CN205440871U - Roll wing pitch -changing mechanism - Google Patents
Roll wing pitch -changing mechanism Download PDFInfo
- Publication number
- CN205440871U CN205440871U CN201620164545.0U CN201620164545U CN205440871U CN 205440871 U CN205440871 U CN 205440871U CN 201620164545 U CN201620164545 U CN 201620164545U CN 205440871 U CN205440871 U CN 205440871U
- Authority
- CN
- China
- Prior art keywords
- pitch change
- change axes
- pitch
- oar
- changing mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Springs (AREA)
Abstract
The utility model provides a roll wing pitch -changing mechanism, includes 2 oar dishes, oar dish center pin, second grade displacement axle, one -level displacement axle, spring, uide bushing. By second grade displacement axle, one -level displacement axle, spring and uide bushing constituteed roll wing pitch -changing mechanism's displacement pole respectively. 2 the both ends at this oar dish center pin are installed respectively to individual oar dish. The displacement pole equally divide for 2 groups and respectively the equipartition on the circumference of each oar dish to constitute the flexible arm of a cycloid oar by being located two a pair of displacement poles on the oar dish respectively, the wing that respectively rolls of aircraft splices the top at each flexible arm respectively. This roll wing pitch -changing mechanism has 2, and the distribution of symmetry is in the aircraft fuselage both sides. The utility model discloses the utilization is rolled the centrifugal force that the wing self rotate to produce and has been realized that it rolls the flexible of the wing to roll wing unmanned aerial vehicle, has realized rolling the flexible pitch -changing mechanism of wing size, makes its can be adapted to different environment states, has extended the application of rolling wing unmanned aerial vehicle, still has simple structure simultaneously, and the energy consumption is few, light in weight's characteristics.
Description
Technical field
The invention belongs to field of mechanical technique, be specifically related to a kind of change rolling wing machine two that realizes and sidewinder the pitch-changing mechanism of wing size.
Background technology
Rolling wing machine is a kind of to use cycloid propeller to provide the aircraft of driving force.In current unmanned plane field, the common unmanned plane such as fixed-wing, many rotors has been obtained for utilization widely, in Small and micro-satellite research field, the good behaviour under low reynolds number of the flapping wing unmanned plane also result in the interest of many experts and scholars, and nowadays research worker research in terms of flapping wing unmanned plane also achieves certain achievement.And for comparing other common unmanned plane, rolling wing unmanned plane then seems the strangest, the mankind can trace back to nineteen thirties for the research of rolling wing machine in fact, but owing under the limiting factor of theoretical, material and scientific and technological level etc. at that time, its correlational study stagnates always, even without associated document during nineteen forty-three in last century was by 1998.
In recent years, under the developing rapidly of computer science and technology, computational methods and Aerodynamics are able to fast development and progress, and in terms of the research of rolling wing machine, people are more and more deep to the understanding of cycloid propeller.The most worldwide, the prominent university of the countries such as the U.S., Japan, Singapore, Israel, Korea S has carried out the correlational study to rolling wing machine the most, and achieves the achievement of preciousness.Northwestern Polytechnical University has the most successfully taken a flight test in 2011 " Hot Wheels " rolling wing unmanned plane, and repeatedly prize-winning in international unmanned plane contest, attracts wide attention.Various researchs show, rolling wing unmanned plane has and efficient promote efficiency and can provide vectored thrust, possess good maneuvering performance, and noise is little waits good characteristic, are suitable under low reynolds number environment flying.As can be seen here, rolling wing unmanned plane has suitable potential quality.Owing to its rolling wing exactly likes wheel, can be transformed into the amphibious unmanned plane in sky land, mechanism of the present invention i.e. proposes under this background technology, solves elongation and the difficult problem for shortening of rolling wing size.Further, since the low reynolds number characteristic of rolling wing unmanned plane, the most potential send Mars to, serve as the amphibious unmanned vehicle of accompanying flying of Marsokhod and perform inter-related task.
Although rolling wing unmanned plane possesses many merits and potential quality, but due to abundant not enough to its theoretic knowledge, the stability of rolling wing unmanned plane and lifting capacity etc. are also to need the problem researched and solved badly.But, under the development of current science and technology drives, we have reason to believe a day that it moves to maturity eventually, and belong to its application and the epoch are the most coming.
So far, the research mainly flight for rolling wing unmanned vehicle both at home and abroad controls and cycloid propeller pneumatic principle two aspect, not yet finds the pertinent literature record such as the invention device that combine rolling rotor aircraft with pitch-changing mechanism.But in terms of propeller, Northwestern Polytechnical University discloses a kind of propeller that can become oar footpath in the innovation and creation of Publication No. CN104943853A, the technical scheme of this invention is: along with the increase of revolution speed of propeller, the centrifugal force that blade self produces also is continuously increased.When centrifugal force overcomes reducing resistance, blade starts to be become oar footpath state from little oar footpath state；When blade oar footpath to big oar footpath state, its limited spring top bead is the most locked.When rotating speed drops to a certain degree, blade starts by big oar recovering state to little oar footpath state.These innovation and creation overcome existing active variable oar footpath propeller and compensate the shortcoming that weight is the biggest, it is proposed that a kind of can the propeller of feather.This type of propeller can adapt to the different operating modes in high-altitude and low latitude simultaneously.But this innovation and creation structure is complicated, volume is relatively big, is unsuitable for rolling wing unmanned vehicle.
Summary of the invention
For overcoming the deficiency being unsuitable for rolling wing unmanned vehicle present in prior art, the present invention proposes a kind of rolling wing pitch-changing mechanism.
The present invention includes 2 oar dishes, oar disk center axle, two grades of pitch change axes, one-level pitch change axes, spring, fairleads.Wherein said two grades of pitch change axes, one-level pitch change axes, spring 4 are identical with the quantity of fairlead, and on rolling wing machine 2 times of cycloid propeller quantity.The Adjustable length rod of rolling wing pitch-changing mechanism has been separately constituted by described two grades of pitch change axes, one-level pitch change axes, spring and fairlead.Described 2 oar dishes are separately mounted to the two ends of this oar disk center axle.Described Adjustable length rod is divided into 2 groups and is distributed on respectively on the circumference of described each oar dish, and is made up of the telescopic arm of a cycloid propeller a pair Adjustable length rod laid respectively on two oar dishes, and each rolling wing of aircraft links respectively on the top of each telescopic arm.This rolling wing pitch-changing mechanism has 2, and symmetrical is distributed in aircraft fuselage both sides.
1.5 times of the aperture Shi Jiang disk center shaft diameter of the centre bore of described oar dish.There is end plate at the two ends of this oar dish, this end plate has axis hole.The diameter of the aperture Jun Yujiang disk center axle of described axis hole is identical.External peripheral surface at this oar dish is evenly equipped with multiple spring via, and the quantity of this spring via is identical with the quantity of described one-level pitch change axes.
The internal diameter of described one-level pitch change axes is identical with the external diameter of fairlead, and the external diameter of this one-level pitch change axes is slightly larger than the aperture of the spring via being positioned at described oar dish external peripheral surface.Described one-level pitch change axes coordinates the inner face of one end to have the limiting stand of radially protruding with two grades of pitch change axes, the internal diameter of this limiting stand and the reduced diameter section matched in clearance of described two grades of pitch change axes；Prevent two grades of pitch change axes from deviating from from one-level pitch change axes by this limiting stand.
One end of described two grades of pitch change axes is stepped, and its maximum gauge is slightly less than the internal diameter of described fairlead, after making these two grades of pitch change axes load in this fairlead, and matched in clearance therebetween.The other end of described two grades of pitch change axes is faded to flat by rounded transitional, has the installing hole for fixing cycloid propeller in the termination of this flat.
Described fairlead is tubular.The wall thickness of the length of the axial length of this fairlead=one-level pitch change axes+oar dish；External diameter is identical with the internal diameter of one-level pitch change axes, and internal diameter is slightly larger than the external diameter of described spring 4.
Described each fairlead is respectively charged into and is fixed in the endoporus of each one-level pitch change axes；It is separately installed with spring in each fairlead.One end of described each two grades of pitch change axes is socketed with each fairlead respectively.
Oar dish in the present invention is fixed on oar disk center axle, and symmetrical is distributed in aircraft fuselage both sides.When aircraft rotates, this mechanism is driven to rotate by oar disk center axle.Described one-level pitch change axes is seamless with oar dish to be rigidly connected, and makes both become an entirety.Described spring is in the fairlead in one-level pitch change axes and one end and is fixedly linked with oar disk center axle oar dish is internal, and the other end and two grades of pitch change axes one end are fixedly linked.One end that described two grades of pitch change axes are connected with spring is nested among the fairlead of one-level pitch change axes, and the other end is hinged and connected with cycloid propeller.
The centrifugal force that the present invention utilizes rolling wing unmanned vehicle to produce when rotating the rolling wing realizes the elongation of support shaft, and the elastic force utilizing camber of spring to produce realizes the shortening of support shaft.Spring in the present invention is in elongation state all the time.When rolling wing pitch-changing mechanism and being static, under the pulling force effect of spring, two grades of pitch change axes major parts are nested in one-level pitch change axes, and now the size of rolling wing unmanned vehicle minimizes.The rotation of rolling wing pitch-changing mechanism produces under rotating shaft drives, when rotating speed ascending incremental time, centrifugal force increases the most therewith, when centrifugal force is more than the pulling force of spring, two grades of pitch change axes just start to do centrifugal motion along fairlead, in rolling wing unmanned vehicle flight course, rotating speed can be adjusted as the case may be and realize the manipulation to rolling wing size.When rotating speed is sufficiently large, the slip-preventing structure of two grades of pitch change axes ends can stop it to skid off one-level pitch change axes because of the effect of centrifugal force, and keeps this state, and now rolling wing unmanned vehicle is in full-size state, and spring 4 is also at the long status of stretching.Equally, rolling wing rotating speed is descending successively decrease time, the centrifugal force defecation suffered by two grades of pitch change axes is gradually reduced, when its centrifugal force is less than the pulling force of spring, two grades of pitch change axes are just shunk along one-level pitch change axes 3, are slowly returned to roll the minimum dimension state of wing unmanned vehicle.
The present invention based on rolling the current situation of wing unmanned plane now, in conjunction with to it in the prospect of future development, the technical scheme proposed is capable of rolling the pitch-changing mechanism that wing size is flexible.The centrifugal force that the present invention utilizes rolling wing own rotation to produce achieves the flexible of the rolling wing unmanned plane rolling wing so that it is is adapted to different ambient conditions, has expanded the application of rolling wing unmanned plane, such as, be transformed into the amphibious unmanned plane in sky land.The present invention also has simple in construction, less energy consumption, lightweight feature simultaneously.
Accompanying drawing explanation
Fig. 1 be the present invention with aircraft coordinate schematic diagram；
Fig. 2 is the structural representation of the present invention；
Fig. 3 is Adjustable length rod sectional view when reaching maximal tensility；
Fig. 4 is the schematic diagram after Adjustable length rod shrinks；
Fig. 5 is the schematic diagram of reel；
Fig. 6 is that the A-A of Fig. 5 is to schematic diagram；
Fig. 7 is the structural representation of two grades of pitch change axes；
Fig. 8 is the structural representation of one-level pitch change axes；
Fig. 9 is the structural representation after Adjustable length rod shrinks；
Figure 10 is Adjustable length rod structural representation when reaching maximal tensility；
Figure 11 be two grades of pitch change axes with one-level pitch change axes coordinate schematic diagram.In figure:
1. oar dish；2. two grades of pitch change axes；3. one-level pitch change axes；4. spring；5. oar disk center axle；6. cycloid propeller；7. fairlead.
Detailed description of the invention
The present embodiment is a kind of rolling wing pitch-changing mechanism, and this rolling wing pitch-changing mechanism has 2, and symmetrical is distributed in aircraft fuselage both sides.The structure of described 2 rolling wing pitch-changing mechanisms is identical, and the present embodiment is illustrated as a example by one of them.
Described rolling wing pitch-changing mechanism includes 2 oar dishes 1, oar disk center axle 5, two grades of pitch change axes 2, one-level pitch change axes 3, spring 4, fairleads 7.Wherein said two grades of pitch change axes 2, one-level pitch change axes 3, spring 4 are identical with the quantity of fairlead 7, and on rolling wing machine 2 times of cycloid propeller quantity.
Described each fairlead 7 is respectively charged into and is fixed in the endoporus of described each one-level pitch change axes 3；Spring 4 it is separately installed with in each fairlead.One end of described each two grades of pitch change axes 2 is socketed with each fairlead 7 respectively.The Adjustable length rod of rolling wing pitch-changing mechanism has been separately constituted by described two grades of pitch change axes 2, one-level pitch change axes 3, spring 4 and fairlead 7.
Described 2 oar dishes 1 are separately mounted to the two ends of this oar disk center axle 5.Described Adjustable length rod is divided into 2 groups and is distributed on respectively on the circumference of described each oar dish 1, and is made up of the telescopic arm of a cycloid propeller a pair Adjustable length rod laid respectively on two oar dishes 1, and each rolling wing of aircraft links respectively on the top of each telescopic arm.
Described oar dish 1 is hollow revolving body.1.5 times of the aperture Shi Jiang disk center shaft diameter of this oar center hole.There is end plate at the two ends of this oar dish, this end plate has axis hole.The diameter of the aperture Jun Yujiang disk center axle of described axis hole is identical.External peripheral surface at this oar dish is evenly equipped with multiple spring via, and the quantity of this spring via is identical with the quantity of described one-level pitch change axes 3.In the present embodiment, the quantity of described spring via is 4.After described each spring is respectively charged in this via, matched in clearance between spring and via, to meet the space requirement needed for spring contraction.
Described one-level pitch change axes 3 is hollow housing.The internal diameter of this one-level pitch change axes is identical with the external diameter of fairlead 7, and the external diameter of this one-level pitch change axes is slightly larger than the aperture of the spring via being positioned at described oar dish external peripheral surface.Described one-level pitch change axes 3 coordinates the inner face of one end to have the limiting stand of radially protruding with two grades of pitch change axes 2, the internal diameter of this limiting stand and the reduced diameter section matched in clearance of described two grades of pitch change axes；Prevent two grades of pitch change axes 2 from deviating from from one-level pitch change axes by this limiting stand.
One end of described two grades of pitch change axes 2 is stepped, and its maximum gauge is slightly less than the internal diameter of described fairlead 7, after making these two grades of pitch change axes load in this fairlead, and matched in clearance therebetween.The other end of described two grades of pitch change axes 2 is faded to flat by rounded transitional, has the installing hole for fixing cycloid propeller 6 in the termination of this flat.
Described spring 4 is tension spring, and spring terminal arranges long drag hook or semicircle drag hook.Described spring, in the case of not stressing, is in closure state, does not i.e. have space between turn.Spring 4 is positioned in fairlead 7, and diameter is slightly less than fairlead 7 so that it is normally can work in fairlead 7.
Described fairlead 7 is tubular.The wall thickness of the length of the axial length of this fairlead=one-level pitch change axes+oar dish；External diameter is identical with the internal diameter of one-level pitch change axes 3, and internal diameter is slightly larger than the external diameter of described spring 4.
Claims (7)
1. a rolling wing pitch-changing mechanism, it is characterised in that include 2 oar dishes, oar disk center axle, two grades of pitch change axes, one-level pitch change axes, spring, fairleads；Wherein said two grades of pitch change axes, one-level pitch change axes, spring 4 are identical with the quantity of fairlead, and on rolling wing machine 2 times of cycloid propeller quantity；The Adjustable length rod of rolling wing pitch-changing mechanism has been separately constituted by described two grades of pitch change axes, one-level pitch change axes, spring and fairlead；Described 2 oar dishes are separately mounted to the two ends of this oar disk center axle；Described Adjustable length rod is divided into 2 groups and is distributed on respectively on the circumference of described each oar dish, and is made up of the telescopic arm of a cycloid propeller a pair Adjustable length rod laid respectively on two oar dishes, and each rolling wing of aircraft links respectively on the top of each telescopic arm.
2. a kind of rolling wing pitch-changing mechanism, it is characterised in that 1.5 times of the aperture Shi Jiang disk center shaft diameter of the centre bore of described oar dish；There is end plate at the two ends of this oar dish, this end plate has axis hole；The diameter of the aperture Jun Yujiang disk center axle of described axis hole is identical；External peripheral surface at this oar dish is evenly equipped with multiple spring via, and the quantity of this spring via is identical with the quantity of described one-level pitch change axes.
3. a kind of rolling wing pitch-changing mechanism, it is characterised in that the internal diameter of described one-level pitch change axes is identical with the external diameter of fairlead, and the external diameter of this one-level pitch change axes is slightly larger than the aperture of the spring via being positioned at described oar dish external peripheral surface；Described one-level pitch change axes coordinates the inner face of one end to have the limiting stand of radially protruding with two grades of pitch change axes, the internal diameter of this limiting stand and the reduced diameter section matched in clearance of described two grades of pitch change axes；Prevent two grades of pitch change axes from deviating from from one-level pitch change axes by this limiting stand.
4. a kind of rolling wing pitch-changing mechanism, it is characterised in that one end of described two grades of pitch change axes is stepped, and its maximum gauge is slightly less than the internal diameter of described fairlead, after making these two grades of pitch change axes load in this fairlead, matched in clearance therebetween；The other end of described two grades of pitch change axes is faded to flat by rounded transitional, has the installing hole for fixing cycloid propeller in the termination of this flat.
5. a kind of rolling wing pitch-changing mechanism, it is characterised in that described fairlead is tubular；The wall thickness of the length of the axial length of this fairlead=one-level pitch change axes+oar dish；External diameter is identical with the internal diameter of one-level pitch change axes, and internal diameter is slightly larger than the external diameter of described spring 4.
6. a kind of rolling wing pitch-changing mechanism, it is characterised in that described each fairlead is respectively charged into and is fixed in the endoporus of each one-level pitch change axes；It is separately installed with spring in each fairlead；One end of described each two grades of pitch change axes is socketed with each fairlead respectively.
7. a kind of rolling wing pitch-changing mechanism, it is characterised in that this rolling wing pitch-changing mechanism has 2, and symmetrical is distributed in aircraft fuselage both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620164545.0U CN205440871U (en) | 2016-03-03 | 2016-03-03 | Roll wing pitch -changing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620164545.0U CN205440871U (en) | 2016-03-03 | 2016-03-03 | Roll wing pitch -changing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205440871U true CN205440871U (en) | 2016-08-10 |
Family
ID=56605549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620164545.0U Expired - Fee Related CN205440871U (en) | 2016-03-03 | 2016-03-03 | Roll wing pitch -changing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205440871U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620749A (en) * | 2016-03-03 | 2016-06-01 | 三翼航空科技南通有限公司 | Rollin wing variable pitch mechanism |
| CN106321371A (en) * | 2016-11-07 | 2017-01-11 | 郑志刚 | Cycloid paddle capable of being used for wind power, hydropower, navigation and aviation |
-
2016
- 2016-03-03 CN CN201620164545.0U patent/CN205440871U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620749A (en) * | 2016-03-03 | 2016-06-01 | 三翼航空科技南通有限公司 | Rollin wing variable pitch mechanism |
| CN106321371A (en) * | 2016-11-07 | 2017-01-11 | 郑志刚 | Cycloid paddle capable of being used for wind power, hydropower, navigation and aviation |
| CN106321371B (en) * | 2016-11-07 | 2018-09-18 | 郑志刚 | It is a kind of can be used for wind-powered electricity generation, water power, navigation, aviation cycloid slurry |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101863306B (en) | Omnidirectional vectored thrust cycloidal propeller | |
| CN106005389B (en) | Lifting airscrew compound motion parallel drive unit | |
| CN202896880U (en) | Spherical micro unmanned aerial vehicle | |
| CN105620749A (en) | Rollin wing variable pitch mechanism | |
| CN205440871U (en) | Roll wing pitch -changing mechanism | |
| WO2016138139A1 (en) | Solar powered aircraft with a variable geometry wing and telecommunications networks utilizing such aircraft | |
| CN106427438A (en) | Airphibian with retractable rotor and control method of airphibian with retractable rotor | |
| CN103287570A (en) | Z-shaped folding wing mechanism | |
| CN104943853B (en) | A kind of screw for being capable of reducing | |
| CN102556335B (en) | Flying-wing layout aircraft provided with cycloidal propellers | |
| CN106470899A (en) | The elimination torque of propeller type VTOL flying object and compatible device of keeping in balance | |
| CN102963525A (en) | Unmanned aerial vehicle | |
| CN201712785U (en) | Cycloidal propeller | |
| CN107933892A (en) | Inflatable propeller | |
| CN106275422A (en) | A kind of variable speed rigid rotor aircraft propeller hub | |
| CN201321159Y (en) | Unmanned aircraft with vertical ducts | |
| JP2008106619A (en) | Composite magnus wing | |
| CN206871360U (en) | A kind of multiple degrees of freedom flapping-wing modal with high propulsive efficiency | |
| CN115123533A (en) | Mixed rotor configuration coaxial unmanned aerial vehicle | |
| CN208915439U (en) | Adjustable wing swallow shape simulation type unmanned plane | |
| CN102849210A (en) | Spherical small unmanned aircraft | |
| CN103693195B (en) | A kind of minute vehicle | |
| CN207157510U (en) | A kind of air-ground amphibious MAV | |
| CN109850144B (en) | Solar flapping wing bionic aircraft | |
| CN103552688A (en) | Flapping wing and rotary wing coupling configuration and corresponding minitype aircraft design |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180528 Address after: 710065 room 10908, block B, electronic community, western section of electronic road, Xi'an High-tech Zone, Shaanxi, China Co-patentee after: SANYI AVIATION TECHNOLOGY NANTONG CO., LTD. Patentee after: Xi'an three wing Aviation Technology Co., Ltd. Address before: 226399 Sheng Fa science and Technology Park, 299 Xingyuan Road, Nantong, Jiangsu Patentee before: SANYI AVIATION TECHNOLOGY NANTONG CO., LTD. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160810 Termination date: 20200303 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |