CN205311894U - Unmanned aerial vehicle undercarriage - Google Patents
Unmanned aerial vehicle undercarriage Download PDFInfo
- Publication number
- CN205311894U CN205311894U CN201520988889.9U CN201520988889U CN205311894U CN 205311894 U CN205311894 U CN 205311894U CN 201520988889 U CN201520988889 U CN 201520988889U CN 205311894 U CN205311894 U CN 205311894U
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- China
- Prior art keywords
- landing gear
- roller
- bracing wire
- man
- undercarriage
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicle, in particular to unmanned aerial vehicle undercarriage. Including undercarriage I, undercarriage II, undercarriage stopper, torsional spring and act as go -between and pack up the mechanism, wherein undercarriage I and undercarriage II articulate in unmanned aerial vehicle's fuselage below and locate through the cover through the hinge respectively it opens to the outside to cut with scissors epaxial torsional spring, undercarriage I and undercarriage II open the angle respectively through set up in two undercarriage stopper restrictions on the fuselage, act as go -between pack up the establishment of institution in the top of fuselage is connected with undercarriage I and undercarriage II respectively through the through wires hole that fuselage both sides were equipped with, act as go -between and pack up mechanism drive undercarriage I and pack up to the inboard with undercarriage II. The utility model discloses can alleviate the weight of aircraft, increase time of endurance, on changing and maintain, also more convenient than screw -nut, the cost also can be much lower simultaneously.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, in particular to one without man-machine landing gear.
Background technology
Unmanned spacecraft, is called for short without man-machine, its have maneuverability, reaction fast, unmanned flight, advantage that operational requirement is low. Without man-machine by carrying multiclass sensor, it is possible to realize image real-time Transmission, high-risk area detecting function, it is that satellite remote sensing supplements with the strong of tradition airborne remote sensing.
At present, it is take photo by plane without man-machine main application fields, supports without man-machine effect owing to landing gear plays, realize 360 ° take photo by plane without man-machine cloud platform is mutually confidential, will inevitably clap by landing gear, affecting so very much result of use, current solution is all landing gear collapsed configuration. What employing packed up by current landing gear is the form of feed screw nut, and this structure is heavy, considerably increases without man-machine weight, affects cruise duration.
Practical novel content
For the problems referred to above, the purpose of this utility model is to provide a kind of without man-machine landing gear. This is simple without man-machine landing gear structure, and lighter in weight is easy to operate.
In order to realize above-mentioned purpose, the utility model by the following technical solutions:
A kind of without man-machine landing gear, comprise landing gear I, landing gear II, landing gear limited block, torsion spring and bracing wire stow mechanism, wherein landing gear I and landing gear II are articulated with without below man-machine fuselage by hinge respectively, and opened laterally by the torsion spring being sheathed on described hinge, the opening angle of described landing gear I and landing gear II is limited by two the landing gear limited blocks being arranged on described fuselage respectively, described bracing wire stow mechanism is arranged at the top of described fuselage, and the threading hole being provided with by fuselage both sides is connected with landing gear I and landing gear II respectively, described bracing wire stow mechanism drives landing gear I and landing gear II to pack up to the inside.
Described bracing wire stow mechanism comprises drive-motor, roller I, bracing wire I, bracing wire II, roller II and roller III, wherein roller I and roller II are installed in rotation on the threading hole place of described fuselage both sides respectively, described roller III is arranged on the output shaft of drive-motor, and between roller I and roller II, described bracing wire I is through roller I, and two ends are connected with described roller III and described landing gear I respectively, described bracing wire II is through roller II, and two ends are connected with described roller III and described landing gear II respectively, described drive-motor drives roller III to rotate, and drive landing gear I and landing gear II to pack up simultaneously.
Described roller III is provided with twice annular groove, and described bracing wire I is separately fixed at the twice annular groove on roller III Nei with one end of bracing wire II and winding direction is identical.
Described bracing wire I laying parallel with bracing wire II.
The threading hole of described fuselage both sides lays respectively at the inner side of described landing gear I and landing gear II, and the both sides in each threading hole are respectively equipped with ear seat, and described roller I and roller II are installed in rotation on corresponding ear seat respectively.
The inner side of described landing gear limited block is provided with installation gap, and one end of described landing gear I and landing gear II is arranged in the installation gap on corresponding landing gear limited block by hinge, and can rotate around hinge.
Described torsion spring is placed in the installation gap on landing gear limited block Nei and is set on described hinge, and one end of described torsion spring is connected with landing gear limited block, and the other end is connected with described landing gear I or landing gear II.
Described landing gear I and landing gear II are equipped with torsion spring junction and are connected block, and described connection block is provided with and connects hole, and the other end of described torsion spring is inserted in the connection hole on described connection block.
Described landing gear is two groups, and the bracing wire stow mechanism in two groups of landing gears is that cross intersection is arranged.
Advantage of the present utility model and useful effect be:
Bracing wire stow mechanism of the present utility model adopts roller and guy structure, it is possible to alleviate the weight of aircraft, increases cruise duration. Simultaneously on changing and safeguarding, also convenient compared with feed screw nut, cost also can be much lower.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the A-A sectional view of Fig. 1;
Fig. 3 is I place enlarged view in Fig. 1;
Fig. 4 is the upward view of Fig. 1;
Fig. 5 is II place's enlarged view in Fig. 4;
Fig. 6 is the utility model landing gear collapsed state schematic diagram.
In figure: 1 is roller I, 2 for bracing wire I, 3 for bracing wire II, 4 be roller II, 5 be roller III, and 6 is drive-motor, and 7 is fuselage, and 8 is landing gear I, and 9 is landing gear II, and 10 is landing gear limited block, and 11 is torsion spring, and 12 is connection block, and 13 is hinge, and 14 is threading hole.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As Figure 1-5, the one that the utility model provides is without man-machine landing gear, comprise landing gear I 8, landing gear II 9, landing gear limited block 10, torsion spring 11 and bracing wire stow mechanism, wherein landing gear I 8 and landing gear II 9 respectively by hinge 13 be articulated with without below man-machine fuselage 7 and opened respectively to outside by the torsion spring 11 being sheathed on described hinge 13. The opening angle of described landing gear I 8 and landing gear II 9 is limited by two the landing gear limited blocks 10 being arranged on fuselage 7 respectively, described bracing wire stow mechanism is arranged at the top of described fuselage 7 and the threading hole 14 that is provided with by fuselage 7 both sides is connected with landing gear I 8 and landing gear II 9 respectively, and described bracing wire stow mechanism drives landing gear I 8 and landing gear II 9 to pack up to the inside.
Described bracing wire stow mechanism comprises drive-motor 6, roller I 1, bracing wire I 2, bracing wire II 3, roller II 4 and roller III 5, wherein roller I 1 and roller II 4 are installed in rotation on the threading hole 14 of described fuselage 7 both sides, described roller III 5 be arranged on the output shaft of drive-motor 6 and between roller I 1 and roller II 4. Described bracing wire I 2 through roller I 1 and two ends be connected with described roller III 5 and described landing gear I 8 respectively, described bracing wire II 3 through roller II 4 and two ends be connected with described roller III 5 and described landing gear II 9 respectively, described drive-motor 6 drives roller III 5 to rotate, and drives landing gear I 8 and landing gear II 9 to pack up simultaneously.
Described roller III 5 is circumferentially provided with twice annular groove, described bracing wire I 2 is separately fixed at the twice annular groove on roller III 5 Nei with one end of bracing wire II 3 and is wrapped in twice annular groove along identical direction, described bracing wire I 2 laying parallel with bracing wire II 3, as shown in Figure 3. Described roller III 5 arranges twice annular groove and is wound around bracing wire I 2 and bracing wire II 3 respectively, avoid bracing wire I 2 and bracing wire II 3 to produce to be wound around mutually the phenomenon affecting normal operation when packing up and discharge and occur. Described bracing wire I 2 is extended laterally by the bottom of roller III 5 and is connected with landing gear I 8 through roller I 1. Described bracing wire II 3 is outwards extended by the top of roller III 5 and is connected with landing gear II 9 through roller II 4. The above-mentioned canoe of described bracing wire I 2 and bracing wire II 3, it is achieved that the object simultaneously packed up by the rotation of roller III 5. In the present embodiment, described bracing wire I 2 and bracing wire II 3 are nylon wire.
The threading hole 14 of described fuselage 7 both sides lays respectively at the inner side of described landing gear I 8 and landing gear II 9, and the both sides in each threading hole 14 are respectively equipped with ear seat, and described roller I 1 and roller II 4 are installed in rotation on corresponding ear seat respectively.
What bracing wire stow mechanism of the present utility model adopted that roller and connected nylon wire structure realize landing gear packs up object, and this structure can alleviate the weight of aircraft, increases cruise duration. Simultaneously on changing and safeguarding, also convenient compared with feed screw nut, cost also can be much lower.
The inner side of described landing gear limited block 10 is provided with installation gap, and one end of described landing gear I 8 and landing gear II 9 is arranged in the installation gap on corresponding landing gear limited block 10 by hinge 13, and can rotate around hinge 13. Described landing gear I 8 and landing gear II 9 are equipped with corresponding torsion spring 11 junction and connect block 12, and described connection block 12 is provided with and connects hole. Described torsion spring 11 is placed in the installation gap on landing gear limited block 10 Nei and is set on described hinge 13, and one end of described torsion spring 11 is connected with landing gear limited block 10, and the other end is inserted in the connection hole on described connection block 12, as shown in Figure 5.
Described landing gear limited block 10 is the installation pedestal of landing gear I 8 and landing gear II 9, again landing gear I 8 and landing gear II 9 is played position-limiting action simultaneously, this configuration simplifies installation structure, alleviate mechanism's weight simultaneously, add cruise duration.
Further, described landing gear is two groups, and the bracing wire stow mechanism in two groups of landing gears is that cross intersection is arranged. Drive-motor 6 in two groups of landing gears and roller III 5 are all positioned at the central position of fuselage 7, and the bracing wire in two groups of landing gears is cross intersects and arrange, and namely the bracing wire I 2 in a group is vertical with bracing wire II 3 with another bracing wire I 2 organized with bracing wire II 3, as shown in Figure 1.
Principle of work of the present utility model is:
When drive-motor 6 is failure to actuate, described landing gear I 8 and landing gear II 9 under the effect of torsion spring 11, can open certain angle. The size of the opening angle of described landing gear I 8 and landing gear II 9 is determined by the height of landing gear limited block 10, before taking off with land before, described landing gear I 8 and all open-shaped state of landing gear II 9, as shown in Figure 2.
When without man-machine need 360 ° to take photo by plane aloft time, described landing gear I 8 and landing gear II 9 are packed up. Packing up action is drive roller III 5 to rotate by drive-motor 6, and roller III 5 rotates and bracing wire I 2 and bracing wire II 3 packed up, and described bracing wire I 2 and bracing wire II 3 drive landing gear I 8 and landing gear II 9 to pack up respectively, as shown in Figure 6.
Claims (9)
1. one kind without man-machine landing gear, it is characterized in that, comprise landing gear I (8), landing gear II (9), landing gear limited block (10), torsion spring (11) and bracing wire stow mechanism, wherein landing gear I (8) and landing gear II (9) are articulated with without man-machine fuselage (7) lower section by hinge (13) respectively, and opened laterally by the torsion spring (11) being sheathed on described hinge (13), the opening angle of described landing gear I (8) and landing gear II (9) is limited by two the landing gear limited blocks (10) being arranged on described fuselage (7) respectively, described bracing wire stow mechanism is arranged at the top of described fuselage (7), and the threading hole (14) being provided with by fuselage (7) both sides is connected with landing gear I (8) and landing gear II (9) respectively, described bracing wire stow mechanism drives landing gear I (8) and landing gear II (9) to pack up to the inside.
2. according to claim 1 without man-machine landing gear, it is characterized in that, described bracing wire stow mechanism comprises drive-motor (6), roller I (1), bracing wire I (2), bracing wire II (3), roller II (4) and roller III (5), wherein roller I (1) and roller II (4) are installed in rotation on threading hole (14) place of described fuselage (7) both sides respectively, described roller III (5) is arranged on the output shaft of drive-motor (6), and it is positioned between roller I (1) and roller II (4), described bracing wire I (2) is through roller I (1), and two ends are connected with described roller III (5) and described landing gear I (8) respectively, described bracing wire II (3) is through roller II (4), and two ends are connected with described roller III (5) and described landing gear II (9) respectively, described drive-motor (6) drives roller III (5) to rotate, and drive landing gear I (8) and landing gear II (9) to pack up simultaneously.
3. according to claim 2 without man-machine landing gear, it is characterized in that, described roller III (5) is provided with twice annular groove, and described bracing wire I (2) is separately fixed at the twice annular groove on roller III (5) Nei with one end of bracing wire II (3) and winding direction is identical.
4. according to claim 3 without man-machine landing gear, it is characterised in that, described bracing wire I (2) and the parallel laying of bracing wire II (3).
5. according to claim 2 without man-machine landing gear, it is characterized in that, the threading hole (14) of described fuselage (7) both sides lays respectively at the inner side of described landing gear I (8) and landing gear II (9), the both sides of each threading hole (14) are respectively equipped with ear seat, and described roller I (1) and roller II (4) are installed in rotation on corresponding ear seat respectively.
6. according to claim 1 without man-machine landing gear, it is characterized in that, the inner side of described landing gear limited block (10) is provided with installation gap, one end of described landing gear I (8) and landing gear II (9) is arranged in the installation gap on corresponding landing gear limited block (10) by hinge (13), and can rotate around hinge (13).
7. according to claim 6 without man-machine landing gear, it is characterized in that, described torsion spring (11) is placed in the installation gap on landing gear limited block (10) Nei and is set on described hinge (13), one end of described torsion spring (11) is connected with landing gear limited block (10), and the other end is connected with described landing gear I (8) or landing gear II (9).
8. according to claim 7 without man-machine landing gear, it is characterized in that, described landing gear I (8) and landing gear II (9) are equipped with torsion spring (11) junction and are connected block (12), described connection block (12) is provided with and connects hole, and the other end of described torsion spring (11) is inserted in the connection hole on described connection block (12).
9. according to the arbitrary item of claim 1-8 without man-machine landing gear, it is characterised in that, described landing gear is two groups, the bracing wire stow mechanism in two groups of landing gears be cross intersect arrange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520988889.9U CN205311894U (en) | 2015-12-02 | 2015-12-02 | Unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520988889.9U CN205311894U (en) | 2015-12-02 | 2015-12-02 | Unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205311894U true CN205311894U (en) | 2016-06-15 |
Family
ID=56315674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520988889.9U Withdrawn - After Issue CN205311894U (en) | 2015-12-02 | 2015-12-02 | Unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205311894U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416574A (en) * | 2015-12-02 | 2016-03-23 | 上海云犀智能***有限公司 | Unmanned aerial vehicle undercarriages |
| CN107600393A (en) * | 2017-09-19 | 2018-01-19 | 中国科学院工程热物理研究所 | The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane |
| WO2018053715A1 (en) * | 2016-09-21 | 2018-03-29 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN109305333A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | A kind of retractable unmanned plane of undercarriage |
| CN109319092A (en) * | 2018-11-06 | 2019-02-12 | 深圳市富裕泰贸易有限公司 | It is a kind of can gear up unmanned plane |
| CN109319093A (en) * | 2018-11-06 | 2019-02-12 | 深圳市富裕泰贸易有限公司 | A kind of unmanned plane |
| US10710711B2 (en) | 2016-09-21 | 2020-07-14 | SZ DJI Technology Co., Ltd. | Systems and methods for UAV sensor placement |
| CN112124572A (en) * | 2020-09-21 | 2020-12-25 | 宁波工程学院 | Energy-concerving and environment-protective flight formula robot |
-
2015
- 2015-12-02 CN CN201520988889.9U patent/CN205311894U/en not_active Withdrawn - After Issue
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416574A (en) * | 2015-12-02 | 2016-03-23 | 上海云犀智能***有限公司 | Unmanned aerial vehicle undercarriages |
| WO2018053715A1 (en) * | 2016-09-21 | 2018-03-29 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| US10710711B2 (en) | 2016-09-21 | 2020-07-14 | SZ DJI Technology Co., Ltd. | Systems and methods for UAV sensor placement |
| US20200339251A1 (en) * | 2016-09-21 | 2020-10-29 | SZ DJI Technology Co., Ltd. | Systems and methods for uav sensor placement |
| CN107600393A (en) * | 2017-09-19 | 2018-01-19 | 中国科学院工程热物理研究所 | The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane |
| CN109305333A (en) * | 2018-11-05 | 2019-02-05 | 深圳市金鑫城纸品有限公司 | A kind of retractable unmanned plane of undercarriage |
| CN109319092A (en) * | 2018-11-06 | 2019-02-12 | 深圳市富裕泰贸易有限公司 | It is a kind of can gear up unmanned plane |
| CN109319093A (en) * | 2018-11-06 | 2019-02-12 | 深圳市富裕泰贸易有限公司 | A kind of unmanned plane |
| CN112124572A (en) * | 2020-09-21 | 2020-12-25 | 宁波工程学院 | Energy-concerving and environment-protective flight formula robot |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160615 Effective date of abandoning: 20171031 |