CN208630863U - Multifunctional universal suspension arrangement - Google Patents
Multifunctional universal suspension arrangement Download PDFInfo
- Publication number
- CN208630863U CN208630863U CN201822014944.0U CN201822014944U CN208630863U CN 208630863 U CN208630863 U CN 208630863U CN 201822014944 U CN201822014944 U CN 201822014944U CN 208630863 U CN208630863 U CN 208630863U
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- Prior art keywords
- suspension
- interface
- leading portion
- back segment
- multifunctional universal
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- 239000000725 suspension Substances 0.000 title claims abstract description 116
- 238000009434 installation Methods 0.000 claims description 5
- 230000000694 effects Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 3
- 210000000245 forearm Anatomy 0.000 description 2
- 230000003447 ipsilateral effect Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 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
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
- Details Of Aerials (AREA)
Abstract
This application provides a kind of multifunctional universal suspension arrangements, belong to Aircraft Suspension Equipment design field, the suspension arrangement includes suspension body, the upper side of the suspension body is equipped with a plurality of types of upper interfaces to be adapted to the downside of different aircraft platform hanging point and the suspension body and be equipped with a plurality of types of lower interfaces with the hanger of carry different interface type.At least there are following advantageous effects in the multifunctional universal suspension arrangement of the utility model: different aircraft platforms, hanging point and different types of hanger are applicable to by designing multiple groups interface, so that suspension arrangement has more versatility.
Description
Technical field
The application belongs to airborne external hanging device design field, in particular to a kind of multifunctional universal suspension arrangement.
Background technique
Suspension arrangement usually only designs one group of mechanical electric interface both at home and abroad at present, is exclusively used in the force with same-interface
Device/hanger, while each suspension arrangement has a single function, Universal and scalability is unable to satisfy many types of aircraft platform, different extensions
The suspension use demand of point and multiple types weapon.
Summary of the invention
The object of the present invention is to provide a kind of multifunctional universal suspension arrangements, for solving existing Aircraft Suspension Equipment
It has a single function, be not applied for the problem of more aircraft platforms and/or multiple types weapon.
The technical solution of the application is: a kind of multifunctional universal suspension arrangement, the suspension arrangement includes suspension body, described
The top of suspension body is equipped with a plurality of types of upper interfaces to be adapted to the lower part of different aircraft platform hanging point and the suspension body
Equipped with a plurality of types of lower interfaces with the hanger of carry different interface type.
In one embodiment of the application, the suspension body is hollow structure, for accommodating equipment.
In one embodiment of the application, the suspension body include suspension leading portion, suspension middle section and suspension back segment, it is described on
Interface and the lower interface are located at the upper and lower surface in the suspension middle section, and the suspension leading portion and suspension back segment are fixedly installed on institute
State the rear and front end in suspension middle section.
In one embodiment of the application, the width of the width of the suspension leading portion and the suspension back segment is all larger than described
Hang the width in middle section.
In one embodiment of the application, the suspension leading portion includes leading portion front, in the middle part of leading portion and preceding segment trailer, described
Leading portion front, in the middle part of leading portion and preceding segment trailer is sequentially connected, the leading portion front for install satellite signal receiving equipment and/or
Wireless antenna, the leading portion middle part is for installing inertial navigation equipment, and the preceding segment trailer with the suspension middle section for connecting.
In one embodiment of the application, the interior positioning datum being equipped with for installing the inertial navigation equipment in the middle part of the leading portion
Face, the positioning reference plane are used to guarantee the operating accuracy of the inertial navigation equipment.
In one embodiment of the application, the suspension back segment includes back segment front and rear segment trailer, back segment front and institute
It states rear segment trailer to be sequentially connected, wherein the back segment front is for accommodating Fire control calculation equipment and/or power-supply device.
In one embodiment of the application, the tail end of the back segment front is equipped with groove, and the leading portion of the rear segment trailer is set
There is quick-detachable lock, the groove and the quick-detachable lock are coupled for realizing the fixation of the back segment front and the rear segment trailer
Connection.
In one embodiment of the application, the type of the upper interface includes lifting lug type structure and slotting ear type structure.
In one embodiment of the application, the upper interface of the lifting lug type structure includes lifting lug and at least two for installing
The mounting hole of lifting lug, the lifting lug are installed on the mounting hole of different location to generate the lifting lug of different spacing.
In one embodiment of the application, the upper interface of the slotting ear type structure includes the interface along the first of course setting
Interface rear portion on front and first, interface rear portion is sunk structure on interface front and first on described first, the recess
Structure is used to complete installation with the cooperation of the projective structure of aircraft platform.
At least there are following advantageous effects in multifunctional universal suspension arrangement of the invention: can by design multiple groups interface
Suitable for different aircraft platforms, hanging point and different types of weapon, so that suspension arrangement has more versatility.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is the multifunctional universal suspension device structure diagram of one embodiment of the application.
Fig. 2 is the suspension front segment structure schematic diagram of one embodiment of the application.
Fig. 3 is the suspension rear section structure schematic diagram of one embodiment of the application.
Appended drawing reference:
100- suspension body；
10- hangs leading portion, 11- leading portion front, in the middle part of 12- leading portion, segment trailer before 13-, and 14- inertial navigation equipment, 15- satellite letter
Number receiving device, 16- wireless antenna, the front 111- hatch door, hatch door in the middle part of 121-, 1121- front left face, the front 1122- are right
Side, 122- sliding rail, the tail portion 131- interface, 132- sliding slot；
20- hangs middle section, interface front on 211- first, interface rear portion on 212- first, interface front on 221- second,
Interface rear portion on 222- second, interface front in 231- third, interface rear portion in 232- third, 241- lower interface front, 242-
Lower interface rear portion supports forearm on 251-, postbrachium, 26- bomb shackle is supported on 252-；
30- hangs back segment, 31- back segment front, segment trailer after 32-, 311- Fire control calculation equipment, 312- power-supply device,
313- card slot, 314- pivot pin, 315- back segment hatch door, 321- quick-detachable lock, the tail portion 3221- upper side, the tail portion 3222- downside,
The tail portion 3223- arc surface.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
In the description of the present application, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is that orientation based on the figure or position are closed
System is merely for convenience of description the application and simplifies description, rather than the device or element of indication or suggestion meaning must have
Specific orientation is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application protection scope.
In order to solve in the prior art, it is flat that the suspension arrangement of the single model hanger of carry can only adapt to single aircraft
Platform, present applicant proposes a kind of multifunctional universal suspension arrangements.
The multifunctional universal suspension arrangement of the application mainly provides structure platform for external fire control system
And actuation mechanism, it is realized general to mounting for different aircraft platforms and hanging point, and designed compound outer by design multiple groups interface
Shape structure is integrated with the installation for realizing ejection mechanism, sensor and various control equipment, it is ensured that the shape of suspension arrangement, interface,
Intensity, rigidity and Support etc. meet the use demand of external fire control system.
For this purpose, the Multifunctional suspension device of the application includes a suspension body 100, the top of suspension body 100 is equipped with multiple types
The upper interface of type be adapted to different aircraft platform hanging point and suspension body 100 lower part be equipped with a plurality of types of lower interfaces with
The hanger of carry different interface type.
In the embodiment of the application, suspension body 100 is hollow structure, for accommodating equipment.Various equipment are accommodated
Inside suspension body 100, the effective protection to various equipment can be played.Signified equipment in the application, reference can be made to hereafter.
In the embodiment of the application, suspension body 100 includes suspension leading portion 10, suspension middle section 20 and hangs back segment 30,
Suspension leading portion 10, suspension middle section 20 and suspension back segment 30 are sequentially connected on the H of course.Upper interface and lower interface are located at suspension middle section
20 top and bottom, upper interface is for being adapted to different aircraft platforms, and lower interface is used for the different types of hanger of carry, before suspension
Section 10 and suspension back segment 30 are fixedly installed on the rear and front end in suspension middle section 20.
In the embodiment of the application, the type of upper interface includes lifting lug type structure and slotting ear type structure.
Embodiment as shown in Figure 1, upper interface share three types, respectively by interface front 211 and first on first
Interface on the first of 212 the first length specification constituted after upper interface, by interface on interface front 221 and second on second after
Interface and by interface rear portion 232 in interface front 231 in third and third on the second of second of length specification that portion 222 is constituted
Interface in the third of the third length specification constituted.
Interface is identical lifting lug type in interface and third on second, when in use, aircraft platform stretches out hook suspension
Interface on second, interface is sealed condition in third at this time, but when needing to adjust spacing, can be by the lifting lug of interface on second
(front and rear) is replaced to interface in third, and the closure of interface is replaced to interface on second in third, then is passed through
The hook that aircraft platform stretches out is matching, and the change of spacing can be completed.
Interface is slotting ear type on first comprising is connect on interface front 211 and first on first be arranged on the H of course
Metastomium 212, interface rear portion 212 is sunk structure on interface front 211 and first on first, when in use, passing through aircraft
The sunk structure of interface is mating in the structures such as the convex sheet being arranged on platform and first, i.e. completion fastening aircraft and suspension
The fixation of device.
For example, the extension of interface is away from can be 1150mm on first, the extension of interface is away from can be 762mm on second, in third
The extension of interface is away from that can be 355.6mm, by the way that different extensions is arranged away from suspension arrangement can be adapted to different aircraft platforms.
In addition, in the application, what the upper side in suspension middle section 20 was also made of support forearm 251 and support postbrachium 252
Support arm structure, support arm structure, which can play, keeps suspension arrangement holding horizontal or the effect of reduction suspension arrangement vibration.
The lower interface of suspension arrangement in the application includes being made of lower interface front 241 and lower interface rear portion 242
Second lower interface of the first lower interface of the first specification and second of specification being made of the bomb shackle 26 of single-point type, the two
The lower interface of different size can on the downside of suspension arrangement carry different size or length/weight hanger.
It should be noted that the upper interface and lower interface in the application are multiple types, and only illustrate in embodiment
Property gives three kinds of specifications to upper interface and gives two kinds of specifications to lower interface, so a variety of in the application refer to
No less than two kinds.
In one embodiment of the application, the width of the width and suspension back segment 30 that hang leading portion 10 is all larger than suspension middle section 20
Width.Suspension leading portion 10 and the inside for hanging back segment 30 are used to accommodate some electrical equipments or electronic equipment, hang middle section 20
It then realizes function pipeline, realize suspension leading portion 10 and hangs the route connection of the electrical equipment or electronic equipment between back segment 30,
Therefore, the shape for hanging leading portion 10 and suspension back segment 30 need to be larger compared to suspension middle section 20.
Further, since suspension arrangement has windage in aircraft flight, the width and suspension back segment of leading portion 10 are hung
The width that 30 width is all larger than suspension middle section 20 can also effectively reduce windage.
It should be noted that width described in the present embodiment can for exhibition Xiang Kuandu, or pitching to width, or
The combination of both persons.
In one embodiment of the application, suspension leading portion 10 includes leading portion front 11, leading portion middle part 12 and preceding segment trailer 13, preceding
Section front 11, leading portion middle part 12 and preceding segment trailer 13 are sequentially connected on the H of course, and leading portion front 11 can be used for installing satellite letter
Number receiving device 15 and/or wireless antenna 16,12 for installing inertial navigation equipment 14 in the middle part of leading portion, and preceding segment trailer 13 is used for and suspension
Middle section 20 connects.
In one preferred embodiment of the application, satellite signal receiving equipment 15 and wireless antenna 16 are installed on front end front 11
Upside to prevent it to be set to bring signal shielding in suspension arrangement the problems such as.It can be equipped in the side of front end front 11
Front hatch door 111, although satellite signal receiving equipment 15 and wireless antenna 16 are installed on the upside of front end front 11, it is related
Route is then placed in the space of front end front 11, can easily safeguard that satellite signal receiving is set by the front hatch door 111 opened up
For 15 and/or the route of wireless antenna 16.
In one preferred embodiment of the application, preceding segment trailer 13 is used in the middle part of leading portion 12 and is slidably connected, can be more convenient
Maintenance leading portion in the middle part of 12 inside install inertial navigation equipment 14.Specifically, sliding slot 132 is set in the downside of preceding segment trailer 13,
12 downside is provided with the sliding rail 122 cooperated with sliding slot 132 in the middle part of leading portion, and the two is used cooperatively, when needing to inertial navigation equipment
14 when being installed or being safeguarded, can be by preceding segment trailer 13 along the reversed pull-out of course H.
In addition, 12 side can offer middle section hatch door in the middle part of leading portion in order to safeguard to inertial navigation equipment 14
121, middle section hatch door 121 is connected to the space of 12 placement inertial navigation equipments 14 in the middle part of leading portion, safeguards leading portion by middle section hatch door 121
Inertial navigation equipment 14 in middle part 12.
It should be noted that front hatch door 111 and middle part hatch door 121 are preferentially opened in together in embodiments herein
Side can reduce the workload of operator in maintenance.But it can be realized the satellite-signal to 11 upside of front end front
Receiving device 15 and wireless antenna 16 and on the basis of the safeguarding of the inertial navigation equipment 14 in the middle part of leading portion 12, front hatch door
111 and middle part hatch door 121 can also be opened in it is not ipsilateral.
In one embodiment of the application, since inertial navigation equipment 14 needs precisely to guide, in order to improve the system of inertial navigation equipment 14
Lead accuracy, 12 in the middle part of the leading portion in be provided with multiple positioning reference planes, inertial navigation equipment 14 is installed with positioning reference plane, is thus come
Guarantee the operating accuracy of inertial navigation equipment 14.
In one embodiment of the application, suspension back segment 30 include back segment front 31 and rear segment trailer 32, back segment front 31 with
Segment trailer 32 is sequentially connected afterwards, wherein back segment front 31 is for accommodating Fire control calculation equipment 311 and/or power-supply device 312.
In this embodiment, power-supply device 312 can be fixed by pin shaft 314 and back segment front 31, Fire control calculation equipment
311 can complete to fix by power-supply device 312 to its extruding, using bonding or can also be fixed on back segment by connector
On front 31.
In addition, the side of back segment front 31 is also provided with back segment hatch door 315 in the present embodiment, pass through back segment hatch door 315
To safeguard the Fire control calculation equipment 311 or power-supply device 312 in back segment front 31.
It should be noted that back segment hatch door 315 equally can be preferentially opened in front hatch door 111 and middle part hatch door 121
The same side, in addition to the workload for reducing operator's rolling or adjustment suspension arrangement, hatch door, which is all set in the same side, can reduce thunder
Up to a possibility that detection.Likewise, can be realized relevant device is safeguarded under the premise of, three hatch doors can also open up
Not ipsilateral.
In one embodiment of the application, the tail end of back segment front 31 is equipped with groove 313, and the leading portion of rear segment trailer 32 is equipped with convex
Quick-detachable lock 321 out, groove 313 and quick-detachable lock 321 are coupled for realizing the fixation of back segment front 31 and rear segment trailer 32
Connection.It is real by being rapidly separated for groove 313 and quick-detachable lock 321 when needing that power-supply device 312 is installed or safeguarded
Existing back segment front 31 is come with dividing for rear segment trailer 32, and then can safeguard to power-supply device 312, convenient and efficient.
In an embodiment of the present invention, leading portion front 11 includes on the right side of front left face 1121 and front along the course direction H
Face 1122, front left face 1121 and front right side 1122 are symmetrical set tapered front end and can reduce to greatest extent
Windage.
In embodiments of the present invention, rear segment trailer 32 includes back segment upper side 3221 and back segment downside along the course direction H
3222, back segment upper side 3221 and back segment downside 3222 are symmetrically formed wake structure, reduce windage.In addition, rear segment trailer 32
It further include back segment arc surface 3223, the round and smooth excessive connection back segment upper side 3221 of back segment arc surface 3223 and back segment downside
3222, suspension arrangement tail portion can be prevented or mitigated and form sinuous flow.
It is different that there is the multifunctional universal suspension arrangement of the application the upper interface of composite general can be adapted on the whole
Aircraft platform hanging point and with a plurality of types of lower interfaces constitute hanging point with the hanger of carry different interface type, and
It realizes with special streamlined structure to satellite signal receiving equipment, wireless antenna, inertial navigation equipment, Fire control calculation equipment, electricity
The installation of source device etc. and integrated, general structure platform is provided for external fire control system, is that a kind of collection hangs
It hangs, delivery, launch the suspension arrangement that function and antenna/power supply/control management equipment installation function etc. are integrated, greatly improve dress
The availability and expansion set.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (11)
1. a kind of multifunctional universal suspension arrangement, which is characterized in that the suspension arrangement includes suspension body (100), the suspension
The top of body (100) is equipped with a plurality of types of upper interfaces to be adapted to different aircraft platform hanging points, under the suspension body (100)
Portion is equipped with a plurality of types of lower interfaces to be adapted to the hanger of different interface type.
2. multifunctional universal suspension arrangement as described in claim 1, which is characterized in that the suspension body (100) is hollow knot
Structure, for accommodating equipment.
3. multifunctional universal suspension arrangement as claimed in claim 2, which is characterized in that the suspension body (100) includes suspension
Leading portion (10), suspension middle section (20) and suspension back segment (30), the upper interface and the lower interface are located at the suspension middle section
(20) upper and lower surface, suspension leading portion (10) and suspension back segment (30) are fixedly installed on the front and back of suspension middle section (20)
Both ends.
4. multifunctional universal suspension arrangement as claimed in claim 3, which is characterized in that it is described suspension leading portion (10) width and
The width of suspension back segment (30) is all larger than the width of suspension middle section (20).
5. the multifunctional universal suspension arrangement as described in claim 3 to 4 is any, which is characterized in that the suspension leading portion (10)
(12) and preceding segment trailer (13) in the middle part of leading portion front (11), leading portion, the leading portion front (11), leading portion middle part are (12) and preceding
Segment trailer (13) is sequentially connected, and the leading portion front (11) is for installing satellite signal receiving equipment (15) and/or wireless antenna
(16), (12) are used to install inertial navigation equipment (14) in the middle part of the leading portion, and the preceding segment trailer (13) is used for and the suspension middle section
(20) it connects.
6. multifunctional universal suspension arrangement as claimed in claim 5, which is characterized in that be equipped with and use in (12) in the middle part of the leading portion
In the positioning reference plane for installing the inertial navigation equipment (14), the positioning reference plane is used to guarantee the work of the inertial navigation equipment (14)
Make precision.
7. multifunctional universal suspension arrangement as claimed in claim 3, which is characterized in that the suspension back segment (30) includes back segment
Front (31) and rear segment trailer (32), back segment front (31) are sequentially connected with the rear segment trailer (32), wherein before the back segment
Portion (31) is for accommodating Fire control calculation equipment (311) and/or power-supply device (312).
8. multifunctional universal suspension arrangement as claimed in claim 7, which is characterized in that the tail end of the back segment front (31) is set
The leading portion of fluted (313), the rear segment trailer (32) is equipped with quick-detachable lock (321), the groove (313) and the quick-detachable lock
(321) be coupled for realizing the back segment front (31) with it is described after segment trailer (32) be fixedly connected.
9. multifunctional universal suspension arrangement as described in claim 1, which is characterized in that the type of the upper interface includes lifting lug
Type structure and slotting ear type structure.
10. multifunctional universal suspension arrangement as claimed in claim 9, which is characterized in that the upper interface of the lifting lug type structure
Including lifting lug and at least two for installing the mounting hole of lifting lug, the lifting lug is installed on the mounting hole of different location to generate not
With the lifting lug of spacing.
11. multifunctional universal suspension arrangement as claimed in claim 9, which is characterized in that the upper interface of the slotting ear type structure
Including along first that course is arranged on interface front (211) and first interface rear portion (212), interface front on described first
(211) and on first interface rear portion (212) are sunk structure, and the sunk structure is used to match with the projective structure of aircraft platform
It closes and completes installation.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822014944.0U CN208630863U (en) | 2018-12-03 | 2018-12-03 | Multifunctional universal suspension arrangement |
| PCT/CN2019/122495 WO2020114360A1 (en) | 2018-12-03 | 2019-12-02 | Multifunctional universal suspension device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822014944.0U CN208630863U (en) | 2018-12-03 | 2018-12-03 | Multifunctional universal suspension arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208630863U true CN208630863U (en) | 2019-03-22 |
Family
ID=65744229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822014944.0U Active CN208630863U (en) | 2018-12-03 | 2018-12-03 | Multifunctional universal suspension arrangement |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN208630863U (en) |
| WO (1) | WO2020114360A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367788A (en) * | 2018-12-03 | 2019-02-22 | 中航技进出口有限责任公司 | Multifunctional universal suspension arrangement |
| WO2020114360A1 (en) * | 2018-12-03 | 2020-06-11 | 中航技进出口有限责任公司 | Multifunctional universal suspension device |
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| US3911786A (en) * | 1973-12-26 | 1975-10-14 | Us Navy | Ordnance alignment and loading apparatus |
| US4829876A (en) * | 1987-02-20 | 1989-05-16 | Varo, Inc. | Aircraft missile launcher sway brace apparatus |
| US6929214B2 (en) * | 2003-07-22 | 2005-08-16 | Northrop Grumman Corporation | Conformal airliner defense (CAD) system |
| US9180967B2 (en) * | 2012-02-28 | 2015-11-10 | The Boeing Company | Configurable pod structure and store stowage and deployment system and method |
| DE102014005300B4 (en) * | 2014-04-10 | 2024-06-20 | Mbda Deutschland Gmbh | Weapon carrier for attaching at least one unmanned aerial vehicle to a carrier aircraft, weapon system and aircraft |
| CN209700950U (en) * | 2018-12-03 | 2019-11-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional universal suspension arrangement with arcuate front ends |
| CN209700946U (en) * | 2018-12-03 | 2019-11-29 | 中国航空工业集团公司沈阳飞机设计研究所 | The adjustable multifunctional universal suspension arrangement of interface |
| CN109367788B (en) * | 2018-12-03 | 2023-08-22 | 中航技进出口有限责任公司 | Multifunctional universal suspension device |
| CN209700947U (en) * | 2018-12-03 | 2019-11-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional universal suspension arrangement with tapered front end |
| CN208630863U (en) * | 2018-12-03 | 2019-03-22 | 中航技进出口有限责任公司 | Multifunctional universal suspension arrangement |
| CN209700949U (en) * | 2018-12-03 | 2019-11-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Multifunctional universal suspension arrangement with lid |
| CN209814290U (en) * | 2018-12-03 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft with built-in fire control system and external fire control system |
| CN209700948U (en) * | 2018-12-03 | 2019-11-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Sliding type multifunctional all-purpose suspended device |
| CN209814279U (en) * | 2018-12-03 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft with external fire control system |
-
2018
- 2018-12-03 CN CN201822014944.0U patent/CN208630863U/en active Active
-
2019
- 2019-12-02 WO PCT/CN2019/122495 patent/WO2020114360A1/en active Application Filing
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367788A (en) * | 2018-12-03 | 2019-02-22 | 中航技进出口有限责任公司 | Multifunctional universal suspension arrangement |
| WO2020114360A1 (en) * | 2018-12-03 | 2020-06-11 | 中航技进出口有限责任公司 | Multifunctional universal suspension device |
| CN109367788B (en) * | 2018-12-03 | 2023-08-22 | 中航技进出口有限责任公司 | Multifunctional universal suspension device |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2020114360A1 (en) | 2020-06-11 |
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