CN203996884U - Four-axle aircraft motor system - Google Patents
Four-axle aircraft motor system Download PDFInfo
- Publication number
- CN203996884U CN203996884U CN201420369255.0U CN201420369255U CN203996884U CN 203996884 U CN203996884 U CN 203996884U CN 201420369255 U CN201420369255 U CN 201420369255U CN 203996884 U CN203996884 U CN 203996884U
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- motor
- cantilever
- supporting piece
- support element
- screw
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Abstract
The utility model discloses a kind of four-axle aircraft motor system, this four-axle aircraft motor system comprises four S. A.s, eight motors and eight screw propellers, two motors and two screw propellers are installed on each S. A., in order to guarantee the centre of gration conllinear of two motors on same S. A., by two consistent strut members of specification, connect respectively two motors, again above-mentioned two strut members are connected, for above-mentioned two motors and two strut members are mounted and fixed on to the assigned address in cantilever, cantilever is split into removable cantilever main body and cantilever bottom, and cantilever main body and cantilever bottom are affixed by bolt, thereby two motors and two strut members are all fixedly mounted in cantilever.
Description
Technical field
The utility model relates to a kind of aircraft motor system, is specifically related to a kind of four-axle aircraft motor system.
Background technology
Four-axle aircraft is also referred to as four-rotor helicopter, it is a kind of aircraft that has four S. A.s and four screw propellers, it is a kind of minute vehicle, also be a kind of intelligent robot, four-axle aircraft utilizes four rotors to carry out airflight as flight engine, and its size is less, weight is light, be applicable to carrying, and can carry certain mission payload, meanwhile, four-axle aircraft possesses autonomous navigation flight performance, can under complicated, dangerous environment, complete specific aerial mission.But still there are a lot of defects in four-axle aircraft of the prior art, as not ideal enough in flying speed, aircraft underaction, flight safety is not high, is prone to accidents and crash etc.
For above-mentioned reasons, the inventor carries out in-depth study to existing vehicle technology, to design the course of new aircraft that can address the above problem, it is flight safety, flying speed is fast, aircraft more flexibly, final discovery can achieve the above object by special four-axle aircraft motor system is set.
Utility model content
In order to overcome the problems referred to above, the inventor has carried out research with keen determination, design a kind of four-axle aircraft motor system, this four-axle aircraft motor system comprises four S. A.s, eight motors and eight screw propellers, two motors and two screw propellers are installed on each S. A., in order to guarantee the centre of gration conllinear of two motors on same S. A., by two consistent strut members of specification, connect respectively two motors, again above-mentioned two strut members are connected, for above-mentioned two motors and two strut members are mounted and fixed on to the assigned address in cantilever, cantilever is split into removable cantilever main body and cantilever bottom, and cantilever main body and cantilever bottom are affixed by bolt, thereby make two motors and two strut members all be fixedly mounted in cantilever, thereby complete the utility model.
Specifically, the purpose of this utility model is to provide following aspect:
(1) a kind of four-axle aircraft motor system, it is characterized in that, this motor system comprises: upper motor 1 and lower motor 2 that center of gyration overlaps, and the rotor of upper motor 1 upward, the rotor of lower motor 2 down, between upper motor 1 and lower motor 2, be provided with consistent and upper supporting piece 3 and the lower support elements 4 in the form of annular discs all of specification
Wherein, upper supporting piece 3 is affixed by screw and upper motor 1, and lower support element 4 is affixed by screw and lower motor 2,
Between upper supporting piece 3 and lower support element 4, be provided with sleeve 5, bolt passes lower support element 4, sleeve 5 and upper supporting piece 3 from bottom to top successively, and coordinates and screw with nut;
Four-axle aircraft comprises aircraft body 6 and four cantilevers 7, described cantilever comprises cantilever main body 71 and is removably mounted on the cantilever bottom 72 in cantilever main body 71, at cantilever, away from one end of aircraft body, offer the vertical hole that holds motor, lower motor and upper supporting piece and lower support element, described vertical hole is from top to bottom successively through cantilever main body 71 and cantilever bottom 72.
(2) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that there are four for the screw of affixed upper supporting piece 3 and upper motor 1, described four screws are evenly distributed in the position near upper supporting piece center.
(3) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that there are four for the screw of affixed lower support element 4 and lower motor 2, described four screws are evenly distributed in the position near lower support element center.
(4) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that, on the rotor of upper motor 1 and lower motor 2, be separately installed with screw propeller.
(5) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that, in upper supporting piece 3 disc face, near center position, four tapped bore are set, in lower support element 4 disc face, near center position, four tapped bore are set.
(6) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that, the height of sleeve is more than the twice of screw termination 11 thickness.
(7) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that, in upper supporting piece 3 position that keeps to the side, offer evenly distributedly four upper through holes 31 that pass for bolts, accordingly, in lower support element 4 position that keeps to the side, offer evenly distributedly four lower through-holes 41 that pass for bolts, bolt passes the upper through hole of lower through-hole, sleeve and the upper supporting piece of lower support element from bottom to top successively, and coordinates and screw with nut.
(8) according to the four-axle aircraft motor system above-mentioned (1) Suo Shu, it is characterized in that, between cantilever main body 71 and cantilever bottom 72, pass through screw-tightened, and cantilever main body 71 and cantilever bottom 72 connection locations are coated with to waterproof layer.
The beneficial effect that the utility model has comprises:
(1) motor system providing according to the utility model, comes affixed upper motor and lower motor by the consistent upper supporting piece of structure and lower support element, makes the centering of motor and lower motor good, has guaranteed that the center of gyration of two motors overlaps.
(2) motor system providing according to the utility model, by the bolted between cantilever main body and cantilever bottom, fix two motors and two systems that strut member forms, make motor system simple in structure, field-strip is convenient, adopt water-proofing treatment simultaneously, made aircraft sealing property better.
(3) four-axle aircraft in the utility model has eight screw propellers, controls respectively by eight motors, makes aircraft more flexible, and flying speed is fast.
(4) aircraft in the utility model has eight screw propellers, even if there are even several screw propellers to damage or et out of order, other screw propeller still can normally be worked, and makes the aircraft recurrence of can landing safely, has avoided the aircraft damage of crashing.
Accompanying drawing explanation
Fig. 1 illustrates according to the lower motor of a kind of preferred implementation of the utility model and lower support element installation and is related to schematic diagram;
Fig. 2 illustrates according to the aircraft motor system integral structure of a kind of preferred implementation of the utility model and installs and be related to schematic diagram;
Fig. 3 illustrates according to the cantilever main body of a kind of preferred implementation of the utility model and the installation of cantilever bottom and is related to schematic diagram;
Fig. 4 illustrates the aircraft integral structure schematic diagram according to a kind of preferred implementation of the utility model.
Drawing reference numeral explanation:
The upper motor of 1-
11-screw termination
Motor under 2-
3-upper supporting piece
4-lower support element
5-sleeve
6-aircraft body
7-cantilever
71-cantilever main body
72-cantilever bottom
The specific embodiment
Below by drawings and Examples, the utility model is further described.By these explanations, it is more explicit that feature of the present utility model and advantage will become.
Here special-purpose word " exemplary " means " as example, embodiment or illustrative ".Here as " exemplary " illustrated any embodiment, needn't be interpreted as being better than or being better than other embodiment.Although the various aspects of embodiment shown in the drawings, unless otherwise indicated, needn't draw accompanying drawing in proportion.
A kind of four-axle aircraft motor system providing according to the utility model, as Fig. 1, Fig. 2, Fig. 3, shown in Fig. 4, this system comprises two motors, the dead in line of two motors, and the rotor of two motors outwardly, two motors are respectively the upper motor 1 that is positioned at top and the lower motor 2 that is positioned at below, wherein, between two motors, be provided with two strut members, be respectively upper supporting piece 3 and lower support element 4, upper supporting piece 3 is connected with upper motor, lower support element 4 is connected with lower motor 2, between two strut members, by bolt, be connected, and then upper and lower two motors are fixed as one, again described two motors that are fixed as one are extend in the through hole of cantilever 5 one sides, upper motor stretches out from through hole, upper supporting piece is stuck in through hole, again cantilever bottom 72 is enclosed within to lower motor outside, simultaneously that cantilever bottom and cantilever main body is fastening, and then complete the assembling of whole motor system.
One preferred embodiment in, as shown in fig. 1, affixed by screw between upper motor and upper supporting piece, on upper motor and upper supporting piece, be respectively arranged with reserved tapped bore, four tapped bore are preferably set respectively, by through the tapped bore of upper supporting piece and be screwed into screw in upper motor tapped bore be connected upper motor and upper supporting piece in the utility model.Answer in contrast ground, on lower motor and lower support element, be respectively arranged with reserved tapped bore, four tapped bore are preferably set respectively, by through the tapped bore of lower support element and be screwed into screw in lower motor tapped bore be connected lower motor and lower support element in the utility model.
In further preferred embodiment, as shown in Figure 2, upper motor is consistent with the planform of lower motor, size, the shape of upper supporting piece and lower support element are consistent, preferably, upper supporting piece and identical Mould Machining casting for lower support element, to save production cost.
One preferred embodiment in, as shown in fig. 1, all in the form of annular discs at upper supporting piece and lower support element, above-mentionedly for the screw thread being connected with motor, start on disk the position near middle part, at upper supporting piece and lower support element, near disk border position, four through holes are set respectively, this through hole passes through for bolt, and this through hole is all well-distributed, the lead to the hole site of upper supporting piece is corresponding with the lead to the hole site of lower support element, the diameter dimension of through hole is slightly larger than the bolt shank diameter through through hole, and is less than the diameter of nut.
One preferred embodiment in, as shown in Fig. 2, Fig. 3, affixed between upper motor and upper supporting piece, and descend afterwards affixed between motor and lower support element after, can carry out affixed between upper and lower two motors.Between upper and lower two strut members, be also placed with the sleeve of playing a supporting role, sleeve shares four, with above-mentioned through hole to mating, bolt for fixing upper lower support element passes the through hole on through hole, sleeve and the upper supporting piece on lower support element from bottom to top successively, by nut, be tightened, that is, four bolts and four nuts screw cooperation again, make the common clamp sleeve of upper supporting piece and lower support element, and be fixedly connected with as a whole.The object that above-mentioned sleeve is set is to avoid upper and lower two strut members to stick together, and after strut member and motor are affixed by screw, the screw termination 11 of screw root is stayed on the surface that upper supporting piece is adjacent with lower support element, accordingly, four screw terminations on lower support element upper surface, have also been retained, make can not fit completely between upper supporting piece and lower support element, and the height of setting sleeve in the utility model is more than or equal to the twice of above-mentioned screw termination thickness, thereby avoided screw termination to impact centering and parallel position relationship between upper lower support element, because the dimensions of four sleeves is consistent, make two surfaces that upper supporting piece and lower support element are adjacent parallel to each other.
One preferred embodiment in, as shown in Figure 4, four-axle aircraft comprises aircraft body and is distributed in main body four cantilevers around, cantilever one end and aircraft body are affixed, on the cantilever other end, be installed with aircraft engine installation, described aircraft engine installation is above-mentioned two motors and two affixed devices that form of strut member.
One preferred embodiment in, at above-mentioned aircraft engine installation two ends, be installed with respectively screw propeller, on two motors rotor toward the outer side, be separately installed with screw propeller.
One preferred embodiment in; aircraft engine installation runs through and is arranged on cantilever inside; and on the close cantilever of this device,, away from one end of aircraft body, the outside that is provided with one end of aircraft engine installation on above-mentioned cantilever is provided with screw propeller protective case.
One preferred embodiment in, the part that is connected with screw propeller on two motors is stretched out cantilever from the above and below of cantilever respectively, and the sponson at upper and lower two ends size is consistent with length, screw propeller is installed respectively on described sponson, in the utility model, the diameter dimension of upper supporting piece and lower support element is all greater than the diameter dimension of motor, for aircraft engine installation can successfully be extend in cantilever, and affixed with cantilever, first on cantilever, place the position of aircraft engine installation and offer a hole, this hole is offered along vertical direction, the slightly larger in diameter of this hole in or equal the diameter dimension of motor, and at this hole location place, cantilever consists of upper and lower two parts, be positioned at the cantilever main body and the cantilever bottom that is positioned at below of top, first aircraft engine installation is extend in the hole of cantilever main body, again cantilever bottom is arranged in cantilever main body, the motor that is simultaneously positioned at below has also passed the hole on cantilever bottom, finally by bolt, cantilever main body and cantilever bottom is affixed.Thereby completed affixed between two motors and cantilever, made on a cantilever, to there are two motors and two screw propellers simultaneously.
One preferred embodiment in, the connection location between cantilever main body and cantilever bottom is carried out to water-proofing treatment, cantilever is sealed completely.
One preferred embodiment in, the line of centers of four cantilevers is all in same plane.
One preferred embodiment in, in four cantilevers, the line of centers of two relative cantilevers overlaps, further preferably, the direction that the aircraft flight of take is advanced is the place ahead, on the other side is rear, and the line of centers angulation of two cantilevers in close the place ahead and identical near the line of centers angulation of two cantilevers in rear is all 87～90 degree.
One preferred embodiment in, the S. A. conllinear of two motors, further preferably, the S. A. of motor is perpendicular to the line of centers of adjacent cantilever with it, still more preferably, the S. A. of any one motor is perpendicular to the axis of any one cantilever.The line of centers of the cantilever described in the utility model refers to sets cantilever for cylinder or cylinder-like structure, to the center of gyration of column or tubular structure, be the line of centers of described cantilever, certainly, cantilever can be made regular tubular or column, also can be fitfull, or there is the shape of certain radian, the utility model is not particularly limited this, when cantilever is that other are when irregularly shaped, above-mentioned cantilever line of centers can be understood as approximate virtual lines, the position relationship of miscellaneous part and described cantilever line of centers, equally can be suitable be similar to.
One preferred embodiment in, cantilever integral body is the column of hollow, the column object that cantilever is made to hollow is to alleviate the weight of aircraft integral body, and the length of cantilever is determined according to the size of aircraft integral body, to guarantee that aircraft has enough intensity and good dynamic performance.
The beneficial effect that the utility model has comprises:
(1) motor system providing according to the utility model, comes affixed upper motor and lower motor by the consistent upper supporting piece of structure and lower support element, makes the centering of motor and lower motor good, has guaranteed that the center of gyration of two motors overlaps.
(2) motor system providing according to the utility model, by the bolted between cantilever main body and cantilever bottom, fix two motors and two systems that strut member forms, make motor system simple in structure, field-strip is convenient, adopt water-proofing treatment simultaneously, made aircraft sealing property better.
(3) four-axle aircraft in the utility model has eight screw propellers, controls respectively by eight motors, makes aircraft more flexible, and flying speed is fast.
(4) aircraft in the utility model has eight screw propellers, even if there are even several screw propellers to damage or et out of order, other screw propeller still can normally be worked, and makes the aircraft recurrence of can landing safely, has avoided the aircraft damage of crashing.
More than combine preferred embodiment the utility model is illustrated, but these embodiments are only exemplary, only play illustrative effect.On this basis, can carry out multiple replacement and improvement to the utility model, these all fall in protection domain of the present utility model.
Claims (8)
1. a four-axle aircraft motor system, it is characterized in that, this motor system comprises: upper motor (1) and lower motor (2) that center of gyration overlaps, and the rotor of upper motor (1) upward, the rotor of lower motor (2) down, between upper motor (1) and lower motor (2), be provided with consistent and upper supporting piece (3) and the lower support elements (4) in the form of annular discs all of specification
Wherein, upper supporting piece (3) is affixed by screw and upper motor (1), and lower support element (4) is affixed by screw and lower motor (2),
Between upper supporting piece (3) and lower support element (4), be provided with sleeve (5), bolt passes lower support element (4), sleeve (5) and upper supporting piece (3) from bottom to top successively, and coordinates and screw with nut;
Four-axle aircraft comprises aircraft body (6) and four cantilevers (7), described cantilever comprises cantilever main body (71) and is removably mounted on the cantilever bottom (72) in cantilever main body (71), at cantilever, away from one end of aircraft body, offer the vertical hole that holds motor, lower motor and upper supporting piece and lower support element, described vertical hole is from top to bottom successively through cantilever main body (71) and cantilever bottom (72).
2. four-axle aircraft motor system according to claim 1, is characterized in that, for the screw of affixed upper supporting piece (3) and upper motor (1), has four, and described four screws are evenly distributed in the position near upper supporting piece center.
3. four-axle aircraft motor system according to claim 1, is characterized in that, for the screw of affixed lower support element (4) and lower motor (2), has four, and described four screws are evenly distributed in the position near lower support element center.
4. four-axle aircraft motor system according to claim 1, is characterized in that, on the rotor of upper motor (1) and lower motor (2), is separately installed with screw propeller.
5. four-axle aircraft motor system according to claim 1, is characterized in that, in upper supporting piece (3) disc face, near center position, four tapped bore is set, and in lower support element (4) disc face, near center position, four tapped bore is set.
6. four-axle aircraft motor system according to claim 1, is characterized in that, the height of sleeve is more than the twice of screw termination (11) thickness.
7. four-axle aircraft motor system according to claim 1, it is characterized in that, in upper supporting piece (3) position that keeps to the side, offer evenly distributedly four upper through holes (31) that pass for bolts, accordingly, in lower support element (4) position that keeps to the side, offer evenly distributedly four lower through-holes (41) that pass for bolts, bolt passes the upper through hole of lower through-hole, sleeve and the upper supporting piece of lower support element from bottom to top successively, and coordinates and screw with nut.
8. four-axle aircraft motor system according to claim 1, it is characterized in that, between cantilever main body (71) and cantilever bottom (72), pass through screw-tightened, and cantilever main body (71) and cantilever bottom (72) connection location are coated with to waterproof layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420369255.0U CN203996884U (en) | 2014-07-04 | 2014-07-04 | Four-axle aircraft motor system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420369255.0U CN203996884U (en) | 2014-07-04 | 2014-07-04 | Four-axle aircraft motor system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203996884U true CN203996884U (en) | 2014-12-10 |
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ID=52036924
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420369255.0U Expired - Fee Related CN203996884U (en) | 2014-07-04 | 2014-07-04 | Four-axle aircraft motor system |
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| CN (1) | CN203996884U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017107720A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle |
-
2014
- 2014-07-04 CN CN201420369255.0U patent/CN203996884U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017107720A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle |
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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: 20141210 Termination date: 20160704 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |