CN203593176U - Connection and disconnection device - Google Patents
Connection and disconnection device Download PDFInfo
- Publication number
- CN203593176U CN203593176U CN201320734455.7U CN201320734455U CN203593176U CN 203593176 U CN203593176 U CN 203593176U CN 201320734455 U CN201320734455 U CN 201320734455U CN 203593176 U CN203593176 U CN 203593176U
- Authority
- CN
- China
- Prior art keywords
- mandrel
- block structure
- slide block
- bearing
- connection
- 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.)
- Expired - Lifetime
Links
- 238000009434 installation Methods 0.000 claims description 14
- 238000005259 measurement Methods 0.000 claims description 9
- 230000000994 depressogenic effect Effects 0.000 claims description 6
- 239000003638 chemical reducing agent Substances 0.000 claims description 2
- 230000033001 locomotion Effects 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Images
Abstract
The utility model provides a connection and disconnection device which comprises an active unit installed on an effective load and a passive unit installed outside an aircraft cabin body. The active unit comprises an active shell, a power device and a mandrel. The upper end of the mandrel is arranged on the active shell and connected with the power device and pin rollers are evenly distributed at the lower end of the mandrel. The passive unit comprises a passive shell, a sliding block structure and a supporting seat. The upper end of the sliding block structure is provided with spiral groove structures matched with the pin rollers, the lower end of the sliding block structure is sleeved with a disc spring and extends into the supporting seat, the disc spring is pre-tightened between the sliding block structure and the supporting seat, and the supporting seat is installed on the passive shell. The active unit and the passive unit are connected and disconnected through the match between the pin rollers on the mandrel and the spiral groove structures on the sliding block structure. The connection and disconnection device has the advantages that the effective load and the aircraft cabin body can be connected and disconnected, connection and disconnection are rapid and convenient, the structure is simple, and weight is low.
Description
Technical field
The utility model relate to aerospacecraft out of my cabin assembly connect tripper technical field, relate in particular to can implementation space aircraft out of my cabin the one between capacity weight and cabin body be connected tripper.
Background technology
At present, known aerospacecraft is out of my cabin in the connecting device of capacity weight and aircraft cabin body, the technical scheme that mainly adopts fastener to connect.Although can realize linkage function, while changing capacity weight, need astronaut to participate in fastener to remove, complicated operation is difficult to realize the quick connection of the capacity weight newly changing simultaneously, can not meet the requirement such as connection and release quickly and easily.
Utility model content
The utility model is a kind of tripper that connects, for realizing connection and the release between capacity weight and aircraft cabin body, this connection tripper is made up of active cell and passive unit two parts, described active cell is installed on described capacity weight, and described passive unit is installed in the external side in described aircraft cabin; Wherein,
Described active cell comprises engine installation, mandrel, and the upper end of described mandrel is connected with described engine installation, and described engine installation provides power that described mandrel is rotated; On the lower end lateral surface of described mandrel, be evenly equipped with roller;
Described passive unit comprises slide block structure, bearing, and the upper end of described slide block structure is provided with a depressed part, is provided with the helical groove structure matching with described roller on the medial surface of described depressed part; The lower end of described slide block structure is arranged with spring, and the lower end of described slide block structure puts in described bearing, and described spring pre-tightening is between described slide block structure and described bearing;
Between described active cell and described passive unit, by the coordinating of described roller and described plug helix inner structure, realize being connected and release between described active cell and described passive unit.
In some embodiment, described active cell also comprises active casing, and the upper end of described mandrel is arranged on described active casing by bearing, is provided with the first end-tooth on the lower surface of described active casing.
In some embodiment, described passive unit also comprises passive housing, and described bearing is installed on described passive housing, and the upper surface of described passive housing is provided with the second end-tooth matching with described the first end-tooth.
In some embodiment, described engine installation comprises motor and speed reducer, and the upper end of described mandrel is connected with described motor by described retarder.
In some embodiment, on described motor, be also provided with and revolve change measurement mechanism, and described in revolve become measurement mechanism be connected with described motor.
In some embodiment, described retarder includes output shaft, and described output shaft is connected with described mandrel by spline pair.
In some embodiment, described active cell also comprises cover plate, and described cover plate is connected with described active casing, and described reductor is arranged on described cover plate.
In some embodiment, described spring by fastening nuts between described slide block structure and described bearing.
In some embodiment, described spring adopts dish spring.
In some embodiment, on described bearing, sliding groove structure is set, rotates between described slide block mechanism and described bearing for preventing.
The utility model is owing to adopting above technical scheme, make it compared with prior art, there is following advantage and good effect: can realize connection and release between capacity weight and aircraft cabin body, connection and release are quick and convenient, have obtained the beneficial effects such as simple in structure, quality is light simultaneously.
Accompanying drawing explanation
By reference to the accompanying drawings, describe in detail by narration below, can more clearly understand above-mentioned and other feature and advantage of the present utility model, wherein:
Fig. 1 is the structural representation before the utility model main quilt moving cell connects and after release;
Fig. 2 is the structural representation after the utility model main quilt moving cell connects.
Nomenclature:
1-active casing
2-cover plate
3-retarder
4-motor
5-mandrel
6-bearing
7-roller
8-dish spring
9-slide block structure
10-nut
11-bearing
The passive housing of 12-
13-the first end-tooth
14-the second end-tooth
15-helical groove structure
16-sliding groove structure
The specific embodiment
Referring to the accompanying drawing that the utility model embodiment is shown, the utility model below will be described in more detail.But the utility model can be with many multi-form realizations, and should not be construed as the restriction of the embodiment being subject in this proposition.On the contrary, it is abundant and complete open in order to reach proposing these embodiment, and makes those skilled in the art understand scope of the present utility model completely.In these accompanying drawings, for clarity sake, may amplify size and the relative size in layer and region.
With reference to Fig. 1-2, the one that the utility model provides connects tripper, for realizing connection and the release between capacity weight and aircraft cabin body, this connection tripper is made up of active cell and passive unit two parts, active cell is installed on capacity weight, and passive unit is installed in the external side in aircraft cabin.
Concrete, active cell comprises active casing 1, cover plate 2, engine installation, mandrel 5.The upper end of mandrel 5 is arranged on active casing 1 by bearing 6, and cover plate 2 is arranged on the upper end with active casing 1, and is connected with active casing 1; In the present embodiment, engine installation comprises motor 4 and retarder 6, motor 4 is connected with retarder 6, on retarder 6 installations and cover plate 2, and the projecting shaft of retarder 6 is connected with mandrel 5 by spline pair, after motor 4 energising, produce power, and by transmission of power to retarder 6, make the output shaft rotation of retarder 6, thereby band moving mandrel 5 rotates; Certainly, engine installation also can adopt alternate manner to realize, as long as can it be rotated for mandrel 5 provides power, be restricted herein.On outside, lower end one circle of mandrel 5, be evenly provided with two and plural roller 7, the number of roller 7 and shape all can design as the case may be, in the present embodiment, are evenly equipped with three rollers 7 on mandrel 5 lower ends.
In the present embodiment, passive unit comprises passive housing 12, slide block structure 9, bearing 11.Wherein, on the upper end of slide block structure 9, be provided with a depressed part, on the madial wall of depressed part, be evenly provided with three helical groove structures 15, and these three helical groove structures 15 all match with three roller 7 positions, sizes on mandrel 5; In the time that active cell is connected with passive unit, mandrel 5 rotates in slide block structure 9, is realized and being connected with the cooperation of helical structure 15 by roller 7.The lower end of slide block structure 9 puts in bearing 11, and can slide axially along bearing 11 inwalls; On bearing 11, be provided with sliding groove structure 16, the lower end of slide block structure 9 is provided with the connecting bridge matching with sliding groove structure, when being connected with bearing 11, slide block structure 9 by the coordinating of sliding groove structure 16 and connecting bridge, rotates between slide block structure 9 and bearing 11 for preventing.On the lower end of slide block structure 9, be also arranged with spring, spring adopts dish spring 8 herein, and dish spring 8 passes through nut 10 pretensions between slide block structure 9 and bearing 11.Bearing 11 is installed on passive housing 12, and slide block structure 9 and bearing 11 be whole is positioned at passive housing 12.
In the present embodiment, on the lower surface of active casing 1, be provided with the first end-tooth 13, on the upper surface of passive housing 12, be provided with the second end-tooth 14 matching with the first end-tooth 13; In the time that active cell is connected with passive unit, the lower end of mandrel 5 is stretched in slide block structure 9, the lower surface of active casing 1 contacts with the upper surface of passive housing 12, and intermeshing by the first end-tooth 13 and the second end-tooth 14, thereby prevent from rotating between active casing 1 and passive housing 12.
Whether in the present embodiment, be also provided with and revolve change measurement mechanism on motor 4, this revolves and becomes measurement mechanism and be connected with motor 4, rotate and put in place, and after mandrel 5 is rotated in place, control motor 4 and stop operating for measuring mandrel 5.Certainly, revolving change measurement mechanism can carry into motor 4, also can arrange in addition, and its setting position, can set as the case may be, is not restricted herein.
Concrete connection, the releasing process of the connection tripper that the utility model provides are as follows:
With reference to figure 2, for the utility model active cell is connected the cutaway view of state afterwards with passive unit.Motor 4 energisings start, forward rotation, and power passes to retarder 3 through the output shaft of motor 4, and the output shaft of retarder 3 rotates by spline pair band moving mandrel 5.Active cell is applied to certain external force, three rollers 7 on mandrel 5 are entered in three plug helixs on slide block structure 9, roller 7 is by 15 positive movements of the helical groove structure along slide block structure 9.Mandrel 5 cannot move along axis direction due to the effect of bearing 6, forces slide block structure 9 relative motions.Slide block structure 9, can only be with respect to bearing 11 along axis direction upward movement because the constraint that is subject to bearing 11 sliding groove structures 16 cannot be rotated.Slide block structure 9 upward movements will drive nut 10 compact disc springs 8, and the power that dish spring 8 distortion produces makes to produce between active cell and passive unit connection power.Motor 4 by revolve become measurement mechanism and measure mandrel 5 and rotate in place after stop motion, roller 7 produces self-locking with slide block structure 9 helical groove structures because helical angle is less than friction angle, active cell and passive unit maintenance coupled condition.
With reference to figure 1, it is the cutaway view of state after the utility model active cell and passive unit release.When release, motor 4 rotates backward.Power passes to retarder 3 through the output shaft of motor 4, and the output shaft of retarder 3 rotates by spline pair band moving mandrel 5.Three rollers 7 on mandrel 5 are by the helical groove structure counter motion along slide block structure 9.Mandrel 5 cannot move along axis direction due to the effect of bearing 6, forces slide block structure 9 relative motions.Slide block structure 9, because the constraint that is subject to bearing 11 upper hopper chute structures 16 cannot be rotated, can only move downward along axis direction with respect to bearing 11.Slide block structure 9 moves downward drive nut 10 is loosened to dish spring 8, and dish spring 8 loosens makes to remove between active cell and passive unit connection power.Motor 4 by revolve become measurement mechanism and measure mandrel 5 and rotate in place after stop motion, the position of three rollers 7 on active cell mandrel 5 is corresponding with three helical groove structure 15 positions on passive unit, mandrel 5 can depart from slide block structure 9, now capacity weight can separate with aircraft cabin body, realizes release.
The utility model can be realized connection and the release between capacity weight and aircraft cabin body, and connection and release are quick and convenient, have obtained the beneficial effects such as simple in structure, quality is light simultaneously.
In sum, the utility model provides a kind of connection tripper, comprises the active cell being installed on capacity weight and is installed on the passive unit in the external side in aircraft cabin.Active cell comprises active casing, engine installation, mandrel, and the upper end of mandrel is arranged on active casing and with engine installation and is connected, and is evenly equipped with roller on lower end.Passive unit comprises passive housing, slide block structure, bearing, the upper end of slide block structure is provided with the helical groove structure matching with roller, the lower end cover of slide block structure is provided with dish spring and puts in bearing, and dish spring pretension is between slide block structure and bearing, and bearing is installed on passive housing.Coordinating of plug helix inner structure by the roller on mandrel and slide block structure between active cell and passive unit, realize connection and release between the two.The utility model can be realized connection and the release between capacity weight and aircraft cabin body, and connection and release are quick and convenient, have obtained the beneficial effects such as simple in structure, quality is light simultaneously.
Those skilled in the art should be understood that the utility model can not depart from spirit or scope of the present utility model with many other concrete forms realizations.Although also described embodiment of the present utility model, should understand the utility model and should not be restricted to these embodiment, within the utility model spirit and scope that those skilled in the art can define as appended claims, make and change and revise.
Claims (10)
1. a connection tripper, for realizing connection and the release between capacity weight and aircraft cabin body, it is characterized in that, this connection tripper is made up of active cell and passive unit two parts, described active cell is installed on described capacity weight, and described passive unit is installed in the external side in described aircraft cabin; Wherein,
Described active cell comprises engine installation, mandrel, and the upper end of described mandrel is connected with described engine installation, and described engine installation provides power that described mandrel is rotated; On the lower end lateral surface of described mandrel, be evenly equipped with roller;
Described passive unit comprises slide block structure, bearing, and the upper end of described slide block structure is provided with a depressed part, is provided with the helical groove structure matching with described roller on the medial surface of described depressed part; The lower end of described slide block structure is arranged with spring, and the lower end of described slide block structure puts in described bearing, and described spring pre-tightening is between described slide block structure and described bearing;
Between described active cell and described passive unit, by the coordinating of described roller and described plug helix inner structure, realize being connected and release between described active cell and described passive unit.
2. connection tripper according to claim 1, is characterized in that, described active cell also comprises active casing, and the upper end of described mandrel is arranged on described active casing by bearing, is provided with the first end-tooth on the lower surface of described active casing.
3. connection tripper according to claim 2, it is characterized in that, described passive unit also comprises passive housing, and described bearing is installed on described passive housing, and the upper surface of described passive housing is provided with the second end-tooth matching with described the first end-tooth.
4. according to the connection tripper described in claim 1 or 3, it is characterized in that, described engine installation comprises motor and speed reducer, and the upper end of described mandrel is connected with described motor by described retarder.
5. connection tripper according to claim 4, is characterized in that, on described motor, be also provided with and revolve change measurement mechanism, and described in revolve become measurement mechanism be connected with described motor.
6. connection tripper according to claim 4, is characterized in that, described retarder includes output shaft, and described output shaft is connected with described mandrel by spline pair.
7. connection tripper according to claim 4, is characterized in that, described active cell also comprises cover plate, and described cover plate is connected with described active casing, and described reductor is arranged on described cover plate.
8. connection tripper according to claim 1, is characterized in that, described spring by fastening nuts between described slide block structure and described bearing.
9. connection tripper according to claim 1, is characterized in that, described spring adopts dish spring.
10. connection tripper according to claim 1, is characterized in that, on described bearing, sliding groove structure is set, and rotates between described slide block mechanism and described bearing for preventing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320734455.7U CN203593176U (en) | 2013-11-20 | 2013-11-20 | Connection and disconnection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320734455.7U CN203593176U (en) | 2013-11-20 | 2013-11-20 | Connection and disconnection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203593176U true CN203593176U (en) | 2014-05-14 |
Family
ID=50674079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320734455.7U Expired - Lifetime CN203593176U (en) | 2013-11-20 | 2013-11-20 | Connection and disconnection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203593176U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104760710A (en) * | 2015-03-31 | 2015-07-08 | 中国科学院长春光学精密机械与物理研究所 | Electric connection and disconnection device of satellite and launch vehicle |
| CN104908980A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Flexible capturing connection device and capturing connection method thereof |
| CN104908045A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Space mechanical arm capable of conducting automatic locking and releasing |
| CN105465225A (en) * | 2015-11-30 | 2016-04-06 | 上海宇航系统工程研究所 | Self-lock type engaging and disengaging device |
| CN105510073A (en) * | 2015-11-27 | 2016-04-20 | 北京卫星制造厂 | Mechanical reinforcement pin-type connection separation mechanism |
| CN106516173A (en) * | 2016-12-14 | 2017-03-22 | 哈尔滨工业大学 | Repeated locking and releasing mechanism of space mechanical arm |
| CN107187610A (en) * | 2017-05-26 | 2017-09-22 | 中国航天空气动力技术研究院 | Bomb radiolysis locking device |
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
| CN108045602A (en) * | 2017-12-07 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of capture connecting integration drive transmission device for periphery lock |
| CN111762344A (en) * | 2020-07-01 | 2020-10-13 | 中国人民解放军63921部队 | Connecting device and replaceable solar wing structure |
| CN112141370A (en) * | 2020-09-04 | 2020-12-29 | 中国空间技术研究院 | Connecting interface between module and cabin section |
| CN112709732A (en) * | 2020-12-29 | 2021-04-27 | 中北大学 | Automatic butt joint device |
| CN113173271A (en) * | 2021-05-28 | 2021-07-27 | 重庆协点通讯技术有限公司 | Star chain receiving arrangement convenient to adjust |
| CN114321314A (en) * | 2021-12-31 | 2022-04-12 | 哈尔滨工业大学 | Irreversible transmission mechanism |
-
2013
- 2013-11-20 CN CN201320734455.7U patent/CN203593176U/en not_active Expired - Lifetime
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104760710B (en) * | 2015-03-31 | 2016-12-07 | 中国科学院长春光学精密机械与物理研究所 | A kind of electronic satellite and the rocket connect segregation apparatus |
| CN104760710A (en) * | 2015-03-31 | 2015-07-08 | 中国科学院长春光学精密机械与物理研究所 | Electric connection and disconnection device of satellite and launch vehicle |
| CN104908980A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Flexible capturing connection device and capturing connection method thereof |
| CN104908045A (en) * | 2015-05-11 | 2015-09-16 | 上海宇航系统工程研究所 | Space mechanical arm capable of conducting automatic locking and releasing |
| CN104908045B (en) * | 2015-05-11 | 2016-10-26 | 上海宇航系统工程研究所 | A kind of auto lock and the space manipulator of release |
| CN105510073B (en) * | 2015-11-27 | 2018-07-24 | 北京卫星制造厂 | A kind of mechanical booster pin type connection separation mechanism |
| CN105510073A (en) * | 2015-11-27 | 2016-04-20 | 北京卫星制造厂 | Mechanical reinforcement pin-type connection separation mechanism |
| CN105465225A (en) * | 2015-11-30 | 2016-04-06 | 上海宇航系统工程研究所 | Self-lock type engaging and disengaging device |
| CN105465225B (en) * | 2015-11-30 | 2017-09-12 | 上海宇航系统工程研究所 | A kind of self-locking clutch device |
| CN106516173A (en) * | 2016-12-14 | 2017-03-22 | 哈尔滨工业大学 | Repeated locking and releasing mechanism of space mechanical arm |
| CN106516173B (en) * | 2016-12-14 | 2018-08-07 | 哈尔滨工业大学 | A kind of space manipulator repetition locking relieving mechanism |
| CN107187610A (en) * | 2017-05-26 | 2017-09-22 | 中国航天空气动力技术研究院 | Bomb radiolysis locking device |
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
| CN107380487B (en) * | 2017-06-06 | 2020-11-24 | 上海卫星工程研究所 | Integrated square-to-round satellite-rocket connecting ring |
| CN108045602A (en) * | 2017-12-07 | 2018-05-18 | 上海宇航系统工程研究所 | A kind of capture connecting integration drive transmission device for periphery lock |
| CN108045602B (en) * | 2017-12-07 | 2020-11-17 | 上海宇航系统工程研究所 | Capturing and connecting integrated driving transmission mechanism for peripheral lock |
| CN111762344A (en) * | 2020-07-01 | 2020-10-13 | 中国人民解放军63921部队 | Connecting device and replaceable solar wing structure |
| CN111762344B (en) * | 2020-07-01 | 2023-12-22 | 中国人民解放军63921部队 | Connecting device and replaceable solar wing structure |
| CN112141370A (en) * | 2020-09-04 | 2020-12-29 | 中国空间技术研究院 | Connecting interface between module and cabin section |
| CN112709732A (en) * | 2020-12-29 | 2021-04-27 | 中北大学 | Automatic butt joint device |
| CN113173271A (en) * | 2021-05-28 | 2021-07-27 | 重庆协点通讯技术有限公司 | Star chain receiving arrangement convenient to adjust |
| CN114321314A (en) * | 2021-12-31 | 2022-04-12 | 哈尔滨工业大学 | Irreversible transmission mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203593176U (en) | Connection and disconnection device | |
| CN104619589B (en) | There is the electromechanical actuator of antiblock device | |
| CN105555661B (en) | The drive system of undercarriage for aircraft | |
| CN104058108B (en) | A kind of satellite is independently annotated in-orbit and is used docking mechanism actuating device | |
| CN103241368A (en) | Linear actuator and aircraft component comprising same | |
| CN109120831A (en) | A kind of Telescopic pick-up head device and mobile phone | |
| CN102615643B (en) | Four-degree-of-freedom parallel manipulator | |
| CN208605866U (en) | A kind of high school mathematics teaching geometric projection device | |
| CN202301776U (en) | An electric wheel hub reduction gear | |
| CN105460240A (en) | Small aircraft capturing connection and separation device | |
| CN109790908A (en) | Overload protection arrangement | |
| CN105734905A (en) | Washing machine speed reduction clutch and washing machine | |
| CN201476527U (en) | Shaft furnace charging device with driving device for distribution chute | |
| CN102601794B (en) | High-rigidity four-degree-of-freedom parallel mechanism capable of adjusting postures | |
| CN105734885B (en) | Speed reducing clutch for washing machine and washing machine | |
| CN207206340U (en) | A kind of waterproof jacket mounting tool | |
| CN105734909A (en) | Washing machine speed reduction clutch and washing machine | |
| KR101767977B1 (en) | Electric motor actuator with dc motor | |
| CN103496425A (en) | Device and use method for replenishing energy to flywheel battery by electricity generated when bicycle runs down slope | |
| CN204740993U (en) | Electric operating mechanism with separation and reunion and oneway drive function target in place | |
| CN105734900A (en) | Washing machine speed reduction clutch and washing machine | |
| CN210859604U (en) | Circumferential resistance drive clutch | |
| CN205315632U (en) | Rotary motion changes linear movement device | |
| CN112024135A (en) | Double-row test tube centrifugation method | |
| CN203796895U (en) | Worm gear combination slewing bearing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170705 Address after: 201108 D, room 101, No. 730, Lu Chun Road, Shanghai, Minhang District Patentee after: SHANGHAI ASES SPACEFLIGHT TECHNOLOGY Ltd. Address before: 201108 Minhang District, Shanghai Jin Road, No. 3805 Patentee before: AEROSPACE SYSTEM ENGINEERING SHANGHAI |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140514 |
|
| CX01 | Expiry of patent term |