CN210479048U - Helicopter cargo hook device - Google Patents
Helicopter cargo hook device Download PDFInfo
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- CN210479048U CN210479048U CN201921380323.2U CN201921380323U CN210479048U CN 210479048 U CN210479048 U CN 210479048U CN 201921380323 U CN201921380323 U CN 201921380323U CN 210479048 U CN210479048 U CN 210479048U
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- 238000009434 installation Methods 0.000 description 10
- 238000013016 damping Methods 0.000 description 8
- 230000000712 assembly Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 5
- 240000007643 Phytolacca americana Species 0.000 description 3
- 235000009074 Phytolacca americana Nutrition 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 238000003756 stirring Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000746 Structural steel Inorganic materials 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model discloses a helicopter cargo hook device, which comprises a left hook frame, a right hook frame, a mounting bolt, a hook beam assembly, a solenoid assembly, a mechanical release assembly, a rocker arm assembly for limiting the hook beam assembly and a cam assembly for limiting the rocker arm assembly, wherein the upper ends of the left hook frame and the right hook frame are respectively provided with a mounting part, and the mounting parts of the left hook frame and the right hook frame are fixedly connected through the mounting bolt; the solenoid assembly is connected with the aviation socket; hook beam subassembly rotates through the pivot to be installed on left side hook rack and the right hook rack, rotate through the rocking arm bolt in the middle of the rocking arm subassembly and install on left side hook rack and the right hook rack, the cam subassembly passes through the cam bolt and rotates to be installed on left side hook rack and the right hook rack, solenoid subassembly and mechanical release subassembly respectively with left side hook rack and right hook rack fixed connection and be used for driving the cam subassembly rotates. The device has the advantages of simple structure, high reliability and low cost.
Description
Technical Field
The utility model relates to a cargo hook technical field especially relates to a helicopter cargo hook device.
Background
The cargo hook is a device installed on the belly of the helicopter, a hook beam on the cargo hook can be used for hanging an outer hanging object, and a locking device of the cargo hook is provided with two sets of releasing mechanisms which can unlock the cargo hook, so that the outer hanging object can be normally released. After the helicopter is additionally provided with the cargo hook, a cargo hoisting, emergency rescue and hanging fire extinguishing device can be further additionally arranged, so that more various operation tasks can be executed, and the helicopter is widely selected and installed equipment. The cargo hooks in the market are developed by foreign companies at present, the product series is less, and the bearing capacity cannot completely cover various hanging operation load intervals of the helicopter; in addition, the cargo hook products have the defects of large self weight, complex structure, difficult maintenance, high price and the like.
SUMMERY OF THE UTILITY MODEL
To the deficiency of the prior art, the technical problem to be solved by the present patent application is: how to provide a simple structure, the reliability is high, easily dismantles the maintenance, and light in weight, with low costs helicopter cargo hook device.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a cargo hook device of a helicopter comprises a left hook frame, a right hook frame, a mounting bolt, a hook beam assembly, a solenoid assembly, a mechanical release assembly, a rocker arm assembly for limiting the hook beam assembly and a cam assembly for limiting the rocker arm assembly, wherein mounting parts are arranged at the upper ends of the left hook frame and the right hook frame, and the mounting parts of the left hook frame and the right hook frame are fixedly connected through the mounting bolt; the solenoid assembly is connected with the aviation socket; hook beam subassembly rotates through the pivot to be installed on left side hook rack and the right hook rack, rotate through the rocking arm bolt in the middle of the rocking arm subassembly and install on left side hook rack and the right hook rack, the cam subassembly passes through the cam bolt and rotates to be installed on left side hook rack and the right hook rack, solenoid subassembly and mechanical release subassembly respectively with left side hook rack and right hook rack fixed connection and be used for driving the cam subassembly rotates.
Therefore, the left hook frame and the right hook frame are main frameworks of the cargo hook device, the installation parts of the left hook frame and the right hook frame are connected through the installation bolts, the installation bolts between the left hook frame and the right hook frame are used for being connected with the helicopter, and an interface used for being connected with the helicopter is formed. The hook beam assembly is an interface for hanging an external hanging object by the cargo hook device, and the hook beam assembly rotates around the rotating shaft to realize opening and locking. The rocker arm assembly can rotate around the rocker arm bolt, the rocker arm assembly can limit the hook beam assembly, the rocker arm assembly is a lever mechanism, the load transmitted by an external object can be further reduced, the force required by the solenoid assembly and the mechanical release assembly to operate the cam assembly is reduced, the cam assembly can rotate around the cam bolt, and the cam assembly is used for limiting the rocker arm assembly and receiving the driving of the mechanical release assembly and the solenoid assembly. The solenoid assembly is connected to an aircraft receptacle, which is an electrical interface of the cargo hook device for controlling the solenoid assembly to unlatch the cargo hook device.
Furthermore, a shaft sleeve and a rocker arm rotating shaft are respectively rotatably mounted at two ends of the rocker arm assembly in the rotating direction, a locking end and a hooking end are respectively arranged at two ends of the hook beam assembly in the rotating direction, and a limiting part for locking the locking end of the hook beam assembly is formed between the shaft sleeve and the rocker arm bolt; the cam assembly sets up hook beam assembly top, the cam assembly has action end, link and spacing end, still be provided with on the cam assembly with hook beam assembly return point complex roller bearing, the both sides of the action end of cam assembly are outwards provided with first catch bar and second catch bar respectively, the solenoid subassembly is used for promoting the action of first catch bar, mechanical release subassembly is used for promoting the action of second catch bar, the spacing end of cam assembly is used for spacing to the rocking arm pivot.
Like this, when the locking of goods hook device, external hanging thing weight has the trend that makes hook beam assembly rotate and then relieve the locking, but, and spacing portion that axle sleeve and rocking arm bolt formed carries out the locking spacing to hook beam assembly's locking end for hook beam assembly can't rotate, and at this moment, rocking arm pivot of rocking arm subassembly is withstood by the spacing end of cam pack and can't rotate, and pressure passes through the axis of rotation on the cam pack. Specifically, because the hook frame moves the spout position, corresponds the recess of cam pack promptly, the cam pack can only rotate along one direction, and the unblock is realized to anticlockwise rotation promptly. The solenoid assembly and the mechanical release assembly generate damping which limits the cam assembly to rotate towards the direction, when the mass of the external hanging object does not exceed the design load, the weight of the external hanging object cannot overcome the damping generated by the solenoid assembly and the mechanical release assembly, and the cam assembly, the rocker arm assembly and the hook beam assembly cannot rotate, so that the cargo hook device is locked.
Further, the solenoid subassembly includes solenoid mounting box, solenoid and cam disc, the solenoid with cam disc fixed connection, the solenoid is installed in the solenoid mounting box, the solenoid mounting box is installed on the hook frame of a left side, the outside fixed mounting of cam disc has first poker rod, correspond on the hook frame of a left side first catch bar is provided with the first spout that rotates that matches with it, first catch bar sliding fit is in the first spout that rotates, first poker rod with first catch bar contact, the link of cam subassembly with connect the setting through the extension spring between the hook frame of a left side.
Therefore, the solenoid assembly is connected with the aviation socket, when the aviation socket is powered on, the solenoid rotates to drive the cam disc to rotate, the first poking rod is arranged on the cam disc, the first poking rod pokes the first pushing rod to slide along the first rotating chute, the cam assembly is driven to rotate by an angle by overcoming the tension of the tension spring, when the rocker arm rotating shaft at the limiting end of the cam assembly is dislocated, the cam assembly relieves the limiting on the rocker arm assembly, the rocker arm assembly rotates to relieve the limiting on the locking end of the hook beam assembly, and the hook beam assembly can rotate around the rotating shaft to realize unlocking.
Further, the mechanical release assembly comprises a protective cover, a mechanical switch, a torsion spring and a torsion spring cover, the protective cover is fixedly connected with the right hook frame, the torsion spring cover is fixedly installed in the protective cover, one end of the torsion spring is fixedly connected with the right hook frame, the other end of the torsion spring bypasses the torsion spring cover and is provided with a hook, a second push rod at an action end on the cam assembly is positioned in the hook, the mechanical switch is rotatably installed in the protective cover and is positioned at one end of the torsion spring cover opposite to the right hook frame, a second poking rod is fixedly installed on the mechanical switch and is in contact with the second push rod, a second rotating chute matched with the second push rod is arranged on the right hook frame corresponding to the second push rod, the second push rod is in sliding fit in the second rotating chute, a steel cable opening and a poking opening are arranged on the protective cover, one end of the mechanical switch is positioned outside the toggle opening, and the steel cable penetrates through the steel cable opening and then is connected with a steel cable mounting interface on the mechanical switch.
Like this, the pulling cable wire drives mechanical switch and rotates, the last second poker rod that is provided with of mechanical switch, the second poker rod stirs the second catch bar and slides along the second rotation spout, overcome the torsion of torsional spring, extension spring, and then drive cam module and rotate an angle, when the spacing end rocking arm pivot dislocation of cam module, cam module removes spacing to the rocking arm subassembly, the rocking arm subassembly rotates, removes spacing to the locking end of hook roof beam subassembly, the hook roof beam subassembly can revolute the rotation of axes, realize the unblock. The torsion spring is used to provide damping that limits rotation of the cam assembly.
The cargo hook device adopts a manual mode to reset and lock, the manual rotation of the hook beam assembly overcomes the damping of the solenoid assembly and the mechanical release assembly, the locking end of the hook beam assembly jacks off the shaft sleeve of the rocker arm assembly, meanwhile, the return point on the hook beam assembly jacks off the needle roller bearing on the cam assembly, the hook beam assembly, the rocker arm assembly and the cam assembly all return to the locking position, and the cargo hook device realizes the reset and lock.
Further, the rotation angle of the cam plate is 20-25 degrees. The cam component can be better driven to rotate.
Furthermore, the solenoid installation box and the protective cover are fixedly connected with the left hook frame and the right hook frame through locking bolts. The installation and connection are convenient, and the later maintenance is convenient.
In conclusion, the device has the following beneficial effects:
1. the release mode has two mechanical and electrical release modes specified by civil aviation airworthiness regulations, and the functional reliability is high.
2. The parts and components are fewer, the parts and components are connected through bolts, the structure is simple, the disassembly and the maintenance are easy, and the product weight is light.
3. The aircraft helicopter is made of conventional aviation aluminum alloy and structural steel materials, home-made components widely applied in the industrial field are selected, the product cost is well controlled, the economy is good, and the aircraft helicopter is suitable for modification of light and medium helicopters.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic diagram of the structure of the present invention;
FIG. 3 is a schematic view of the internal locking principle of the present invention;
FIG. 4 is an exploded view of a solenoid assembly according to the present invention;
FIG. 5 is an exploded view of the mechanical release assembly of the present invention;
in the attached drawings, 1, a mounting bolt, 2, a left hook frame, 3 solenoid assemblies, 4 aviation sockets, 5 hook beam assemblies, 6 mechanical release assemblies, 7 right hook frames, 8 rocker arm assemblies, 9 cam assemblies, 10, a rotating shaft, 11, a shaft sleeve, 12 and rocker arm rotating shafts; 13. a tension spring 14, a solenoid mounting box; 15. a solenoid; 16. a cam plate; 17. a protective cover; 18. a mechanical switch; 19. a torsion spring; 20. a torsion spring cover; 21. a first push rod; 22. a second push rod; 23. a first poke rod; 24. a second poker rod; 25. a steel cable mounting interface; 26. (ii) a homing site; 27 needle roller bearing.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
With reference to figures 1-5 of the drawings,
a cargo hook device of a helicopter comprises a left hook frame 2, a right hook frame 7, a mounting bolt 1, a hook beam assembly 5, a solenoid assembly 3, a mechanical release assembly 6, a rocker arm assembly 8 for limiting the hook beam assembly 5 and a cam assembly 9 for limiting the rocker arm assembly 8, wherein mounting parts are arranged at the upper ends of the left hook frame 2 and the right hook frame 7, and the mounting parts of the left hook frame 2 and the right hook frame 7 are fixedly connected through the mounting bolt 1; the solenoid assembly 3 is connected with an aviation socket 4; hook beam subassembly 5 rotates through pivot 10 to be installed on left side hook frame 2 and the right hook frame 7, rotate through the rocking arm bolt in the middle of the rocking arm subassembly 8 and install on left side hook frame 2 and the right hook frame 7, cam subassembly 9 rotates through the cam bolt and installs on left side hook frame 2 and the right hook frame 7, solenoid subassembly 3 and mechanical release subassembly 6 respectively with left side hook frame 2 and right hook frame 7 fixed connection and be used for driving cam subassembly 9 rotates.
Therefore, the left hook frame and the right hook frame are main frameworks of the cargo hook device, the installation parts of the left hook frame and the right hook frame are connected through the installation bolts, the installation bolts between the left hook frame and the right hook frame are used for being connected with the helicopter, and an interface used for being connected with the helicopter is formed. The hook beam assembly is an interface for hanging an external hanging object by the cargo hook device, and the hook beam assembly rotates around the rotating shaft to realize opening and locking. The rocker arm assembly can rotate around the rocker arm bolt, the rocker arm assembly can limit the hook beam assembly, the rocker arm assembly is a lever mechanism, the load transmitted by an external object can be further reduced, the force required by the solenoid assembly and the mechanical release assembly to operate the cam assembly is reduced, the cam assembly can rotate around the cam bolt, and the cam assembly is used for limiting the rocker arm assembly and receiving the driving of the mechanical release assembly and the solenoid assembly. The solenoid assembly is connected to an aircraft receptacle, which is an electrical interface of the cargo hook device for controlling the solenoid assembly to unlatch the cargo hook device.
Further, a shaft sleeve 11 and a rocker arm rotating shaft 12 are respectively rotatably mounted at two ends of the rocker arm assembly 8 in the rotating direction, a locking end and a hooking end are respectively arranged at two ends of the hook beam assembly 5 in the rotating direction, and a limiting part for locking the locking end of the hook beam assembly is formed between the shaft sleeve 11 and the rocker arm bolt; cam subassembly 9 sets up hook beam subassembly 5 top, cam subassembly 9 has action end, link and spacing end, still be provided with on cam subassembly 3 with hook beam subassembly 5 go up return point 26 complex roller bearing 27, the both sides of cam subassembly 9's action end are outwards provided with first catch bar 21 and second catch bar 22 respectively, solenoid subassembly 3 is used for promoting the action of first catch bar 21, mechanical release subassembly 6 is used for promoting the action of second catch bar 22, cam subassembly 9's spacing end is used for spacing rocking arm pivot 8.
Like this, when the locking of goods hook device, external hanging thing weight has the trend that makes hook beam assembly rotate and then relieve the locking, but, and spacing portion that axle sleeve and rocking arm bolt formed carries out the locking spacing to hook beam assembly's locking end for hook beam assembly can't rotate, and at this moment, rocking arm pivot of rocking arm subassembly is withstood by the spacing end of cam pack and can't rotate, and pressure passes through the axis of rotation on the cam pack. Specifically, because the hook frame goes up the setting of moving the spout, the recess that corresponds the position of cam subassembly promptly, the cam subassembly can only rotate along a direction, and the unblock is realized to anticlockwise rotation promptly. The solenoid assembly and the mechanical release assembly generate damping which limits the cam assembly to rotate towards the direction, when the mass of the external hanging object does not exceed the design load, the weight of the external hanging object cannot overcome the damping generated by the solenoid assembly and the mechanical release assembly, and the cam assembly, the rocker arm assembly and the hook beam assembly cannot rotate, so that the cargo hook device is locked. The cargo hook device adopts a manual mode to reset and lock, the manual rotation of the hook beam assembly overcomes the damping of the solenoid assembly and the mechanical release assembly, the locking end of the hook beam assembly jacks off the shaft sleeve of the rocker arm assembly, meanwhile, the return point on the hook beam assembly jacks off the needle roller bearing on the cam assembly, the hook beam assembly, the rocker arm assembly and the cam assembly all return to the locking position, and the cargo hook device realizes the reset and lock.
Further, solenoid subassembly 3 includes solenoid mounting box 14, solenoid 15 and cam disc 16, solenoid 15 with cam disc 16 fixed connection, solenoid 15 installs in solenoid mounting box 14, solenoid mounting box 14 with on the left side hook frame 2, the outside fixed mounting of cam disc 16 has first poker rod 23, correspond on the hook frame 2 of a left side first catch bar 21 is provided with the first spout that rotates that matches with it, first catch bar 21 sliding fit is in the first spout that rotates, first poker rod 23 with first catch bar 21 contacts, the link of cam subassembly 9 with connect the setting through extension spring 13 between the hook frame 2 of a left side.
Therefore, the solenoid assembly is connected with the aviation socket, when the aviation socket is powered on, the solenoid rotates to drive the cam disc to rotate, the first poking rod is arranged on the cam disc, the first poking rod pokes the first pushing rod to slide along the first rotating chute, the cam assembly is driven to rotate by an angle by overcoming the tension of the tension spring, when the rocker arm rotating shaft at the limiting end of the cam assembly is dislocated, the cam assembly relieves the limiting on the rocker arm assembly, the rocker arm assembly rotates to relieve the limiting on the locking end of the hook beam assembly, and the hook beam assembly can rotate around the rotating shaft to realize unlocking.
Further, the mechanical releasing component 6 comprises a protective cover 17, a mechanical switch 18, a torsion spring 19 and a torsion spring cover 20, the protective cover 17 is fixedly connected with the right hook frame 7, the torsion spring cover 20 is fixedly installed in the protective cover 17, one end of the torsion spring 19 is fixedly connected with the right hook frame 7, the other end of the torsion spring cover 20 bypasses the torsion spring cover 20 and is provided with a hook, a second push rod 22 of an action end on the cam component 9 is positioned in the hook, the mechanical switch 18 is rotatably installed in the protective cover 17 and is positioned at one end of the torsion spring cover 20 opposite to the right hook frame 7, a second poking rod 24 is fixedly installed on the mechanical switch 18, the second poking rod 24 is in contact with the second push rod 22, a second rotating chute matched with the second push rod 22 is arranged on the right hook frame 7 corresponding to the second push rod 22, and the second push rod 22 is in sliding fit with the second rotating chute, the protective cover 17 is provided with a steel cable opening and a toggle opening, one end of the mechanical switch 18 is located outside the toggle opening, and the steel cable penetrates through the steel cable opening and then is connected with a steel cable mounting interface on the mechanical switch 18.
Like this, the pulling cable wire drives mechanical switch and rotates, is provided with the second poker rod on the mechanical switch, and the second poker rod stirs the second catch bar and slides along the second rotation spout, overcomes the torsion of torsional spring, and then drives cam module rotation an angle, and when cam module's spacing end rocking arm pivot dislocation, cam module removes spacing to the rocking arm subassembly, and the rocking arm subassembly rotates, removes spacing to the locking end of hook roof beam subassembly, and the hook roof beam subassembly can revolute the rotation of axes, realizes the unblock. The torsion spring is used to provide damping that limits rotation of the cam assembly.
Further, the rotation angle of the cam plate 16 is 20-25 °. The cam component can be better driven to rotate.
Further, the solenoid installation box 16 and the protection cover 17 are fixedly connected with the left hook frame 2 and the right hook frame 7 through locking bolts. The installation and connection are convenient, and the later maintenance is convenient.
The working process is as follows:
when the locking operation of the cargo hook device needs to be released, the solenoid is electrified to enable the cam disc 16 to push the first push rod 21 on the cam component 9 to rotate or pull the steel cable to enable the mechanical switch 18 to push the second push rod 22 on the cam component 9 to rotate, the cam component 9 rotates and then releases the limit of the rocker arm component 8, the weight of the external hanging object drives the hook beam component 5 to rotate and push the rocker arm component 8 to be limited, the cargo hook device releases the locking, and therefore the external hanging object is released.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (6)
1. A cargo hook device of a helicopter is characterized by comprising a left hook frame, a right hook frame, a mounting bolt, a hook beam assembly, a solenoid assembly, a mechanical release assembly, a rocker arm assembly for limiting the hook beam assembly and a cam assembly for limiting the rocker arm assembly, wherein mounting parts are arranged at the upper ends of the left hook frame and the right hook frame, and the mounting parts of the left hook frame and the right hook frame are fixedly connected through the mounting bolt; the solenoid assembly is connected with the aviation socket; hook beam subassembly rotates through the pivot to be installed on left side hook rack and the right hook rack, rotate through the rocking arm bolt in the middle of the rocking arm subassembly and install on left side hook rack and the right hook rack, the cam subassembly passes through the cam bolt and rotates to be installed on left side hook rack and the right hook rack, solenoid subassembly and mechanical release subassembly respectively with left side hook rack and right hook rack fixed connection and be used for driving the cam subassembly rotates.
2. The helicopter cargo hook device of claim 1, wherein a shaft sleeve and a rocker arm rotating shaft are rotatably mounted at two ends of the rocker arm assembly in the rotating direction, a locking end and a hooking end are respectively arranged at two ends of the hook beam assembly in the rotating direction, and a limiting part for locking the locking end of the hook beam assembly is formed between the shaft sleeve and the rocker arm bolt; the cam assembly sets up hook beam assembly top, the cam assembly has action end, link and spacing end, still be provided with on the cam assembly with hook beam assembly return point complex roller bearing, the both sides of the action end of cam assembly are outwards provided with first catch bar and second catch bar respectively, the solenoid subassembly is used for promoting the action of first catch bar, mechanical release subassembly is used for promoting the action of second catch bar, the spacing end of cam assembly is used for spacing to the rocking arm pivot.
3. A helicopter cargo hook device according to claim 2, characterized in that solenoid subassembly includes solenoid mounting box, solenoid and cam disc, the solenoid with cam disc fixed connection, the solenoid is installed in the solenoid mounting box, the solenoid mounting box is installed on the left side hooking bracket, the outside fixed mounting of cam disc has first poker rod, correspond on the left side hooking bracket first catch bar is provided with the first spout that rotates that matches with it, first catch bar sliding fit is in the first spout that rotates, first poker rod with first catch bar contact, the link of cam subassembly with connect the setting through the extension spring between the left hooking bracket.
4. The helicopter cargo hook apparatus of claim 1, wherein the mechanical release assembly comprises a protective cover, a mechanical switch, a torsion spring and a torsion spring cover, the protective cover is fixedly connected with the right hook frame, the torsion spring cover is fixedly installed in the protective cover, one end of the torsion spring is fixedly connected with the right hook frame, the other end of the torsion spring cover is provided with a hook by bypassing, a second pushing rod of the action end of the cam assembly is positioned in the hook, the mechanical switch is rotatably installed in the protective cover and positioned at one end of the torsion spring cover opposite to the right hook frame, a second poking rod is fixedly installed on the mechanical switch, the second poking rod is in contact with the second pushing rod, a second rotating chute matched with the second pushing rod is arranged on the right hook frame corresponding to the second pushing rod, and the second pushing rod is in sliding fit with the second rotating chute, the protective cover is provided with a steel cable opening and a toggle opening, one end of the mechanical switch is positioned outside the toggle opening, and the steel cable penetrates through the steel cable opening and then is connected with a steel cable mounting interface on the mechanical switch.
5. A helicopter cargo hook apparatus as defined in claim 3 wherein said cam plate is rotatable through an angle of between 20 ° and 25 °.
6. A helicopter cargo hook apparatus as defined in claim 3 wherein said solenoid mounting box and said protective cover are each fixedly connected to said left and right hook brackets by a locking bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921380323.2U CN210479048U (en) | 2019-08-23 | 2019-08-23 | Helicopter cargo hook device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921380323.2U CN210479048U (en) | 2019-08-23 | 2019-08-23 | Helicopter cargo hook device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210479048U true CN210479048U (en) | 2020-05-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921380323.2U Expired - Fee Related CN210479048U (en) | 2019-08-23 | 2019-08-23 | Helicopter cargo hook device |
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| CN (1) | CN210479048U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110371297A (en) * | 2019-08-23 | 2019-10-25 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of helicopter cargo hook device |
-
2019
- 2019-08-23 CN CN201921380323.2U patent/CN210479048U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110371297A (en) * | 2019-08-23 | 2019-10-25 | 重庆恩斯特龙通用航空技术研究院有限公司 | A kind of helicopter cargo hook device |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200508 |
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