CN203958622U - Depopulated helicopter parachute emission coefficient - Google Patents
Depopulated helicopter parachute emission coefficient Download PDFInfo
- Publication number
- CN203958622U CN203958622U CN201420366708.4U CN201420366708U CN203958622U CN 203958622 U CN203958622 U CN 203958622U CN 201420366708 U CN201420366708 U CN 201420366708U CN 203958622 U CN203958622 U CN 203958622U
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- CN
- China
- Prior art keywords
- air bag
- parachute
- emission coefficient
- depopulated helicopter
- gas generator
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000003042 antagnostic effect Effects 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 10
- 238000004880 explosion Methods 0.000 description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
A kind of depopulated helicopter parachute emission coefficient, described projector is air bag device for ejecting, described air bag device for ejecting comprises air bag, gas generator, control ignition lock, wireless receiver, gas generator is connected with air bag, controls ignition lock respectively at gas generator and wireless receiver electrical connection.Depopulated helicopter parachute emission coefficient is utilized the parachute-opening of air bag device for ejecting, the air bag opening rapidly can be given the landing pack thrust of all directions upward, make parachute launch rapidly and leave the scope of downwash flow, improve the success ratio of parachute-opening, and air bag disperses to the power of landing pack very much, make its antagonistic force can be too unconcentrated, the vibration of generation be little, can not damage unmanned plane body and inner member.
Description
Technical field
The utility model relates to unmanned aircraft parachute descent and reclaims field, is specifically related to a kind of parachute emission coefficient of depopulated helicopter.
Background technology
Depopulated helicopter is in the process of flight, and rotor High Rotation Speed, produces a large amount of downwash flows, for unmanned plane provides flight required lift.And for the ease of the recovery of unmanned plane, and prevent that unmanned plane from surprisingly crashing, and parachute has been installed on unmanned plane, parachute is generally positioned at the top of rotor.Downwash flow produces huge lift upwards, has also produced huge suction, in this case simultaneously, the scope of downwash flow if can not speed away when parachute is opened, downwash flow is easy to parachute to suck back, and is wound on rotor, cause Parachute Opening failure, unmanned plane crashes.
In order to prevent that downwash flow from affecting the success ratio of Parachute Opening, current unmanned aircraft parachute descent device, for example patent " unmanned plane recovery landing system " application number formerly: 201420093587.0, the conventional method that upwards explosion is launched is opened parachute.Also there is very large deficiency in this parachute-opening mode, the ejector that explosion triggers will produce very large antagonistic force to rotor, directly impact the gear that power is provided for rotor, cause the damage of unmanned plane power drive system, the huge vibrations that produce when explosion also can damage other inner members in unmanned plane body and body, and pulling open as far as possible upwards when upwards explosion also can only ensure Parachute Opening, can not ensure that parachute can leave the scope of downwash flow in the direction of width, parachute-opening success ratio is still lower, and the parachuting device of these unmanned planes is directly installed on rotor head, and along with rotor rotates together, increase the reactive torque of helicopter, stability while having reduced unmanned plane during flying and manipulative capability, also make the tail-rotor of unmanned plane need larger power to carry out balance reactive torque, the unmanned plane fuel increasing or the consumption of battery, reduce the cruise duration of unmanned plane.
Utility model content
The utility model is easily received the impact of downwash flow for current unmanned plane parachute, parachute-opening success ratio is low, the fragile unmanned plane of explosion parachute-opening, also cannot improve parachute-opening success ratio, reactive torque is large, and stability and the manipulative capability of flight are poor, and power consumption is fast, the problems such as cruise duration is short, have designed a kind of new depopulated helicopter parachute emission coefficient.
Depopulated helicopter parachute emission coefficient of the present utility model, described depopulated helicopter comprises body, rotor head, described emission coefficient comprises umbrella storehouse, connecting device, umbrella storehouse is fixedly connected with body by connecting device, umbrella position in storehouse is in rotor head top, described umbrella storehouse comprises hatchcover, landing pack, projector and umbrella disk, hatchcover is fastened on umbrella disk, in the cavity that landing pack forms between hatchcover and umbrella disk, described projector is air bag device for ejecting, described air bag device for ejecting comprises air bag, gas generator, control ignition lock, wireless receiver, gas generator is connected with air bag, control ignition lock respectively at gas generator and wireless receiver electrical connection.
Preferably, described connecting device is mandrel, and mandrel bottom and body are affixed, and mandrel top and umbrella disk are affixed, and mandrel is arranged in the main shaft of hollow of rotor head setting.
Preferably, landing pack is fixedly connected with air bag.
The beneficial effects of the utility model are: depopulated helicopter parachute emission coefficient is utilized the parachute-opening of air bag device for ejecting, the air bag opening rapidly can be given the landing pack thrust of all directions upward, make parachute launch rapidly and leave the scope of downwash flow, improve the success ratio of parachute-opening, and air bag disperses to the power of landing pack very much, make its antagonistic force can be too unconcentrated, the vibration of generation be little, can not damage unmanned plane body and inner member.The umbrella storehouse that landing pack is housed is arranged on mandrel, make parachuting device static with respect to the body of unmanned plane, reduce the reactive torque of unmanned plane, stability while having improved unmanned plane during flying and manipulative capability, also reduced the power output of tail-rotor, reduce energy resource consumption, improved the cruise duration of unmanned plane operation.Landing pack is also directly fixed on air bag, makes the air bag of opening between parachute and unmanned plane, form a gas spring, prevents that the antagonistic force of the air resistance increasing suddenly when parachute is opened from impacting to unmanned plane, prevents that unmanned plane from damaging.
Brief description of the drawings
Accompanying drawing 1 is the constructional drawing of depopulated helicopter parachute emission coefficient;
Accompanying drawing 2 is the constructional drawing of air bag device for ejecting;
The constructional drawing that accompanying drawing 3 is mandrel;
Accompanying drawing 4 is the use constitution diagram of depopulated helicopter parachute emission coefficient.
Detailed description of the invention
Depopulated helicopter parachute emission coefficient of the present utility model, as shown in Figures 1 to 4, described depopulated helicopter comprises body 1, rotor head 2, described emission coefficient comprises umbrella storehouse 3, connecting device 4, umbrella storehouse 3 is fixedly connected with body 4 by connecting device 4, and umbrella storehouse 3 is positioned at rotor head 2 tops, and described umbrella storehouse 3 comprises hatchcover 5, landing pack 6, projector 7 and umbrella disk 8, hatchcover 5 is fastened on umbrella disk 8, in the cavity that landing pack 6 forms between hatchcover 5 and umbrella disk 8.
As shown in Figure 2, projector 7 is air bag device for ejecting, described air bag device for ejecting comprises air bag 9, gas generator 10, controls ignition lock 11, wireless receiver 12, gas generator 10 is connected with air bag 9, controls ignition lock 11 and is electrically connected respectively at gas generator 10 and wireless receiver 12.Landing pack 6 can be fixedly connected with umbrella disk 8, also can be fixedly connected with air bag 9.In the time that landing pack 6 is connected with air bag 9, in the process of parachuting, air bag 9 can be used as the gas spring between parachute and body 1, on the body of the reaction force acts that the air resistance increasing suddenly when buffering deployment produces, avoid impacting body, cause body with and inner member damage.
As shown in Figure 3, connecting device is mandrel 13, and mandrel 13 bottoms and body 1 are affixed, and mandrel 13 tops and umbrella disk 8 are affixed, and mandrel 13 is arranged in the main shaft 14 of the hollow that rotor head 2 arranges.
When unmanned plane needs parachuting, operating personal utilizes long-range control setup to send wireless control signal, control ignition lock 11 and receive wireless control signal by wireless receiver 12, thereby trigger gas generator 10, produce rapidly the gases such as nitrogen, carbonic oxide, be filled in air bag, air bag is expanded rapidly.The air bag 9 expanding is pushed landing pack 6, strut hatchcover 5, and the pack 6 that makes to land is launched into rapidly parachute.When air bag 9 is opened, be to strut towards all directions of umbrella disk 8 tops, when air bag 9 is opened, also be to push landing pack 6 towards all directions of umbrella disk 8 tops, the pack 6 that makes the to land expansion that upwards scatters, departs from the scope of downwash flow, ensures the success ratio of Parachute Opening.
Claims (3)
1. a depopulated helicopter parachute emission coefficient, described depopulated helicopter comprises body (1), rotor head (2), described emission coefficient comprises umbrella storehouse (3), connecting device (4), umbrella storehouse (3) is fixedly connected with body (4) by connecting device (4), umbrella storehouse (3) is positioned at rotor head (2) top, described umbrella storehouse (3) comprises hatchcover (5), landing pack (6), projector (7) and umbrella disk (8), hatchcover (5) is fastened on umbrella disk (8), landing pack (6) is arranged in the cavity forming between hatchcover (5) and umbrella disk (8), it is characterized in that, described projector (7) is air bag device for ejecting, described air bag device for ejecting comprises air bag (9), gas generator (10), control ignition lock (11), wireless receiver (12), gas generator (10) is connected with air bag (9), control ignition lock (11) respectively at gas generator (10) and wireless receiver (12) electrical connection.
2. depopulated helicopter parachute emission coefficient according to claim 1, it is characterized in that, described connecting device is mandrel (13), mandrel (13) bottom and body (1) are affixed, mandrel (13) top and umbrella disk (8) are affixed, and mandrel (13) is arranged in the main shaft (14) of hollow of rotor head (2) setting.
3. depopulated helicopter parachute emission coefficient according to claim 1, is characterized in that, landing pack (6) is fixedly connected with air bag (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420366708.4U CN203958622U (en) | 2014-07-03 | 2014-07-03 | Depopulated helicopter parachute emission coefficient |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420366708.4U CN203958622U (en) | 2014-07-03 | 2014-07-03 | Depopulated helicopter parachute emission coefficient |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203958622U true CN203958622U (en) | 2014-11-26 |
Family
ID=51919242
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420366708.4U Expired - Fee Related CN203958622U (en) | 2014-07-03 | 2014-07-03 | Depopulated helicopter parachute emission coefficient |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203958622U (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908953A (en) * | 2015-06-24 | 2015-09-16 | 江苏建筑职业技术学院 | Automatic life-saving protection device and method for preventing airplane from crashing and being hijacked |
| CN106741886A (en) * | 2017-01-13 | 2017-05-31 | 必扬星环（北京）航空科技有限公司 | For the rotor head assembly of depopulated helicopter |
| CN108058833A (en) * | 2017-12-03 | 2018-05-22 | 中国直升机设计研究所 | A kind of list rotor unmanned helicopter parachute landing system |
| CN108177782A (en) * | 2018-02-05 | 2018-06-19 | 天津曙光天成科技有限公司 | Unmanned helicopter parachute trigger mechanism and unmanned helicopter |
| CN109094788A (en) * | 2018-10-10 | 2018-12-28 | 常州市小域智能科技有限公司 | A kind of unmanned aerial vehicle ejecting apparatus and system |
| WO2019010699A1 (en) * | 2017-07-14 | 2019-01-17 | 广东黄赛航空科技有限公司 | Unmanned aerial vehicle |
| US10202198B2 (en) | 2015-01-30 | 2019-02-12 | Vysoke Uceni Technicke V Brne | Life-saving equipment for unmanned air vehicles |
| CN110312657A (en) * | 2017-03-01 | 2019-10-08 | Rps航空航天技术股份有限公司 | A kind of aircraft equipped with assisting in flying component |
| CN110893911A (en) * | 2018-09-12 | 2020-03-20 | 台山市金桥铝型材厂有限公司 | Parachute device and aluminium system multiaxis unmanned aerial vehicle |
| CN111252254A (en) * | 2018-12-01 | 2020-06-09 | 哈尔滨火萤科技有限公司 | Small gas generating device for parachute of unmanned aerial vehicle |
| CN117284484A (en) * | 2023-11-09 | 2023-12-26 | 南京航空航天大学 | Helicopter rotor tail rotor failure protection system and helicopter |
-
2014
- 2014-07-03 CN CN201420366708.4U patent/CN203958622U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10202198B2 (en) | 2015-01-30 | 2019-02-12 | Vysoke Uceni Technicke V Brne | Life-saving equipment for unmanned air vehicles |
| CN104908953A (en) * | 2015-06-24 | 2015-09-16 | 江苏建筑职业技术学院 | Automatic life-saving protection device and method for preventing airplane from crashing and being hijacked |
| CN106741886A (en) * | 2017-01-13 | 2017-05-31 | 必扬星环（北京）航空科技有限公司 | For the rotor head assembly of depopulated helicopter |
| CN106741886B (en) * | 2017-01-13 | 2024-02-23 | 重庆星环航空科技有限公司 | Rotor head assembly for unmanned helicopter |
| CN110312657A (en) * | 2017-03-01 | 2019-10-08 | Rps航空航天技术股份有限公司 | A kind of aircraft equipped with assisting in flying component |
| WO2019010699A1 (en) * | 2017-07-14 | 2019-01-17 | 广东黄赛航空科技有限公司 | Unmanned aerial vehicle |
| CN108058833A (en) * | 2017-12-03 | 2018-05-22 | 中国直升机设计研究所 | A kind of list rotor unmanned helicopter parachute landing system |
| CN108177782A (en) * | 2018-02-05 | 2018-06-19 | 天津曙光天成科技有限公司 | Unmanned helicopter parachute trigger mechanism and unmanned helicopter |
| CN110893911A (en) * | 2018-09-12 | 2020-03-20 | 台山市金桥铝型材厂有限公司 | Parachute device and aluminium system multiaxis unmanned aerial vehicle |
| CN110893911B (en) * | 2018-09-12 | 2021-06-04 | 台山市金桥铝型材厂有限公司 | Aluminium system multiaxis unmanned aerial vehicle |
| CN109094788A (en) * | 2018-10-10 | 2018-12-28 | 常州市小域智能科技有限公司 | A kind of unmanned aerial vehicle ejecting apparatus and system |
| CN111252254A (en) * | 2018-12-01 | 2020-06-09 | 哈尔滨火萤科技有限公司 | Small gas generating device for parachute of unmanned aerial vehicle |
| CN117284484A (en) * | 2023-11-09 | 2023-12-26 | 南京航空航天大学 | Helicopter rotor tail rotor failure protection system and helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20160128 Granted publication date: 20141126 |
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| RINS | Preservation of patent right or utility model and its discharge | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20160728 Granted publication date: 20141126 |
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| RINS | Preservation of patent right or utility model and its discharge | ||
| 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: 20141126 |