CN103791002A - Brake device of unmanned aerial vehicle rotor wing - Google Patents
Brake device of unmanned aerial vehicle rotor wing Download PDFInfo
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- CN103791002A CN103791002A CN201410074380.3A CN201410074380A CN103791002A CN 103791002 A CN103791002 A CN 103791002A CN 201410074380 A CN201410074380 A CN 201410074380A CN 103791002 A CN103791002 A CN 103791002A
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Abstract
The invention relates to a brake device of an unmanned aerial vehicle rotor wing. The brake device comprises a drive shaft, a concentric drive gear, a brake disc A, a driven shaft, a concentric driven gear and a brake disc B. The concentric drive gear is fixedly connected to the output end of the drive shaft, the brake disc A is arranged on the drive shaft, the concentric driven gear is fixedly connected to the input end of the driven shaft, and the brake disc B is arranged on the driven shaft. The rotor wing comprises a rotor wing head and a main shaft, and a concentric main shaft gear is arranged on the main shaft. A brake component A is arranged on the brake disc A of the brake device, and a brake component B is arranged on the brake disc B. The drive gear and the driven gear are symmetrically arranged in a concentric mode, the main shaft gear is respectively meshed with the drive gear and the driven gear, and the main shaft gear, the drive gear and the driven gear are spiral beveled gears. In the prior art, when the main shaft gear brakes for deceleration, abrasion, caused by relative torsion and stress concentration, to the main shaft gear is reduced, and stability is improved when the rotor wing decelerates for transmission.
Description
Technical field
The invention belongs to braking device technical field, specifically, relate to a kind of braking device that is applied to unmanned plane rotor.
Background technique
Along with the development of unmanned plane technology, the especially fast development of pilotless helicopter, its application surface is more and more wider, all embodies indispensable significance at civil area and military domain.But when pilotless helicopter operation aloft, the rotational speed of driven by engine rotor is exceedingly fast, rotor to sweep away area larger, fuselage and rotor inertia in movement process is larger.In the time that rotor is out of control, as can not be in time to its braking, its powerful collapsing force over the ground dough figurine group or building causes very big harm.
Chinese patent CN203009640U discloses a kind of unmanned heligyro braking device aloft, and its structure is: the concentric gear inside in mast is provided with cavity, and multiple eccentric brake pads are set in cavity.Its friction by eccentric brake pad and gear cavity inner side reaches reduction gear rotational speed, thereby finally reduces the object of gyroplane rotate speed.Its shortcoming is: gear inside arranges cavity, has reduced the intensity of gear, has shortened the working life of gear; The eccentric brake pad of deceleration component is arranged at gear inside, is inconvenient to detect and keep in repair; Only slow down by the effect of frictional force, brake response is slow, and retardation efficiency is lower.
Summary of the invention
For solving the problems of the technologies described above, the present invention proposes one does not increase gear loss, and relatively simple for structure, brake response is fast, the unmanned plane rotor brake device that retardation efficiency is high.
Technological scheme of the present invention is: a kind of unmanned plane rotor brake device, and described rotor comprises rotor head and main shaft, main shaft is provided with concentric mainshaft gear; Described braking device comprises driving shaft, is fixed in the concentric driving gear of driving shaft output terminal, be arranged at the brake disc A on driving shaft, driven shaft, be fixed in the concentric driven gear of driven shaft input end, be arranged at the brake disc B on driven shaft, described brake disc A is provided with brake member A, and brake disc B is provided with brake member B; Described driving gear and driven gear are symmetrical arranged with one heart, and described mainshaft gear engages with described driving gear and driven gear respectively, and mainshaft gear, driving gear and driven gear are spiral bevel gear.Described driving gear, mainshaft gear A and driven gear engage and are symmetrical arranged between two, torsion and stress equilibrium that when this structure can be by mainshaft gear transmission, gear bears are dispersed on driving gear and driven gear, cancelling out each other of realizable force, reduce gear wear, the stability while having increased aircraft rotor braking deceleration.
Described brake member A comprises brake block A and controls the servomechanism A of brake block A; Brake block A is for carrying out retarding braking to brake disc A.Servomechanism A selects fluid servomotor.
Described brake member B comprises brake block B and controls the servomechanism B of brake block B; Brake block B is for carrying out retarding braking to brake disc B.Servomechanism B selects fluid servomotor.
Described mainshaft gear, driving gear and driven gear outer cladding arrange lock case.
Described main shaft is provided with dividing plate.Dividing plate is the positioning device of mast, for main shaft is fixed and is supported.
Described driving shaft and driven shaft pass through respectively bearings.The effect of bearing is that driving shaft and driven shaft are fixed and are supported.
Beneficial effect of the present invention is:
1, in the present invention, adopted the symmetrically arranged structure of brake member and transmission part to carry out braking deceleration to mainshaft gear, torsion the concentrate mainshaft gear wearing and tearing that cause, the stability while simultaneously having increased rotor gearing down relative to stress of having born while having reduced mainshaft gear braking deceleration in prior art.
2, in the present invention, utilize brake block and brake disc driving shaft to be carried out to the mode of braking of retarding braking, braking deceleration reaction is fast, and brake speed can be controlled according to the degree of tightness of brake block, and retardation efficiency is higher.
3, structure of the present invention is relatively simple, and installation and maintenance are more convenient.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the structural representation of brake part A in the present invention.
Wherein, 1, rotor head; 2, main shaft; 3, mainshaft gear; 4, driving shaft; 5, driving gear; 6, lock case; 7, dividing plate; 8, driven gear; 9, driven shaft; 10, brake member A, 11, brake block A, 12, servomechanism A, 13, brake disc A; 20, brake member B, 21, brake block B, 22, servomechanism B, 23, brake disc B.
Embodiment
Illustrate the present invention below in conjunction with drawings and Examples.
Embodiment 1:
As depicted in figs. 1 and 2, unmanned plane rotor brake device of the present invention, its rotor comprises rotor head 1 and main shaft 2, main shaft 2 is provided with concentric mainshaft gear 3; Its braking device comprises driving shaft 4, is fixed in the concentric driving gear 5 of driving shaft 4 output terminals, be arranged at the brake disc A13 on driving shaft 4, driven shaft 9, be fixed in the concentric driven gear 8 of driven shaft 9 input ends, be arranged at the brake disc B23 on driven shaft 9, brake disc A13 is provided with brake member A10, and brake disc B23 is provided with brake member B20; Driving gear 5 and driven gear 8 are symmetrical arranged with one heart, and mainshaft gear 3 engages with driving gear 5 and driven gear 8 respectively, and mainshaft gear 3, driving gear 5 and driven gear 8 are spiral bevel gear.
Embodiment 2:
Outside lower difference, other are with embodiment 1.
Brake member A10 comprises brake block A11 and controls the servomechanism A12 of brake block A11.
Brake member B20 comprises brake block B21 and controls the servomechanism B22 of brake block B21.
Embodiment 3:
Outside lower difference, other are with embodiment 2.
Mainshaft gear 3, driving gear 5 and driven gear 8 outer claddings arrange lock case 6.
Embodiment 4:
Outside lower difference, other are with embodiment 2.
Working procedure of the present invention is as follows: when unmanned plane operation aloft, driving shaft 4 rotates and drives driving gear 5 and brake disc A13 to rotate, drive rotor head 1 to rotate by driving gear 5 with engaging of mainshaft gear 3, mainshaft gear 3 drives driven gear 8 to rotate according to the direction contrary with driving gear 5 simultaneously, and driven gear 8 drives driven shaft 9 and brake disc B23 to rotate.In the time that needs carry out braking deceleration to rotor head 1, servomechanism A12 control brake block A11 tightens up with brake disc A13 and rubs, and produces and rotates contrary moment of torsion with driving shaft 4, progressively stops and stops driving shaft 4.Servomechanism B22 control brake block B21 tightens up with brake disc B23 and rubs, and produces and rotates contrary moment of torsion with driven shaft 9, progressively stops and stops driven shaft 9.Driving shaft 4 and driven shaft 9 are progressively stopped and are stopped driving driving gear 5 and driven gear 8 progressively to stop and stop, and by with the friction interlock of mainshaft gear 3, make mast 2 source that runs out of steam, thereby reach the object that rotor head 1 stops operating, finally realize the retarding braking of unmanned plane rotor.
Claims (5)
1. a unmanned plane rotor brake device, its rotor comprises rotor head (1) and main shaft (2), main shaft (2) is provided with concentric mainshaft gear (3); It is characterized in that, its braking device comprises driving shaft (4), is fixed in the concentric driving gear (5) of driving shaft (4) output terminal, be arranged at the brake disc A(13 on driving shaft (4)), driven shaft (9), be fixed in the concentric driven gear (8) of driven shaft (9) input end, be arranged at the brake disc B(23 on driven shaft (9)), brake disc A(13) be provided with brake member A(10), brake disc B(23) be provided with brake member B(20); Driving gear (5) and driven gear (8) are symmetrical arranged with one heart, and mainshaft gear (3) engages with described driving gear (5) and driven gear (8) respectively, and mainshaft gear (3), driving gear (5) and driven gear (8) are spiral bevel gear.
2. unmanned plane rotor brake device according to claim 1, is characterized in that, described brake member A(10) comprise brake block A(11) and control brake block A(11) servomechanism A(12).
3. unmanned plane rotor brake device according to claim 1 and 2, is characterized in that, described brake member B(20) comprise brake block B(21) and control brake block B(21) servomechanism B(22).
4. unmanned plane rotor brake device according to claim 3, is characterized in that, described mainshaft gear (3), driving gear (5) and driven gear (8) outer cladding arrange lock case (6).
5. unmanned plane rotor brake device according to claim 3, is characterized in that, described main shaft (2) is provided with dividing plate (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410074380.3A CN103791002B (en) | 2014-03-03 | 2014-03-03 | Unmanned plane rotor brake device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410074380.3A CN103791002B (en) | 2014-03-03 | 2014-03-03 | Unmanned plane rotor brake device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103791002A true CN103791002A (en) | 2014-05-14 |
| CN103791002B CN103791002B (en) | 2016-03-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410074380.3A Active CN103791002B (en) | 2014-03-03 | 2014-03-03 | Unmanned plane rotor brake device |
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| CN (1) | CN103791002B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105501439A (en) * | 2015-12-31 | 2016-04-20 | 北京航空航天大学 | Rotor wing decelerating and locking device for rotor wing and fixed wing combined type vertical take-off and landing air vehicle |
| CN105644779A (en) * | 2014-11-20 | 2016-06-08 | 中国直升机设计研究所 | Pressure accumulator assembly for helicopter rotor wing brake |
| CN106809384A (en) * | 2017-02-28 | 2017-06-09 | 中航维拓（天津）科技有限公司 | A kind of rotor craft electromagnetic damping rotor brake device |
| CN106956770A (en) * | 2017-05-08 | 2017-07-18 | 莆田市双普信息科技有限公司 | A kind of aircraft active differential mechanism speed adjusting gear |
| CN107448582A (en) * | 2016-05-30 | 2017-12-08 | 四川华翼航普航空科技有限公司 | A kind of unmanned plane spiral bevel gear and processing technology |
| CN108087452A (en) * | 2017-12-31 | 2018-05-29 | 贵州大学 | A kind of efficient friction-type brake apparatus |
| CN116558699A (en) * | 2023-03-29 | 2023-08-08 | 中国航发湖南动力机械研究所 | Helicopter rotor wing brake starting torque measurement method and system |
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| US20070051849A1 (en) * | 2005-02-04 | 2007-03-08 | Lockheed Martin Corporation | Uav recovery system |
| US20080149775A1 (en) * | 2006-12-26 | 2008-06-26 | Storm Dunker | Deployment brake release for a parachute |
| CN102963524A (en) * | 2012-09-14 | 2013-03-13 | 马永政 | Slide-wheel composite type small and medium sized UAV landing gear system |
| CN103047319A (en) * | 2012-12-28 | 2013-04-17 | 天津曙光敬业科技有限公司 | Aerial braking device of pilotless rotor helicopter |
| CN103267071A (en) * | 2013-06-13 | 2013-08-28 | 吴林 | Brake mechanism for car |
| CN203743249U (en) * | 2014-03-03 | 2014-07-30 | 天津曙光敬业科技有限公司 | Unmanned aerial vehicle rotor wing braking device |
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2014
- 2014-03-03 CN CN201410074380.3A patent/CN103791002B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070051849A1 (en) * | 2005-02-04 | 2007-03-08 | Lockheed Martin Corporation | Uav recovery system |
| US20080149775A1 (en) * | 2006-12-26 | 2008-06-26 | Storm Dunker | Deployment brake release for a parachute |
| CN102963524A (en) * | 2012-09-14 | 2013-03-13 | 马永政 | Slide-wheel composite type small and medium sized UAV landing gear system |
| CN103047319A (en) * | 2012-12-28 | 2013-04-17 | 天津曙光敬业科技有限公司 | Aerial braking device of pilotless rotor helicopter |
| CN103267071A (en) * | 2013-06-13 | 2013-08-28 | 吴林 | Brake mechanism for car |
| CN203743249U (en) * | 2014-03-03 | 2014-07-30 | 天津曙光敬业科技有限公司 | Unmanned aerial vehicle rotor wing braking device |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644779A (en) * | 2014-11-20 | 2016-06-08 | 中国直升机设计研究所 | Pressure accumulator assembly for helicopter rotor wing brake |
| CN105644779B (en) * | 2014-11-20 | 2018-06-26 | 中国直升机设计研究所 | A kind of accumulator package for lifting airscrew brake |
| CN105501439A (en) * | 2015-12-31 | 2016-04-20 | 北京航空航天大学 | Rotor wing decelerating and locking device for rotor wing and fixed wing combined type vertical take-off and landing air vehicle |
| CN105501439B (en) * | 2015-12-31 | 2018-02-23 | 北京航空航天大学 | A kind of rotor deceleration locking device for rotor fixed-wing combined type vertically taking off and landing flyer |
| CN107448582A (en) * | 2016-05-30 | 2017-12-08 | 四川华翼航普航空科技有限公司 | A kind of unmanned plane spiral bevel gear and processing technology |
| CN106809384A (en) * | 2017-02-28 | 2017-06-09 | 中航维拓（天津）科技有限公司 | A kind of rotor craft electromagnetic damping rotor brake device |
| CN106956770A (en) * | 2017-05-08 | 2017-07-18 | 莆田市双普信息科技有限公司 | A kind of aircraft active differential mechanism speed adjusting gear |
| CN108087452A (en) * | 2017-12-31 | 2018-05-29 | 贵州大学 | A kind of efficient friction-type brake apparatus |
| CN108087452B (en) * | 2017-12-31 | 2024-04-30 | 贵州大学 | High-efficient friction type braking device |
| CN116558699A (en) * | 2023-03-29 | 2023-08-08 | 中国航发湖南动力机械研究所 | Helicopter rotor wing brake starting torque measurement method and system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103791002B (en) | 2016-03-30 |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20140514 Assignee: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Assignor: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. Contract record no.: 2017990000086 Denomination of invention: Brake device of unmanned aerial vehicle rotor wing Granted publication date: 20160330 License type: Exclusive License Record date: 20170314 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20170420 Address after: 300000 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Address before: No. 300151 Tianjin road Hebei District City, Wang Chuanchang Hospital No. 62 Patentee before: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20221010 Address after: Room 105, Building 9, Area B3 (formerly Area 2 of Ronghui Business Park), Enterprise Headquarters Base, Binhai-Zhongguancun Science and Technology Park, Economic and Technological Development Zone, Binhai New Area, Tianjin 300457 Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |