CN104527980A - Transportation throwing mechanism of unmanned helicopter - Google Patents
Transportation throwing mechanism of unmanned helicopter Download PDFInfo
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- CN104527980A CN104527980A CN201410775167.5A CN201410775167A CN104527980A CN 104527980 A CN104527980 A CN 104527980A CN 201410775167 A CN201410775167 A CN 201410775167A CN 104527980 A CN104527980 A CN 104527980A
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- steering wheel
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Abstract
The invention relates to a transportation throwing mechanism of an unmanned helicopter. A cabin door, used for throwing, of the unmanned helicopter is provided with a hinge; the position, close to the hinge, of the cabin door is provided with a door plate connector; the door plate connector is provided with a first fisheye bearing; a lead screw is connected in the first fisheye bearing; the other end of the lead screw is connected with a second fisheye bearing; the second fisheye bearing is connected with a steering engine; the steering engine is fixed on a steering engine fixer; the steering engine fixer is connected to the side wall of the cabin door of the unmanned helicopter; the steering engine is provided with a steering engine rocker; the steering engine rocker is connected with the second fisheye bearing; a conveying rod is vertically inserted in the connecting position of the lead screw and the second fisheye bearing; and the other end of the conveying rod is connected with a side plate connector installed on the side wall of the cabin door of the unmanned helicopter. The transportation throwing mechanism of the unmanned helicopter is capable of stably loading the goods to the appointed position and throwing and reducing the wind resistance and instability, providing the convenience for the airplane to integrate more electronic devices, and enlarging the using range of the unmanned helicopter throwing, and the flying power consumption is small for a long time.
Description
Technical field
The present invention relates to a kind of depopulated helicopter and transport mechanism of jettisoninging, belong to unmanned air vehicle technique field.
Background technology
Along with unmanned plane is applied widely, the functional requirement that unmanned plane can realize is got more and more, unmanned plane relies on self advantage can arrive the higher place of manned danger coefficient to carry out operation, and the mechanism but the transport being never applicable to medium-sized depopulated helicopter is jettisoninged and traditional rope hanging exist center shakiness, windage is large, danger coefficient is higher problem.For this reason, devise and can the transport of load mode to jettisoning its structure of mechanism.
Summary of the invention
For existing above-mentioned shortcoming, the invention provides a kind of depopulated helicopter and transport mechanism of jettisoninging, can jettisoning and windage and fugitiveness can be reduced in pulsation-free loading goods and materials arrival appointed place.
To achieve these goals, technical scheme of the present invention is as follows.
A kind of depopulated helicopter transports mechanism of jettisoninging, on the hatch door of jettisoninging, hinge is provided with at depopulated helicopter, hatch door is provided with door-plate attaching parts near the position of hinge, door-plate attaching parts is provided with the first flake bearing, screw mandrel is connected with in first flake bearing, the screw mandrel other end is connected with the second flake bearing, and the second flake bearing is connected with steering wheel; Steering wheel is fixed on steering wheel connecting element, and steering wheel connecting element is connected on the hatch door sidewall of unmanned plane; Steering wheel is provided with steering wheel rocking arm, steering wheel rocking arm is connected with the second flake bearing; Screw mandrel is vertical with the second flake bearing junction is inserted with driven rod; The driven rod other end is connected with the side plate attaching parts be arranged on the reveal wall of engine room zero people.
Further, the two ends bearing of drive link is respectively arranged with the first locating dowel pin and the second locating dowel pin.
Further, lateral connector is respectively arranged with the first socket head cap screw, the 4th socket head cap screw, the 5th socket head cap screw be fixed in engine room zero people reveal wall.
Further, hinge adopts the second socket head cap screw to be fixed on unmanned plane hatch door.
Further, drive link two ends are provided with flange bearing, and flange bearing adopts the 6th socket head cap screw to be fixed on side plate attaching parts.
Further, steering wheel connecting element is provided with the 3rd socket head cap screw to be connected with engine room zero people reveal wall; Steering wheel connecting element arranged outside has the first fuselage attaching parts.
Further, reveal wall in engine room zero people is provided with the second fuselage attaching parts and the 3rd fuselage attaching parts in order to be connected and fixed this device.
This beneficial effect of the invention is: mechanism of the present invention can jettisoning and can reduce windage and fugitiveness in pulsation-free loading goods and materials arrival appointed place, also very little at flying for long time consumption of current, for the integrated more electronic machine of aircraft is provided convenience, expand the range of use that unmanned plane is jettisoninged.
Accompanying drawing explanation
Fig. 1 is the device inner structure schematic diagram in the embodiment of the present invention.
Fig. 2 is the left TV structure schematic diagram of Fig. 1 equipment therefor.
Fig. 3 is the A-A cross section structure schematic diagram of schematic diagram in Fig. 2.
Fig. 4 is the B-B cross section structure schematic diagram of schematic diagram in Fig. 2.
Fig. 5 is the C-C cross section structure schematic diagram of schematic diagram in Fig. 2.
Fig. 6 is this device closure state schematic diagram in the present embodiment.
Fig. 7 is that schematic diagram is proved in the self-locking of this mechanism in the present embodiment.
Fig. 8 is the unlimited principle schematic of this mechanism in the present embodiment.
Description of symbols in figure: 1, drive link; 2, the first fuselage attaching parts; 3, the first flake bearing; 4, steering wheel connecting element; 5, screw mandrel; 6, the first socket head cap screw; 7, hinge; 8, steering wheel; 9, side plate attaching parts; 10, the first locating dowel pin; 11, the second locating dowel pin; 12, the second fuselage attaching parts; 13, the 3rd fuselage attaching parts; 14, door-plate attaching parts; 15, the second socket head cap screw; 16, the 3rd socket head cap screw; 17, the 4th socket head cap screw; 18, the 5th socket head cap screw; 19, the 6th socket head cap screw; 20, flange bearing; 21, the second flake bearing; 22, steering wheel rocking arm.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described, better to understand the present invention.
Embodiment
As shown in Figure 1, Figure 2, the depopulated helicopter shown in Fig. 3, Fig. 4, Fig. 5 transports mechanism of jettisoninging, on the hatch door of jettisoninging, hinge 7 is provided with at depopulated helicopter, hatch door is provided with door-plate attaching parts 14 near the position of hinge 7, door-plate attaching parts 14 is provided with the first flake bearing 3, screw mandrel 5 is connected with in first flake bearing 3, screw mandrel 5 other end is connected with on the second flake bearing 21, second flake bearing 21 and is connected with steering wheel 8; Steering wheel 8 is fixed on steering wheel connecting element 4, and steering wheel connecting element 4 is connected on the hatch door sidewall of unmanned plane; Steering wheel 8 is provided with steering wheel rocking arm 22, steering wheel rocking arm 22 is connected with the second flake bearing 21; Screw mandrel 5 is vertical with the second flake bearing 21 junction is inserted with driven rod 1; Driven rod 1 other end is connected with the side plate attaching parts 9 be arranged on the reveal wall of engine room zero people.The two ends bearing of drive link 1 is respectively arranged with the first locating dowel pin 10 and the second locating dowel pin 11.Lateral connector 9 is respectively arranged with the first socket head cap screw 6, the 4th socket head cap screw 17, the 5th socket head cap screw 18 be fixed in engine room zero people reveal wall.Hinge 7 adopts the second socket head cap screw 15 to be fixed on unmanned plane hatch door.Drive link 1 two ends are provided with flange bearing 20, and flange bearing 20 adopts the 6th socket head cap screw 19 to be fixed on side plate attaching parts 9.Steering wheel connecting element 4 is provided with the 3rd socket head cap screw 16 to be connected with engine room zero people reveal wall; Steering wheel connecting element 4 arranged outside has the first fuselage attaching parts 2.Engine room zero people reveal wall is provided with the second fuselage attaching parts 12 and the 3rd fuselage attaching parts 13 in order to be connected and fixed this device.
As shown in Figure 6, be this device closure state schematic diagram.During steering wheel angle shown in the figure, hatch door is closure state, and can self-locking by gravity.
Fig. 7 is that schematic diagram is proved in the self-locking of this mechanism in the present embodiment.In figure, hatch door drives the displacement of B point with A point hinge axle center left-hand revolution under gravity, now the displacement of B point want C point with D point for center of circle left-hand revolution make rocking arm point to B point direction just can open hatch door still due to locating dowel pin limit rocking arm with the D point trend that is center of circle left-hand revolution thus under gravity hatch door cannot open, only have steering wheel just can open with hatch door during D point clickwise.
Fig. 8 is the unlimited principle schematic of this mechanism in the present embodiment.In figure, steering wheel is with D point for center of circle clickwise 140 degree drives hatch door to open wide 90 degree, and its stroke I is equal with stroke II.
The concrete installation process of said mechanism is as follows: (1) machine screw of first steering is fixed on steering wheel connecting element; (2) steering wheel rocking arm being loaded on steering wheel, now needing the neutrality point coordinating remote controller to set steering wheel to make steering wheel when opening closed all in stroke range.(3) on rocking arm, fill flake negative thread bearing.(4) silk post is screwed on flake bearing simultaneously at silk post and flake bearing diameter insertion drive link.(5) to screw on flake bearing at the other end of silk post.(6) flake bearing connects hatch door.
Mechanism of the present invention operationally, first manually pull drive link that hatch door is opened, the goods and materials of jettisoninging needed for loading lift drive link again makes hatch door close, steering wheel energising makes it standby, because gravity steering wheel rocking arm is stuck on locating dowel pin, so steering wheel does not now stress, also very little at flying for long time consumption of current, for the integrated more electronic machine of aircraft is provided convenience.This mechanism receives on-off signal at receiver and passes to then master control board controls steering wheel after the analytic signal anglec of rotation to steering wheel instruction, and steering wheel drives rocking arm, rocking arm band movable wire post, silk cornice to move hatch door, completes hatch door and opens closed action.
The above is the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (7)
1. a depopulated helicopter transports mechanism of jettisoninging, it is characterized in that: on the hatch door of jettisoninging, be provided with hinge at depopulated helicopter, hatch door is provided with door-plate attaching parts near the position of hinge, described door-plate attaching parts is provided with the first flake bearing, screw mandrel is connected with in described first flake bearing, the described screw mandrel other end is connected with the second flake bearing, and described second flake bearing is connected with steering wheel; Described steering wheel is fixed on steering wheel connecting element, and described steering wheel connecting element is connected on the hatch door sidewall of unmanned plane; Described steering wheel is provided with steering wheel rocking arm, described steering wheel rocking arm is connected with the second flake bearing; Described screw mandrel is vertical with the second flake bearing junction is inserted with driven rod; The described driven rod other end is connected with the side plate attaching parts be arranged on the reveal wall of engine room zero people.
2. depopulated helicopter according to claim 1 transports mechanism of jettisoninging, and it is characterized in that: the two ends bearing of described drive link is respectively arranged with the first locating dowel pin and the second locating dowel pin.
3. depopulated helicopter according to claim 1 transport is jettisoninged mechanism, it is characterized in that: described lateral connector is respectively arranged with the first socket head cap screw, the 4th socket head cap screw, the 5th socket head cap screw be fixed in engine room zero people reveal wall.
4. depopulated helicopter according to claim 1 transports mechanism of jettisoninging, and it is characterized in that: described hinge adopts the second socket head cap screw to be fixed on unmanned plane hatch door.
5. depopulated helicopter according to claim 1 transports mechanism of jettisoninging, and it is characterized in that: described drive link two ends are provided with flange bearing, and described flange bearing adopts the 6th socket head cap screw to be fixed on side plate attaching parts.
6. depopulated helicopter according to claim 1 transports mechanism of jettisoninging, and it is characterized in that: described steering wheel connecting element is provided with the 3rd socket head cap screw and is connected with engine room zero people reveal wall; Described steering wheel connecting element arranged outside has the first fuselage attaching parts.
7. depopulated helicopter according to claim 1 transport is jettisoninged mechanism, it is characterized in that: described engine room zero people reveal wall is provided with the second fuselage attaching parts and the 3rd fuselage attaching parts in order to be connected and fixed this device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410775167.5A CN104527980B (en) | 2014-12-15 | 2014-12-15 | Transportation throwing mechanism of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410775167.5A CN104527980B (en) | 2014-12-15 | 2014-12-15 | Transportation throwing mechanism of unmanned helicopter |
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| Publication Number | Publication Date |
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| CN104527980A true CN104527980A (en) | 2015-04-22 |
| CN104527980B CN104527980B (en) | 2017-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410775167.5A Active CN104527980B (en) | 2014-12-15 | 2014-12-15 | Transportation throwing mechanism of unmanned helicopter |
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| CN (1) | CN104527980B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043698A (en) * | 2016-06-08 | 2016-10-26 | 青海山水生态科技有限公司 | Unmanned aerial vehicle hung type fire extinguishing bomb throwing bin and method |
| CN106114814A (en) * | 2016-07-22 | 2016-11-16 | 四川克瑞斯航空科技有限公司 | A kind of many rotor wing unmanned aerial vehicles |
| CN109843721A (en) * | 2016-10-27 | 2019-06-04 | 瓦斯菲·阿希达法特 | It searches and rescue unmanned plane is arranged |
| CN112009688A (en) * | 2020-08-29 | 2020-12-01 | 重庆领直航科技有限公司 | Unmanned aerial vehicle operation system and operation method thereof |
| CN112093054A (en) * | 2020-09-11 | 2020-12-18 | 重庆领直航科技有限公司 | Transport box and unmanned aerial vehicle |
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| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| CN1175537A (en) * | 1996-08-30 | 1998-03-11 | 波音公司 | Latch-lock mechanism for load carrying airplane cargo doors |
| CN201136592Y (en) * | 2007-12-13 | 2008-10-22 | 陕西飞机工业（集团）有限公司 | Opener for multi-stage port |
| CN201220748Y (en) * | 2008-05-28 | 2009-04-15 | 江西洪都航空工业集团有限责任公司 | Balancing device for side-turning type hatch cover opening |
| US20130200214A1 (en) * | 2012-02-07 | 2013-08-08 | Bell Helicopter Textron Inc. | Low profile jettisonable door system |
| US20130264424A1 (en) * | 2012-03-15 | 2013-10-10 | Airbus Operations (Sas) | Aircraft door installation |
| CN103790460A (en) * | 2012-11-01 | 2014-05-14 | 上海新跃仪表厂 | Automatic rapid opening and closing mechanism of cabin door |
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2014
- 2014-12-15 CN CN201410775167.5A patent/CN104527980B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4601446A (en) * | 1983-09-29 | 1986-07-22 | The Boeing Company | Aircraft door counterbalance system |
| CN1175537A (en) * | 1996-08-30 | 1998-03-11 | 波音公司 | Latch-lock mechanism for load carrying airplane cargo doors |
| CN201136592Y (en) * | 2007-12-13 | 2008-10-22 | 陕西飞机工业（集团）有限公司 | Opener for multi-stage port |
| CN201220748Y (en) * | 2008-05-28 | 2009-04-15 | 江西洪都航空工业集团有限责任公司 | Balancing device for side-turning type hatch cover opening |
| US20130200214A1 (en) * | 2012-02-07 | 2013-08-08 | Bell Helicopter Textron Inc. | Low profile jettisonable door system |
| US20130264424A1 (en) * | 2012-03-15 | 2013-10-10 | Airbus Operations (Sas) | Aircraft door installation |
| CN103790460A (en) * | 2012-11-01 | 2014-05-14 | 上海新跃仪表厂 | Automatic rapid opening and closing mechanism of cabin door |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043698A (en) * | 2016-06-08 | 2016-10-26 | 青海山水生态科技有限公司 | Unmanned aerial vehicle hung type fire extinguishing bomb throwing bin and method |
| CN106043698B (en) * | 2016-06-08 | 2019-04-12 | 青海山水生态科技有限公司 | A kind of unmanned plane hanging fire extinguisher bomb dispensing cabin and method of dropping a bomb |
| CN106114814A (en) * | 2016-07-22 | 2016-11-16 | 四川克瑞斯航空科技有限公司 | A kind of many rotor wing unmanned aerial vehicles |
| CN109843721A (en) * | 2016-10-27 | 2019-06-04 | 瓦斯菲·阿希达法特 | It searches and rescue unmanned plane is arranged |
| CN109843721B (en) * | 2016-10-27 | 2023-04-21 | 瓦斯菲·阿希达法特 | Search and rescue unmanned aerial vehicle arrangement |
| CN112009688A (en) * | 2020-08-29 | 2020-12-01 | 重庆领直航科技有限公司 | Unmanned aerial vehicle operation system and operation method thereof |
| CN112093054A (en) * | 2020-09-11 | 2020-12-18 | 重庆领直航科技有限公司 | Transport box and unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104527980B (en) | 2017-01-11 |
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