CN205150231U - Novel folded piece of multiaxis aircraft - Google Patents
Novel folded piece of multiaxis aircraft Download PDFInfo
- Publication number
- CN205150231U CN205150231U CN201521010846.XU CN201521010846U CN205150231U CN 205150231 U CN205150231 U CN 205150231U CN 201521010846 U CN201521010846 U CN 201521010846U CN 205150231 U CN205150231 U CN 205150231U
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- CN
- China
- Prior art keywords
- kelly
- permanent seat
- horn base
- shift slot
- horn
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Abstract
The utility model discloses a novel folded piece of multiaxis aircraft, its characterized in that: including quick -witted arm pipe seat (1) and be used for supporting fixing base (2) of quick -witted arm pipe seat (1), the lower side at machine arm pipe seat (1) rear portion pass through axis of rotation (5) with quick -witted arm pipe seat (1) swing joint on fixing base (2), it keeps off position groove (4) still to be provided with in the both sides of fixing base (2), and locate to be provided with the opening in the fender position groove (4) of fixing base (2) front end, the upper end at machine arm pipe seat (1) rear portion is passed through kelly (3) activity and is set up on fixing base (2), and the both ends of kelly (3) are arranged in and are kept off on position groove (4), make upwarping the angle and can alternateing of multiaxis aircraft horn between 0 - 8 - 16 - 24, can turn down upwarping the angle when the high load of needs, can transfer greatly upwarping the angle when the needs high stability, like this alright in order to satisfy different load and stable demand, the anti -wind ability that can also make the multiaxis aircraft increases.
Description
Technical field
The utility model relates to unmanned plane field, specifically, is Multi-axis aircraft new type foldable part.
Background technology
At present, along with current unmanned plane is being taken photo by plane, aerial survey, forest fire protection, and application agriculturally progressively expands, its effect had more and more is subject to people's attention, but the function ratio that current operation unmanned plane has is more single, it is mainly subject to load-carrying, and the impact of these two factors of stability.Also the folding frame product of umbrella shape is had at present still because the angle that upwarps of its horn is changeless, so its scope of work is also limited by very large.So for this situation, in conjunction with design experiences in the past, have devised the new type foldable part of a Multi-axis aircraft.
Utility model content
The object of Multi-axis aircraft new type foldable part is the folding means providing multiaxis unmanned plane, the folded piece of Multi-axis aircraft its act as and can allow the horn of the Multi-axis aircraft folding volume reducing aircraft downwards, make it transport convenient; On the basis that we are former to the folded piece of Multi-axis aircraft in structure and functionally done significant improvement, it is made not only to have folding function, and his horn updip angle can change, to adapt to different operating environments and job requirements between 0 °-8 °-16 °-24 ° according to the needs of task.
The utility model is achieved through the following technical solutions: comprise horn base and the permanent seat for supporting horn base, horn base is movably connected on permanent seat by turning cylinder by the lower side at described horn base rear portion, also shift slot is provided with in the both sides of described permanent seat, and the shift slot place of permanent seat front end is provided with opening, the upper end at described horn base rear portion is movably arranged on permanent seat by kelly, and the two ends of kelly are placed on shift slot.
Further, for better realizing the utility model, be provided with fixed orifice below described horn base and permanent seat, horn base and permanent seat are flexibly connected by fixed orifice by described turning cylinder; The pipe of described horn base is provided with pipe clamp seam, and the side at described horn base rear portion is provided with kelly chute, in described kelly chute, is provided with kelly spring, the two ends of described kelly are placed on kelly spring.
Further, for better realizing the utility model, described shift slot is arranged on 1/3rd height of permanent seat side, and shift slot is provided with four gear notches, and described gear notch and gear notch make the updip angle of horn be the graded of 8 °.
Further, for better realizing the utility model, the two ends of described kelly are provided with baffle plate.Kelly is stuck in shift slot and horn base is immobilized, and it is connected to above horn base by kelly spring, and kelly can be up and down along the kelly chute on horn base, and kelly spring makes kelly be stuck in bottom shift slot due to elastic force effect; When needing the horn folded up to launch, first lift horn, by the time kelly is made can to enter into the breach of shift slot afterbody with an other hand to pressing down kelly when kelly will arrive shift slot afterbody breach (opening part of the shift slot of permanent seat front end), continue upwards to lift horn kelly and by spring upwards jack-up to such an extent as to be stuck in shift slot, gear shifting action will be completed.
Further, for better realizing the utility model, described horn base, permanent seat, shift slot, turning cylinder all adopt 6061T aviation duralumin, and kelly adopts stainless steel.
Further, for better realizing the utility model, the internal diameter of described horn base is 25mm and external diameter is 27mm, described permanent seat length is 50mm and width is 40mm, described kelly length is 53mm, described fixed orifice diameter is 3mm, and described pipe clamp seam width is 2mm and length is 35mm, described kelly chute height be 17.5mm and wide be 3mm.
The utility model compared with prior art, has the following advantages and beneficial effect:
This practical new construction is owing to have employed four different gears, make upwarping angle and can converting between 0 °-8 °-16 °-24 ° of Multi-axis aircraft horn, can turn down upwarping angle when the high load-carrying of needs, can tune up upwarping angle when needs high stability, so just, different load-carryings and durability requirements can be met, the wind loading rating of Multi-axis aircraft can also be made to increase.
Accompanying drawing explanation
Fig. 1 is Multi-axis aircraft new type foldable part block diagram;
Fig. 2 is permanent seat block diagram;
Fig. 3 is horn base block diagram;
Fig. 4 is turning cylinder block diagram;
Fig. 5 is kelly block diagram;
In figure: 1-horn base, 2-permanent seat, 3-kelly, 4-shift slot, 5-turning cylinder, 6-kelly spring, 7-connecting bore, 8-pipe clamp stitches, 9-kelly chute, 10-baffle plate.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
Embodiment 1:
Multi-axis aircraft new type foldable part, as shown in Fig. 1,2,3,4,5, comprise horn base 1 and the permanent seat 2 for supporting horn base 1, horn base 1 is movably connected on permanent seat 2 by turning cylinder 5 by the lower side at described horn base 1 rear portion, shift slot 4 is also provided with in the both sides of described permanent seat 2, and shift slot 4 place of permanent seat 2 front end is provided with opening, the upper end at described horn base 1 rear portion is movably arranged on permanent seat 2 by kelly 3, and the two ends of kelly 3 are placed on shift slot 4, make horn base 1 can be axle center activity along turning cylinder 5.
Embodiment 2:
The present embodiment is at the enterprising one-step optimization in the basis of above-described embodiment, further, for better realizing the utility model, as shown in Fig. 1,2,3,4,5, be provided with fixed orifice 7 below described horn base 1 and permanent seat 2, horn base 1 and permanent seat 2 are axially flexibly connected by fixed orifice 7 by described turning cylinder 5; The pipe of described horn base 1 is provided with pipe clamp seam 8, the side at described horn base 1 rear portion is provided with kelly chute 9, kelly spring 6 is provided with in described kelly chute 9, the two ends of described kelly 3 are placed on kelly spring 6, the kelly 3 that kelly spring 6 withstands, make kelly 3 under the effect of external force can only in kelly chute 9 restraint.
Embodiment 3:
The present embodiment is at the enterprising one-step optimization in the basis of above-mentioned any embodiment, further, for better realizing the utility model, as shown in Fig. 1,2,3,4,5, described shift slot 4 is arranged on 1/3rd height of permanent seat 2 side, and shift slot 4 is provided with four gear notches, and described gear notch and gear notch make the updip angle of horn be the graded of 8 °, shift slot 4 afterbody is provided with breach, kelly 3 can be allowed to slip into or skid off shift slot 4.
Embodiment 4:
The present embodiment is at the enterprising one-step optimization in the basis of above-mentioned any embodiment, further, for better realizing the utility model, as shown in Fig. 1,2,3,4,5, the two ends of described kelly 3 are provided with baffle plate 10, kelly 3 is arranged in the kelly chute 9 of horn base 1, the sway when baffle plate that two ends are arranged on kelly 3 can prevent kelly 3 from moving in chute; The shift slot 4 li that is stuck in of kelly 3 makes horn base 1 immobilize, it is connected to above horn base 1 by kelly spring 6, kelly 3 can be up and down along the kelly chute on horn base 1, kelly spring 6 is positioned in kelly chute, and kelly spring 6 makes kelly 3 be stuck in bottom shift slot 4 due to elastic force effect; When needing the horn folded up to launch, first horn is lifted, by the time kelly 3 is made can to enter into the breach of shift slot afterbody with an other hand to pressing down kelly when kelly 3 will arrive shift slot afterbody breach, continuing upwards to lift horn kelly 3 will by spring upwards jack-up to such an extent as to be stuck in shift slot 4 li, complete gear shifting action, as other gears need be changed, only need switch as stated above.
Embodiment 5:
The present embodiment is at the enterprising one-step optimization in the basis of above-mentioned any embodiment, further, for better realizing the utility model, described parts horn base 1, permanent seat 2, shift slot 4, turning cylinder 5 all adopt 6061T aviation duralumin, and kelly 3 adopts stainless steel.
Embodiment 6:
The present embodiment is at the enterprising one-step optimization in the basis of embodiment 2-5 any embodiment, further, for better realizing the utility model, as shown in Fig. 1,2,3,4,5, the internal diameter of described horn base 1 is 25mm external diameter is 27mm, described permanent seat 2 length is 50mm width is 40mm, described kelly 3 length is 53mm, and described fixed orifice 7 diameter is 3mm, and described pipe clamp stitches 8 width and is 2mm and length is 35mm, the high 17.5mm of described kelly chute 9, wide 3mm.
The above; it is only preferred embodiment of the present utility model; not do any pro forma restriction to the utility model, every any simple modification, equivalent variations done above embodiment according to technical spirit of the present utility model, all falls within protection domain of the present utility model.
Claims (6)
1. Multi-axis aircraft new type foldable part, it is characterized in that: comprise horn base (1) and the permanent seat (2) for supporting horn base (1), horn base (1) is movably connected on permanent seat (2) by turning cylinder (5) by the lower side at described horn base (1) rear portion, shift slot (4) is also provided with in the both sides of described permanent seat (2), and shift slot (4) place of permanent seat (2) front end is provided with opening, the upper end at described horn base (1) rear portion is movably arranged on permanent seat (2) by kelly (3), and the two ends of kelly (3) are placed on shift slot (4).
2. Multi-axis aircraft new type foldable part according to claim 1, it is characterized in that: described horn base (1) and permanent seat (2) below are provided with fixed orifice (7), and horn base (1) and permanent seat (2) are flexibly connected by fixed orifice (7) by described turning cylinder (5); The pipe of described horn base (1) is provided with pipe clamp seam (8), the side at described horn base (1) rear portion is provided with kelly chute (9), in described kelly chute (9), be provided with kelly spring (6), the two ends of described kelly (3) are placed on kelly spring (6).
3. Multi-axis aircraft new type foldable part according to claim 1, it is characterized in that: described shift slot (4) is arranged on 1/3rd height of permanent seat (2) side, and shift slot (4) is provided with four gear notches, described gear notch and gear notch make the updip angle of horn be the graded of 8 °.
4. Multi-axis aircraft new type foldable part according to claim 1, is characterized in that: the two ends of described kelly (3) are also provided with baffle plate (10).
5. Multi-axis aircraft new type foldable part according to claim 1, is characterized in that: described horn base (1), permanent seat (2), shift slot (4), turning cylinder (5) all adopt 6061T aviation duralumin, and described kelly (3) adopts stainless steel.
6. Multi-axis aircraft new type foldable part according to claim 2, it is characterized in that: the internal diameter of described horn base (1) is 25mm and external diameter is 27mm, described permanent seat (2) length is 50mm and width is 40mm, described kelly (3) length is 53mm, described fixed orifice (7) diameter is 3mm, described pipe clamp seam (8) width is 2mm and length is 35mm, described kelly chute (9) height be 17.5mm and wide be 3mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521010846.XU CN205150231U (en) | 2015-12-08 | 2015-12-08 | Novel folded piece of multiaxis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521010846.XU CN205150231U (en) | 2015-12-08 | 2015-12-08 | Novel folded piece of multiaxis aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205150231U true CN205150231U (en) | 2016-04-13 |
Family
ID=55685949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521010846.XU Expired - Fee Related CN205150231U (en) | 2015-12-08 | 2015-12-08 | Novel folded piece of multiaxis aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205150231U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905292A (en) * | 2016-05-03 | 2016-08-31 | 北京京东尚科信息技术有限公司 | Propeller installation structure and unmanned aerial vehicle |
| CN107031828A (en) * | 2016-06-27 | 2017-08-11 | Mmp有限公司 | A kind of unmanned plane |
| CN112977795A (en) * | 2021-04-10 | 2021-06-18 | 黑龙江工程学院 | Intelligent remote sensing unmanned aerial vehicle structure |
-
2015
- 2015-12-08 CN CN201521010846.XU patent/CN205150231U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905292A (en) * | 2016-05-03 | 2016-08-31 | 北京京东尚科信息技术有限公司 | Propeller installation structure and unmanned aerial vehicle |
| CN105905292B (en) * | 2016-05-03 | 2024-04-16 | 北京京东乾石科技有限公司 | Screw mounting structure and unmanned aerial vehicle |
| CN107031828A (en) * | 2016-06-27 | 2017-08-11 | Mmp有限公司 | A kind of unmanned plane |
| CN112977795A (en) * | 2021-04-10 | 2021-06-18 | 黑龙江工程学院 | Intelligent remote sensing unmanned aerial vehicle structure |
| CN112977795B (en) * | 2021-04-10 | 2021-09-14 | 黑龙江工程学院 | Intelligent remote sensing unmanned aerial vehicle structure |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160413 Termination date: 20201208 |