rotation axis direction vertical installation in the fuselage and parallel with the plumb line through the fuselage focus.

4. The hybrid electric multi-rotor aircraft of claim 1, wherein: including a plurality of gesture rotors, every gesture rotor includes motor and the rotor of connecting, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and the plumb line non-intersect through the fuselage focus, has at least one gesture rotor rotation axis direction horizontal installation in the fuselage and intersects through the plumb line of fuselage focus.

5. The hybrid electric multi-rotor aircraft of claim 1, wherein: the two engine rotors are in a group, and the engines with the same rotating speed and opposite directions are adopted to mutually offset the torque on the fuselage; the motor rotor uses every two to offset the fuselage moment of torsion each other as a set of motor that adopts the same direction of rotational speed.