CN104044726B - A kind of mechanism type sealing cover of aircraft store mounting point opening - Google Patents
A kind of mechanism type sealing cover of aircraft store mounting point opening Download PDFInfo
- Publication number
- CN104044726B CN104044726B CN201410279843.XA CN201410279843A CN104044726B CN 104044726 B CN104044726 B CN 104044726B CN 201410279843 A CN201410279843 A CN 201410279843A CN 104044726 B CN104044726 B CN 104044726B
- Authority
- CN
- China
- Prior art keywords
- slide rail
- outer sleeve
- shell
- aircraft
- closing plate
- 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.)
- Active
Links
Landscapes
- Bearings For Parts Moving Linearly (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a kind of mechanism type sealing cover of aircraft store mounting point opening, it comprises the shell be connected with wing, this shell (1) entirety is hexagonal structure, in the middle part of it inwardly one time punching molded go out hexagonal groove, the middle part of this groove stamps out hexagonal leghole, the hanger column coordinated with its grafting is provided with in this leghole, the other end of this hanger column is fixed on hanger, described leghole both sides mirror image is provided with slide rail, the middle part of this slide rail extends outward boss, this boss is fixed on the inner side of shell by slide rail bolt, the both sides of described boss extend outward permanent seat respectively, this permanent seat is provided with outer sleeve.The present invention is installed on aircraft outside face by means of only modes such as screws, be totally independent of aircraft other system, and do not need additionally to provide power and control signal during closing plate closedown, do not need to revise aircaft configuration in a large number, can reequip service aircraft easily, the closing plate outside face after closedown is comparatively level and smooth.
Description
Technical field
The present invention relates to field of airplane structure, be specifically related to a kind of mechanism type sealing cover of aircraft store mounting point opening.
Background technology
Modern invisbile plane for increasing voyage, bullet-loading capacity, and increases the alerting ability carrying ammunition, needs to use store mounting point to carry additional fuel tank and ammunition.When aircraft is executed the task, for ensureing its manoevreability and Stealth Fighter, at aircraft before entering region of war, need additional fuel tank together with hanger jettisoning.In addition, after plug-in ammunition launched by aircraft, also need jettisoning hanger, to reduce rebecca reflective area and aerodynamic drag, ensure aircraft Stealth Fighter and airworthiness.
For mounting hung rack, the covering at aircraft store mounting point place leaves multiple opening, and this aperture area is comparatively large, there is adverse effect to aircraft Stealth Fighter.For ensureing aircraft Stealth Fighter, a kind of mechanism type sealing cover of energy automatic shutter is needed to seal above-mentioned opening.: when not using hanger that sealing cover keeps closing to its requirement; When ground mounting hung rack, by ground staff, sealing cover is opened, then mounting hung rack; After hanger is thrown in, sealing cover is closed automatically, and remains closed condition in flight course afterwards.
Summary of the invention
The object of the invention is to provide a kind of mechanism type sealing cover that can seal aircraft store mounting point place covering opening, it can stay open state after mounting hung rack, automatically close after hanger is thrown in, and hanger throw in after flight course in remain closed condition, it can improve Stealth Fighter and the aeroperformance of aircraft effectively.
In order to solve problem existing in background technology, it comprises the shell 1 be connected with wing, this shell 1 entirety is hexagonal structure, in the middle part of it inwardly one time punching molded go out hexagonal groove, the middle part of this groove stamps out hexagonal leghole, the hanger column 15 coordinated with its grafting is provided with in this leghole, the other end of this hanger column 15 is fixed on hanger 14, described leghole both sides mirror image is provided with slide rail 10, the middle part of this slide rail 10 extends outward boss, this boss is fixed on the inner side of shell 1 by slide rail bolt 11, the both sides of described boss extend outward permanent seat respectively, this permanent seat is provided with outer sleeve 7, this outer sleeve 7 is by outer sleeve bearing pin 8 and permanent seat normal-running fit, described outer sleeve 7 is overall is provided with the hollow tubular structure of opening for the other end, the inner sleeve 6 coordinated with its gap grafting is provided with inside it, spring 17 is provided with between described outer sleeve 7 and inner sleeve 6, the other end of described inner sleeve 6 is by inner sleeve cylinder pin 5 and limited roller support 4 normal-running fit, described limited roller support 4 is arranged on closing plate 2, sealing plate 2 is arranged between two slide rails 10, and be positioned at the both sides of leghole, the both sides of described closing plate 2 are provided with ballframe carriage 3, the inner side of described slide rail 10 offers the guide groove with ballframe carriage 3 bearing fit.
Driving lever is extended respectively to interior mirror image in the side of described outer sleeve 7, and the other end of this driving lever is provided with the driving lever roller 9 with its normal-running fit.
The side that described ballframe carriage 3 is inserted into side in guide groove is provided with the ball 16 with its normal-running fit.
The middle part of described limited roller support 4 inwardly mills out groove, and being provided with in this groove with limited roller 12, two corresponding limited rollers 12 of its normal-running fit is setting of mutually staggering.
Owing to have employed above technical scheme, the present invention has following beneficial effect: be installed on aircraft outside face by means of only modes such as screws, be totally independent of aircraft other system, and do not need additionally to provide power and control signal during closing plate closedown, do not need to revise aircaft configuration in a large number, can reequip service aircraft easily, closing plate outside face after closedown is comparatively level and smooth, affect little on aircraft aerodynamic performance and Stealth Fighter, having stable behavior is reliable, long service life.
Accompanying drawing explanation
In order to be illustrated more clearly in the present invention, below in conjunction with accompanying drawing, embodiment is briefly described.
Fig. 1 is the block diagram structural representation of the present invention in open mode;
Fig. 2 is the three-dimensional exploded view of the present invention in open mode;
Fig. 3 is the birds-eye view of the present invention in open mode;
Fig. 4 is the birds-eye view of the present invention in pre-shutdown state;
Fig. 5 is the block diagram of closed condition of the present invention;
Fig. 6 is the front elevation of shell of the present invention;
Fig. 7 is birds-eye view and the section-drawing of shell of the present invention;
Fig. 8 is rail structure schematic diagram in the present invention;
Fig. 9 is closing plate unit construction schematic diagram of the present invention;
Figure 10 is limited roller arrangement schematic diagram of the present invention;
Figure 11 is ball grooves and ball mounting means schematic diagram;
Figure 12 is actuator configurations schematic diagram;
Figure 13 is outer sleeve bearing pin and shell, slide rail and outer sleeve connection mode schematic diagram;
Wherein:
1. shell, 2. closing plate, 3. ballframe carriage, 4. limited roller support, 5. inner sleeve bearing pin, 6. inner sleeve, 7. outer sleeve, 8. outer sleeve bearing pin, 9. driving lever roller, 10. slide rail, 11. slide rail bolts, 12. limited rollers, 13. shifting blocks, 14. hangers, 15. hanger columns, 16. balls, 17. springs.
Detailed description of the invention
The technological means realized to make the present invention, creation characteristic, reaching object and effect is easy to understand, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention being clearly and completely described.
Embodiment 1
Referring to Fig. 1-13, it comprises the shell 1 be connected with wing, this shell 1 entirety is hexagonal structure, inwardly one time punching moldedly in the middle part of it go out out hexagonal groove, the middle part of this groove stamps out hexagonal leghole, the hanger column 15 coordinated with its grafting is provided with in this leghole, the other end of this hanger column 15 is fixed on hanger 14, described leghole both sides mirror image is provided with slide rail 10, the middle part of this slide rail 10 extends outward boss, this boss is fixed on the inner side of shell 1 by slide rail bolt 11, the both sides of described boss extend outward permanent seat respectively, this permanent seat is provided with outer sleeve 7, this outer sleeve 7 is by outer sleeve bearing pin 8 and permanent seat normal-running fit, described outer sleeve 7 is overall is provided with the hollow tubular structure of opening for the other end, the inner sleeve 6 coordinated with its gap grafting is provided with inside it, spring 17 is provided with between described outer sleeve 7 and inner sleeve 6, the other end of described inner sleeve 6 is by inner sleeve cylinder pin 5 and limited roller support 4 normal-running fit, described limited roller support 4 is arranged on closing plate 2, sealing plate 2 is arranged between two slide rails 10, and be positioned at the both sides of leghole, the both sides of described closing plate 2 are provided with ballframe carriage 3, the inner side of described slide rail 10 offers the guide groove with ballframe carriage 3 bearing fit.
Driving lever is extended respectively to interior mirror image in the side of described outer sleeve 7, and the other end of this driving lever is provided with the driving lever roller 9 with its normal-running fit.
The side that described ballframe carriage 3 is inserted into side in guide groove is provided with the ball 16 with its normal-running fit.
The middle part of described limited roller support 4 inwardly mills out groove, and being provided with in this groove with limited roller 12, two corresponding limited rollers 12 of its normal-running fit is setting of mutually staggering.
Embodiment 2
As shown in Figure 1, x is to be aircraft flight direction, and y is to for opening up to, z to for above aircraft for the definition of sealing cover system of axes.
In fig. 1 and 2, mechanism type sealing cover includes 1 shell, 1,2 closing plates 2 altogether, 4 ballframe carriage, 3,2 limited roller supports, 4,4 inner sleeve bearing pins 5,4 inner sleeves, 6,4 outer sleeves, 7,4 outer sleeve bearing pins 8,4 driving lever rollers, 9,2 slide rails, 10,4 slide rail bolts 11,2 limited rollers, 12,2 shifting blocks 13, hanger 14, hanger pillar 15,8 balls 16 (see Fig. 9) and 4 springs 17 (see Figure 12).
By 1 closing plate, 2,2 ballframe carriage, 3,4 balls, 16,1 limited roller support 4, and 2 inner sleeve bearing pins 5 form a closing plate assembly; Actuator is formed by parts such as 1 outer sleeve, 7,1 inner sleeve, 6,1 driving lever roller 9 and 1 springs 17.
Slide rail 10 by the connection modes such as bolt and shell 1 affixed integral, slide rail 10 opening direction is inside.Closing plate assembly is connected with slide rail 10 by ball 16, and ball 16 can roll along groove in slide rail 10.The inner sleeve 6 of actuator connects closing plate 2 by revolute pair, and outer sleeve 7 is by revolute pair connected with outer casing 1.
Before ground mounting hung rack 14, manually closing plate 2 is opened, open mode as shown in Figure 1, Figure 2 and Figure 3, now in actuator outer sleeve 7 and inner sleeve 6 thrust under, the trend that each oriented both sides of closing plate 2 are opened, but under the position-limiting action of shell 1, closing plate 2 can not outwards be opened, and sealing cover is locked in open mode always.
During mounting hung rack, hanger column 15 is from bottom to top inserted by the hexagonal hole in the middle of shell 1.When hanger column 15 is inserted into certain position, shifting block 13 contacts with driving lever roller 9 respectively, and promotes driving lever roller 9 and move laterally.Driving lever roller 9 drives actuator to turn to the inside around respective outer sleeve bearing pin 8 simultaneously, until limited roller 12 contacts with hanger column 15, as shown in Figure 4.Now under the effect of actuator thrust, closing plate 2 respectively has the trend of closing to the inside, but under the position-limiting action of hanger column 15, closing plate 2 can not be closed, then sealing cover is locked in pre-shutdown state, as shown in Figure 4.In flight course, under the position-limiting action of shifting block 13, closing plate 2 can not come back to open mode as shown in Figure 3.
Hanger 14 and throw in after, hanger column 15 leaves aircraft together with hanger 14.Due to the position-limiting action without hanger column 15, under the effect of actuator thrust, closing plate 2 is inwardly closed, until it moves to midway location, under the effect of slide rail limiting stopper, two pieces of closing plates 2 are locked in tram, as shown in Figure 5.
Shell 1 forms for overall processing, and its global shape is inverted short hexagonal pyramid shape housing, and opening upwards, as shown in Figure 6.The outer rim of one fixed width is had, for being connected with wing outside upper base.Centre bit of going to the bottom is equipped with hexagonal opening, for mounting hung rack column 15.Hexagonal each limit is parallel with major side such as aircraft wing front and rear edges, to drop to minimum by it to the adverse effect of aircraft Stealth Fighter.Fillet process is done to the corner angle of shell 1, makes outer surface of outer cover smooth, protruding mild, so that it is dropped to minimum to the adverse effect of aircraft aerodynamic performance.
In y-direction, the both sides of shell 1 inside bottom are respectively provided with a small boss, for limiting the open position of closing plate.In the x direction, the inner both sides of shell 1 are respectively arranged with 3 boss, and boss is provided with bolt hole, for installing the parts such as slide rail 10 and actuator.In y-direction, middle boss respectively there are two bolts hole, for slide rail 10 being secured to shell by bolt.In y-direction, the boss of both sides respectively there is a bolt hole, for connecting sliding rail 10 and actuator.In y-direction, the bolt hole position in y-direction of both sides will ensure: to open and under the state also not having mounting hung rack 14, the position of actuator outer sleeve bearing pin 8 axis is in the inner side of inner sleeve bearing pin 5 axis in y-direction at closing plate 2; Under the state of mounting hung rack 14, the position of actuator outer sleeve bearing pin 8 axis is in the outside of inner sleeve bearing pin 5 axis in y-direction.
Slide rail 10 forms for overall processing, and its cross-sectional plane is " C " font, as shown in Figure 8.Ball 16 within it rolls along groove.The midway location limited location block of slide rail groove, for arriving correct off position by spacing for closing plate 2.There are three auricles at the back side of slide rail groove, and auricle has bolt hole respectively, for being secured to shell 1.The auricle of both sides there is boss, actuator can not be produced with slide rail 10 in motion process and interfere.After having assembled, necessary locking process is done to the tie bolt of slide rail 10.
A closing plate assembly is formed, as shown in Figure 9 by 1 closing plate, 2,2 ballframe carriage, 3,4 balls, 16,1 limited roller support 4 and 2 inner sleeve bearing pins 5.For matching with the hexagonal apertures on shell 1, closing plate 2 aspect is isosceles trapezoid.
In hanger 14 launch process, hanger column 15 moves downward, and destroys closing plate 2 for avoiding hanger pillar 15 directly to contact with closing plate 2, and a limited roller 12 installed by limited roller support 4, limited roller 12 protrudes from the edge of closing plate 2, as shown in Figure 9.Move downward in process at hanger column 15, limited roller 12 is at hanger column 15 surface scrolls, and closing plate 2 does not but directly contact with hanger column 15.For the limited roller 12 avoiding closing plate 2 to close on latter two closing plate is interfered mutually, two limited rollers 12 are alternately arranged, as shown in Figure 10.
Limited roller support 4 plays the effect of actuator joint simultaneously, has two bolts hole above it, for connecting inner sleeve 6 by inner sleeve bearing pin 5, as shown in Figure 10.Inner sleeve 6, inner sleeve bearing pin 5 form a revolute pair with limited roller support 4, and actuator can rotate around the axis of inner sleeve bearing pin 5.
Together with ballframe carriage 3 is secured to closing plate 2.The outer rim of ballframe carriage 3 is provided with two ball grooves, for installing ball 16, as shown in Figure 9.Trench inner diameter is slightly larger than the thickness of ballframe carriage 3, and the degree of depth is slightly less than ball diameter.After ball 16 is installed, on the upside of ballframe carriage 3, downside and direction, three, outside, ball 16 all protrudes from groove, so that slide rail 10 matches, as shown in figures 9 and 11.Thus, ballframe carriage 3 does not directly contact with slide rail 10, connects between ballframe carriage 3 and slide rail 10 by means of only ball 16.Under the effect of contraction of 4 balls 16 and slide rail 10, closing plate 2 only has one degree of freedom, namely can only do straight-line motion along the groove of slide rail 10, avoiding problems the contact of closing plate 2 and miscellaneous part, friction and wear.In ball 16 and the lubrication doing necessity between ballframe carriage 3 and slide rail 10, make the sealing cover life-span longer, reliability is higher.
For matching with the limiting stopper on slide rail 10, ballframe carriage 3 is positioned at inside the edge on closing plate 2 base, and forms a step with closing plate 2, as shown in Figure 9.Ballframe carriage 3 edge shape matches with the limiting stopper of slide rail 10.
Actuator is formed, as shown in figure 12 by parts such as 1 outer sleeve, 7,1 inner sleeve, 6,1 driving lever roller 9 and 1 springs 17.Actuator is pressure type.Inner sleeve 6 is hollow structure, to ensure the drift of enough springs 17, makes actuator have enough effective compression strokes.Spring 17 is in pressured state all the time.The moment of hanger 14 thrown in by aircraft, and may do the motor-driven of larger overload, now the pressure of spring 17 will guarantee the effect overcoming closing plate 2 force of inertia, is normally closed by closing plate 2.In flight course after aircraft jettisoning hanger 14, also may do the motor-driven of larger overload, now the pressure of spring 17 will guarantee the effect overcoming closing plate 2 force of inertia, and closing plate 2 is remained on normal closed position.Outer sleeve 7 side is provided with driving lever, and driving lever end is provided with a driving lever roller 9.
Outer sleeve bearing pin 8 and shell 1, slide rail 10 and outer sleeve 7 connection mode are as shown in figure 13.Outer sleeve bearing pin 8 is terraced structure.Step on the downside of it is half thread structure, and threaded portion is used for being connected with shell 1.The shaft shoulder for slide rail 10 being pressed on the boss of shell 1, as shown in figure 13.Without screw thread on the step of upside, form a revolute pair with outer sleeve 7, outer sleeve 7 can rotate around the axis of outer sleeve bearing pin 8.
Last it is noted that above embodiment is only in order to illustrate technical scheme of the present invention, be not intended to limit; Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art should be appreciated that it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (3)
1. the mechanism type sealing cover of an aircraft store mounting point opening, it is characterized in that it comprises the shell (1) be connected with wing, this shell (1) entirety is hexagonal structure, in the middle part of it inwardly one time punching molded go out hexagonal groove, the middle part of this groove stamps out hexagonal leghole, the hanger column (15) coordinated with its grafting is provided with in this leghole, the other end of this hanger column (15) is fixed on hanger (14), described leghole both sides mirror image is provided with slide rail (10), the middle part of this slide rail (10) extends outward boss, this boss is fixed on the inner side of shell (1) by slide rail bolt (11), the both sides of described boss extend outward permanent seat respectively, this permanent seat is provided with outer sleeve (7), this outer sleeve (7) is by outer sleeve bearing pin (8) and permanent seat normal-running fit, described outer sleeve (7) is overall is provided with the hollow tubular structure of opening for the other end, the inner sleeve (6) coordinated with its gap grafting is provided with inside it, spring (17) is provided with between described outer sleeve (7) and inner sleeve (6), the other end of described inner sleeve (6) is by inner sleeve cylinder pin (5) and limited roller support (4) normal-running fit, described limited roller support (4) is arranged on closing plate (2), sealing plate (2) is arranged between two slide rails (10), and be positioned at the both sides of leghole, the both sides of described closing plate (2) are provided with ballframe carriage (3), the inner side of described slide rail (10) offers the guide groove with ballframe carriage (3) bearing fit, driving lever is extended respectively to interior mirror image in the side of described outer sleeve (7), the other end of this driving lever is provided with the driving lever roller (9) with its normal-running fit.
2. the mechanism type sealing cover of a kind of aircraft store mounting point opening according to claim 1, is characterized in that the side that described ballframe carriage (3) is inserted into side in guide groove is provided with and the ball of its normal-running fit (16).
3. the mechanism type sealing cover of a kind of aircraft store mounting point opening according to claim 1, it is characterized in that the middle part of described limited roller support (4) inwardly mills out groove, be provided with in this groove and the limited roller of its normal-running fit (12), two corresponding limited rollers (12) are setting of mutually staggering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410279843.XA CN104044726B (en) | 2014-06-23 | 2014-06-23 | A kind of mechanism type sealing cover of aircraft store mounting point opening |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410279843.XA CN104044726B (en) | 2014-06-23 | 2014-06-23 | A kind of mechanism type sealing cover of aircraft store mounting point opening |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104044726A CN104044726A (en) | 2014-09-17 |
| CN104044726B true CN104044726B (en) | 2016-03-09 |
Family
ID=51498212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410279843.XA Active CN104044726B (en) | 2014-06-23 | 2014-06-23 | A kind of mechanism type sealing cover of aircraft store mounting point opening |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104044726B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109663B (en) * | 2015-09-04 | 2017-06-16 | 西北工业大学 | A kind of motor-driven aircraft store mounting point sealing mechanism |
| CN105109664B (en) * | 2015-09-04 | 2017-08-08 | 西北工业大学 | A kind of motor-driven aircraft store mounting point sealing mechanism |
| CN105109662B (en) * | 2015-09-04 | 2017-05-31 | 西北工业大学 | A kind of spring driven aircraft store mounting point sealing mechanism |
| CN105644768B (en) * | 2015-12-30 | 2018-07-20 | 西北工业大学 | A kind of aircraft store mounting point opening obturages lid |
| CN108058805A (en) * | 2017-11-16 | 2018-05-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome of fighter safeguards hatch door |
| CN108674629B (en) * | 2018-05-22 | 2021-10-12 | 西北工业大学 | Mechanism type sealing opening cover of aircraft external hanging point |
| CN110816838A (en) * | 2019-09-12 | 2020-02-21 | 中航光电科技股份有限公司 | Novel automatic separation system for hanger interfaces |
-
2014
- 2014-06-23 CN CN201410279843.XA patent/CN104044726B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104044726A (en) | 2014-09-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104044726B (en) | A kind of mechanism type sealing cover of aircraft store mounting point opening | |
| KR102536081B1 (en) | Two-way vent valves, batteries and electrical devices | |
| CN104787309B (en) | Rotor wing unmanned aerial vehicle undercarriage | |
| CN104089547A (en) | Unfolding and locking device for foldable rudder face | |
| CN203753393U (en) | Double-door release device of unmanned aerial vehicle | |
| US10655381B2 (en) | Locking device and opening and closing mechanism having the same | |
| US9481469B2 (en) | Valve for controlling the internal pressure in a cabin of an aircraft | |
| CN102425591B (en) | Quick release lock with spring device | |
| CN204433058U (en) | The full landform in low latitude collapsible scouting operation one unmanned plane | |
| CN105217012A (en) | Comprise the aircraft being furnished with internal security hatch of pressure-regulating device | |
| JP2014108781A (en) | Retractable equipment system including device optimized for driving protection flaps | |
| CN103057500A (en) | Front grille with charging covering cap | |
| CN104015935A (en) | Airframe supporting platform | |
| WO2019153922A1 (en) | Collector shoe, rail vehicle having same and rail transit system | |
| CN112124630B (en) | Cube star connection and separation device and connection and separation method thereof | |
| CN202381459U (en) | Quick-disassembly lock with spring device | |
| CN211259746U (en) | Pressure-reducing type electric explosion valve | |
| WO2019154068A1 (en) | Charging device for rail vehicle and rail transit system | |
| CN206569278U (en) | A kind of unmanned aerial vehicle onboard disassembly and assembly structure and unmanned plane | |
| CN202491806U (en) | Automatic connector/disconnector for braking wind pipe of railway vehicle | |
| US20140353443A1 (en) | Load Bearing Structure for a Large-scale Vehicle | |
| WO2019154070A1 (en) | Charging control method and charging control system of rail transit vehicle | |
| WO2019154166A1 (en) | Blade contact charger, blade contact charger assembly, and rail transit system | |
| WO2019154069A1 (en) | Charging device for rail vehicle and rail transport system | |
| CN105644768A (en) | Sealing covering cap for opening of outer hanging point of plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |