CN205668640U

CN205668640U - Tilting rotor multi-rotor aerocraft

Info

Publication number: CN205668640U
Application number: CN201620531076.1U
Authority: CN
Inventors: 刘海涛
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-06-04
Filing date: 2016-06-04
Publication date: 2016-11-02
Anticipated expiration: 2026-06-04

Abstract

The utility model proposes a kind of tilting rotor multi-rotor aerocraft, use tilting rotor, lifting body cabin, oil electric mixed dynamic design.Attitude rotor is driven by motor, can rotate with angle in the same direction under the effect of rotor inclining rotary mechanism.Lifting body cabin uses aerofoil profiles, can provide part or all of lift during flight.Also include the power rotor that one or more fuel engines drives.The beneficial effects of the utility model are: tilting rotor angle of inclination, cabin when flight is little, and resistance is little, and loaded article is relatively steady, is conducive to obtaining higher flight speed.Lifting body cabin can provide extra lifting flight in hgher efficiency.Using in the same direction with the setting of angle when rotor verts, flight controls logic and becomes apparent from, beneficially flight stability.Power rotor uses fuel engines to drive, and cruising time is longer, and loading capacity is bigger.

Description

Tilting rotor multi-rotor aerocraft

Technical field

This utility model relates to vehicle technology field, particularly relates to a kind of tilting rotor 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.Have benefited from recent years Microprocessor, the development of sensor technology, multi-rotor aerocraft is widely used in the field such as model plane, aerial photographing platform.Many Rotor craft 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 whole aircraft.

At present, the rotor of multi-rotor aerocraft and fuselage mostly are fixed connection structure.Need when flying before aircraft to reverse fuselage Obtain forward direction component.This mode brings three drawback 1 fuselage torsions that loaded article can be driven to link, and is unfavorable for goods or equipment Stability.2 fuselage torsions can increase flight resistance face, increases power consumption, is unfavorable for obtaining at a high speed.3 adjust flight attitude needs whole Individual fuselage reverses, and motility is poor, increases power consumption.When the above drawback is less at multi-rotor aerocraft build, speed is relatively low Inconspicuous, once aircraft volume is relatively big, and when needing to obtain higher flight speed, such as manned vehicle will be obvious.

Additionally, multi-rotor aerocraft wants to obtain stable flight attitude, need various kinds of sensors accurate perception aircraft State, and send rotary speed instruction by microprocessor to response speed rotor motor quickly and keep state of flight stable, this Individual process needs the reaction of each parts very fast, and aircraft could be kept stable.Wherein, sensor, processor, motor are required for Battery is powered, and the motor power consumption particularly providing power is maximum.Being confined to current battery state-of-art, use battery is Multi-rotor aerocraft universal cruising time of power is short, load capacity is little, which greatly limits the performance table of multi-rotor aerocraft Now and application.For solving short shortcoming in multi-rotor aerocraft cruising time, people consider by engine fuel as dynamic Power.But engine fuel is compared with motor, maximum shortcoming is exactly that response speed is slow, and this cannot meet the many rotors of control rapidly and fly The requirement of row device flight attitude.

Summary of the invention

The purpose of this utility model is to provide a kind of tilting rotor multi-rotor aerocraft compared to traditional many rotor flyings Device flying power is higher, load capacity is bigger, flight speed faster, flight attitude more stable.

This utility model provides a kind of tilting rotor multi-rotor aerocraft, including attitude rotor, rotor inclining rotary mechanism, machine Cabin, airborne equipment case, it is characterised in that:

Described attitude rotor quantity is four or more, motor drive, and all attitude rotors are verted by rotor Mechanism is connected to fuselage, can vert with angle in the same direction under rotor inclining rotary mechanism effect.

Further, also including that one or more power rotor is driven by electromotor, described power rotor can revolve with attitude The wing rotates with angle in the same direction or is vertically fixedly installed in fuselage or level is fixedly installed in fuselage.

Further, described cabin uses lifting body structure, can provide all or part of lift during flight.

Further, described rotor inclining rotary mechanism is steering wheel direct-connected attitude rotor or steering wheel transmission mechanically control Attitude rotor, or manual manipulation mechanical drive mode control attitude rotor.

Further, described mechanical system includes gear drive or belt transmission or hinge linkage transmission.

Further, described power rotor is coaxial double-oar form.

Further, at afterbody, vertical tail is installed.

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

1, tilting rotor multi-rotor aerocraft of the present utility model, obtains by the way of tilting rotor rather than the fuselage that verts Obtain rotor component, make aircraft more stable.

2, tilting rotor multi-rotor aerocraft of the present utility model, obtains by the way of tilting rotor rather than the fuselage that verts Obtain rotor component, advantageously reduce aircraft flight resistance thus obtain higher flight speed.

3, tilting rotor multi-rotor aerocraft of the present utility model, obtains by the way of tilting rotor rather than the fuselage that verts Obtain being adjusted flexibly of rotor component, beneficially flight attitude, reduce power consumption.

4, tilting rotor multi-rotor aerocraft of the present utility model, in that context it may be convenient to realize armstrong's patent manipulation rotor wing rotation Angle controls heading and flight speed, is conducive to simplifying manned vehicle structure and flying to control programming, improves flight Device flight safety.

5, tilting rotor multi-rotor aerocraft of the present utility model, uses oil electric mixed dynamic can realize long continuation of the journey big negative Carry.

6, tilting rotor multi-rotor aerocraft of the present utility model, use lifting body cabin, can provide during flight part or Whole lift, flight efficiency is higher.Cabin itself uses airfoil structure, compares the special compact U.S. of fixed-wing scenario-frame of employing See, save space and be conducive to civil nature, universalness.Can be by motor-driven attitude when the electromotor that fault rate is higher is shut down Rotor manipulation aircraft glides and force-lands, and safety is high.

7, tilting rotor multi-rotor aerocraft of the present utility model, rotor verts and uses in the same direction with the design of angle, flies control Logic becomes apparent from, and drive mechanism is simpler.

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 Obtain clearer.

Accompanying drawing explanation

In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, the accompanying drawing in describing below is this Some embodiments of utility model, for those of ordinary skill in the art, on the premise of not paying creative work, also Other accompanying drawing can be obtained according to these accompanying drawings.

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

Fig. 2 is the cut-away view of a kind of tilting rotor multi-rotor aerocraft in this utility model embodiment 1；

Wherein,

1, cabin, 2, power rotor, 3, attitude rotor, 4, gear bar, 5, rotor shaft gear, 6, rotor shaft, 7, bearing, 8, support, 9, vertical tail, 10, steering wheel gear, 11, steering wheel, 12, airborne equipment case.

Detailed description of the invention

With detailed description of the invention, this utility model is described in detail below in conjunction with the accompanying drawings.

Such as Fig. 1, shown in Fig. 2, the present embodiment provides a kind of tilting rotor multi-rotor aerocraft, including cabin 1, cabin 1, sets It is calculated as lifting body profile, flat can produce lift when flying thus obtain higher flight efficiency.Cabin 1 assembling is installed on support 8, props up Frame 8 two ends be provided with bearing 7, by bearing 7, be connected with rotor shaft 6, be provided with rotor shaft gear 5, two ends in the middle of rotor shaft 6 Connecting dynamic rotor 2 and attitude rotor 3, power rotor are driven by electromotor, attitude rotor is driven by motor.At cabin tail Portion is provided with vertical tail 9, vertical rotor 9 latter half rotatable, play the effect of assisted diversion and steady course.Such as Fig. 2 institute Show, in cabin, be provided with airborne equipment case 12, airborne equipment case 12, be integrated with control chamber, fuel tank and battery case.Control chamber is provided with Fly to control processor and sensor, be used for handling rotor rotating speed, rotor corner, vertical tail corner.Rotation of verting it is additionally provided with in cabin Wing mechanism, is rotated by flying control control steering wheel 11, and steering wheel 11 drives steering wheel gear 10, steering wheel gear 10 and gear bar 4 engaged transmission, Gear bar drive with rotor shaft gear 5, engaged transmission simultaneously rotor shaft 6 rotate drive again two ends power rotor 2 and attitude rotation 3, The most same angular turn.

Flight control principle:

1 takes off:

Power rotor 2 and attitude rotor 3 are in vertical position.Power rotor 2 fly control control to be issued to one higher Stabilized (steady-state) speed, its lift provided is close but is less than and makes lift needed for aircraft takeoff.Open flying to control attitude rotor under control Begin to start, as long as a less lift aircraft will take off.Because engine response speed is relatively slow after taking off, so power rotation Wing rotating speed keeps constant.Attitude rotor is driven fast response time by motor, is responsible for main pose adjustment function.Energy consumption during flight Mainly overcome terrestrial gravitation, the fuel engines that energy density is high the power rotor-borne driven.Serve load capacity Greatly, long-endurance effect.Adjust fast changing flight attitude by the motor-driven attitude rotor-borne quickly responded, Serve flight stability, act on flexibly.

2 low-speed operations:

During low-speed operations, four motor-driven attitude rotors 3, be equivalent to traditional electronic four-axle aircraft, rise, under Fall, pitching, control of sideward roll principle are identical.

3 high-speed flights:

Aircraft by low speed to high-speed flight status transition time, fly control control rotor inclining rotary mechanism allow all attitude rotors, There is verting with angle in the same direction in power rotor.Each rotor strengthens pulling force, keeps that vertical direction pulling force is constant just can protect Hold flying height.Horizontal component can make aircraft obtain onward impulse.Obtain because the acquisition of advance component is tilting rotor, Fuselage need not vert, and during high-speed flight, resistance can greatly reduce.Along with flight speed is more and more higher, the cabin of lifting body structure Start to produce lift.Along with the raising of flight speed, the lift that cabin provides ratio in total life is increasing, and rotor inclines The angle turned is increasing, until perfectly level degree, aircraft becomes closer to the state of fixed wing airplane flight.So Flight efficiency, flight speed are significantly better than traditional multi-rotor aerocraft.When high-speed flight, the effect of vertical tail is also Increasing, serve steady course, control the effect in course.

Certainly, described above is not to restriction of the present utility model, and this utility model is also not limited to the example above, Change that those skilled in the art are made in essential scope of the present utility model, retrofit, add or replace, also should Belong to protection domain of the present utility model.

Claims

1. a tilting rotor multi-rotor aerocraft, including attitude rotor, rotor inclining rotary mechanism, cabin, airborne equipment case, it is special Levy and be:

Described attitude rotor quantity is four or more, motor drive, and all attitude rotors pass through rotor inclining rotary mechanism It is connected to fuselage, can vert with angle in the same direction under rotor inclining rotary mechanism effect.

Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: also include one or more power Rotor is driven by electromotor, described power rotor can vert with angle in the same direction with attitude rotor or vertically be fixedly installed in fuselage or Level is fixedly installed in fuselage.

Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: described cabin uses lifting body knot Structure, can provide all or part of lift during flight.

Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: described rotor inclining rotary mechanism is rudder Machine direct-connected attitude rotor or steering wheel transmission mechanically control attitude rotor, or manual manipulation mechanical drive mode controls appearance State rotor.

Tilting rotor multi-rotor aerocraft the most according to claim 4, it is characterised in that: described mechanical system includes gear Transmission or belt transmission or hinge linkage transmission.

Tilting rotor multi-rotor aerocraft the most according to claim 2, it is characterised in that: described power rotor is coaxial double Oar form.

Tilting rotor multi-rotor aerocraft the most according to claim 1, it is characterised in that: it is provided with vertically at afterbody Empennage.