CN106114862A - Built-in type ammunition electromagnetic launch device on depopulated helicopter - Google Patents
Built-in type ammunition electromagnetic launch device on depopulated helicopter Download PDFInfo
- Publication number
- CN106114862A CN106114862A CN201610621339.2A CN201610621339A CN106114862A CN 106114862 A CN106114862 A CN 106114862A CN 201610621339 A CN201610621339 A CN 201610621339A CN 106114862 A CN106114862 A CN 106114862A
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- China
- Prior art keywords
- ammunition
- guide rail
- armature
- launch device
- electromagnetic launch
- 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.)
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Links
- 230000005484 gravity Effects 0.000 claims abstract description 6
- 238000009413 insulation Methods 0.000 claims description 15
- 239000004020 conductor Substances 0.000 claims description 11
- 239000012634 fragment Substances 0.000 claims description 11
- 239000000945 filler Substances 0.000 claims description 2
- 230000009977 dual effect Effects 0.000 abstract description 2
- 230000001737 promoting effect Effects 0.000 abstract description 2
- 230000001105 regulatory effect Effects 0.000 abstract 1
- 239000007769 metal material Substances 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229940079593 drug Drugs 0.000 description 2
- 239000003814 drug Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- -1 copper Chemical class 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000007921 spray Substances 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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
- B64D1/06—Bomb releasing; Bombs doors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Linear Motors (AREA)
- Train Traffic Observation, Control, And Security (AREA)
- Toys (AREA)
Abstract
nullThe invention discloses the built-in type ammunition electromagnetic launch device on a kind of helicopter，This device includes ammunition guide rail、Electromagnetism guide rail and the armature being arranged on ammunition，Wherein said ammunition guide rail is used for laying、Transport ammunition，Described electromagnetism guide rail includes two slide rails with strong electric conductivity，Described electromagnetism guide rail is used for promoting ammunition to depart from downwards unmanned plane along described slide rail，Described armature has strong electric conductivity，Armature is for along with contacting with two slide rails on electromagnetism guide rail respectively when ammunition enters in electromagnetism guide rail，Constitute closed-loop path，So that generate magnetic field between two slide rails，Electric current is had to pass through on armature，With the armature of electric current under the influence of a magnetic field by the Ampere force on vertical direction，Thus under the dual function of Ampere force and gravity, control ammunition eject from unmanned plane，And the size and Orientation of Ampere force can be regulated and controled as the case may be.
Description
Technical field
The present invention relates to unmanned plane field, the auxiliary equipment launched including ammunition on a kind of unmanned plane, it is specifically related to one
Built-in type ammunition electromagnetic launch device on depopulated helicopter.
Background technology
Along with the range of application of unmanned plane is more and more extensive, its can be performed by of task also gets more and more, and receives more
The concern of many people, by unmanned plane, is done directly the combat duty struck target also the most existing especially by depopulated helicopter
Corresponding Design Conception, but, carry, about depopulated helicopter, the research that ammunition directly injures at present and can only stay in theory
In the stage, due to depopulated helicopter lighter weight, the conventional thrust launched of general ammunition is more than 10,000 newton, fixed according to momentum
Reason, in horizontal direction, the speed of depopulated helicopter will occur change greatly in moment, and meanwhile, recoil effect also can produce perpendicular
Nogata to huge moment, the control system that the generation of the change of speed and moment will upset depopulated helicopter as interference volume,
Cause depopulated helicopter temporary instability, the most out of control；
Ammunition routine launch during, if launching tube from depopulated helicopter excessively close to, combustion gas stream likely spray to
Depopulated helicopter body, destroys unmanned plane surface and internal structure.If launching tube is away from depopulated helicopter, then can produce bigger
Recoil moment, upset unmanned plane control system.Meanwhile, high temperature, discharger can be caused corrosion by combustion gas stream at a high speed, broken
The structure of bad discharger, reduces its life-span and safety.
Existing catapult-launching gear is mechanical ejection device, and such as Pneumatic hydraulic discharger etc., its structure is extremely complex, damages
After not easy-maintaining, and easily produce the accidents such as card bullet, its safety has much room for improvement.
For above-mentioned reasons, existing unmanned plane, especially depopulated helicopter are furtherd investigate by the present inventor, design
Go out the built-in type ammunition electromagnetic launch device on a kind of depopulated helicopter.
Summary of the invention
In order to overcome the problems referred to above, present inventor has performed and study with keen determination, design the built-in type bullet on a kind of helicopter
Medicine electromagnetic launch device, this device includes ammunition guide rail, electromagnetism guide rail and the armature being arranged on ammunition, and wherein said ammunition is led
Rail is used for laying, transporting ammunition, and described electromagnetism guide rail includes that two slide rails with strong electric conductivity, described electromagnetism guide rail are used for pushing away
Medicine of moving departs from downwards unmanned plane along described slide rail, and described armature has strong electric conductivity, and armature is for entering along with ammunition
Contact with two slide rails on electromagnetism guide rail respectively time in electromagnetism guide rail, constitute closed-loop path so that two slide rails it
Between generate magnetic field, armature has electric current pass through, with the armature of electric current under the influence of a magnetic field by the ampere on vertical direction
Power, thus under the dual function of Ampere force and gravity, control ammunition eject from unmanned plane, and can be as the case may be
The size and Orientation of regulation and control Ampere force, thus complete the present invention.
In particular it is object of the present invention to offer following aspect:
(1) the built-in type ammunition electromagnetic launch device on a kind of depopulated helicopter, it is characterised in that this device includes:
Ammunition guide rail 2, is used for placing and carry ammunition 1,
Electromagnetism guide rail 3, ammunition to be launched is transported to electromagnetism guide rail 3 from ammunition guide rail 2, and by the downward bullet of electromagnetism guide rail 3
Penetrate and be allowed to depart from unmanned plane, and
Armature 4, is set with and is fixed on outside ammunition,
Wherein, described electromagnetism guide rail 3 includes two slide rails 31 with electric conductivity,
Described armature 4 has electric conductivity, when entering in electromagnetism guide rail 3 along with ammunition, armature 4 respectively with electromagnetism guide rail
Two slide rails 31 on 3 make electrical contact with.
(2) according to the electromagnetic launch device described in above-mentioned (1), it is characterised in that
Described electromagnetism guide rail 3 also includes ammunition dead lock 32 and power supply 33,
Wherein, described power supply 33 electrically connects with the slide rail 31 being vertically arranged,
Described ammunition dead lock 32 is for the fixing ammunition 1 being positioned in electromagnetism guide rail 3, and needs to depart from unmanned plane at ammunition
Time cancel ammunition is fixed.
(3) according to the electromagnetic launch device described in above-mentioned (1), it is characterised in that
The recess 21 for fixing ammunition 1 it is provided with on described ammunition guide rail 2.
(4) according to the electromagnetic launch device described in above-mentioned (1), it is characterised in that
Described armature 4 is in circular, on the sheathed outer wall being fixed on ammunition, is entering in electromagnetism guide rail 3 along with ammunition 1
And along vertical direction slide time, described armature 4 keeps electrical contact with the slide rail 31 on electromagnetism guide rail 3.
(5) according to the electromagnetic launch device described in above-mentioned (4), it is characterised in that
Ring-type in non-closed of described armature 4, the most described armature 4 is the plain conductor being coiled on ammunition 1 outer wall, and institute
State and leave predetermined gap 5 between two terminations of plain conductor.
(6) according to the electromagnetic launch device described in above-mentioned (5), it is characterised in that
Being provided with insulation shell fragment 6 outside described predetermined gap 5, described insulation shell fragment 6 enters into electromagnetism guide rail 3 at ammunition
Eject time middle, to prevent the termination of described plain conductor from contacting with slide rail 31.
(7) according to the electromagnetic launch device described in above-mentioned (5), it is characterised in that making a reservation between said two termination
It is provided with insulation filler in gap 5.
(8) according to the electromagnetic launch device described in above-mentioned (1), it is characterised in that
Described power supply 33 and armature 4 make electrical contact with two slide rails 31 on electromagnetism guide rail 3 the most respectively, thus constitute and close back
Road, after closed-loop path is formed, generates the magnetic field being perpendicular to two slide rail 31 place planes between two slide rails.
(9) according to the electromagnetic launch device described in above-mentioned (8), it is characterised in that
Described armature is additionally operable under the synergism of magnetic field force and gravity drive body to depart from unmanned plane at a predetermined velocity.
(10) according to the electromagnetic launch device described in above-mentioned (1), it is characterised in that
Described power supply 33 is used for powering to described slide rail 31,
The magnitude of pressure differential between positive pole and negative pole on described power supply is adjustable；
Described power supply 3) electrically connect with the bottom of slide rail 31 or described power supply electrically connects with the top of slide rail 31；
Preferably, described electromagnetic launch device also include double control switch 34, described double control switch 34 be used for controlling power supply with
The bottom electrical connection of slide rail 31 or power supply electrically connect with the top of slide rail 31.
The present invention is had the advantage that to include:
(1) according to the present invention provide depopulated helicopter on built-in type ammunition electromagnetic launch device can regulate and control ammunition from
The speed ejected on unmanned plane so that ammunition ejects at a predetermined rate, and can control in real time；
(2) according to armature in the built-in type ammunition electromagnetic launch device on the depopulated helicopter of present invention offer for being coiled in
Predetermined gap is left, at described predetermined gap between plain conductor on ammunition outer wall, and two terminations of described plain conductor
Outside is provided with insulation shell fragment, and described insulation shell fragment is for ejecting when ammunition enters in electromagnetism guide rail, to prevent described gold
The termination belonging to wire contacts with slide rail, thus avoids the hidden danger of armature from short circuit, and ammunition can be rolled on slide rail.
Accompanying drawing explanation
Fig. 1 illustrates the electromagnetic launch device overall structure front schematic view according to a kind of preferred implementation of the present invention；
Fig. 2 illustrates the perspective view that the electromagnetic launch device according to a kind of preferred implementation of the present invention is overall；
Fig. 3 illustrates the ammunition of the electromagnetic launch device according to a kind of preferred implementation of the present invention and armature structure thereon
Schematic diagram；
Fig. 4 illustrates the armature structure schematic diagram of the electromagnetic launch device according to a kind of preferred implementation of the present invention.
Drawing reference numeral illustrates:
1-ammunition
21-recess
2-ammunition guide rail
3-electromagnetism guide rail
31-slide rail
32-ammunition dead lock
33-power supply
34-double control switch
4-armature
5-predetermined gap
6-insulate shell fragment
Detailed description of the invention
Below by drawings and Examples, the present invention is described in more detail.Illustrated by these, the feature of the present invention
To become more apparent from clearly with advantage.
The most special word " exemplary " means " as example, embodiment or illustrative ".Here as " exemplary "
Illustrated any embodiment should not necessarily be construed as preferred or advantageous over other embodiments.Although embodiment shown in the drawings is each
Kind aspect, but unless otherwise indicated, it is not necessary to accompanying drawing drawn to scale.
According to the built-in type ammunition electromagnetic launch device on the depopulated helicopter that the present invention provides, such as institute in Fig. 1 and Fig. 2
Showing, this device includes ammunition guide rail 2, electromagnetism guide rail 3 and armature 4；Wherein, described ammunition guide rail 2 is used for placing and carrying ammunition
1, specifically, described ammunition guide rail includes at least one conveyer belt, places ammunition on a moving belt, when needs launch ammunition or
When person prepares to launch, drive ammunition to move by conveyer belt, and put down ammunition in precalculated position, preferably by ammunition in the present invention
Transporting and be placed in electromagnetism guide rail 3, described ammunition is preferably disposed vertically with described slide rail.
Described electromagnetism guide rail 3 is used for promoting ammunition to depart from downwards unmanned plane, and the most described electromagnetism guide rail can accommodate ammunition, and
Ammunition is applied with power so that it is eject unmanned plane with speed in the predetermined direction；
Described armature is set with and is fixed on outside ammunition, and it can either be led by contacting the mobile offer for ammunition with slide rail
To, additionally it is possible to constitute the circuit loop of Guan Bi by contacting with two slide rails, thus produce magnetic field, and then produce Ampere force,
Final ejection unmanned plane under the synergism of Ampere force and gravity；
Specifically, described electromagnetism guide rail 3 includes two slide rails 31 with strong electric conductivity, and described electromagnetism guide rail 3 also wraps
Include ammunition dead lock 32 and power supply 33,
Wherein, described slide rail 31 is vertically arranged, and all electrically connects with power supply 33, and described ammunition dead lock 32 is positioned at for fixing
Ammunition 1 in electromagnetism guide rail 3, and ammunition is fixed by cancellation when ammunition needs to depart from unmanned plane, described slide rail 31 is preferred
For vertical bar, and be made up of the metal material that electric conductivity is sufficiently strong, need to be coated with on the metals such as copper, at least its surface
The metal material that can conduct electricity；
In one preferred embodiment, described armature 4 has strong electric conductivity, is made up of metal materials such as copper,
Armature 4 is for along with contacting with two slide rails 31 on electromagnetism guide rail 3 respectively when ammunition enters in electromagnetism guide rail 3, constituting
Closed-loop path；After constituting closed-loop path, loop can there is electric current to pass through, and then produce magnetic field, under the influence of a magnetic field, armature
By the Ampere force on vertical direction, and then in the vertical direction moves, it is therefore preferable to move down.
In one preferred embodiment, described ammunition guide rail 2 is provided with the recess 21 for fixing ammunition 1, institute
State ammunition guide rail 2 in the ammunition transport that will load on unmanned plane to electromagnetism guide rail 3, it is preferable that described recess is arranged on biography
Send on band, i.e. ammunition can be fixed on a moving belt by recess, it is preferable that the insulation bullet that can will eject on ammunition armature
Sheet is placed in recess down, is i.e. compressed in system by insulation shell fragment by the weight of ammunition self, when ammunition is transported to
Along with the rotation of ammunition time in electromagnetism guide rail, described insulation shell fragment can be upspring, thus plays corresponding protective effect.
In one preferred embodiment, as shown in Figures 3 and 4, described armature 4, in circular, sheathed is fixed on
On the outer wall of ammunition, described armature 4 for along with ammunition 1 enter into electromagnetism guide rail 3 slides along vertical direction time with electric
Slide rail 31 on magnetic conductance rail 3 keeps contact, thus ensures that closed-loop path can be continued for, and described magnetic field and Ampere force also are able to
It is continued for, and then Ampere force is persistently provided.
In one preferred embodiment, as shown in Figures 3 and 4, ring-type in non-closed of described armature 4, i.e. institute
Stating armature 4 is the plain conductor being coiled on ammunition 1 outer wall, and leaves predetermined gap between two terminations of described plain conductor
5；Preferably, being provided with insulation shell fragment 6 outside described predetermined gap 5, described insulation shell fragment 6 is for entering into electromagnetism at ammunition
Eject time in guide rail 3, to prevent the termination of described plain conductor from contacting with slide rail 31.
In one preferred embodiment, it is provided with insulation filling in the predetermined gap 5 between said two termination
Thing, thereby further ensures that the insulation of armature two ends disconnects, places the short circuit of described closed loop.
In one preferred embodiment, described slide rail 31 is for after closed-loop path is formed, between two slide rails
Generating the magnetic field being perpendicular to two slide rail 31 place planes, the direction in described magnetic field can be adjusted according to the change of the sense of current
Whole, unmanned plane it is controlled.Described armature is used for conducting electricity, and described armature is positioned in described magnetic field, and described armature is additionally operable to
Body is driven to depart from unmanned plane at a predetermined velocity under the synergism of magnetic field and gravity.Described predetermined speed is that unmanned plane passes through meter
The ideal ammunition ejection speed known, it is preferable that the power adjustable of described power supply, is additionally provided with in described circuit
Rheostat, consequently facilitating adjust the size of electric current in circuit further, thus adjusts the ejection speed of described ammunition.
In one preferred embodiment, described power supply 33 is for powering to described slide rail 31, on described power supply 33
Positive pole and negative pole electrically connect with two slide rails 31 respectively, and the magnitude of pressure differential between positive pole and negative pole on described power supply is scalable
's；
Described power supply 33 electrically connects with the bottom of slide rail 31 or described power supply electrically connects with the top of slide rail 31；The most permissible
Make the action direction of Ampere force that produces upwardly or downwardly, and then can specifically calculate and obtain by initial velocity as required
?；
Preferably, as shown in fig. 1, described electromagnetic launch device also includes that double control switch 34, described double control switch 34 are used
Electrically connect with the bottom of slide rail 31 or power supply electrically connects with the top of slide rail 31 in controlling power supply；Specifically, described two
The top of slide rail and bottom all connect wire, and the wire that power supply is drawn can be with described two cunnings through described double control switch
The wire that rail top connects is connected or is connected with the wire connected bottom described slide rail.
In describing the invention, it should be noted that term " on ", D score, " interior ", the instruction such as " outward " " front " " afterwards "
Orientation or position relationship are based on the orientation under duty of the present invention or position relationship, be for only for ease of description the present invention and
Simplify and describe rather than indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration
And operation, therefore it is not considered as limiting the invention.
Above in association with preferred embodiment describing the present invention, but these embodiments are only exemplary
, only play illustrative effect.On this basis, the present invention can be carried out multiple replacement and improvement, these each fall within this
In the protection domain of invention.
Claims (10)
1. the built-in type ammunition electromagnetic launch device on a depopulated helicopter, it is characterised in that this device includes:
Ammunition guide rail (2), is used for placing and carry ammunition (1),
Electromagnetism guide rail (3), ammunition to be launched is transported to electromagnetism guide rail (3) from ammunition guide rail (2), and by electromagnetism guide rail (3) to
Under launch and be allowed to depart from unmanned plane, and
Armature (4), is set with and is fixed on outside ammunition,
Wherein, described electromagnetism guide rail (3) includes two slide rails (31) with electric conductivity,
Described armature (4) has electric conductivity, and when entering in electromagnetism guide rail (3) along with ammunition, armature (4) is led with electromagnetism respectively
Two slide rail (31) electrical contacts on rail (3).
Electromagnetic launch device the most according to claim 1, it is characterised in that
Described electromagnetism guide rail (3) also includes ammunition dead lock (32) and power supply (33),
Wherein, described power supply (33) electrically connects with the slide rail (31) being vertically arranged,
Described ammunition dead lock (32) is for the fixing ammunition (1) being positioned in electromagnetism guide rail (3), and needs to depart from nobody at ammunition
Cancel during machine and ammunition is fixed.
Electromagnetic launch device the most according to claim 1, it is characterised in that
The recess (21) for fixing ammunition (1) it is provided with on described ammunition guide rail (2).
Electromagnetic launch device the most according to claim 1, it is characterised in that
Described armature (4) is in circular, on the sheathed outer wall being fixed on ammunition, is entering into electromagnetism guide rail (3) along with ammunition (1)
In and along vertical direction slide time, the slide rail (31) on described armature (4) and electromagnetism guide rail (3) keeps electrical contact.
Electromagnetic launch device the most according to claim 4, it is characterised in that
Ring-type in non-closed of described armature (4), the most described armature (4) for be coiled in the plain conductor on ammunition (1) outer wall, and
Predetermined gap (5) is left between two terminations of described plain conductor.
Electromagnetic launch device the most according to claim 5, it is characterised in that
Described predetermined gap (5) outside is provided with insulation shell fragment (6), and described insulation shell fragment (6) enters into electromagnetism at ammunition and leads
Eject time in rail (3), to prevent the termination of described plain conductor from contacting with slide rail (31).
Electromagnetic launch device the most according to claim 5, it is characterised in that
It is provided with insulation filler in predetermined gap (5) between said two termination.
Electromagnetic launch device the most according to claim 1, it is characterised in that
Described power supply (33) and armature (4) make electrical contact with two slide rails (31) on electromagnetism guide rail (3) the most respectively, thus constitute and close
Close loop, after closed-loop path is formed, between two slide rails, generate the magnetic field being perpendicular to two slide rail (31) place planes.
Electromagnetic launch device the most according to claim 8, it is characterised in that
Described armature is additionally operable under the synergism of magnetic field force and gravity drive body to depart from unmanned plane at a predetermined velocity.
Electromagnetic launch device the most according to claim 1, it is characterised in that
Described power supply (33) is used for powering to described slide rail (31),
The magnitude of pressure differential between positive pole and negative pole on described power supply is adjustable；
Described power supply (33) electrically connects with the bottom of slide rail (31) or described power supply electrically connects with the top of slide rail (31)；
Preferably, described electromagnetic launch device also include double control switch (34), described double control switch (34) be used for controlling power supply with
The bottom electrical connection of slide rail (31) or power supply electrically connect with the top of slide rail (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610621339.2A CN106114862B (en) | 2016-08-01 | 2016-08-01 | Built-in type ammunition electromagnetic launch device on unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610621339.2A CN106114862B (en) | 2016-08-01 | 2016-08-01 | Built-in type ammunition electromagnetic launch device on unmanned helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106114862A true CN106114862A (en) | 2016-11-16 |
| CN106114862B CN106114862B (en) | 2018-06-26 |
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ID=57254510
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610621339.2A Active CN106114862B (en) | 2016-08-01 | 2016-08-01 | Built-in type ammunition electromagnetic launch device on unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106114862B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107261376A (en) * | 2017-08-07 | 2017-10-20 | 沈阳金丰春航空科技有限公司 | Unmanned plane and fire-extinguishing |
| CN108088645A (en) * | 2017-11-30 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of built-in type grafts article separated track catching method |
| CN109225591A (en) * | 2018-10-19 | 2019-01-18 | 长兴撒哈拉新材料有限公司 | A kind of feeding device for vertical raw material chopper |
| CN109305372A (en) * | 2018-09-10 | 2019-02-05 | 南京航空航天大学 | Heavy helicopter and its catapult technique with separable crew module |
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| US3840148A (en) * | 1972-01-28 | 1974-10-08 | L Fontana | Conveyance equipment which allows the discharge of all or partly of the load by means of an electromagnetic control device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107261376A (en) * | 2017-08-07 | 2017-10-20 | 沈阳金丰春航空科技有限公司 | Unmanned plane and fire-extinguishing |
| CN108088645A (en) * | 2017-11-30 | 2018-05-29 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of built-in type grafts article separated track catching method |
| CN109305372A (en) * | 2018-09-10 | 2019-02-05 | 南京航空航天大学 | Heavy helicopter and its catapult technique with separable crew module |
| CN109225591A (en) * | 2018-10-19 | 2019-01-18 | 长兴撒哈拉新材料有限公司 | A kind of feeding device for vertical raw material chopper |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106114862B (en) | 2018-06-26 |
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