CN106809396A - A kind of rotor craft parachuting device of use gas generant composition in accordance - Google Patents
A kind of rotor craft parachuting device of use gas generant composition in accordance Download PDFInfo
- Publication number
- CN106809396A CN106809396A CN201710114426.3A CN201710114426A CN106809396A CN 106809396 A CN106809396 A CN 106809396A CN 201710114426 A CN201710114426 A CN 201710114426A CN 106809396 A CN106809396 A CN 106809396A
- Authority
- CN
- China
- Prior art keywords
- accordance
- gas generant
- generant composition
- priming
- housing
- Prior art date
- 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.)
- Pending
Links
- 239000000203 mixture Substances 0.000 title claims abstract description 46
- 230000037452 priming Effects 0.000 claims description 32
- 239000002360 explosive Substances 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 13
- 238000010304 firing Methods 0.000 claims description 3
- 125000000449 nitro group Chemical group [O-][N+](*)=O 0.000 claims description 3
- 230000001988 toxicity Effects 0.000 claims description 3
- 231100000419 toxicity Toxicity 0.000 claims description 3
- 239000007789 gas Substances 0.000 abstract description 44
- 238000010276 construction Methods 0.000 abstract description 2
- 239000003721 gunpowder Substances 0.000 description 3
- 239000000306 component Substances 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 241000380131 Ammophila arenaria Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005422 blasting Methods 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/72—Deployment by explosive or inflatable means
- B64D17/725—Deployment by explosive or inflatable means by explosive means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Air Bags (AREA)
Abstract
The invention discloses a kind of rotor craft parachuting device of use gas generant composition in accordance, it includes igniter, gas generant composition in accordance catapult-launching gear and body.Position annexation between them is：Gas generant composition in accordance catapult-launching gear is located at the upper end of igniter, and the two is fixedly mounted on body top jointly.Present invention mainly solves the problem that current rotor craft parachuting apparatus structure is complicated, weight is big.The present invention is without steering wheel structure, without dynamic component, and lightweight construction is highly reliable；The characteristic of a large amount of gases can be rapidly produced using gas generant composition in accordance, promotes pack quickly to flick, it is to avoid pack is inhaled into rotor.
Description
Technical field
The present invention relates to technical field of aerospace, the rotor craft parachuting device of more particularly to a kind of use gas generant composition in accordance.
Technical background
Parachuting is reclaimed not only as the landing modes of unmanned plane but also can prevent unmanned plane from anticipating as Emergency recovery mode
Outer crash causes unnecessary loss.Rotor craft includes depopulated helicopter, unmanned multi-rotor aerocraft, and it is in flight course
Middle rotor rotates at a high speed, produces purling and causes rotor top negative pressuren zone occur, and this results in unmanned rotary wing aircraft parachuting
During device is easily inhaled into rotor in parachute-opening.So parachuting device is applied to need parachute to launch speed during unmanned rotary wing aircraft
Degree is fast, strength is big, and suction force range of the rotor to it is fled from rapidly.
The parachuting device of current rotor craft, has by the way of the upward explosion of explosive, such as in Chinese patent specification
A kind of unmanned plane parachute of use nailing gun gunpowder was once described in CN-105109693A (Shen Qing Publication day is 2015.12.02)
Ejection system, the invention includes free-wheeling system, ejection mechanism, nailing gun gunpowder, cylinder, piston and parachute, passes through during parachute-opening
Compressed air in servos control ejection mechanism installation nailing gun gunpowder heating cylinder, compressed air thermal stress increases drop of upspringing
Fall umbrella.The invention contains helm gear, and weight is big and mechanism is complicated；Moving component is more, clamping lock failure easily occurs.In Chinese patent
A kind of depopulated helicopter parachute transmitting system was once described in specification CN-203958622U (Shen Qing Publication day is 2014.11.26)
System, the utility model includes depopulated helicopter and emission system, and its emission system core component is transmitter (air bag ejection dress
Put), the device has a large amount of gases and produces and quickly fill with air bag when starting, and pack is ejected by the quick deformation of air bag.Gas
Although capsule can buffer influence of the parachute-opening reaction force to body, the complexity and weight of system are increased.
The content of the invention
In order to overcome the above-mentioned deficiencies of the prior art, the invention provides a kind of rotor craft parachuting of use gas generant composition in accordance
Device.
The technical solution adopted in the present invention is：A kind of rotor craft parachuting device of use gas generant composition in accordance, mainly includes
Igniter, gas generant composition in accordance catapult-launching gear and body.Position annexation between them is：Gas generant composition in accordance catapult-launching gear is located at igniting
The upper end of device, the two is fixedly mounted on body top jointly.
The igniter, including heating wire, housing, priming frame, priming and explosive.The housing is in stepped cylindrical knot
Structure, its latter half is thinner, top half thick and long, there is biography fire screen plate in the middle of thicker top half, passes fire screen plate and sets
There is a series of flash hole.Heating wire is fixedly installed in housing lower end, two electrodes by the reserved hole in housing lower section stretch out with
Corresponding firing circuit is connected；The priming frame is the cylindrical structure with center pillar hole, and priming frame is close in heating wire upper end
Enclosure interior is embedded in, priming is installed on priming frame center and is sufficient filling with the center pillar hole of priming frame；Explosive is filled in biography fire
Between dividing plate and priming frame, its lower end is fully contacted with priming.
The gas generant composition in accordance catapult-launching gear, including gas generant composition in accordance, closure and pack.The gas generant composition in accordance uses nitro camber aerogenesis
Medicine, the gas generant composition in accordance aerogenesis is rapid, toxicity is low and produces gas temperature relatively low, and gas generant composition in accordance is filled in biography fire screen plate upper end；Closure
With inner walls using being tightly connected, non-ejection status ensures that it will not depart from easily with housing for lower end；Pack is placed in closure
Upper end, its umbrella rope is connected with body appropriate location.
Advantage and effect：Compared with prior art, the beneficial effects of the invention are as follows solving current rotor craft parachuting
The problem that apparatus structure is complicated, weight is big.The present invention is without steering wheel structure, without dynamic component, and lightweight construction is highly reliable；Utilize
Gas generant composition in accordance can rapidly produce the characteristic of a large amount of gases, promote pack quickly to flick, it is to avoid pack is inhaled into rotor.
Brief description of the drawings
A kind of rotor craft parachuting device scheme of installation of use gas generant composition in accordance of Fig. 1
A kind of rotor craft parachuting device profile of use gas generant composition in accordance of Fig. 2；
Fig. 3 casing cross-section figures；
Fig. 4 priming frame profiles；
Sign flag is as follows in figure：
1- heating wire；2- housings；3- priming framves；4- priming；5- explosives；6- gas generant composition in accordance；7- closures；8- packs；9- machines
Body.201- passes fire screen plate；202- flash holes；301- center pillars hole.
Specific embodiment
The preferred embodiments of the present invention are illustrated below in conjunction with the accompanying drawings, it should be understood that described herein to be preferable to carry out
Example is merely to illustrate and explain the present invention, and is not intended to limit the present invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of the description present invention and simplify description, rather than the dress for indicating or implying meaning
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The limitation of scope.
In order to overcome the above-mentioned deficiencies of the prior art, the invention provides a kind of rotor craft parachuting of use gas generant composition in accordance
Device.
Referring to Fig. 1-Fig. 3, the igniting related to a kind of rotor craft parachuting device of use gas generant composition in accordance of the present embodiment
Device is mainly consisted of：The igniter, including heating wire 1, housing 2, priming frame 3, priming 4 and explosive 5.The housing
2 is in stepped cylindrical structure, and its latter half is thinner, and top half is thicker, there is biography fire screen plate 201 in the middle of thicker top half,
Pass fire screen plate 201 and be provided with a series of flash hole 202.Heating wire 1 is fixedly installed in the lower end of housing 2, and two electrodes pass through housing 2
The reserved hole in lower section is stretched out and is connected with corresponding firing circuit；The priming frame 3 is the cylindrical structure with center pillar hole 301,
Priming frame 3 is close to the upper end of heating wire 1 and is embedded in inside housing 2, and priming 4 is installed on the center of priming frame 3 and is sufficient filling with priming frame
Center pillar hole 301；Explosive 5 is filled between biography fire screen plate 201 and the frame of priming 4, and its lower end is fully contacted with priming 4.
The gas generant composition in accordance catapult-launching gear master related to a kind of rotor craft parachuting device of use gas generant composition in accordance of the present embodiment
Constitute as follows：The gas generant composition in accordance catapult-launching gear, including gas generant composition in accordance 6, closure 7 and pack 8.The gas generant composition in accordance 6 uses nitro
Camber gas generant composition in accordance, the gas generant composition in accordance aerogenesis is rapid, toxicity is low and produces gas temperature relatively low, and gas generant composition in accordance is filled in biography fire screen plate 201
Upper end；With the inwall of housing 1 using being tightly connected, non-ejection status ensures that it will not depart from easily with housing 1 to the lower end of closure 7；
Pack 8 is placed in the upper end of closure 7, and its umbrella rope is connected with the appropriate location of body 9.
Referring to Fig. 1-Fig. 3, the present embodiment specific operation process is as follows：
When rotor craft runs into failure, electric quantity of power supply be too low and falling speed exceedes preset value when, can be by artificial
Operation or airborne computer automatic identification are set out parachuting device, and now the telegraph circuit of heating wire 1 is connected, the operational heat of heating wire 1
Temperature raises the priming 4 lighted and be in contact with it；The rapid burning explosive blasting 5 of priming 4, the burn rate of explosive 5 is fast, by flash hole
202 uniform gas generant composition in accordance 6 of igniting；Gas generant composition in accordance 6 is burnt a large amount of gases that produce rapidly, and promotes closure 7 and pack 8 and housing 2
Depart from；Pack 8 is flicked rapidly after obtaining larger initial velocity, there is provided the resistance of aircraft stable landing.
The top half of the housing 2 is more long, and its purpose is gas generant composition in accordance is burnt the gas for producing fully to closure 7 and umbrella
Bag 8 does work, and makes pack 8 have larger kinetic energy to break away from the influence of rotor down-wash flow when departing from housing 2；Fire screen plate 201 is passed to make
With being isolation explosive 5 and gas generant composition in accordance 6, prevent the two from being contacted and the property of medicine that interacts under non-working condition, flash hole 202 can be with
Even flame when making explosive 5 burn passes to gas generant composition in accordance；The purpose of explosive 5 is used to be burnt violent characteristic using explosive 5
As the good medium for lighting gas generant composition in accordance 6 and make the combustion even of gas generant composition in accordance 6.
Embodiments of the invention have been described in detail above, but the content is only presently preferred embodiments of the present invention,
It is not to be regarded as limiting practical range of the invention.All impartial changes made according to the present patent application scope and improvement etc.,
All should still belong within patent covering scope of the invention.
Claims (1)
1. the rotor craft parachuting device of a kind of use gas generant composition in accordance, it is characterised in that：It includes that igniter, gas generant composition in accordance are launched
Device and body (9).Position annexation between them is：Gas generant composition in accordance catapult-launching gear is located at the upper end of igniter, the two
Body (9) top is fixedly mounted on jointly.
The igniter, including heating wire (1), housing (2), priming frame (3), priming (4) and explosive (5).The housing (2)
In stepped cylindrical structure, its latter half is thinner, and top half is thicker, there is biography fire screen plate (201) in the middle of thicker top half,
Pass fire screen plate and be provided with a series of flash hole (202).Heating wire (1) is fixedly installed in housing (2) lower end, and two electrodes pass through shell
The reserved hole in body (2) lower section is stretched out and is connected with corresponding firing circuit.The priming frame (3) is with center pillar hole (301)
Cylindrical structure, priming frame (3) is close to heating wire (1) upper end and is embedded in housing (2) inside, and priming (4) is installed in priming frame (3)
The heart is simultaneously sufficient filling with the center pillar hole (301) of priming frame.Explosive (5) be filled in biography fire screen plate (201) and priming (4) frame it
Between, its lower end is fully contacted with priming 4.
The gas generant composition in accordance catapult-launching gear, including gas generant composition in accordance (6), closure (7) and pack (8).The gas generant composition in accordance (6) uses nitro
Camber gas generant composition in accordance, the gas generant composition in accordance aerogenesis is rapid, toxicity is low and produces gas temperature relatively low, and gas generant composition in accordance is filled in biography fire screen plate 201
Upper end.With housing (1) inwall using being tightly connected, non-ejection status ensures that it will not be easily with housing (1) for closure (7) lower end
Depart from；Pack (8) is placed in closure (7) upper end, and its umbrella rope is connected with body (9) appropriate location.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710114426.3A CN106809396A (en) | 2017-02-28 | 2017-02-28 | A kind of rotor craft parachuting device of use gas generant composition in accordance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710114426.3A CN106809396A (en) | 2017-02-28 | 2017-02-28 | A kind of rotor craft parachuting device of use gas generant composition in accordance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106809396A true CN106809396A (en) | 2017-06-09 |
Family
ID=59112066
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710114426.3A Pending CN106809396A (en) | 2017-02-28 | 2017-02-28 | A kind of rotor craft parachuting device of use gas generant composition in accordance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106809396A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110291010A (en) * | 2018-08-31 | 2019-09-27 | 深圳市大疆创新科技有限公司 | The guard method and UAV system of unmanned plane lost-control protection method, equipment, UAV system |
| CN110406682A (en) * | 2019-08-29 | 2019-11-05 | 江西科技学院 | Parachute assembly, control method and control system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8332083D0 (en) * | 1982-12-01 | 1984-01-11 | Spitzer E | Helicopters |
| US20030056680A1 (en) * | 2001-09-25 | 2003-03-27 | Falken, S.A. | Device with combustible charge with smoke-generating, tear-generating or signaling effects |
| CN201357806Y (en) * | 2008-11-24 | 2009-12-09 | 上海东方久乐汽车安全气囊有限公司 | Gas generator for pre-tightening type safety belt |
| CN103979110A (en) * | 2014-05-29 | 2014-08-13 | 襄阳宏伟航空器有限责任公司 | Ballistic parachute life-saving system |
| CN204701768U (en) * | 2015-04-03 | 2015-10-14 | 王剑刚 | A kind of parachute and parachute opener, rope distributor |
| CN105109693A (en) * | 2015-09-08 | 2015-12-02 | 天峋创新（北京）科技有限公司 | Unmanned aerial vehicle parachute ejection system using nail gun powder |
| CN206579849U (en) * | 2017-02-28 | 2017-10-24 | 中航维拓（天津）科技有限公司 | A kind of rotor craft parachuting device of use gas generant composition in accordance |
-
2017
- 2017-02-28 CN CN201710114426.3A patent/CN106809396A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8332083D0 (en) * | 1982-12-01 | 1984-01-11 | Spitzer E | Helicopters |
| US20030056680A1 (en) * | 2001-09-25 | 2003-03-27 | Falken, S.A. | Device with combustible charge with smoke-generating, tear-generating or signaling effects |
| CN201357806Y (en) * | 2008-11-24 | 2009-12-09 | 上海东方久乐汽车安全气囊有限公司 | Gas generator for pre-tightening type safety belt |
| CN103979110A (en) * | 2014-05-29 | 2014-08-13 | 襄阳宏伟航空器有限责任公司 | Ballistic parachute life-saving system |
| CN204701768U (en) * | 2015-04-03 | 2015-10-14 | 王剑刚 | A kind of parachute and parachute opener, rope distributor |
| CN105109693A (en) * | 2015-09-08 | 2015-12-02 | 天峋创新（北京）科技有限公司 | Unmanned aerial vehicle parachute ejection system using nail gun powder |
| CN206579849U (en) * | 2017-02-28 | 2017-10-24 | 中航维拓（天津）科技有限公司 | A kind of rotor craft parachuting device of use gas generant composition in accordance |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110291010A (en) * | 2018-08-31 | 2019-09-27 | 深圳市大疆创新科技有限公司 | The guard method and UAV system of unmanned plane lost-control protection method, equipment, UAV system |
| WO2020042151A1 (en) * | 2018-08-31 | 2020-03-05 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle out-of-control protection method and device, unmanned aerial vehicle system protection method and unmanned aerial vehicle system |
| 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 |
| CN110406682A (en) * | 2019-08-29 | 2019-11-05 | 江西科技学院 | Parachute assembly, control method and control system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170609 |