CN205524965U

CN205524965U - Multi -rotor aircraft

Info

Publication number: CN205524965U
Application number: CN201620309118.7U
Authority: CN
Inventors: 刘海涛
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-04-14
Filing date: 2016-04-14
Publication date: 2016-08-31
Anticipated expiration: 2026-04-14

Abstract

The utility model provides a multi -rotor aircraft, including two by independent engine driven's power rotor and four or four above motor drive's gesture rotor. The power rotor mainly provides flight power, and its rotation rate is invariable relatively, and the gesture rotor receives the nimble adjustment flight gesture of control box flight control system control. The beneficial effects of the utility model are that: it is long to have adopted fuel engine to be major impetus time of endurance, has adopted the nimble adjustment flight gesture of motor rotor simultaneously. Corotation and the moment of torsion of the equal cancel each other out of reversal rotor quantity to the fuselage, keep -It -Simple -Control, energy saving. Twin engine is provided with to do benefit to and improves flight power, avoids complicated drive mechanism, raises the efficiency, is favorable to the fuselage overall arrangement, can realize emergent the descending when an arbitrary engine or an arbitrary motor break down under the cooperation of steering wheel, and the security is higher.

Description

Multi-rotor aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to a many rotor crafts.

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, compared with the motor, the fuel engine has the biggest defect of low response speed, and 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.

In the scheme of adopting the oil-electricity hybrid power to solve the endurance capacity of the multi-rotor aircraft, a rotor variable-pitch mode is mostly adopted, and the mode is greatly influenced by the accuracy of a steering engine and the environment and has larger jitter. The scheme in addition adopts the mode that an engine then transmits power to each rotor wing through drive mechanism, and this kind of mode structure is complicated, and is inefficient, and the trouble is high, is unfavorable for fuselage spatial layout. And once the engine is invalid, all rotors connected through the transmission mechanism can be invalid, so that the crash is easily caused, and the safety is lower.

Disclosure of Invention

An object of the utility model is to provide a many rotor crafts in order to realize that many rotor crafts duration is long, load capacity is big, response speed is fast, simple structure, has the effect of higher factor of safety.

The utility model provides a many rotor crafts, including power rotor, gesture rotor, fuselage support, control box, battery box, oil tank and undercarriage, its characterized in that:

the two power rotor wings are vertically arranged on the airframe and symmetrically distributed along the vertical line of the center of gravity of the airframe, and each power rotor wing is driven by an independent engine;

the number of the attitude rotor wings is four or more than four and is even, the attitude rotor wings are arranged on the fuselage along the vertical direction, every two attitude rotor wings are a group of attitude rotor wings and are symmetrically distributed along the gravity center plumb line of the fuselage, and each attitude rotor wing is driven by an independent motor.

Further, the two power rotors rotate in opposite directions when providing the same-direction pulling force.

Furthermore, when the attitude rotors provide tension in the same direction, the forward rotation quantity and the reverse rotation quantity of all the attitude rotors are the same.

Furthermore, the attitude rotor wing is movably connected to the fuselage and can rotate on a vertical plane under the control of the steering engine.

Compared with the prior art, the utility model discloses a many rotor crafts has following characteristics and advantage:

1. the utility model discloses a many rotor crafts, long continuation of the journey, the big load capacity of the many rotor crafts that possess engine power still possess quick response, the nimble characteristics of adjusting the aircraft flight gesture of many rotor crafts of motor power.

2. The utility model discloses a many rotor crafts adopts the configuration of twin-engine, still can descend through emergent flight mode safety under the condition of an engine inefficacy or the condition of an arbitrary motor inefficacy, and the security is higher, is fit for manned flight or carries the condition of more valuable goods.

3. The utility model discloses a many rotor crafts adopts the configuration of twin-engine to provide bigger bearing capacity to do not need complicated drive mechanism, simple structure, the fault rate is low, and is efficient, can arrange the power rotor in the fuselage outer end, and the fuselage middle part does not have drive mechanism, relatively is favorable to the fuselage overall arrangement.

4. The utility model discloses a many rotor crafts gesture rotor can realize multiple emergent flight mode in the flight through the cooperation of steering wheel, and flight safety is higher.

After reading the detailed description of the present invention in conjunction with the drawings, the features and advantages of the present invention will become more apparent.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described 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 multi-rotor aircraft according to embodiment 1 of the present invention;

fig. 2 is a schematic view of an emergency mode of a multi-rotor aircraft according to embodiment 1 of the present invention;

fig. 3 is a perspective view of a 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, motor, 7, gesture rotor, 8, engine, 9, power rotor, 10, steering wheel.

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.

As shown in fig. 1, this embodiment 1 provides a many rotor crafts, assembly connection has an oil tank 2 on undercarriage 1, assembly connection has a battery box 3 on the oil tank, assembly connection has a control box 4 on the battery box, assembly connection has fuselage support 5 on the battery box, at two vertical installation power rotors 9 of fuselage support 5 both ends symmetric distribution, two power rotors 9 adopt positive and negative oar setting respectively, the direction of rotation is opposite when providing syntropy lift, can offset each other to the fuselage moment of torsion. Each power rotor 9 is driven by a separate engine 8. The outer end of the fuselage support 5 is symmetrically provided with four attitude rotors 7 which are vertically installed and driven by motors, the attitude rotors which are diagonally distributed are both positive propellers or both negative propellers, and the number of the positive propellers and the negative propellers of the four attitude rotors is consistent. The four attitude rotors are movably connected to the airframe bracket through the steering gears 10 and can rotate on a vertical plane through the control of the steering gears. The oil tank 2 is connected with the engine 8 through an oil conveying pipeline, the battery pack 3 is electrically connected with the motor 6 through a conducting wire, the engine and the motor which are used as power are simultaneously arranged on the multi-rotor aircraft, the performance of long endurance and large load capacity of the engine power aircraft is achieved, and the characteristic of flexibly adjusting flight attitude through quick response of the motor power aircraft is achieved. The upper part of the battery pack 3 is connected with a control box 4 in an assembling way, a flight control device is installed in the control box, and the control box 4 is electrically connected with the battery pack 3 and is in signal connection with a motor 6 and a steering engine 10. The flight attitude of the multi-rotor aircraft is adjusted by controlling the rotating speed of the motor 6 through the control box 4, and the attitude rotor angle is controlled through the steering engine 10. The power rotor wing 9 is the main power source of the aircraft, and has long endurance time and large load capacity. However, the response speed of the engine is slow, and the flight attitude can be only roughly adjusted at a relatively constant rotating speed. The precise adjustment of the flight attitude is carried out by a motor with higher response speed. During take-off, the two engines 8 are started, so that the combined lift force of the two engines is close to but less than the take-off lift force as much as possible. At the moment, the four attitude rotors can be started to take off the aircraft only by small force. The control mode of the four attitude rotors after taking off is the same as the principle of the traditional electric four-axis aircraft, and the four attitude rotors can control the pitching, rolling, steering, lifting and other actions of the aircraft. The rotating speed of the engine is constant in the flying process, and the attitude rotor wing is responsible for flexibly changing and correcting the flying attitude.

As shown in fig. 2, embodiment 1 provides a multi-rotor aircraft, which can manually or automatically start an emergency mode according to a preset flight control program when an airborne fault occurs. There are two types of failures:

1. if the engine A breaks down, the engine A is shut down in the air, and other parts operate normally. At the moment, the flight control automatically enters an emergency flight mode: the attitude rotor E is controlled to stop, and the attitude rotor F rotates 90 degrees under the control of the steering engine and becomes a horizontal position. The attitude rotor wing attitude C, D runs with full force, improves the lift force, and makes up the power loss caused by losing one engine. The attitude rotor C, D can control the pitching attitude of the aircraft with the same tension and direction, and can control the rolling attitude of the aircraft with different tensions. Because of losing an engine, lead to total positive and negative oar quantity inconsistent to produce the effect to fuselage torque, can be controlled by the gesture rotor F that is in horizontal position and offset or realize controlled the turning to, realize the aircraft from out of control, the purpose that the safety lands.

2. If the attitude rotor E breaks down, the aircraft is shut down in the air, and other components fly normally. The attitude rotor F rotates 90 degrees under the control of the steering engine and becomes a horizontal position. The attitude rotor C, D can control the pitching attitude of the aircraft with the same tension and direction, and can control the rolling attitude of the aircraft with different tensions. The steering is controlled by the attitude rotor F in the horizontal position, so that the purposes of no runaway and safe landing of the aircraft are realized.

As shown in fig. 3, embodiment 2 provides a multi-rotor aircraft, and embodiment 2 is a simplified solution, and the application of a steering engine is eliminated. The situation in normal flight is the same as in example 1. When one engine or one motor is in failure, the pitching and rolling flight attitude of the aircraft can be controlled. However, since the spin and steering attitude of the aircraft cannot be controlled by the application of the steering engine, the effect is inferior to that of embodiment 1 although safe landing can be realized. The device is suitable for occasions with sensitive cost and low safety requirements, such as application of agricultural plant protection machines.

Of course, the above description is not intended to limit the present invention, and the present invention is not limited to the above examples, and the changes, modifications, additions or substitutions made by those skilled in the art within the scope of the present invention should also belong to the protection scope of the present invention.

Claims

1. The utility model provides a many rotor crafts, includes power rotor, gesture rotor, fuselage support, control box, battery box, oil tank and undercarriage, its characterized in that:

2. The multi-rotor aerial vehicle of claim 1, wherein: the two power rotors rotate in opposite directions when providing tension in the same direction.

3. The multi-rotor aerial vehicle of claim 1, wherein: when the attitude rotors provide tension in the same direction, the forward rotation and reverse rotation of all the attitude rotors are the same in quantity.

4. The multi-rotor aerial vehicle of claim 1, wherein: the posture rotor wing is movably connected to the fuselage and can rotate on a vertical plane under the control of the steering engine.