CN105620749A - Rollin wing variable pitch mechanism - Google Patents
Rollin wing variable pitch mechanism Download PDFInfo
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- CN105620749A CN105620749A CN201610122372.0A CN201610122372A CN105620749A CN 105620749 A CN105620749 A CN 105620749A CN 201610122372 A CN201610122372 A CN 201610122372A CN 105620749 A CN105620749 A CN 105620749A
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- pitch change
- change axes
- oar
- grades
- spring
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- 230000007246 mechanism Effects 0.000 title claims abstract description 31
- 238000005096 rolling process Methods 0.000 claims abstract description 33
- 238000006073 displacement reaction Methods 0.000 claims description 23
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 230000004323 axial length Effects 0.000 claims description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000018109 developmental process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000004904 shortening Methods 0.000 description 2
- 241000271460 Crotalus cerastes Species 0.000 description 1
- 244000225256 Gaillardia pulchella Species 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 210000002700 urine Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Springs (AREA)
Abstract
A rolling wing variable pitch mechanism comprises two propeller disks, a propeller disk center shaft, a second-stage variable pitch shaft, a first-stage variable pitch shaft, a spring and a guiding sleeve. The second-stage variable pitch shaft, the first-stage variable pitch shaft, the spring and the guiding sleeve form variable pitch rods of the rolling wing variable pitch mechanism. The two propeller disks are installed at the two ends of the propeller disk center shaft respectively. The variable pitch rods are divided into to two groups and evenly distributed on the circumferences of the propeller disks, each pair of variable pitch rods located on the two propeller disks form a telescopic arm of a cycloid propeller, and rolling wings of an aircraft are hinged to the top ends of the telescopic arms respectively. Two rolling wing variable pitch mechanisms are arranged and symmetrically distributed on the two sides of an aircraft airframe. By means of centrifugal force generated due to rotation of the rolling wings, telescopic movement of the rolling wings of the rolling wing unmanned aerial vehicle is achieved, the variable pitch mechanism with the changeable rolling wing size is obtained and can adapt to different environment states, application of the rolling wing unmanned aerial vehicle is widened, and meanwhile the rolling wing variable pitch mechanism has the advantages of being simple in structure, small in energy consumption and light in weight.
Description
Technical field
The invention belongs to field of mechanical technique, be specifically related to a kind of realize changing roll the displacement mechanism that wing machine two sidewinders wing size size.
Background technology
Rolling wing machine is a kind of use cycloid oar to provide the aircraft of motivating force. Current without man-machine field, it is fixing that the wing, many rotors etc. are common has obtained utilization widely without man-machine, in Small and micro-satellite research field, flapping wing also result in the interest of many experts and scholars without man-machine good behaviour under low reynolds number, and nowadays researchist also achieves certain achievement at flapping wing without the research in man-machine. And it is common without man-machine to compare other, roll the wing without man-machine, seem very strange, the mankind can trace back to nineteen thirties for the research rolling wing machine in fact, but owing under the limiting factor of theoretical, material and scientific and technological level etc. at that time, its correlative study stagnates always, during nineteen forty-three in last century was by 1998, even there is no associated document.
In recent years, under the develop rapidly of computer science and technology, method of calculation and Aerodynamics are able to fast development and progress, and in the research rolling wing machine, people are also more and more deep to the understanding of cycloid oar. Worldwide, nowadays the prominent university of the country such as the U.S., Japan, Singapore, Israel, Korea S has been carried out the correlative study rolling wing machine all, and achieves valuable achievement. Northwestern Polytechnical University once successfully taken a flight test in 2011 " wind fire wheel " roll the wing without man-machine, and repeatedly prize-winning in the world is without man-machine contest, attract wide attention. Various research shows, rolling the unmanned facility of the wing has and efficiently promote efficiency and can provide vector thrust, possesses good steering characteristics, and the good characteristic such as noise is little, flies under being adapted at low reynolds number environment. It thus is seen that roll the unmanned facility of the wing have suitable potential quality. Exactly liking wheel owing to it rolls the wing, can be transformed into sky land amphibious without man-machine, namely mechanism of the present invention proposes under this background technology, solves a difficult problem for elongation and the shortening rolling wing size. In addition, owing to rolling the wing without man-machine low reynolds number characteristic, very potential send Mars to, serve as the amphibious unmanned flight's device of accompanying flying of Marsokhod and perform inter-related task.
Although rolling the unmanned facility of the wing for numerous advantage and potential quality, but owing to its theoretic knowledge is abundant not enough, rolling the wing without man-machine stability and weight-carrying ability etc. is also 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 also coming.
So far, both at home and abroad for research mainly flight controlling and cycloid oar pneumatic principle two aspect rolling wing unmanned flight's device, not yet find to roll the pertinent literature records such as contrive equipment that rotor aircraft combines with displacement mechanism. But in water screw, Northwestern Polytechnical University discloses a kind of water screw that can become oar footpath in the innovation and creation that publication number is CN104943853A, the technical scheme of this invention is: along with the increase of propeller speed, and the centrifugal force that blade self produces also constantly increases. When centrifugal force overcomes reducing resistance, blade starts to turn into oar footpath state from little oar footpath state; When blade oar footpath is to big oar footpath state, its limited spring top bead is locked extremely again. When rotating speed drops to a certain degree, blade starts to return to little oar footpath state by big paddle state. These innovation and creation overcome existing active variable oar footpath water screw and compensate the too big shortcoming of weight, it is proposed that a kind of can the water screw of feather. This type of water screw can adapt to the different operating modes in high-altitude and low latitude simultaneously. But this innovation and creation complex structure, volume is relatively big, is unsuitable for rolling wing unmanned flight's device.
Summary of the invention
The deficiency being unsuitable for rolling wing unmanned flight's device existed for overcoming in prior art, the present invention proposes a kind of Gun Yi displacement mechanism.
The present invention comprises 2 oar dishes, oar disk center axle, two grades of pitch change axes, one-level pitch change axes, spring, orienting sleeves. Wherein said two grades of pitch change axes, one-level pitch change axes, spring 4 are identical with the quantity of orienting sleeve, and for rolling 2 times of cycloid oar quantity on wing machine. The Adjustable length rod of Gun Yi displacement mechanism is constituted respectively by described two grades of pitch change axes, one-level pitch change axes, spring and orienting sleeve. Described 2 oar dishes are arranged on the two ends of this oar disk center axle respectively. Described Adjustable length rod is divided into 2 groups and is distributed on described each oar dish respectively circumferentially, and Adjustable length rod forms the telescopic boom of a cycloid oar by lay respectively on two oar dishes one, and the wing that respectively rolls of aircraft links respectively on the top of each telescopic boom. This Gun Yi displacement 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 hole 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 and crosses hole, and the quantity that hole crossed by this spring 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 orienting sleeve, and the external diameter of this one-level pitch change axes crosses the aperture in hole slightly larger than the spring 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 radial protrusion, the internal diameter of this limiting stand and the reduced diameter section running fit of described two grades of pitch change axes with 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 ladder shape, and its maximum diameter is slightly less than the internal diameter of described orienting sleeve, these two grades of pitch change axes is loaded after in this orienting sleeve, running fit therebetween. The other end of described two grades of pitch change axes fades to flat tabular by rounded transitional, has the open holes for fixing cycloid oar in the termination of this flat plate.
Described orienting sleeve is tubular. The wall thickness of the length of the axial length of this orienting sleeve=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 orienting sleeve is respectively charged into and is fixed in the interior hole of each one-level pitch change axes; It is separately installed with spring in each orienting sleeve. One end of described each two grades of pitch change axes is socketed with each orienting sleeve 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 and oar dish is seamless is rigidly connected, makes both become as a whole. The orienting sleeve that described spring is in one-level pitch change axes and one end are fixedly linked with oar disk center axle oar dish is inner, 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 orienting sleeve of one-level pitch change axes, and the other end and cycloid oar are hinged and connected.
The present invention utilizes and rolls the elongation that wing unmanned flight's device rotates the centrifugal force realization support axle produced when rolling the wing, and the elastic force utilizing spring distortion to produce realizes the shortening of support axle. Spring in the present invention is in elongation state all the time. When Gun Yi displacement mechanism is 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 the size now rolling wing unmanned flight's device reaches minimum. The rotation of Gun Yi displacement mechanism produces under rotating shaft drives, when rotating speed by little to when increasing progressively greatly, centrifugal force also increases thereupon, when centrifugal force is greater than the pulling force of spring, two grades of pitch change axes just start to do centrifugal motion along orienting sleeve, rolling in wing unmanned flight's device flight course, it is possible to adjust rotating speed according to particular case and realize the manipulation rolling wing size. When rotating speed is enough big, 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, now rolls wing unmanned flight's device and is in overall dimension state, and spring 4 is also in the most long status of stretching. Equally, rolling wing rotating speed by, time greatly to little successively decreasing, the centrifugal force stool and urine suffered by two grades of pitch change axes reduces gradually, 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 the minimum size state rolling wing unmanned flight's device.
The present invention is based on rolling the wing now without man-machine current situation, and in conjunction with the prospect it developed in future, the technical scheme proposed can realize rolling the flexible displacement mechanism of wing size size. The present invention utilizes and rolls the centrifugal force that wing own rotation produces and achieve and roll the wing and roll the flexible of the wing without man-machine so that it is is adapted to different environment states, has expanded and rolled the wing without man-machine application, such as, is transformed into sky land amphibious without man-machine. It is simple that the present invention simultaneously also has structure, less energy consumption, lightweight feature.
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 the sectional view of Adjustable length rod 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 the structural representation of Adjustable length rod 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 oar; 7. orienting sleeve.
Embodiment
The present embodiment is a kind of Gun Yi displacement mechanism, and this Gun Yi displacement mechanism has 2, and symmetrical is distributed in aircraft fuselage both sides. The structure of described 2 Ge Gunyi displacement mechanisms is identical, and the present embodiment is illustrated for one of them.
Described Gun Yi displacement mechanism comprises 2 oar dishes 1, oar disk center axle 5, two grades of pitch change axes 2, one-level pitch change axes 3, spring 4, orienting sleeves 7. Wherein said two grades of pitch change axes 2, one-level pitch change axes 3, spring 4 are identical with the quantity of orienting sleeve 7, and for rolling 2 times of cycloid oar quantity on wing machine.
Described each orienting sleeve 7 is respectively charged into and is fixed in the interior hole of described each one-level pitch change axes 3; Spring 4 it is separately installed with in each orienting sleeve. One end of described each two grades of pitch change axes 2 is socketed with each orienting sleeve 7 respectively. The Adjustable length rod of Gun Yi displacement mechanism is constituted respectively by described two grades of pitch change axes 2, one-level pitch change axes 3, spring 4 and orienting sleeve 7.
Described 2 oar dishes 1 are arranged on the two ends of this oar disk center axle 5 respectively. Described Adjustable length rod is divided into 2 groups and is distributed on described each oar dish 1 respectively circumferentially, and Adjustable length rod forms the telescopic boom of a cycloid oar by lay respectively on two oar dishes 1 one, and the wing that respectively rolls of aircraft links respectively on the top of each telescopic boom.
Described oar dish 1 is hollow solid of revolution. 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 and crosses hole, and the quantity that hole crossed by this spring is identical with the quantity of described one-level pitch change axes 3. In the present embodiment, the quantity in hole crossed by described spring is 4. Crossing after in hole when described each spring is respectively charged into this, spring and excessively running fit between hole, 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 orienting sleeve 7, and the external diameter of this one-level pitch change axes crosses the aperture in hole slightly larger than the spring 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 radial protrusion, the internal diameter of this limiting stand and the reduced diameter section running fit of described two grades of pitch change axes with two grades of pitch change axes 2; 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 ladder shape, and its maximum diameter is slightly less than the internal diameter of described orienting sleeve 7, these two grades of pitch change axes is loaded after in this orienting sleeve, running fit therebetween. The other end of described two grades of pitch change axes 2 fades to flat tabular by rounded transitional, has the open holes for fixing cycloid oar 6 in the termination of this flat plate.
Described spring 4 is pulling force spring, and spring terminal arranges long drag hook or semicircle drag hook. Described spring, when not stressing, is in closed state, does not namely have space between spring ring. Spring 4 is arranged in orienting sleeve 7, and diameter is slightly less than orienting sleeve 7 so that it is can in orienting sleeve 7 normal operation.
Described orienting sleeve 7 is tubular. The wall thickness of the length of the axial length of this orienting sleeve=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 Zhong Gunyi displacement mechanism, it is characterised in that, comprise 2 oar dishes, oar disk center axle, two grades of pitch change axes, one-level pitch change axes, spring, orienting sleeves; Wherein said two grades of pitch change axes, one-level pitch change axes, spring 4 are identical with the quantity of orienting sleeve, and for rolling 2 times of cycloid oar quantity on wing machine; The Adjustable length rod of Gun Yi displacement mechanism is constituted respectively by described two grades of pitch change axes, one-level pitch change axes, spring and orienting sleeve; Described 2 oar dishes are arranged on the two ends of this oar disk center axle respectively; Described Adjustable length rod is divided into 2 groups and is distributed on described each oar dish respectively circumferentially, and Adjustable length rod forms the telescopic boom of a cycloid oar by lay respectively on two oar dishes one, and the wing that respectively rolls of aircraft links respectively on the top of each telescopic boom.
2. Gun Yi displacement mechanism as claimed in claim 1, it is characterised in that, 1.5 times of the aperture Shi Jiang disk center shaft diameter of the centre hole 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 and crosses hole, and the quantity that hole crossed by this spring is identical with the quantity of described one-level pitch change axes.
3. Gun Yi displacement mechanism as claimed in claim 1, it is characterised in that, the internal diameter of described one-level pitch change axes is identical with the external diameter of orienting sleeve, and the external diameter of this one-level pitch change axes crosses the aperture in hole slightly larger than the spring 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 radial protrusion, the internal diameter of this limiting stand and the reduced diameter section running fit of described two grades of pitch change axes with 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. Gun Yi displacement mechanism as claimed in claim 1, it is characterised in that, one end of described two grades of pitch change axes is ladder shape, and its maximum diameter is slightly less than the internal diameter of described orienting sleeve, these two grades of pitch change axes is loaded after in this orienting sleeve, running fit therebetween; The other end of described two grades of pitch change axes fades to flat tabular by rounded transitional, has the open holes for fixing cycloid oar in the termination of this flat plate.
5. a Zhong Gunyi displacement mechanism, it is characterised in that, described orienting sleeve is tubular; The wall thickness of the length of the axial length of this orienting sleeve=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. Gun Yi displacement mechanism as claimed in claim 1, it is characterised in that, described each orienting sleeve is respectively charged into and is fixed in the interior hole of each one-level pitch change axes; It is separately installed with spring in each orienting sleeve; One end of described each two grades of pitch change axes is socketed with each orienting sleeve respectively.
7. Gun Yi displacement mechanism as claimed in claim 1, it is characterised in that, this Gun Yi displacement mechanism has 2, and symmetrical is distributed in aircraft fuselage both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610122372.0A CN105620749A (en) | 2016-03-03 | 2016-03-03 | Rollin wing variable pitch mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610122372.0A CN105620749A (en) | 2016-03-03 | 2016-03-03 | Rollin wing variable pitch mechanism |
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| CN105620749A true CN105620749A (en) | 2016-06-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201610122372.0A Pending CN105620749A (en) | 2016-03-03 | 2016-03-03 | Rollin wing variable pitch mechanism |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107225925A (en) * | 2017-05-23 | 2017-10-03 | 南京航空航天大学 | Being dwelt a kind of rolling wing VTOL aircraft more |
| CN108163195A (en) * | 2018-01-08 | 2018-06-15 | 南京航空航天大学 | A kind of four axis rolling rotor aircraft |
| CN109229370A (en) * | 2018-11-15 | 2019-01-18 | 邱子航 | A kind of drum-type telescopic rotor device |
| CN111688921A (en) * | 2020-06-19 | 2020-09-22 | 中国民航大学 | Rolling wing aircraft |
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