CN205327405U

CN205327405U - Multi -rotor aircraft

Info

Publication number: CN205327405U
Application number: CN201620118236.XU
Authority: CN
Inventors: 刘海涛
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-02-10
Filing date: 2016-02-10
Publication date: 2016-06-22
Anticipated expiration: 2026-02-10

Abstract

The utility model provides a multi -rotor aircraft, including the power rotor of a vertical installation and a plurality of horizontal installation's gesture rotor. The power rotor can be by engine or motor drive, and the gesture rotor is by motor drive. The beneficial effects of the utility model are that: 1 single action power rotor craft is better from equilibrium stability in the air, can use the engine long as power time of endurance. 2 control that the principle is simple, parts are few, purchasing cost, use cost are than lower. 3 the flexibility that has kept electric machine control flight gesture.

Description

Multi-rotor aerocraft

Technical field

This utility model relates to vehicle technology field, particularly relates to a kind of multi-rotor aerocraft。

Background technology

The aircraft that multi-rotor aerocraft is a kind of simple in construction, manipulation is flexible, flight attitude is stable。Having benefited from the development of microprocessor, sensor technology in recent years, multi-rotor aerocraft is widely used in the fields such as model plane, aerial photographing platform, agricultural plant protection。Multi-rotor aerocraft passes through various kinds of sensors perception state of flight, and sends rotary speed instruction by microprocessor to rotor motor and adjust the different flight attitudes of aircraft。

At present, multi-rotor aerocraft wants to obtain stable flight attitude needs the accurate perception flight state of various kinds of sensors, and send rotary speed instruction by microprocessor to response speed rotor motor quickly and keep state of flight stable, this process needs the reaction of each parts very fast, and aircraft could be kept stable。Wherein, sensor, processor, motor are required for battery and power, and the motor power consumption particularly providing power is maximum。Being confined to current battery state-of-art, the multi-rotor aerocraft general cruising time using battery to be power is short, load capacity is little, which greatly limits the performance of multi-rotor aerocraft and application。For solving short shortcoming in multi-rotor aerocraft cruising time, people consider by engine fuel as power。But engine fuel is compared with motor, maximum shortcoming is exactly that response speed is slow, and this cannot meet the requirement controlling rapidly multi-rotor aerocraft flight attitude。

Summary of the invention

The purpose of this utility model is in that to provide a kind of multi-rotor aerocraft that can use fuel engines higher compared to conventional electric multi-rotor aerocraft flying power, and load capacity is bigger, conventional electric multi-rotor aerocraft can be kept to manipulate advantage flexibly simultaneously。

This utility model provides a kind of multi-rotor aerocraft, fuel tank including undercarriage and undercarriage assembly connection, battery case with fuel tank assembly connection, control chamber with battery case assembly connection, power rotor with control chamber assembly connection, power rotor is one, and rotor wing rotation direction of principal axis is vertically arranged to fuselage by body nodal point。Attitude rotor is multiple, each attitude rotor includes the rotor of motor and connection thereof, rotor wing rotation direction of principal axis is horizontally installed to fuselage, has and only one of which attitude rotor wing rotation direction of principal axis is non-intersect with by the plumb line of body nodal point, and other attitude rotor wing rotation direction of principal axis intersect with described plumb line。

Further, described power rotor includes the rotor of a power part and connection thereof, or multiple rotors of a power part and connection thereof, or multiple rotors that multiple power part connects, described all rotors are all pressed rotor wing rotation axle coaxial line direction and are connected, and described power part includes electromotor or motor。

Compared with prior art, multi-rotor aerocraft of the present utility model has the characteristics that and advantage:

1, multi-rotor aerocraft of the present utility model, it is possible to fuel engines for major impetus, longer for its cruising time compared to conventional electric multi-rotor aerocraft, load capacity is bigger。

2, multi-rotor aerocraft of the present utility model, controls flight attitude mainly through motor, maintains tradition multi-rotor aerocraft and controls advantage flexibly。

3, multi-rotor aerocraft of the present utility model adopts single-power rotor, and aerial self-balancing stability is better, not easily topples, and manipulation principle is simple, and parts are few, and working service cost is low。

After reading in conjunction with the accompanying detailed description of the invention of the present utility model, other features of the present utility model and advantage will become clearer from。

Accompanying drawing explanation

In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, the accompanying drawing used required in embodiment or description of the prior art will be briefly described below, apparently, accompanying drawing in the following describes is embodiments more of the present utility model, for those of ordinary skill in the art, under the premise not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings。

Fig. 1 is the axonometric chart of a kind of multi-rotor aerocraft in this utility model embodiment 1；

Wherein,

1, undercarriage, 2, fuel tank, 3, set of cells, 4, control chamber, 5, attitude rotor, 51, motor, 6, power rotor, 61, electromotor, 62, electromotor rotor。

Detailed description of the invention

Below in conjunction with the drawings and specific embodiments, this utility model is described in detail。

As shown in Figure 1, the present embodiment 1 provides a kind of multi-rotor aerocraft, including undercarriage 1, fuel tank 2 with undercarriage assembly connection, battery case 3 with fuel tank assembly connection, control chamber 4 with battery case assembly connection, electromotor 61 with the vertical assembly connection of control chamber, the electromotor rotor 62 being connected with electromotor, two attitude rotors 5 are horizontally installed to fuselage outer side, two attitude rotor wing rotation direction of principal axis are mutually perpendicular to and are positioned at same horizontal plane, and rotor wing rotation direction of principal axis is with to intersect another by the plumb line of body nodal point non-intersect。Fuel tank 2 is connected through pipeline road with electromotor 61, set of cells 3 and motor 51, electrically connect through wire, it is achieved that with electromotor for power on multi-rotor aerocraft, cruising time length, characteristic that loading capability is big, it is simultaneously achieved motor and controls flight attitude, the feature of fast response time。The top assembly connection of set of cells 3 has control chamber 4, be provided with in control chamber various kinds of sensors, processor can perception, control flight attitude, control chamber 4 electrically connects with set of cells 3, and is connected with electromotor 61, motor 51 signal。Engine throttle size and motor speed and rotation direction is controlled by control chamber 4。Executing the multi-rotor aerocraft in example 1, main flying power is provided by power rotor 6, and it is driven cruising time long by electromotor 61。Single-power rotor craft center of gravity is on the lower, similar with the pendulum of lightness sensation in the upper and heaviness in the lower, relatively good by gravity airflight attitude self-balancing, not easily topples, this simplify the requirement to aircraft flight gesture stability。Increase and decrease engine throttle can realize the rise and fall of aircraft。Two attitude rotors 5 being horizontally installed to fuselage outer side are the parts of major control flight attitude。The attitude rotor wherein intersected with by body nodal point plumb line is responsible for controlling the forward-reverse of aircraft。The attitude rotor not intersected with by body nodal point plumb line is responsible for offsetting electromotor rotor 62 and the reaction torque of fuselage and control aircraft is horizontally diverted。It is achieved thereby that the manipulation to multi-rotor aerocraft flight attitude。

Certainly; described above is not to restriction of the present utility model; this utility model is also not limited to the example above, the change made in essential scope of the present utility model of those skilled in the art, remodeling, interpolation or replacement, also should belong to protection domain of the present utility model。

Claims

1. a multi-rotor aerocraft, including power rotor, attitude rotor, it is characterised in that:

Described power rotor is one, and rotor wing rotation direction of principal axis is vertically arranged to fuselage by body nodal point；

Described attitude rotor is multiple, each attitude rotor includes the rotor of motor and connection thereof, rotor wing rotation direction of principal axis is horizontally installed to fuselage, having and only one of which attitude rotor wing rotation direction of principal axis is non-intersect with by the plumb line of body nodal point, other attitude rotor wing rotation direction of principal axis intersect with described plumb line。

2. multi-rotor aerocraft according to claim 1, it is characterized in that: described power rotor includes the rotor of a power part and connection thereof, or multiple rotors of a power part and connection thereof, or multiple rotors that multiple power part connects, described all rotors are all pressed rotor wing rotation axle coaxial line direction and are connected, and described power part includes electromotor or motor。