CN203975218U - Some twin shafts are starched Flight Vehicle Structure more - Google Patents
Some twin shafts are starched Flight Vehicle Structure more Download PDFInfo
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- CN203975218U CN203975218U CN201420227488.7U CN201420227488U CN203975218U CN 203975218 U CN203975218 U CN 203975218U CN 201420227488 U CN201420227488 U CN 201420227488U CN 203975218 U CN203975218 U CN 203975218U
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Abstract
The utility model relates to some twin shafts and starches Flight Vehicle Structure more, comprise fixed support, gondola, dynamical axis, power rotor, power motor, attitude rotor and attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed with gondola, dynamical axis is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed on this dynamical axis, this power rotor is driven and is rotated by the power motor that is arranged on its underpart, adopt coaxial double-oar structure, the overlapping vertical layout of two oars.The utility model is simple in structure, safe and reliable, conserve space, be convenient to mobilely, facilitates field work, upper end screw propeller control attitude, the multiple screw propellers in below provide power to do, aerial bearing capacity is large, fully meet take photo by plane, the work requirements such as communication.
Description
Technical field
The utility model belongs to unmanned plane field, and especially a kind of some twin shafts are starched Flight Vehicle Structure more.
Background technology
In field, the world today, the flight mode of cyclogyro has four kinds:
The one, single rotor structure, most of autogyros all adopt this structure in the world;
The 2nd, coaxial double-oar structure, represents that type has Muscovite cassette series model, as card-50, and card-28 etc.;
The 3rd, the two paddle structures of twin shaft, represent that type has the C-47 of the U.S. to prop up slave's dry type helicopter;
The 4th, many rotor structures, mainly adopt in SUAV (small unmanned aerial vehicle) field.Be characterized in: realize the attitude control of aircraft by adjusting the rotating speed of each rotor.Mainly contain at grade the types such as four rotors, six rotors, eight rotors, all adopt automatically controlled posture adjustment state to regulate and control the sense of motion of aircraft.The utility model also adopts automatically controlled, but is not the differential posture adjustment of adjusting a rotor, but adjusts heading by the attitude of adjusting upper axle.
And the aircraft of present patent application is the 5th kind of flight mode outside above four kinds of cyclogyros flight control structure system, be therefore a kind of innovation of the mode of flying, in current cyclogyro field or peerless.
Find other patent documents of following near field through retrieval:
A kind of multi-rotor aerocraft (CN102806993A), this aircraft comprises four main rotor system, two secondary rotor systems, body and be arranged on the flight system ensemble in body; The initial point of aircraft body axis system is the center of gravity of aircraft, and upwards, x axle is perpendicular to z axle for z axle vertical, directed forward, and y axle is determined by right-hand rule; Four main rotor system are distributed in respectively in four quadrants of body axis system xy plane, each rotation axis of four main rotor system and the z axle of the body axis system θ that has angle, and the projection of each rotation axis in body axis system xoy plane to body axis system initial point line, the projection in body axis system xoy plane overlaps with centre of gration.The utility model changes by regulating the rotating speed of four main rotor system and two secondary rotor systems can realize aircraft movements and attitude, the actions such as aircraft can be realized vertical takeoff and landing, frontly flies, inverted flight, hovering, rolling, and stability and control is good.
A kind of small-sized vertical takeoff and landing morphing aircraft (CN202414160U), wing panel, main wing section, folding wing panel, fold mechanism, vertical fin, power pack section and recce pack in the middle of aircraft comprises, the vertical fin of aircraft is symmetrical in upper surface and the lower surface of aircraft, be symmetrically installed with between the middle wing panel and main wing section of aircraft, the afterbody of the middle wing panel of aircraft is stretched out in the rear end of vertical fin; Main wing section is connected by fold mechanism with folding wing panel, and fold mechanism comprises a folding rotary shaft parallel with aircraft axis, and fold mechanism is placed in main wing section, and folding wing panel is carried out 180 ° at the uniform velocity folding around folding rotary shaft.The utility model has used a kind of brand-new variant mode, can change aspect ratio and aerofoil profile simultaneously, and its deformation range is wider and airworthiness is more superior, and this variant mechanism is comparatively simple, and engineering realizability is stronger.
Through comparative analysis, there is internal difference in mode of operation and above aircraft in present patent application, here only compares with many cyclogyros, and this aircraft has following characteristics:
1, take up room little: multi-rotor aerocraft is plane figure, and rotor takes up room larger more; The utility model is the overlapping layout of rotor, not only takes up room little, and compact conformation, be easy to carry.
2, can realize modular mode and promote complete machine usefulness: many rotors can promote load-carrying by increasing rotor quantity, and the utility model can improve load-carrying by the mode that increases rotor quantity equally, a just horizontal arrangement, one is arranged vertically.
3,, with the comparison of many cyclogyros, the body angle of inclination problem while not there is not posture adjustment, has improved the precision of observation thus greatly.
Many rotors are in the time adjusting aspect, necessary complete machine inclination certain angle, ability adjust operation direction, this is for hanging storehouse with the observation of body rigidity connection, also the corresponding angle that must tilt, if in the situation that wind-force is larger, body must be adjusted frequently attitude and could keep aerial and must stablize, if used as aerial observation platform, the precision of its observation will inevitably be influenced.The utility model, because adopt upper lower shaft to connect by the mode of universal joint articulated, need be only capable of regulating flight attitude by adjusting the inclination angle of the rotor on upper axle, irrelevant with lower shaft, also just with lower shaft below observation to hang storehouse more irrelevant.That is to say how no matter go up rotor moves, and lower shaft and observation are hung storehouse all the time in horizontality, therefore the precision of observation just can not be affected.
4, be a aircraft of realizing non-structure weight: no matter which kind of aircraft, the design maximum target of pursuit improves flight usefulness by alleviating structural weight exactly.The utility model is the unique a kind of aircraft that can realize non-structure weight, and in the situation that power is identical, overall efficiency is all more much higher than other any aircraft.
Utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art part, provides a kind of demonstration simple in structure, convenient, safe and reliable, space-saving some twin shafts to starch Flight Vehicle Structure more.
The utility model solves its technical matters and takes following technical scheme to realize:
Some twin shafts are starched Flight Vehicle Structure more, comprise fixed support, gondola, dynamical axis, power rotor, power motor, attitude rotor and attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed with gondola, dynamical axis is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed on this dynamical axis, this power rotor is driven and is rotated by the power motor that is arranged on its underpart, it is characterized in that: adopt coaxial double-oar structure, the overlapping vertical layout of two oars; Described coaxial double-oar structure comprises attitude rotor, attitude motor, rotating shaft, stand, expansion link, swinging mounting and attitude axle, the upper end, four summits of described support bracket fastened cross bracket is all by a rotating shaft hinge dress stand, four stand outsides are all provided with an expansion link, these four stand upper ends be jointly provided with one with criss cross swinging mounting, this coaxial Installation posture axle in swinging mounting middle part, on this attitude axle, install by the motor-driven attitude rotor of attitude, attitude rotor is provided with an attitude motor.
Advantage of the present utility model and good effect are:
1, this structure will adopt the coaxial up and down multiple rotors of longitudinal one-point type, the angle of the rotor at top is adjustable, by changing the aerial statue of angle control aircraft of top rotor, remove the rotor that flank and other angles are installed from, significantly save space, stronger for the comformability of flight space and storage space.
2, the attitude rotor of this structure adopts with power rotor the twin shaft design not being connected, power rotor shaft is that vertical working shaft drives power rotor High Rotation Speed to produce pulling force upwards, rise and aerial major impetus of being detained as aircraft, attitude rotor shaft can need to be carried out angular adjustment according to flight.
3, the power rotor of this structure can longitudinally superpose and install multiplely, and bearing capacity is cumulative, is convenient to calculate, and structure is installed comparatively simple, and structural reliability is strong.
4, simple in structure, safe and reliable, the conserve space of the utility model, be convenient to mobilely, facilitate field work, upper end screw propeller control attitude, the multiple screw propellers in below provide power to do, aerial bearing capacity is large, fully meet take photo by plane, the work requirements such as communication.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model;
Fig. 2 is that Fig. 1 removes anterior support bracket fastened structural representation;
Fig. 3 is the birds-eye view of Fig. 1;
Fig. 4 is the structural representation that the utility model increases the quantity of motor and rotor.
Mark in accompanying drawing: 1 attitude rotor; 2 attitude motors; 3 angle controllers; 4 power motors; 5 power rotors; 6 swinging mountings; 7 stands; 8 expansion links; 9 rotating shafts; 10 fixed supports; 11 gondolas; 12 dynamical axiss; 13 attitude axles.
Detailed description of the invention
Below in conjunction with accompanying drawing and by specific embodiment, the utility model is described in further detail, and following examples are descriptive, are not determinate, can not limit protection domain of the present utility model with this.
A kind of some twin shafts are starched Flight Vehicle Structure more, comprise fixed support 10, gondola 11, dynamical axis 12, power rotor 5 and power motor 4, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, on fixed support, all lateral separation is uniform is shaped with multiple through holes, and Stability Analysis of Structures and total quality are light; Fixed support lower end is coaxially fixed with gondola, and this gondola is used for carrying the equipment such as pick up camera; Dynamical axis is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed on this dynamical axis, this power rotor is driven and is rotated by the power motor that is arranged on its underpart, thereby produce pulling force upwards, as active force, aircraft be raised to aerial from ground and provide power that aircraft is detained aloft.
Innovative point of the present utility model is:
Adopt coaxial double-oar structure, this pair of overlapping vertical layout of oar, but its control system remains by the attitude of link rod control rotor and regulates and controls heading.The motor of upper axle is to become hinged with the motor of lower shaft with oar versatile spindle to be linked togather with oar.The more overlapping layout of axle and lower shaft in formation.Therefore say some twin shafts.The regulation and control of flight attitude are to become two steering wheels of 90 degree horizontal arrangement to realize by upper axle below.
The concrete structure of the present embodiment is:
Coaxial double-oar structure comprises attitude rotor 1, attitude motor 2, rotating shaft 9, stand 7, expansion link 8, swinging mounting 6 and attitude axle 13, described power rotor top is hinged with an attitude rotor, the angle of this attitude rotor can be carried out multidimensional angular adjustment, attitude rotor is provided with an attitude motor, attitude motor is as the auxiliary motor of electrical machinery of active force, auxiliary power is provided, adjust mooring product attitude aloft, concrete mounting structure is referring to Figure of description, the upper end, four summits of support bracket fastened cross bracket is all by a rotating shaft hinge dress stand, four stand outsides are all provided with an expansion link, these four stand upper ends be jointly provided with one with criss cross swinging mounting, this coaxial Installation posture axle in swinging mounting middle part, on this attitude axle, install by the motor-driven attitude rotor of attitude.When work, the expansion link of rotation support one side extends, and the expansion link of rotation support opposite side shortens, stand is around rotating shaft rotation, thereby drive swinging mounting rotation certain angle, attitude rotor is along with rotation support carries out rotation, thereby the propulsive force of different directions is provided to aircraft.
In order to control more accurately the angle of attitude rotor, between described swinging mounting and attitude axle, angle controller 3 is installed.
Whole aircraft can improve load-carrying by the quantity that increases motor and rotor on lower shaft, on described dynamical axis, multiple power rotors can be coaxially sequentially installed, power rotor lower end is all provided with power motor, and every group of power cyclogyro power motor can provide the lift of 10kg.
Aircraft is in the past that the rotor of the many oars of twin shaft or multi-rotor aerocraft in one plane launches, and the area that therefore takes up room is large.Although and the overlapping vertical layout of coaxial double-oar of the present utility model two oar, its control system remains by the attitude of link rod control rotor and regulates and controls heading.
Difference of the present utility model is: two oars or many oars are overlapping is arranged vertically, the motor of upper axle is to become hinged with the motor of lower shaft with oar versatile spindle to be linked togather with oar.The more overlapping layout of axle and lower shaft in formation.Therefore say some twin shafts.The regulation and control of flight attitude are to become two steering wheels of 90 degree horizontal arrangement to realize by upper axle below.
In a word, twin shaft arranged perpendicular, controls flight attitude with the drift angle of axle in transmission mechanism control, improves load-carrying to increase rotor quantity, is technical essential of the present utility model.Also be innovation and the utility model of cyclogyro flight mode.
Claims (1)
1. 1 twin shaft is starched Flight Vehicle Structure more, comprise fixed support, gondola, dynamical axis, power rotor, power motor, attitude rotor and attitude motor, fixed support is horizontally disposed transverse and longitudinal intersection cross bracket, fixed support lower end is coaxially fixed with gondola, dynamical axis is coaxially installed in fixed support upper end, the power rotor parallel with fixed support is installed on this dynamical axis, this power rotor is driven and is rotated by the power motor that is arranged on its underpart, it is characterized in that: adopt coaxial double-oar structure, the overlapping vertical layout of two oars; Described coaxial double-oar structure comprises attitude rotor, attitude motor, rotating shaft, stand, expansion link, swinging mounting and attitude axle, the upper end, four summits of described support bracket fastened cross bracket is all by a rotating shaft hinge dress stand, four stand outsides are all provided with an expansion link, these four stand upper ends be jointly provided with one with criss cross swinging mounting, this coaxial Installation posture axle in swinging mounting middle part, on this attitude axle, install by the motor-driven attitude rotor of attitude, attitude rotor is provided with an attitude motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420227488.7U CN203975218U (en) | 2014-05-06 | 2014-05-06 | Some twin shafts are starched Flight Vehicle Structure more |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420227488.7U CN203975218U (en) | 2014-05-06 | 2014-05-06 | Some twin shafts are starched Flight Vehicle Structure more |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203975218U true CN203975218U (en) | 2014-12-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420227488.7U Expired - Fee Related CN203975218U (en) | 2014-05-06 | 2014-05-06 | Some twin shafts are starched Flight Vehicle Structure more |
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| CN (1) | CN203975218U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104506758A (en) * | 2014-12-10 | 2015-04-08 | 马人欢 | Camera for outdoor security protection |
| CN110673228A (en) * | 2019-08-30 | 2020-01-10 | 北京航空航天大学 | Formula of throwing sonde under imitative dandelion structure |
-
2014
- 2014-05-06 CN CN201420227488.7U patent/CN203975218U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104506758A (en) * | 2014-12-10 | 2015-04-08 | 马人欢 | Camera for outdoor security protection |
| CN104506758B (en) * | 2014-12-10 | 2017-12-08 | 盐城咏恒投资发展有限公司 | Outdoor security protection camera |
| CN110673228A (en) * | 2019-08-30 | 2020-01-10 | 北京航空航天大学 | Formula of throwing sonde under imitative dandelion structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141203 Termination date: 20170506 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |