CN205469794U - Driving system and aircraft of structure aircraft - Google Patents

Abstract

The utility model provides a driving system and aircraft of structure aircraft belongs to the aircraft field, and this driving system includes vane actuated mechanism, and vane actuated mechanism includes rotatable rotation axis and screw, and the rotation axis is connected with rotation control mechanism, and rotation control mechanism includes controlling means and drive mechanism, and controlling means passes through drive mechanism with the rotation axis and is connected, and the screw rotates with drive arrangement is connected drive arrangement and rotation axis vane actuated mechanism 1. This driving system can construct and compromise the aircraft that VTOL, hover in air, flying speed are fast, the flight time is long.

Description

A kind of dynamical system constructing aircraft and aircraft

Technical field

This utility model relates to aircraft field, constructs aircraft in particular to one Dynamical system and aircraft.

Background technology

At present, aeromodelling aerocraft of a great variety, such as four-axle aircraft and fixed-wing are unmanned Machine etc..

The rotor of four-axle aircraft is symmetrically distributed in four direction around body, and four Individual rotor is in sustained height plane, and the structure of four rotors is the most identical with radius, four Motor is symmetrically installed on the bracket end of aircraft, and support intermediate space is laid flight and controlled meter Calculation machine and external equipment.Four-axle aircraft changes rotor by four motor speeds of regulation and turns Speed, it is achieved the change of lift, thus control attitude and the position of aircraft, in the mistake of regulation The electric energy consumed in journey is bigger, and high energy consumption directly results in short problem in cruising time；Four axles Vehicle flight speeds is slow, and the vertical ascent of the middle-size and small-size four-axle aircraft of current higher-end is Big speed is generally 9m/s, and horizontal velocity maximum only has 25m/s；Owing to cruising time is short, Flight speed is slow, causes such as transporting, express delivery, line walking etc. are all difficult to effectively realize.At present The application of four-axle aircraft great majority is all carried out in extremely limited space, time range.

Why fixed-wing unmanned plane can fly up, and the lift being because wing overcomes gravity. The lift of wing is that the upper and lower air pressure difference of wing is formed.General fixed-wing model plane are dependent on The motor of head drives propeller to run up, and then provides thrust, when thrust is more than sliding During the frictional resistance taken turns, aircraft will travel forward.Fixed wing airplane flight speed aloft Comparatively fast, need steering hands to have good respond, also have stronger operation skill, compare For multiaxis unmanned plane, operation is more complicated.Further, since fixed-wing unmanned plane Only one of which provides the propeller of thrust, and direction is level, in the vertical direction of aircraft The most additional upper power carrys out the gravity of balance airplane body, does not has additional power to adjust and flies The attitude of machine, thus fixed-wing can only flight aloft time, utilize wing and empennage to produce Lift and other power, could keep balance, and can not hover over aerial.

At present, there is no one and take into account that VTOL, hovering, flight speed be fast, flight The aircraft of time length.

Utility model content

This utility model provides a kind of dynamical system constructing aircraft and aircraft, it is intended to Improve the problems referred to above.

This utility model is achieved in that

A kind of dynamical system constructing aircraft, including rotor mechanism, described rotor mechanism bag Including rotating rotary shaft and propeller, described rotary shaft is connected with rotation control mechanism, institute State rotation control mechanism and include controlling device and drive mechanism, described control device and described rotation Rotating shaft is connected by described drive mechanism, and described propeller is rotationally connected with driving means, institute State that driving means and described rotary shaft are fixing to be connected.

Further, described drive mechanism includes driving gear and travelling gear, described active Gear engages with described travelling gear, and described driving gear is connected with described control device, institute State travelling gear fixed cover to be located in described rotary shaft.

Using the drive mechanism that driving gear and driven gear are meshed, transmission is the quickest. During control, control device and drive driving gear to rotate, driving gear band nutating gear, by It is fixed in rotary shaft in travelling gear, thus axle is rotated and rotates.

Further, described control device includes control module and controls motor, described control Module electrically connects with described control motor, and described control motor is connected with described driving gear.

Controlling motor work drives driving gear to rotate, and control module controls opening of motor Stop, rotating and rotating speed etc., thus realize turning of rotary shaft and stop, turn to and rotating speed etc., The control making rotary shaft is accurate, realizes the switching of plurality of flight quickly and efficiently.

Further, described rotor mechanism is four, and wherein, described rotary shaft is two, Described propeller is four；

The two ends of two described rotary shafts are provided with a propeller, two described rotations respectively Being provided with cross bar between rotating shaft, described cross bar includes the first cross bar and the second cross bar, Qi Zhongyi Individual rotary shaft by described rotation control mechanism and described axostylus axostyle bindiny mechanism respectively with described the One cross bar and described second cross bar connect, and another rotary shaft passes through described axostylus axostyle bindiny mechanism It is connected with described first cross bar and described second cross bar respectively with described rotation control mechanism.

Use four propellers so that this dynamical system can construct the aircraft of four axles, and Rotary shaft is two so that four propellers are one group two-by-two, two propellers of same group Co-rotation.

Further, described rotation control mechanism also includes the first connector, described cross bar with Described rotary shaft is connected by described first connector, and described control device is installed on described the On a connection piece.

By arranging the first connector, it is possible to play fixation to controlling device, can realize This rotation control mechanism and the first cross bar or the connection of the second cross bar and fixing.

Further, described first connector includes the first T-connecting piece and the first fixed plate, Described first T-connecting piece includes the first connecting portion and the first fixed part, and described first connects Portion is connected by bearing with described rotary shaft, described cross bar be fixed on described first fixed part and Between described first fixed plate, described control device is installed on described first fixed part.

Control device to be fixed on the first fixed part, fixed, enable control device very Control well driving gear to rotate.When rotary shaft rotates under the drive of travelling gear, bearing Rotate, the rotation of rotary shaft can either be ensured, it is also possible to make rotary shaft securely with first even The portion that connects connects, and makes rotary shaft skew will not occur or rock, and transmission is more accurate.

Further, described axostylus axostyle bindiny mechanism includes the second connector, and described second connects Part includes that the second T-connecting piece and the second fixed plate, described second T-connecting piece include Two connecting portions and the second fixed part, described second connecting portion is with described rotary shaft by bearing even Connecing, described cross bar is fixed between described second T-connecting piece and described second fixed plate.

Second connecting portion is connected fixing by bearing with rotary shaft, and the second fixed part and second is admittedly Determine plate to be clamped between the second fixed part and the second fixed plate by cross bar when connecting, make cross bar Firm can be connected with rotary shaft, both ensure that the rotation of rotary shaft, again can be to rotary shaft Play support and interconnection function.

Further, described driving means includes that motor, described motor are fixed on propeller admittedly In reservation, the axle of described propeller stretches into described propeller and fixes seat and be connected with described motor, Described propeller fixes that seat and described rotary shaft are fixing to be connected.

Propeller is fixed seat and motor is played fixing and protective effect, and propeller fixes seat and rotation Rotating shaft is fixing to be connected, it is ensured that rotary shaft drives propeller to deflect when rotating.

Further, the two ends of the bottom that described propeller fixes seat are respectively arranged with base plate, Being arranged with two connecting plates in described rotary shaft, described base plate and described connecting plate pass through bolt Connect.

Connection by base plate Yu connecting plate, it is possible to propeller is fixed seat fine with rotary shaft Fix, it is simple to rotary shaft rotate time drive propeller deflect.

This utility model additionally provides a kind of aircraft, solves above-mentioned technical problem with auxiliary, This aircraft, including the dynamical system of any of the above-described structure aircraft.

The dynamical system of the structure aircraft that this utility model provides provides the benefit that: this moves During Force system work, can control drive mechanism action by controlling device, drive mechanism drives Rotary shaft rotates, and rotary shaft drives driving means to rotate, so that propeller deflects, Controlled the rotation of rotary shaft by rotation control mechanism, the tune in propeller works direction can be realized Whole.Use the aircraft that this dynamical system constructs when taking off, the propeller of this dynamical system Operative orientation vertical, utilize the rotation of propeller to produce lift, and controlled by corresponding Realize VTOL and hovering；In flight course, rotary shaft rotates, and makes propeller Operative orientation consistent with heading, propeller rotate to be aircraft provide thrust, accelerate Flight speed, and saved energy consumption, cruising time is long.Therefore, this dynamical system energy Enough structures take into account VTOL, hovering, flight speed flight fast, high-time Device.

Accompanying drawing explanation

In order to be illustrated more clearly that the technical scheme of this utility model embodiment, below will be to reality Execute the required accompanying drawing used in example to be briefly described, it will be appreciated that the following drawings is only shown Go out some embodiment of the present utility model, be therefore not construed as the restriction to scope, For those of ordinary skill in the art, on the premise of not paying creative work, also Other relevant accompanying drawings can be obtained according to these accompanying drawings.

The dynamical system of the structure aircraft that Fig. 1 provides for this utility model first embodiment Structural representation；

The dynamical system of the structure aircraft that Fig. 2 provides for this utility model first embodiment The structural representation of the bottom, side perspective of rotation control mechanism；

The dynamical system of the structure aircraft that Fig. 3 provides for this utility model first embodiment Propeller fixes the structural representation of seat；

Fig. 4 exists for the dynamical system of the structure aircraft that this utility model the second embodiment provides Structural representation during two propeller co-rotations；

The dynamical system of the structure aircraft that Fig. 5 provides for this utility model the second embodiment The structural representation of the bottom, side perspective of axostylus axostyle bindiny mechanism；

The dynamical system of the structure aircraft that Fig. 6 provides for this utility model the second embodiment Structural representation；

The structure at the end face visual angle of the aircraft that Fig. 7 provides for this utility model the 3rd embodiment Schematic diagram；

The structure at the visual angle, bottom surface of the aircraft that Fig. 8 provides for this utility model the 3rd embodiment Schematic diagram.

Figure acceptance of the bid note is respectively as follows:

Rotary shaft 101；Propeller 102；Control device 103；Driving means 104；Actively Gear 105；Travelling gear 106；Cross bar 107；First cross bar 108；Second cross bar 109； First T-connecting piece 110；First fixed plate 111；First connecting portion 112；First fixes Portion 113；Second T-connecting piece 114；Second fixed plate 115；Second connecting portion 116； Second fixed part 117；Motor 118；Propeller fixes seat 119；Base plate 120；Connecting plate 121；Multiaxis rotor frame 122；Fixed-wing 123.

Detailed description of the invention

For making the purpose of this utility model embodiment, technical scheme and advantage clearer, under The accompanying drawing that face will combine in this utility model embodiment, to the skill in this utility model embodiment Art scheme is clearly and completely described, it is clear that described embodiment is that this practicality is new The a part of embodiment of type rather than whole embodiments.Generally described in the accompanying drawing herein and The assembly of this utility model embodiment illustrated can be arranged with various different configurations and set Meter.Therefore, detailed description to the embodiment of the present utility model provided in the accompanying drawings below It is not intended to limit claimed scope of the present utility model, but is merely representative of this practicality Novel selected embodiment.Based on the embodiment in this utility model, ordinary skill The every other embodiment that personnel are obtained under not making creative work premise, all belongs to Scope in this utility model protection.

First embodiment

Refer to Fig. 1, present embodiments provide a kind of dynamical system constructing aircraft, use In structure aircraft, this dynamical system includes that rotor mechanism, rotor mechanism include rotating Rotary shaft 101 and propeller 102, rotary shaft 101 is connected with rotation control mechanism, rotates Controlling organization includes controlling device 103 and drive mechanism, controls device 103 and rotary shaft 101 Being connected by drive mechanism, propeller 102 is rotationally connected with driving means 104, drives dress Put 104 fixing with rotary shaft 101 to be connected.

Rotor mechanism can be multiple, and the quantity of propeller 102 is unrestricted, each spiral Oar 102 connects a driving means 104, and driving means 104 is preferably motor 118.Such as, Rotor mechanism is three, becomes isosceles triangle distribution, and one of them is located close to fixed-wing 123 The position of head, the line of another two is vertical with the bearing of trend of fixed-wing 123.

Furthermore it is possible to be that a propeller 102 is equipped with a rotary shaft 101, each spiral Oar 102 is all an independent entirety, and realization in space that can be independent arbitrarily rotates； Can also be that a rotary shaft 101 installs multiple propeller 102.Rotation control mechanism is used for Control the rotation of rotary shaft 101.Furthermore it is possible to be that a rotation control mechanism is by one Rotary shaft 101 is connected with a propeller 102, controls the deflection of a propeller 102, Can also be that a rotation control mechanism controls two propellers by same rotary shaft 101 The deflection of 102, now the two propeller 102 co-rotation, coaxial situation refers to Fig. 5.

During this power system operational, drive mechanism action can be controlled by controlling device 103, Drive mechanism is rotated axle 101 and rotates, and rotary shaft 101 drives driving means 104 to rotate, So that propeller 102 deflects, control rotary shaft 101 by rotation control mechanism Rotate, the adjustment of propeller 102 operative orientation can be realized.This dynamical system is used to construct Aircraft is when taking off, and the operative orientation of the propeller 102 of this dynamical system is vertical, utilizes The rotation of propeller 102 produces lift, and by corresponding control realization VTOL and sky Middle hovering；In flight course, rotary shaft 101 rotates, and makes the work side of propeller 102 To consistent with heading, propeller 102 rotates to be aircraft and provides thrust, accelerates and flies Line speed, and saved energy consumption, cruising time is long.Therefore, this dynamical system can structure Make and take into account VTOL, hovering, flight speed aircraft fast, high-time.

Further, referring to Fig. 1 and Fig. 2, drive mechanism includes driving gear 105 He Travelling gear 106, driving gear 105 engages with travelling gear 106, driving gear 105 Being connected with controlling device 103, travelling gear 106 fixed cover is located in rotary shaft 101.

Using the drive mechanism that driving gear 105 and driven gear are meshed, transmission is the fastest Speed.During control, control device 103 and drive driving gear 105 to rotate, driving gear 105 Band nutating gear 106, owing to travelling gear 106 is fixed in rotary shaft 101, thus Axle 101 is rotated rotate.

Control device 103 include control module and control motor 118, control module and control Motor 118 electrically connects, and controls motor 118 and is connected with driving gear 105.

Controlling motor 118 work drives driving gear 105 to rotate, and control module controls The start and stop of motor 118, rotating and rotating speed etc., thus realize rotary shaft 101 turn stop, Turn to and rotating speed etc. so that the control of rotary shaft 101 is accurate, realize many quickly and efficiently Plant the switching of offline mode.

Referring to Fig. 1 and Fig. 2, rotation control mechanism also includes the first connector, this power System includes that cross bar 107, cross bar 107 are connected by the first connector with rotary shaft 101, Control device 103 to be installed on the first connector.

By arranging cross bar 107 and the first connector, it is possible to play solid to controlling device 103 It is set for use, the connection of this rotation control mechanism and cross bar 107 can be realized and fix.

Referring to Fig. 1 and Fig. 2, the first connector includes the first T-connecting piece 110 and One fixed plate 111, the first T-connecting piece 110 includes that the first connecting portion 112 and first is solid Determining portion 113, the first connecting portion 112 is connected by bearing with rotary shaft 101, cross bar 107 It is fixed between the first fixed part 113 and the first fixed plate 111, controls device 103 and install On the first fixed part 113.

Control device 103 to be fixed on the first fixed part 113, fixed, make control fill Put 103 can control driving gear 105 well and rotate.Rotary shaft 101 is at travelling gear When rotating under the drive of 106, bearing rotates, and can either ensure the rotation of rotary shaft 101, It also is able to make rotary shaft 101 be connected with the first connecting portion 112 securely, makes rotary shaft 101 Skew will not occur or rock, transmission is more accurate.

Referring to Fig. 1 and Fig. 3, driving means 104 includes that motor 118, motor 118 are fixed In propeller fixes seat 119, the axle of propeller 102 stretches into propeller and fixes seat 119 also Being connected with motor 118, propeller fixes that seat 119 and rotary shaft 101 is fixing to be connected.Spiral Oar is fixed seat 119 and motor 118 is played fixing and protective effect, and propeller fixes seat 119 Fix with rotary shaft 101 and be connected, it is ensured that rotary shaft 101 drives propeller 102 when rotating Deflect.

Referring to Fig. 1 and Fig. 3, the two ends of the bottom that propeller fixes seat 119 are respectively provided with Have base plate 120, rotary shaft 101 be arranged with two connecting plates 121, base plate 120 be connected Plate 121 is bolted.Connection by base plate 120 with connecting plate 121, it is possible to will Propeller is fixed seat 119 and is fixed well with rotary shaft 101, it is simple to rotary shaft 101 is turning Propeller 102 is driven to deflect time dynamic.

Second embodiment

The dynamical system of the structure aircraft that the present embodiment is provided, its basic structure and principle And the technique effect of generation is identical with first embodiment, for briefly describing, the present embodiment part Not mentioned part, refers to corresponding contents in first embodiment.

Referring to Fig. 4～Fig. 6, in the present embodiment, rotor mechanism is four, wherein, rotates Axle 101 is two, and propeller 102 is four.The two ends of two rotary shafts 101 are respectively It is provided with a propeller 102, between two rotary shafts 101, is provided with cross bar 107, cross bar 107 include the first cross bar 108 and the second cross bar 109, and one of them rotary shaft 101 is by rotation Turn controlling organization and axostylus axostyle bindiny mechanism connects with the first cross bar 108 and the second cross bar 109 respectively Connect, another rotary shaft 101 by axostylus axostyle bindiny mechanism and rotation control mechanism respectively with the One cross bar 108 and the second cross bar 109 connect.It is to say, one end of the first cross bar 108 Being connected by rotation control mechanism with one of them rotary shaft 101, the other end revolves with another Rotating shaft 101 is connected by axostylus axostyle bindiny mechanism；Rotatrol is passed through with the first cross bar 108 The rotary shaft 101 that structure connects is connected by axostylus axostyle bindiny mechanism with the second cross bar 109, The rotary shaft 101 being connected by axostylus axostyle bindiny mechanism with the first cross bar 108 and the second cross bar 109 are connected by rotation control mechanism.

Use four propellers 102 so that this dynamical system can construct the aircraft of four axles, Such as fixed-wing four-axle aircraft, and rotary shaft 101 is two so that four propellers 102 are one group two-by-two, two propeller 102 co-rotations of same group.

Axostylus axostyle bindiny mechanism includes that the second connector, the second connector include that the second T-shaped connects Part 114 and the second fixed plate 115, the second T-connecting piece 114 includes the second connecting portion 116 With the second fixed part 117, the second connecting portion 116 is connected by bearing with rotary shaft 101, It is solid that first cross bar 108 or the second cross bar 109 are fixed on the second T-connecting piece 114 and second Determine between plate 115.

Second connecting portion 116 is connected fixing by bearing with rotary shaft 101, the second fixed part 117 and second fixed plate 115 connect time the second cross bar 109 is clamped in the second fixed part 117 and second between fixed plate 115, makes the second cross bar 109 can jail with rotary shaft 101 By connecting, both ensure that the rotation of rotary shaft 101, and rotary shaft 101 can have been played again and prop up Support and interconnection function.

3rd embodiment

Present embodiments providing a kind of aircraft, this aircraft includes what the second embodiment provided The dynamical system of structure aircraft, refers to Fig. 7 and Fig. 8, and this aircraft also includes multiaxis Rotor frame 122 and fixed-wing 123, cross bar 107 is arranged in multiaxis rotor frame 122, I.e. cross bar 107 is a part for multiaxis rotor frame 122.Rotation control mechanism passes through cross bar 107 are connected with multiaxis rotor frame 122.Fly for fixed-wing multiaxis on this aerocraft real Device, the advantage being provided simultaneously with Fixed Wing AirVehicle and Multi-axis aircraft, multiaxis mould can be realized Formula, fixed-wing 123 pattern and fixed-wing 123 and multiaxis mixed model, taken into account vertical Landing, hovering, flight speed feature fast, high-time.

The operation principle of this fixed-wing Multi-axis aircraft is:

A. multiaxis pattern: when landing, the multiple propellers 102 in multiaxis rotor frame 122 Operative orientation be perpendicular to fuselage, rely only on multiple propeller 102 provide lift hang down Straight landing.When its vertical ascent to a certain height, utilize the balance of multiaxis to make it hang It is parked in aerial.The power that the multiple vertical propeller 102 of recycling Multi-axis aircraft provides Flight forward.

B. fixed-wing 123 pattern: after aircraft speed arrives certain speed, propeller 102 Carrying out the deflection of 90 °, operative orientation is consistent with aircraft flight direction.And fixed-wing 123 Offline mode and four axle offline mode can quickly, switch repeatedly such that it is able to multiple appearance State is flown.

C. fixed-wing 123 and the mixed model of multiaxis: when aircraft uses fixed-wing 123 mould During formula flight aloft, run into some emergency situations, such as: sinuous flow, one or one group of spiral shell Rotation oar 102 breaks down, and will take mixed model.Due to two groups of propellers 102 of front and back Motor 118 be co-rotation, and be all independently controlled.So, (1) is disorderly when meeting During stream, it can allow the most independent one group of propeller 102 continue the work shape that holding is original State, another set propeller 102 carries out co-rotation, carries out aircraft balance and attitude Adjust.(2) when meeting one propeller 102 of aircraft and breaking down, the one of aircraft The propeller 102 of the normal work organizing intact propeller 102 and another group is joined Close, control rotating speed and the direction of three propellers 102, adjust attitude of flight vehicle.(3) If any one group of propeller 102 of aircraft breaks down, then that group remaining is just Often propeller 102 some angles of the most coaxial deflection of work, and reduce the flight speed of aircraft Degree, to keep aircraft smooth flight.

This fixed-wing Multi-axis aircraft has the advantage that

1. there is the wing of Fixed Wing AirVehicle so that it is can utilize relatively low in flight course Energy consumption (thrust) obtain bigger lift, and then reduce energy consumption, be greatly promoted aircraft Flying power.

2. there is the function of Multi-axis aircraft VTOL, take off and no longer retrained by orographic condition, Can complete to take off, land in any landform.

3. having the function of hovering, its flight path is no longer affected by geographical environment, can With normal flight in the environment of the flight spaces such as such as jungle, gully, building are narrow and small.

4. rotary shaft 101 is rotatable so that propeller 102 rotates, and lift change propulsive flies Line speed is greatly improved, dramatically expansive approach field.

5. fixed-wing 123 pattern and multiaxis pattern can be switched fast, and have mixing control Ability such that it is able to fly with many attitude, strengthens flight stability and maneuverability.

6. use modularized design so that it is can preferably carry out with existing Multi-axis aircraft Modular design, the function of extension Multi-axis aircraft and application.

In description of the present utility model, it is to be understood that term " " center ", " longitudinally ", " laterally ", " length ", " width ", " thickness ", " on ", D score, "front", "rear", " left ", " right ", " vertically ", " level ", " top ", " end " " interior ", " outward ", " clockwise ", " inverse Hour hands " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship, It is for only for ease of description this utility model and simplifies description rather than instruction or hint indication Equipment or element must have specific orientation, with specific azimuth configuration and operation, because of This is it is not intended that to restriction of the present utility model.

Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that Indicate or imply relative importance or the implicit quantity indicating indicated technical characteristic.By This, define " first ", the feature of " second " can express or implicitly include one Or more this feature.In description of the present utility model, " multiple " are meant that two Or two or more, unless otherwise expressly limited specifically.

In this utility model, unless otherwise clearly defined and limited, term " install ", " be connected ", " connection ", the term such as " fixing " should be interpreted broadly, for example, it may be solid Fixed connection, it is also possible to be to removably connect, or integral；Can be to be mechanically connected, it is possible to To be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, can To be connection or the interaction relationship of two elements of two element internals.For this area Those of ordinary skill for, can understand that above-mentioned term is new in this practicality as the case may be Concrete meaning in type.

In this utility model, unless otherwise clearly defined and limited, fisrt feature is Two features it " on " or D score can include that the first and second features directly contact, also Can include that the first and second features are not directly contact but other by between them Characterisation contact.And, fisrt feature second feature " on ", " top " and " above " Including fisrt feature directly over second feature and oblique upper, or it is merely representative of fisrt feature water Flat height is higher than second feature.Fisrt feature second feature " under ", " lower section " and " under Face " include fisrt feature immediately below second feature and obliquely downward, or it is special to be merely representative of first Levy level height less than second feature.

The foregoing is only preferred embodiment of the present utility model, be not limited to this Utility model, for a person skilled in the art, this utility model can have various more Change and change.All within spirit of the present utility model and principle, any amendment of being made, Equivalent, improvement etc., within should be included in protection domain of the present utility model.

Claims (10)

1. the dynamical system constructing aircraft, it is characterized in that, including rotor mechanism, described rotor mechanism includes rotating rotary shaft and propeller, described rotary shaft is connected with rotation control mechanism, and described rotation control mechanism includes controlling device and drive mechanism, and described control device is connected by described drive mechanism with described rotary shaft, described propeller is rotationally connected with driving means, and described driving means is fixing with described rotary shaft to be connected.

The dynamical system of structure aircraft the most according to claim 1, it is characterized in that, described drive mechanism includes driving gear and travelling gear, described driving gear engages with described travelling gear, described driving gear is connected with described control device, and described travelling gear fixed cover is located in described rotary shaft.

The dynamical system of structure aircraft the most according to claim 2, it is characterised in that described control device includes control module and controls motor, and described control module electrically connects with described control motor, and described control motor is connected with described driving gear.

The dynamical system of structure aircraft the most according to claim 2, it is characterised in that described rotor mechanism is four, wherein, described rotary shaft is two, and described propeller is four；

The two ends of two described rotary shafts are provided with a propeller respectively, it is provided with cross bar between two described rotary shafts, described cross bar includes the first cross bar and the second cross bar, one of them rotary shaft is connected with described first cross bar and described second cross bar respectively by described rotation control mechanism and axostylus axostyle bindiny mechanism, and another rotary shaft is connected with described first cross bar and described second cross bar respectively by described axostylus axostyle bindiny mechanism and described rotation control mechanism.

The dynamical system of structure aircraft the most according to claim 4, it is characterized in that, described rotation control mechanism also includes that the first connector, described cross bar are connected by described first connector with described rotary shaft, and described control device is installed on described first connector.

The dynamical system of structure aircraft the most according to claim 5, it is characterized in that, described first connector includes the first T-connecting piece and the first fixed plate, described first T-connecting piece includes the first connecting portion and the first fixed part, described first connecting portion is connected by bearing with described rotary shaft, described cross bar is fixed between described first fixed part and described first fixed plate, and described control device is installed on described first fixed part.

The dynamical system of structure aircraft the most according to claim 4, it is characterized in that, described axostylus axostyle bindiny mechanism includes the second connector, described second connector includes the second T-connecting piece and the second fixed plate, described second T-connecting piece includes the second connecting portion and the second fixed part, described second connecting portion is connected by bearing with described rotary shaft, and described cross bar is fixed between described second T-connecting piece and described second fixed plate.

The dynamical system of structure aircraft the most according to claim 1, it is characterized in that, described driving means includes motor, described motor is fixed on propeller to be fixed in seat, the axle of described propeller stretches into described propeller and fixes seat and be connected with described motor, and described propeller fixes that seat and described rotary shaft are fixing to be connected.

The dynamical system of structure aircraft the most according to claim 8, it is characterised in that the two ends of the bottom that described propeller fixes seat are respectively arranged with base plate, described rotary shaft is arranged with two connecting plates, and described base plate is bolted with described connecting plate.

10. an aircraft, it is characterised in that include the dynamical system constructing aircraft as described in any one of claim 1-9.