CN204452930U - The four-axle aircraft of telescopic folding - Google Patents
The four-axle aircraft of telescopic folding Download PDFInfo
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- CN204452930U CN204452930U CN201420803524.XU CN201420803524U CN204452930U CN 204452930 U CN204452930 U CN 204452930U CN 201420803524 U CN201420803524 U CN 201420803524U CN 204452930 U CN204452930 U CN 204452930U
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- propeller
- expansion link
- extension bar
- external extension
- conical gear
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Abstract
The utility model relates to the four-axle aircraft of telescopic folding, and comprise central supporting mechanism and four cover propeller mechanisms, improvement is: four cover propeller mechanisms are the telescopic propeller mechanism of identical four cover of structure; Often overlap telescopic propeller mechanism and comprise small conical gear, expansion link, screw propeller, motor and lift arm mechanism, also comprise large conical gear and servomotor; Servomotor, large conical gear and four small conical gears form the driver train that four overlap the expansion link of propeller mechanisms; Under the driving of servomotor, four small conical gears drive four expansion links realize overhanging or inside contract by screw flight transmission respectively simultaneously.Improve and also comprise four cover fold mechanisms, often overlap fold mechanism and drive that often to overlap telescopic propeller mechanism folding or launch.The utility model, by setting up telescoping mechanism and fold mechanism, makes four axle fuselages realize significantly folding and unfolding, compares existing product, effectively reduce the volume of aircraft, be convenient for carrying.
Description
Technical field
The utility model belongs to multi-rotor aerocraft technical field, is specifically related to a kind of four-axle aircraft.
Background technology
Multi-rotor aerocraft military affairs can be used for ground reconnaissance, no-fly zone patrol and close support, on civilian can post-disaster search and rescue, race take photo by plane, traffic patrolling etc.Existing four-axle aircraft fuselage, based on integral type, adopts mould molding more, without initial breakdown interface (large boundary is smart); Minority large-scale four-axle aircraft fuselage is upper lower wall panels, carbon fibre tube glueds joint, being spirally connected forms, and horn is pinned between lower wall panels interlayer, can rotate around bearing pin between interlayer, and horn possesses flat-folded function (leaping 650).Front a kind of fuselage oar dish and horn Joint strenght high, assembly stress is little, but fuselage ability to dismantle is poor, fuselage can not folding and unfolding, aloft cannot stretch during flight horn, limit the ability of four-axle aircraft reply complex-terrain, the demand that such as scout's folding and unfolding is carried, taken off fast cannot be met simultaneously.The collapsible fuselage of rear one is flat-folded, if add horn Telescopic, stretches, folds and can produce interference, and this folding mode limits horn and has flexible potential possibility concurrently, also cannot develop the activity space of four-axle aircraft further.
Utility model content
In order to adjust the position of four screw propellers distance central authorities when realizing four-axle aircraft flight, and realize folding and unfolding easily and carry, the utility model provides one telescopic Telescopic folding four-axle aircraft aloft.
Concrete structural development technical scheme is as follows:
The four-axle aircraft of telescopic folding comprises central supporting mechanism and four cover propeller mechanisms, and described central supporting mechanism is connected and composed by supporting studs 2 by upper flat plate 1 parallel up and down and lower dull and stereotyped 3; Four cover propeller mechanisms are all laid on upper flat plate 1, and the screw propeller 33 of four cover propeller mechanisms is distributed on the periphery of upper flat plate 1, and below every screw propeller 33, correspondence is provided with lift arm mechanism;
Described four cover propeller mechanisms are the telescopic propeller mechanism of identical four cover of structure; Often overlap telescopic propeller mechanism and comprise small conical gear 13, expansion link, screw propeller 33, motor 32 and lift arm mechanism, described screw propeller 33 is located on the output shaft of motor 32, and screw propeller 33 and motor 32 are positioned at the outer end of expansion link, described small conical gear 13 correspondence is positioned at the inner of expansion link; The middle part of upper flat plate 1 is located at by the large conical gear 12 overlapping four small conical gear 13 engaged transmission of propeller mechanism with four, and large conical gear 12 is connected to the output shaft of servomotor 11, in the space of described servomotor 11 between upper flat plate 1 and lower dull and stereotyped 3; Described servomotor 11, large conical gear 12 and four small conical gears 13 form the driver train of the expansion link of four cover propeller mechanisms;
Under the driving of servomotor 11, large conical gear 12 and four small conical gear 13 engaged transmission, four small conical gears 13 drive four expansion links realize overhanging or inside contract by the screw-driven of screw rod 14 respectively simultaneously.
Described expansion link comprises external extension bar 18 and interior expansion link 15, and external extension bar 18 and interior expansion link 15 are square tube, and the inner of interior expansion link 15 is plugged in the outer end of external extension bar 18, and the inner internal fixtion of interior expansion link 15 is provided with nut 17; Described screw rod 14 is positioned at external extension bar 18, is polished rod with small conical gear 13 coupling end, and screw rod 14 is connected nut 17; The inner internal fixtion of external extension bar 18 is provided with bearing 16, and the inner sleeve engagement sleeves of bearing 16 is located on described polished rod; When screw rod rotates forward or backwards, nut 17 is with the internal contraction of the outside expansion link 18 of interior expansion link 15, and screw rod oppositely or when rotating forward, nut 17 stretches out with the outside of the outside expansion link 18 of interior expansion link 15.
The periphery of described nut 17 is square, and is fixed in the inner of interior expansion link 15 of square tube type.
The expansion link often overlapping telescopic propeller mechanism is located on upper flat plate 1 by fold mechanism; Described fold mechanism comprises U-shaped fixture block 5, pillar stiffener 4, hinge and connecting rod mechanism; Described U-shaped fixture block 5 is fixed on the periphery of upper flat plate 1, the inner of external extension bar 18 and the dynamic cooperation of U-shaped fixture block 5, and by chain connection between external extension bar 18 and U-shaped fixture block 5; Described connecting rod mechanism comprises connecting rod 21 and lower link 23, is flexibly connected between one end of upper connecting rod 21 and one end of lower link 23 by pitman shaft 22; The other end of upper connecting rod 21 is flexibly connected external extension bar 18, and the other end of lower link 23 is flexibly connected the lower end of pillar stiffener 4, and the upper end of pillar stiffener 4 had both been connected to the bottom of described U-shaped fixture block 5, is connected to again the bottom of described upper flat plate 1; When external extension bar 18 departs from U-shaped fixture block 5, the bottom that lower link 23 is swung down to pillar stiffener 4 is vertical configuration, and drives external extension bar 18 to be swung down to hang by upper connecting rod 21, now, rectangular-shaped in 90 degree between upper connecting rod 21 and lower link 23; When external extension bar 18 cooperation is positioned at U-shaped fixture block 5, external extension bar 18 is horizontal, now, and upper connecting rod 21 and the linearity of lower link 23 in 180 degree of angles.
Advantageous Effects of the present utility model embodies in the following areas:
1, the utility model employing gear transmission, screw-driven match, driven by servomotor power uniform and stable passed to four interior telescopic shafts, physical construction is simple and driving efficiency is higher, the remote control telescopic when flying can be realized, stretching speed, between 0-20mm/s, is that existing four-axle aircraft fuselage institute is irrealizable.The arm shrinking four screw propellers by remote control makes aircraft enter narrow space, such as post-disaster search and rescue, site inspection etc.Large-scale four-axle aircraft flight stability is convenient to take photo by plane, small-sized four-axle aircraft maneuverability, application space is wide, and the four-axle aircraft of different work need for environment different size, can make the advantage of large-scale four-axle aircraft both by the arm of remote control telescopic four screw propellers;
2, horn of the present utility model adopts fold mechanism, and time folding, horn corner can reach 90 degree, folding and unfolding four-axle aircraft fuselage to greatest extent, that existing flat-folded fuselage is beyond one's reach, make four axle fuselages realize significantly folding and unfolding, the large-scale four-axle aircraft volume after contraction reduces, and is easy to carry;
3, the utility model adopts double leval jib location, locking mechanism, and after horn opens completely, double leval jib is just parked in dead center position, and draw-in groove blocks horn, by locked for four axle horn positions simultaneously; In horn folding process, horn both sides connecting rod can limit folded trajectory.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Fig. 2 is gears meshing schematic diagram.
Fig. 3 is telescopic arm structure schematic diagram.
Fig. 3-A is the partial enlarged drawing at A place in Fig. 3.
Fig. 3-B is the partial enlarged drawing at B place in Fig. 3.
Fig. 4 is the schematic diagram of fold mechanism.
Fig. 5 is central supporting structural scheme of mechanism.
Fig. 6 is fold mechanism folding state figure.
Fig. 7 is the expansion link contraction state figure of propeller mechanism.
Fig. 8 is the utility model folded state schematic diagram.
Sequence number in upper figure: upper flat plate 1, supporting studs 2, lower dull and stereotyped 3, pillar stiffener 4, U-shaped fixture block 5, servomotor 11, large conical gear 12, small conical gear 13, screw rod 14, interior expansion link 15, bearing 16, nut 17, external extension bar 18, upper connecting rod 21, pitman shaft 22, lower link 23, hinge 24, motor 32, screw propeller 33, roller 41, roller shaft 42, hold-down arm 43.
Detailed description of the invention
Below in conjunction with accompanying drawing, by embodiment, the utility model is further described.
Embodiment
See Fig. 1, the four-axle aircraft of telescopic folding comprises central supporting mechanism and four cover propeller mechanisms, and central supporting mechanism is connected and composed by four supporting studs 5 by upper flat plate 1 parallel up and down and lower dull and stereotyped 3, sees Fig. 5; Four cover propeller mechanisms are all laid on upper flat plate 1, and the screw propeller 33 of four cover propeller mechanisms is distributed on the periphery of upper flat plate 1, and below every screw propeller 33, correspondence is provided with lift arm mechanism, and lift arm mechanism comprises hold-down arm 43, roller 41 and roller shaft 42.
See Fig. 3, four cover propeller mechanisms are the telescopic propeller mechanism of identical four cover of structure.Often overlap telescopic propeller mechanism and comprise small conical gear 13, expansion link, screw propeller 33, motor 32 and lift arm mechanism.Screw propeller 33 is installed on the output shaft of motor 32, and screw propeller 33 and motor 32 are positioned at the outer end of expansion link; Small conical gear 13 correspondence is positioned at the inner of expansion link; See Fig. 2 and Fig. 1, the large conical gear 12 overlapping four small conical gear 13 engaged transmission of propeller mechanism with four is positioned at the middle part of upper flat plate 1, large conical gear 12 is connected to the output shaft of servomotor 11, in the space of servomotor 11 between upper flat plate 1 and lower dull and stereotyped 3; Servomotor 11, large conical gear 12 and four small conical gears 13 form the driver train of the expansion link of four cover propeller mechanisms.
See Fig. 3 A, expansion link comprises external extension bar 18 and interior expansion link 15, and external extension bar 18 and interior expansion link 15 are square tube, and the inner of interior expansion link 15 is plugged in the outer end of external extension bar 18, and the inner internal fixtion of interior expansion link 15 is provided with nut 17; Screw rod 14 is positioned at external extension bar 18, is polished rod with small conical gear 13 coupling end, and screw rod is connected nut 17, and the periphery of nut 17 is square; See Fig. 3 B, the inner internal fixtion of external extension bar 18 is provided with bearing 16, and the inner sleeve engagement sleeves of bearing 16 is contained on polished rod; When screw rod rotates forward or backwards, nut 17 is with the internal contraction of the outside expansion link 18 of interior expansion link 15, and screw rod oppositely or when rotating forward, nut 17 stretches out with the outside of the outside expansion link 18 of interior expansion link 15.
See Fig. 1, the expansion link often overlapping telescopic propeller mechanism is installed on upper flat plate 1 by fold mechanism.See Fig. 4, fold mechanism comprises U-shaped fixture block 5, pillar stiffener 4, hinge 24 and connecting rod mechanism.U-shaped fixture block 5 is fixedly installed on the periphery of upper flat plate 1, the inner of external extension bar 18 and the dynamic cooperation of U-shaped fixture block 5, and by chain connection between external extension bar 18 and U-shaped fixture block 5; Connecting rod mechanism comprises connecting rod 21 and lower link 23, is flexibly connected between one end of upper connecting rod 21 and one end of lower link 23 by pitman shaft 22; The other end of upper connecting rod 21 is flexibly connected external extension bar 18, and the other end of lower link 23 is flexibly connected the lower end of pillar stiffener 4, and the upper end of pillar stiffener 4 had both been connected to the bottom of U-shaped fixture block 5, was connected to again the bottom of upper flat plate 1.See Fig. 6, when external extension bar 18 departs from U-shaped fixture block 5, the bottom that lower link 23 is swung down to pillar stiffener 4 is vertical configuration, and drives external extension bar 18 to be swung down to hang by upper connecting rod 21, now, rectangular-shaped in 90 degree between upper connecting rod 21 and lower link 23; See Fig. 4, when external extension bar 18 cooperation is positioned at U-shaped fixture block 5, external extension bar 18 is horizontal, now, and upper connecting rod 21 and the linearity of lower link 23 in 180 degree of angles.
Principle of work of the present utility model:
1), when carrying, fuselage is in complete folding shrinking state, sees Fig. 8; Aircraft horn launches on ground by manipulator, and connecting rod mechanism and U-shaped fixture block, by locked for external extension bar 18 (horn), are shown in Fig. 7; Horn is made to stretch out order by remote control equipment (RCE) to flight controller transmitting, flight controller controls servomotor 11 and rotates according to certain speed, drive the rotation of large conical gear 12, drive the rotation of four small conical gears 13 by gears meshing and then drive four screw rods 14 to rotate, under the pulling of nut 17, interior expansion link 15 trails, and sees Fig. 1;
2) controlling lift system makes four-axle aircraft take off, and the signal aloft launched by remote control equipment (RCE) can realize the synchronous automatic telescopic of the expansion link of the telescopic propeller mechanism of four covers, to tackle various complicated;
3) controlled the horn contraction of aircraft after aircraft lands by remote control equipment (RCE), connecting rod mechanism is pulled from dead point by manipulator, is folded by horn, so far completes the folding of four-axle aircraft.
Claims (4)
1. the four-axle aircraft of telescopic folding, comprise central supporting mechanism and four cover propeller mechanisms, described central supporting mechanism is connected and composed by supporting studs (2) by upper flat plate (1) parallel up and down and lower flat board (3); Four cover propeller mechanisms are all laid on upper flat plate (1), and the screw propeller (33) of four cover propeller mechanisms is distributed on the periphery of upper flat plate (1), and every screw propeller (33) below correspondence is provided with lift arm mechanism; It is characterized in that: described four cover propeller mechanisms are the telescopic propeller mechanism of identical four cover of structure; Often overlap telescopic propeller mechanism and comprise small conical gear (13), expansion link, screw propeller (33), motor (32) and lift arm mechanism, described screw propeller (33) is located on the output shaft of motor (32), and screw propeller (33) and motor (32) are positioned at the outer end of expansion link, described small conical gear (13) correspondence is positioned at the inner of expansion link; The middle part of upper flat plate (1) is located at by the large conical gear (12) overlapping four small conical gear (13) engaged transmission of propeller mechanism with four, large conical gear (12) is connected to the output shaft of servomotor (11), and described servomotor (11) is positioned at the space between upper flat plate (1) and lower flat board (3); Described servomotor (11), large conical gear (12) and four small conical gears (13) form the driver train that four overlap the expansion link of propeller mechanisms;
Under the driving of servomotor (11), large conical gear (12) and four small conical gear (13) engaged transmission, four small conical gears (13) drive four expansion links realize overhanging or inside contract by the screw-driven of screw rod (14) respectively simultaneously.
2. the four-axle aircraft of telescopic folding according to claim 1, it is characterized in that: described expansion link comprises external extension bar (18) and interior expansion link (15), external extension bar (18) and interior expansion link (15) are square tube, the inner of interior expansion link (15) is plugged in the outer end of external extension bar (18), and the inner internal fixtion of interior expansion link (15) is provided with nut (17); Described screw rod (14) is positioned at external extension bar (18), is polished rod with small conical gear (13) coupling end, and screw rod (14) is connected nut (17); The inner internal fixtion of external extension bar (18) is provided with bearing (16), and the inner sleeve engagement sleeves of bearing (16) is located on described polished rod; When screw rod rotates forward or backwards, nut (17) is with the internal contraction of the outside expansion link (18) of interior expansion link (15), screw rod oppositely or when rotating forward, nut (17) stretches out with the outside of the outside expansion link (18) of interior expansion link (15).
3. the four-axle aircraft of telescopic folding according to claim 2, is characterized in that: the periphery of described nut (17) is square, and is fixed in the inner of interior expansion link (15) of square tube type.
4. the four-axle aircraft of telescopic folding according to claim 1, is characterized in that: the expansion link often overlapping telescopic propeller mechanism is located on upper flat plate (1) by fold mechanism; Described fold mechanism comprises U-shaped fixture block (5), pillar stiffener (4), hinge (24) and connecting rod mechanism; Described U-shaped fixture block (5) is fixed on the periphery of upper flat plate (1), the inner of external extension bar (18) and the dynamic cooperation of U-shaped fixture block (5), and connected by hinge (24) between external extension bar (18) and U-shaped fixture block (5); Described connecting rod mechanism comprises connecting rod (21) and lower link (23), is flexibly connected between one end of upper connecting rod (21) and one end of lower link (23) by pitman shaft (22); The other end of upper connecting rod (21) is flexibly connected external extension bar (18), the other end of lower link (23) is flexibly connected the lower end of pillar stiffener (4), the upper end of pillar stiffener (4) had both been connected to the bottom of described U-shaped fixture block (5), was connected to again the bottom of described upper flat plate (1); When external extension bar (18) departs from U-shaped fixture block (5), the bottom that lower link (23) is swung down to pillar stiffener (4) is vertical configuration, and drive external extension bar (18) to be swung down to hang by upper connecting rod (21), now, rectangular-shaped in 90 degree between upper connecting rod (21) and lower link (23); When external extension bar (18) cooperation is positioned at U-shaped fixture block (5), external extension bar (18) is horizontal, now, and upper connecting rod (21) and the linearity of lower link (23) in 180 degree of angles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420803524.XU CN204452930U (en) | 2014-12-18 | 2014-12-18 | The four-axle aircraft of telescopic folding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420803524.XU CN204452930U (en) | 2014-12-18 | 2014-12-18 | The four-axle aircraft of telescopic folding |
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| CN204452930U true CN204452930U (en) | 2015-07-08 |
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| CN201420803524.XU Expired - Fee Related CN204452930U (en) | 2014-12-18 | 2014-12-18 | The four-axle aircraft of telescopic folding |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648664A (en) * | 2014-12-18 | 2015-05-27 | 合肥工业大学 | Retractable folding quad rotor |
| CN104960663A (en) * | 2015-07-09 | 2015-10-07 | 杨小韬 | Multi-rotor aircraft and control method thereof |
| CN105270613A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Foldable telescopic six-shaft aircraft |
| CN105292477A (en) * | 2015-12-02 | 2016-02-03 | 熊先泽 | Wrist type portable accompanying flight autonomous supervision unmanned aerial vehicle |
| CN106005443A (en) * | 2016-07-29 | 2016-10-12 | 安翔泰岳（镇江）航空科技有限公司 | Unmanned aerial vehicle |
| CN106672233A (en) * | 2017-01-04 | 2017-05-17 | 四川克瑞斯航空科技有限公司 | Novel folding rotor arm structure of unmanned aerial vehicle |
| CN107117311A (en) * | 2017-04-27 | 2017-09-01 | 南京理工大学 | A kind of changeable wheelbase unmanned plane |
| CN108466694A (en) * | 2018-03-16 | 2018-08-31 | 广东容祺智能科技有限公司 | One kind is verted wing unmanned plane and its control method |
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
-
2014
- 2014-12-18 CN CN201420803524.XU patent/CN204452930U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648664A (en) * | 2014-12-18 | 2015-05-27 | 合肥工业大学 | Retractable folding quad rotor |
| CN104648664B (en) * | 2014-12-18 | 2017-02-22 | 合肥工业大学 | Retractable folding quad rotor |
| CN104960663A (en) * | 2015-07-09 | 2015-10-07 | 杨小韬 | Multi-rotor aircraft and control method thereof |
| CN105270613A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Foldable telescopic six-shaft aircraft |
| CN105292477A (en) * | 2015-12-02 | 2016-02-03 | 熊先泽 | Wrist type portable accompanying flight autonomous supervision unmanned aerial vehicle |
| CN106005443A (en) * | 2016-07-29 | 2016-10-12 | 安翔泰岳（镇江）航空科技有限公司 | Unmanned aerial vehicle |
| CN106672233A (en) * | 2017-01-04 | 2017-05-17 | 四川克瑞斯航空科技有限公司 | Novel folding rotor arm structure of unmanned aerial vehicle |
| CN107117311A (en) * | 2017-04-27 | 2017-09-01 | 南京理工大学 | A kind of changeable wheelbase unmanned plane |
| CN108466694A (en) * | 2018-03-16 | 2018-08-31 | 广东容祺智能科技有限公司 | One kind is verted wing unmanned plane and its control method |
| CN108919674A (en) * | 2018-08-14 | 2018-11-30 | 正德职业技术学院 | UAV Flight Control analogue system |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150708 Termination date: 20161218 |