CN203419258U - Rear three-point guiding device for unmanned aerial vehicle - Google Patents
Rear three-point guiding device for unmanned aerial vehicle Download PDFInfo
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- CN203419258U CN203419258U CN201320480952.9U CN201320480952U CN203419258U CN 203419258 U CN203419258 U CN 203419258U CN 201320480952 U CN201320480952 U CN 201320480952U CN 203419258 U CN203419258 U CN 203419258U
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- attaching parts
- main shaft
- unmanned plane
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- connecting rod
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Abstract
The utility model provides a rear three-point guiding device for an unmanned aerial vehicle. The guiding device comprises a main shaft 1, a vertical fin connecting part 2, a vehicle body connecting part 3, a main shaft connecting part 4, a guide wheel 5, a transverse bearing 6, a longitudinal bearing 7, a buffer part 8, a first connecting part 9 and a second connecting part 10. The guiding device has the advantages as follows: 1, guiding during the taking off, landing and ground sliding processes of the unmanned aerial vehicle is flexible; 2, good damping effect is achieved when the unmanned aerial vehicle lands on the ground; 3, the structural design is simple, and easy to understand, and the disassembling and assembling are convenient; 4, the structure quality is good and the weight is small.
Description
Technical field
The utility model relates to guide piece after unmanned plane, is specifically related to 3 guide piecees after a kind of unmanned plane.
Background technology
Due to the sliding race runway that unmanned plane takes off and the basic need that lands is long and wider, and in civilian unmanned plane operation, tend to run into take-off venue bad, be difficult to desirable landing site, owing to taking off power, by screw propeller high speed rotating, produce powerful pulling force forward again, and the component that screw propeller can produce left and make progress, thereby cause aircraft be difficult on a narrow road, run without excessively multi-control in the situation that straight, and because vertical fin rudder face need to be in the situation that air speed runs, steerage just has some effects, and often aircraft in the situation that speed is not also got up or is had crosswind, the aircraft vertical fin just nothing of performance has acted on, thereby make aircraft easily in the sliding race in landing land, uncontrollable and hit roadside, cause the damage of aircraft or knock passerby, thereby cause unnecessary loss and danger.In addition, aircraft runs landing while contacting to earth sliding, because the effect of power is mutual, so ground can be to undercarriage one the powerful power that rebounds, thereby causes breaking of airframe.Therefore, need to work out a aircraft that can lead flexibly, there is again the guide piece of cushioning effect, in order to avoid cause unnecessary loss and danger.
But, in realizing process of the present utility model, contriver finds, at least has following defect in prior art:
After existing aircraft, track adjusting wheel is basic only by a wheel support, and wheel and aircraft are hard links, therefore, on the one hand: in taking off process, along with airplane throttle slowly increases, when landing site is undesirable and the crosswind that takes off is larger, aircraft also can slowly produce deflection force left accordingly, and this burst of deflection force also can increase accordingly along with the variation of throttle, thereby make the easy sideslip of aircraft, a but wheel, only rely on vertical fin guiding, aircraft is turned to dumb, when even vertical fin maximum torque is not offset screw propeller deflection force yet, aircraft will knock roadside and pedestrian, on the other hand: in aircraft landing process, because air speed is very fast and inertia is larger, so when aircraft contacts to earth, ground has burst powerful power to alighting gear, and alighting gear and fuselage hard link easily damage fuselage when landing.
Utility model content
The defect existing for prior art, the utility model provides after a kind of unmanned plane 3 guide piecees and guidance method, is applied to the rear guiding of civil small-scale unmanned plane, has unmanned plane guiding and landing damping effect flexibly.
The technical solution adopted in the utility model is as follows:
The utility model provides 3 guide piecees after a kind of unmanned plane, comprising: main shaft (1), vertical fin attaching parts (2), fuselage attaching parts (3), main shaft attaching parts (4), track adjusting wheel (5), laterally bearing (6), longitudinally bearing (7), damper element (8), the first attaching parts (9) and the second attaching parts (10);
Described main shaft (1) vertically arranges, the bottom of described main shaft (1) is fixedly connected with described horizontal bearing (6) centre, and the top of described main shaft (1) is fixedly connected with described fuselage attaching parts (3) by described longitudinal bearing (7); Described main shaft (1) is also fixedly connected with described vertical fin attaching parts (2) by described main shaft attaching parts (4);
One end of described horizontal bearing (6) is fixedly connected with a side in described track adjusting wheel (5) axle center by described the first attaching parts (9); The other end of described horizontal bearing (6) is fixedly connected with the opposite side in described track adjusting wheel (5) axle center by described the second attaching parts (10);
Described damper element (8) is fixedly installed between described main shaft (1) and described track adjusting wheel (5).
Preferably, described main shaft attaching parts (4) comprises first connecting rod (41), second connecting rod (42) and third connecting rod (43); One end of described first connecting rod (41) is fixedly connected with described vertical fin attaching parts (2); The other end of described first connecting rod (41) is fixedly connected with one end of described second connecting rod (42); The other end of described second connecting rod (42) is fixedly connected with one end of described third connecting rod (43); The other end of described third connecting rod (43) and described main shaft (1) are in transmission connection.
Preferably, groove is offered in the bottom of described main shaft (1), and described groove fixes the periphery at described horizontal bearing (6).
Preferably, described damper element (8) comprising: the first strut bar (81), the second strut bar (82) and buffer unit (83); Described the first strut bar (81) is fixed on described main shaft (1), described the second strut bar (82) is fixed on the transverse axis in the middle of described attaching parts (9) and attaching parts (10), and described buffer unit (83) is fixedly mounted between described the first strut bar (81) and described the second strut bar (82).
Preferably, described buffer unit (83) is spring.
Preferably, described track adjusting wheel (5) is rubber track adjusting wheel; Described horizontal bearing (6) is cylinder bearing; Described longitudinal bearing (7) is cylinder bearing; Described main shaft (1) is aluminum alloy main shaft; Described the first attaching parts (9) and described the second attaching parts (10) are respectively carbon fiber attaching parts.
The utility model also provides a kind of method of applying 3 guide piecees after unmanned plane, comprises the following steps:
S1, the described vertical fin attaching parts (2) of 3 guide piecees after described unmanned plane is fixedly installed to unmanned plane vertical fin rudder face position, described fuselage attaching parts (3) is fixedly installed to unmanned aerial vehicle body position, makes after described unmanned plane 3 guide piecees and unmanned plane vertical fin in the same way;
S2, when unmanned plane sideslip, sends corrected signal to the vertical fin steering wheel of unmanned plane, and vertical fin steering wheel is controlled vertical fin according to described corrected signal and rotated; When vertical fin rotates, drive 3 guide piecees after described unmanned plane to rotate, realize unmanned plane and turn to;
When unmanned plane landing is contacted to earth in process, stress is fed back to unmanned plane in ground, and under the effect of this stress, described track adjusting wheel (5) is upwards rotated according to the radius to described main shaft (1), and then compression damper element (8), damper element (8) is offset the effect of this stress;
Preferably, in S2, by manual control or computer mode, to the vertical fin steering wheel of unmanned plane, send corrected signal.
Preferably, in S2, when vertical fin rotates, drive 3 guide piecees after described unmanned plane to rotate, realize unmanned plane and turn to and be specially:
When vertical fin rotates, drive the vertical fin attaching parts (2) being fixedly connected with vertical fin to rotate; Under the drive of rotating at vertical fin attaching parts (2), drive the main shaft attaching parts (4) being fixedly connected with vertical fin attaching parts (2) to rotate; Under the drive of rotating at main shaft attaching parts (4), drive the main shaft (1) being fixedly connected with main shaft attaching parts (4) to rotate;
When main shaft (1) rotates, drive the horizontal bearing (6) being fixedly connected with main shaft (1) to rotate;
Under the drive that laterally bearing (6) rotates, final drive with the track adjusting wheel (5) that laterally bearing (6) is fixedly connected with rotated, and realizes unmanned plane and turns to.
3 guide piecees and guidance method after the unmanned plane that the utility model provides, have the following advantages:
(1) can in the sliding race process of unmanned plane landing, lead flexibly;
(2) when contacting to earth, aircraft landing there is good damping effect;
(3) have that structure design is easily understood, quick detachable and easy-to-install advantage;
(4) there is good, the lightweight advantage of architecture quality.
Accompanying drawing explanation
The marking structure schematic diagram of 3 guide piecees after the unmanned plane that Fig. 1 provides for the utility model;
The structural representation of 3 guide piecees after the unmanned plane that Fig. 2 provides for the utility model;
The birds-eye view of 3 guide piecees after the unmanned plane that Fig. 3 provides for the utility model;
The lateral plan of 3 guide piecees after the unmanned plane that Fig. 4 provides for the utility model;
The front elevation of 3 guide piecees after the unmanned plane that Fig. 5 provides for the utility model;
Fig. 6 for the unmanned plane that the utility model is provided after 3 guide piecees be installed to the integral structure schematic diagram on unmanned plane; Wherein, 22---vertical fin; 23---yaw rudder; 3 guide piecees after 24---unmanned plane.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is elaborated:
As Figure 1-5, the utility model provides 3 guide piecees after a kind of unmanned plane, as shown in Figure 6, and for 3 guide piecees after this unmanned plane are installed to the integral structure schematic diagram on unmanned plane.After unmanned plane, 3 guide piecees comprise: main shaft 1, vertical fin attaching parts 2, fuselage attaching parts 3, main shaft attaching parts 4, track adjusting wheel 5, horizontal bearing 6, longitudinal bearing 7, damper element 8, the first attaching parts 9 and the second attaching parts 10; Wherein, main shaft 1 vertically arranges, and the bottom of main shaft 1 is fixedly connected with horizontal bearing 6 centres, and the top of main shaft 1 is fixedly connected with fuselage attaching parts 3 by longitudinal bearing 7; Main shaft 1 is also fixedly connected with vertical fin attaching parts 2 by main shaft attaching parts 4; Laterally one end of bearing 6 is fixedly connected with a side in track adjusting wheel 5 axle center by the first attaching parts 9; Laterally the other end of bearing 6 is fixedly connected with the opposite side in track adjusting wheel 5 axle center by the second attaching parts 10; Damper element 8 is fixedly installed between main shaft 1 and track adjusting wheel 5.
Concrete, main shaft attaching parts 4 comprises first connecting rod 41, second connecting rod 42 and third connecting rod 43; One end of first connecting rod 41 is fixedly connected with vertical fin attaching parts 2; The other end of first connecting rod 41 is fixedly connected with one end of second connecting rod 42; The other end of second connecting rod 42 is fixedly connected with one end of third connecting rod 43; The other end of third connecting rod 43 and main shaft 1 are in transmission connection.By main shaft attaching parts 4, whole guide piece is connected with vertical fin, this rear alighting gear and vertical fin are led in the same way, and then make aircraft guiding safety more flexibly.Fuselage attaching parts 3 is combined whole guide piece with fuselage, fuselage attaching parts 3 is assembled together with longitudinal bearing 7 by lead to outside from fuselage interior, whole guide piece is fixed on fuselage, wherein, longitudinally bearing 7 is preferably a cylinder bearing, have and make the level and smooth effect of rotating of whole guide piece, thus effectively alleviate vertical fin steering wheel to power, guarantee that track adjusting wheel rotates smoothly and prevent the overexertion of vertical fin steering wheel and sweep tooth.Groove is offered in the bottom of main shaft 1, and groove fixes the periphery at horizontal bearing 6.By the effect of groove, main shaft 1 is fixedly connected with horizontal bearing 6, when main shaft 1 rotates, can drive horizontal bearing 6 to rotate.
In the utility model, track adjusting wheel 5 can adopt High molecular material rubber wheel, there is the features such as soft, wear-resisting, thereby there is suitable damping effect, aircraft is when landing simultaneously, fuselage, to track adjusting wheel pressure, makes track adjusting wheel and ground produce powerful friction force, the effect of slowing down in the time of so just well reaching aircraft landing.Main shaft 1 can adopt aluminum alloy to be made, and it has high strength, the feature such as lightweight; The first attaching parts 9 and the second attaching parts 10 are preferably respectively high-intensity carbon fiber attaching parts, and it act as and makes the axis of guide and main shaft perfect adaptation.Horizontal bearing 6 is preferably horizontal cylinder minor axis and holds, and its effect is to spring, to play the effect of buffering, can make track adjusting wheel according to the radius of main shaft 1, upwards rotate when being subject to ground impact, thereby play good damping effect.
The utility model also provides a kind of method of applying 3 guide piecees after above-mentioned unmanned plane, comprises the following steps:
S1, is fixedly installed to unmanned plane vertical fin rudder face position by the vertical fin attaching parts 2 of 3 guide piecees after unmanned plane, and fuselage attaching parts 3 is fixedly installed to unmanned aerial vehicle body position, makes after unmanned plane 3 guide piecees and unmanned plane vertical fin in the same way;
S2, (1), when unmanned plane sideslip, sends corrected signal to the vertical fin steering wheel of unmanned plane, and vertical fin steering wheel is controlled vertical fin according to corrected signal and is rotated; When vertical fin rotates, after drive unmanned plane, 3 guide piecees rotate, and realize unmanned plane and turn to; Wherein, can pass through manual control or computer mode, to the vertical fin steering wheel of unmanned plane, send corrected signal.
Wherein, when vertical fin rotates, drive unmanned plane after 3 guide piecees rotate, realize unmanned plane and turn to and be specially:
When vertical fin rotates, drive the vertical fin attaching parts 2 being fixedly connected with vertical fin to rotate; Under the drive of rotating at vertical fin attaching parts 2, drive the main shaft attaching parts 4 being fixedly connected with vertical fin attaching parts 2 to rotate; Under the drive of rotating at main shaft attaching parts 4, drive the main shaft 1 being fixedly connected with main shaft attaching parts 4 to rotate;
When main shaft 1 rotates, drive the horizontal bearing 6 being fixedly connected with main shaft 1 to rotate;
Under the drive that laterally bearing 6 rotates, final drive with the track adjusting wheel 5 that laterally bearing 6 is fixedly connected with rotated, and realizes unmanned plane and turns to.
(2) when unmanned plane landing, contact to earth in process, stress is fed back to unmanned plane in ground, under the effect of this stress, track adjusting wheel 5 is upwards rotated according to the radius to main shaft 1, and then compression damper element 8, the transmission by power with disperse, damper element 8 is offset the effect of most stress.
In sum, 3 guide piecees and guidance method after the unmanned plane that the utility model provides, have the following advantages:
(1) can in the sliding race process of unmanned plane landing, lead flexibly;
(2) when contacting to earth, aircraft landing there is good damping effect;
(3) have that structure design is easily understood, quick detachable and easy-to-install advantage;
(4) there is good, the lightweight advantage of architecture quality.
The above is only preferred implementation of the present utility model; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of the utility model principle; can also make some improvements and modifications, these improvements and modifications also should be looked protection domain of the present utility model.
Claims (6)
1. 3 guide piecees after a unmanned plane, it is characterized in that, comprising: main shaft (1), vertical fin attaching parts (2), fuselage attaching parts (3), main shaft attaching parts (4), track adjusting wheel (5), horizontal bearing (6), longitudinal bearing (7), damper element (8), the first attaching parts (9) and the second attaching parts (10);
Described main shaft (1) vertically arranges, the bottom of described main shaft (1) is fixedly connected with described horizontal bearing (6) centre, and the top of described main shaft (1) is fixedly connected with described fuselage attaching parts (3) by described longitudinal bearing (7); Described main shaft (1) is also fixedly connected with described vertical fin attaching parts (2) by described main shaft attaching parts (4);
One end of described horizontal bearing (6) is fixedly connected with a side in described track adjusting wheel (5) axle center by described the first attaching parts (9); The other end of described horizontal bearing (6) is fixedly connected with the opposite side in described track adjusting wheel (5) axle center by described the second attaching parts (10);
Described damper element (8) is fixedly installed between described main shaft (1) and described track adjusting wheel (5).
2. 3 guide piecees after unmanned plane according to claim 1, is characterized in that, described main shaft attaching parts (4) comprises first connecting rod (41), second connecting rod (42) and third connecting rod (43); One end of described first connecting rod (41) is fixedly connected with described vertical fin attaching parts (2); The other end of described first connecting rod (41) is fixedly connected with one end of described second connecting rod (42); The other end of described second connecting rod (42) is fixedly connected with one end of described third connecting rod (43); The other end of described third connecting rod (43) and described main shaft (1) are in transmission connection.
3. 3 guide piecees after unmanned plane according to claim 1, is characterized in that, groove is offered in the bottom of described main shaft (1), and described groove fixes the periphery at described horizontal bearing (6).
4. 3 guide piecees after unmanned plane according to claim 1, is characterized in that, described damper element (8) comprising: the first strut bar (81), the second strut bar (82) and buffer unit (83); Described the first strut bar (81) is fixed on described main shaft (1), described the second strut bar (82) is fixed on the transverse axis in the middle of described the first attaching parts (9) and described the second attaching parts (10), and described buffer unit (83) is fixedly mounted between described the first strut bar (81) and described the second strut bar (82).
5. 3 guide piecees after unmanned plane according to claim 4, is characterized in that, described buffer unit (83) is spring.
6. 3 guide piecees after unmanned plane according to claim 1, is characterized in that, described track adjusting wheel (5) is rubber track adjusting wheel; Described horizontal bearing (6) is cylinder bearing; Described longitudinal bearing (7) is cylinder bearing; Described main shaft (1) is aluminum alloy main shaft; Described the first attaching parts (9) and described the second attaching parts (10) are respectively carbon fiber attaching parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320480952.9U CN203419258U (en) | 2013-08-07 | 2013-08-07 | Rear three-point guiding device for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320480952.9U CN203419258U (en) | 2013-08-07 | 2013-08-07 | Rear three-point guiding device for unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN203419258U true CN203419258U (en) | 2014-02-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320480952.9U Withdrawn - After Issue CN203419258U (en) | 2013-08-07 | 2013-08-07 | Rear three-point guiding device for unmanned aerial vehicle |
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| CN (1) | CN203419258U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104071332A (en) * | 2013-08-07 | 2014-10-01 | 中科宇图天下科技有限公司 | Tail wheel guiding device for unmanned aerial vehicle and method using device |
| CN105923148A (en) * | 2016-05-19 | 2016-09-07 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage damping device |
-
2013
- 2013-08-07 CN CN201320480952.9U patent/CN203419258U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104071332A (en) * | 2013-08-07 | 2014-10-01 | 中科宇图天下科技有限公司 | Tail wheel guiding device for unmanned aerial vehicle and method using device |
| CN104071332B (en) * | 2013-08-07 | 2016-02-10 | 中科宇图天下科技有限公司 | 3 guide piecees and apply the method for this device after unmanned plane |
| CN105923148A (en) * | 2016-05-19 | 2016-09-07 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage damping device |
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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 |
Granted publication date: 20140205 Effective date of abandoning: 20160210 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |