CN205327402U

CN205327402U - Multi -rotor aircraft

Info

Publication number: CN205327402U
Application number: CN201620111183.9U
Authority: CN
Inventors: 刘海涛
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-02-04
Filing date: 2016-02-04
Publication date: 2016-06-22
Anticipated expiration: 2026-02-04

Abstract

The utility model provides a multi -rotor aircraft, including one or more power rotor, when the power rotor be one, rotor rotation axis orientation was vertical through the body nodal point, and the power rotor is when a plurality of, and a plurality of power rotors centered on the plumb line symmetric distribution of body nodal point, dynamic rotor vertical body nodal point and a set of or multiunit gesture rotor subassembly of passing through of orientation of making a concerted effort during vertical lift. The beneficial effects of the utility model are that: compare in the electronic many rotors of tradition the utility model discloses can use the fuel engine as power, time of endurance is longer, has kept the flexibility of electric machine control flight gesture simultaneously.

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 field such as model plane, aerial photographing platform。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 higher compared to tradition 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 or more, when power rotor is one, rotor wing rotation direction of principal axis is vertically through body nodal point, when power rotor is multiple, multiple power rotors are symmetrical around the plumb line crossing body nodal point, and during vertical lift, the dynamic rotor resultant direction of institute is vertically through body nodal point。It is also equipped with attitude rotor assemblies in the outside of fuselage, attitude rotor assemblies is one or more groups, attitude rotor assemblies is made up of the motor rotor of multiple motors and connection thereof, having at least its rotating shaft direction of two motor rotors to be respectively at horizontally and vertically position, all motor rotor wing rotation direction of principal axis are non-intersect with the plumb line crossing body nodal point。

Further, 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, 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。

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；

Fig. 2 is the axonometric chart of a kind of multi-rotor aerocraft in this utility model embodiment 2；

Wherein,

1, undercarriage, 2, fuel tank, 3, set of cells, 4, control chamber, 5, power rotor, 51, electromotor, 52, the positive oar rotor of electromotor, 53, the anti-oar rotor of electromotor, 6, attitude rotor assemblies, 61, motor, 62, motor 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 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, two electromotors 51 with the vertical assembly connection of control chamber, the electromotor positive oar rotor 52 being connected with electromotor and the anti-oar rotor 53 of electromotor, two groups of attitude rotor assemblies 6 are installed in the side of two power rotors 5, often group attitude rotor assemblies includes two motors 61, and the motor rotor 62 connected, two motor rotor wing rotation direction of principal axis are respectively at horizontally and vertically position。Fuel tank 2 is connected through pipeline road with electromotor 51, set of cells 3 and motor 61, 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 61 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 51, motor 61 signal。Engine throttle size and motor speed and rotation direction is controlled by control chamber 4。

A kind of multi-rotor aerocraft in this utility model embodiment 1 as shown in Figure 1, its main flying power is provided by two electromotors 51, and the plumb line that two power rotors walk around body nodal point is symmetrical。Two electromotor rotors are respectively adopted electromotor positive oar rotor 52 and the anti-oar rotor 53 of electromotor, it is provided that during lift, rotation direction is cancelled out each other the reaction torque effect to fuselage on the contrary, strengthen simultaneously and reduce the throttle of electromotor and can control the raising and lowering of aircraft。For ease of describing with power rotor for heading and direction of advance, during flight, multi-rotor aerocraft is in horizontal original state。When the identical lifting tail in the lift size direction that two vertical motor rotors produce, bowing before aircraft, power rotor produces component forward and drives aircraft to advance。When the lift size direction that two vertical motor rotors produce is identical force down tail time, aircraft is swung back, and power rotor produces component backward and drives aircraft to retreat。The fuselage roll when the lift size equidirectional that two vertical motor rotors produce is contrary, power rotor generation cross component force realizes side and flies。When the motor rotor that two levels are installed produces pulling force, fuselage realizes being horizontally diverted。

A kind of multi-rotor aerocraft in this utility model embodiment 2 as shown in Figure 2, embodiment 2 is a kind of comparatively succinct design。Its advantage is that parts are few, and fuselage is compact。Control principle is similar with Fig. 1, power rotor 5 provide main flying power, and the vertical motor rotor in attitude rotor assemblies 6 is responsible for body pitching, and the motor rotor that level is installed is responsible for offsetting reaction torque that power rotor brings to fuselage and control is horizontally diverted。

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 assemblies, fuel tank, set of cells, control chamber, undercarriage, it is characterised in that:

Described power rotor is one or more, when power rotor is one, rotor wing rotation direction of principal axis is vertically through body nodal point, when power rotor is multiple, multiple power rotors are symmetrical around the plumb line crossing body nodal point, and during vertical lift, the dynamic rotor resultant direction of institute is vertically through body nodal point；

Described attitude rotor assemblies is one or more groups, attitude rotor assemblies is made up of the motor rotor of multiple motors and connection thereof, having at least its rotating shaft direction of two motor rotors to be respectively at horizontally and vertically position, all motor rotor wing rotation direction of principal axis are non-intersect with the plumb line crossing body nodal point。

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