CN103818557B - Aircraft safety seat - Google Patents
Aircraft safety seat Download PDFInfo
- Publication number
- CN103818557B CN103818557B CN201410079297.5A CN201410079297A CN103818557B CN 103818557 B CN103818557 B CN 103818557B CN 201410079297 A CN201410079297 A CN 201410079297A CN 103818557 B CN103818557 B CN 103818557B
- Authority
- CN
- China
- Prior art keywords
- rod
- hydraulic
- piston
- subchannel
- seat
- 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 - Fee Related
Links
Landscapes
- Tires In General (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The present invention relates to a kind of aircraft safety seat; particularly solve the seat of passenger safety; described safety seat is below aircraft seat, arrange a primary-secondary type hydraulic communication device (8); this primary-secondary type hydraulic communication device (8) is made up of hydraulic compartment (7), hydraulic channel, hydraulic piston (5); cylinder shape hydraulic channel is distributed with in hydraulic compartment (7) top; with dissolve fall inertial impact force, stir time produce elastic pulling force; safe elastic restoring force is protected and takes people, ensure the safety taking people.
Description
Technical field
The present invention relates to a kind of aircraft safety seat, particularly solve the seat of passenger safety.
Background technology
At present, the safety control that people taken by aircraft only rests on safety inspection, maintaining before running aircraft and fastens seat belts, although carried out accurate safety inspection, maintaining, aeroplane accident still occurs.After aeroplane accident, the powerful power of falling in high-altitude causes that to take people's rate of surviving very little very little, and the public quails, and the harmony of impact society is stable and hinder the development of the economy.
Summary of the invention
For the problems referred to above, the invention provides a kind of aircraft safety seat, with dissolve fall inertial impact force, stir time produce elastic pulling force, safe elastic restoring force is protected and takes people, ensure to take the safety of people.
For technical solution problem, the technical solution used in the present invention: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is by hydraulic compartment 7, hydraulic channel, hydraulic piston 5 is formed, cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 3-6 subchannel 6 is distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, the high strength elastic rope 2 be connected with seat 1 is had at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10, elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, a round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Further: described elastic telescopicing rod 3 is made up of the 2-5 section body of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, and the open end of the body of rod has bayonet socket, and body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, and the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually.
Further: described primary-secondary type hydraulic communication device 8 bottom is equal with ground, and open end is to seat back sweep 30-60 degree.
Further: under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9.
Further: high strength elastic rope 2 quantity that described each passage is connected is 3-6 bar.
Further: with spring D13 around described support end 14.
Primary-secondary type hydraulic communication device 8 described in aircraft safety seat is for the protection of fuel tanker.
Advantageous Effects: with dissolve fall inertial impact force, stir time produce elastic pulling force, safe elastic restoring force is protected and takes people, ensure to take the safety of people.
Accompanying drawing illustrates:
Fig. 1: longitudinal sectional structure chart of the present invention;
Fig. 2: the structural representation of Elastic expansion link of the present invention;
In figure, 1-seat, 2-high strength elastic rope, 3-elastic telescopicing rod, the 31-heavy caliber body of rod, the small-bore body of rod of 32-, 33-spring C, 40-spring A, 41-spring B, 5-hydraulic piston, 6-subchannel, 7-hydraulic compartment, 8-primary-secondary type hydraulic communication device, the female passage of 9-, 10-piston rod, 11-support face, the circular spheroid of 12-, 13-spring D, 14-support end.
Detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention will be further described, to facilitate the technical staff to understand.
During aircraft normal flight, the elastic telescopicing rod 3 on subchannel 6 is punctured into most short status, jack-up seat, or as holding the pin at seat under safe condition, the high strength elastic rope 2 be connected with seat 1 is had at the Ge Installed in porthole of subchannel 6 and female passage 9, when aeroplane accident, taking under the effect of people's strong impact force, hold the pin fracture at seat, support end 14 under seat 1 promotes support face 11 according to pendant force direction, the hydraulic piston 5 promoted in female passage 9 presses down, elastic telescopicing rod 3 in subchannel 6 stretches upwards, if power generation break-in when stretching, spring A 40 bottom elastic telescopicing rod 3 can follow break-in, after break-in, high strength elastic rope 2 is held, spring A 40 shrinks and keeps not departed from, form overall break-in pulling force, device is reduced.The impact of force of inertia is dissolved by the push-and-pull of piston force.If wrecked aircraft generation rolling type falls, when turning upside down, under the prerequisite of fastening seat belts, under the effect that the spring of the elastic telescopicing rod 3 of high strength elastic rope 2 and subchannel 6 makes expansion link retract in storehouse, elasticity holds seat 1, the hydraulic piston 5 returned at ordinary times in subchannel 6, female passage 9 runs according to the size of power, is in steady status.Do not cause the prerequisite of crushing damage at wrecked aircraft body under, make people can get rid of various huge External force interference in seat, ensure the safety taking people.
Embodiment 1: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is made up of hydraulic compartment 7, hydraulic channel, hydraulic piston 5, and primary-secondary type hydraulic communication device 8 bottom is equal with ground, and open end is to seat back sweep 30 degree; Cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 3 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, have 2 high strength elastic ropes 2 be connected with seat 1 at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10; Elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 2 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually; A round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Embodiment 2: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is made up of hydraulic compartment 7, hydraulic channel, hydraulic piston 5, and primary-secondary type hydraulic communication device 8 bottom is equal with ground, and open end is to seat back sweep 60 degree; Cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 4 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, have 4 high strength elastic ropes 2 be connected with seat 1 at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10; Elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 5 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually; A round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Embodiment 3: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is by hydraulic compartment 7, hydraulic channel, hydraulic piston 5 is formed, primary-secondary type hydraulic communication device 8 bottom is equal with ground, open end is to seat back sweep 40 degree, cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 6 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, 5 high strength elastic ropes 2 be connected with seat 1 are had at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10, elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 3 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually, a round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Embodiment 4: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is made up of hydraulic compartment 7, hydraulic channel, hydraulic piston 5, and primary-secondary type hydraulic communication device 8 bottom is equal with ground, and open end is to seat back sweep 30 degree; Cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 3 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, have 2 high strength elastic ropes 2 be connected with seat 1 at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10; Elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 2 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually; A round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, with spring D13 around support end 14, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Embodiment 5: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is made up of hydraulic compartment 7, hydraulic channel, hydraulic piston 5, and primary-secondary type hydraulic communication device 8 bottom is equal with ground, and open end is to seat back sweep 60 degree; Cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 4 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, have 4 high strength elastic ropes 2 be connected with seat 1 at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10; Elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 5 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually; A round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, with spring D13 around support end 14, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Embodiment 6: aircraft safety seat, a primary-secondary type hydraulic communication device 8 is set below aircraft seat, this primary-secondary type hydraulic communication device 8 is by hydraulic compartment 7, hydraulic channel, hydraulic piston 5 is formed, primary-secondary type hydraulic communication device 8 bottom is equal with ground, open end is to seat back sweep 40 degree, cylinder shape hydraulic channel is distributed with above hydraulic compartment 7, hydraulic channel is divided into female passage 9 and subchannel 6, their open end is all sealed by hydraulic piston 5, female passage 9 is positioned at midway location, 6 subchannels 6 are distributed in the surrounding of female passage 9, the volume of female passage 9 is greater than subchannel 6 volume sum, under normal condition, the liquid level of subchannel 6 is lower than the liquid level of female passage 9, 5 high strength elastic ropes 2 be connected with seat 1 are had at the Ge Installed in porthole of subchannel 6 and female passage 9, the piston end of subchannel 6 is connected with piston push rod 10, elastic telescopicing rod 3 is connected to below seat 1 by spring A 40 and between piston rod 10 end, described elastic telescopicing rod 3 is made up of 3 sections of bodies of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod 32 is inserted in the heavy caliber body of rod 31, the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod 32 plugs freely but mutually can not depart from the heavy caliber body of rod 31, each pole has spring C 33, the combination of bar and bar is connected in the upper end of a bar spring C 33 on hollow part, and the body of rod is combined to form form short and small gradually, a round concave shape support face 11 of caving in upwards is had to be connected by the piston of spring B 41 with passage 9 above the piston being positioned at female passage 9, medium position below seat 1 is equipped with the support end 14 of a back taper, with spring D13 around support end 14, support end 14 end has a circular spheroid 12, circular spheroid 12 withstands in the groove in support face 11, is not connected.
Primary-secondary type hydraulic communication device 8 described in embodiment 1-6 is for the protection of fuel tanker.
The present invention is described by accompanying drawing, without departing from the present invention, various conversion and equivalent replacement can also be carried out to the present invention, therefore, patent of the present invention is not limited to disclosed specific implementation process, and should comprise the whole embodiments fallen within the scope of the claims in the present invention.
Claims (7)
1. aircraft safety seat, it is characterized in that, a primary-secondary type hydraulic communication device (8) is set below aircraft seat, this primary-secondary type hydraulic communication device (8) is by hydraulic compartment (7), hydraulic channel, hydraulic piston (5) is formed, cylinder shape hydraulic channel is distributed with in hydraulic compartment (7) top, hydraulic channel is divided into female passage (9) and subchannel (6), their open end is all sealed by hydraulic piston (5), female passage (9) is positioned at midway location, 3-6 subchannel (6) is distributed in the surrounding of female passage (9), the volume of female passage (9) is greater than subchannel (6) volume sum, the high strength elastic rope (2) be connected with seat (1) is had at the Ge Installed in porthole of subchannel (6) and female passage (9), the piston end of subchannel (6) is connected with piston push rod (10), elastic telescopicing rod (3) is by spring A(40) be connected between below, seat (1) and piston rod (10) end, a round concave shape support face (11) of caving in upwards is had to be connected by the piston of spring B (41) with passage (9) above the piston being positioned at female passage (9), the medium position of below, seat (1) is equipped with the support end (14) of a back taper, support end (14) end has a circular spheroid (12), circular spheroid (12) withstands in the groove of support face (11), is not connected.
2. aircraft safety seat according to claim 1, it is characterized in that, aircraft safety seat according to claim 1, it is characterized in that, described elastic telescopicing rod (3) is made up of the 2-5 section body of rod, the body of rod is cannulated sleeve, body of rod bore reduces gradually, the small-bore body of rod (32) is inserted in the heavy caliber body of rod (31), the open end of the body of rod has bayonet socket, body of rod end has collar, the small-bore body of rod (32) plugs freely but mutually can not depart from the heavy caliber body of rod (31), each pole has spring C(33), the combination of bar and bar is connected in a bar spring C(33 on hollow part) upper end, the body of rod is combined to form form short and small gradually.
3. the aircraft safety seat according to claim 1 or 2 any one, is characterized in that, described primary-secondary type hydraulic communication device (8) bottom is equal with ground, and open end is to seat back sweep 30-60 degree.
4. aircraft safety seat according to claim 3, is characterized in that, under normal condition, the liquid level of subchannel (6) is lower than the liquid level of female passage (9).
5. aircraft safety seat according to claim 4, is characterized in that, high strength elastic rope (2) quantity that each passage is connected is 3-6 bar.
6. aircraft safety seat according to claim 5, is characterized in that, described support end (14) is around with spring D(13).
7. the aircraft safety seat described in claim 1,2,4,5,6 any one, described primary-secondary type hydraulic communication device (8) is for the protection of fuel tanker.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410079297.5A CN103818557B (en) | 2014-03-06 | 2014-03-06 | Aircraft safety seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410079297.5A CN103818557B (en) | 2014-03-06 | 2014-03-06 | Aircraft safety seat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103818557A CN103818557A (en) | 2014-05-28 |
| CN103818557B true CN103818557B (en) | 2015-10-28 |
Family
ID=50753916
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410079297.5A Expired - Fee Related CN103818557B (en) | 2014-03-06 | 2014-03-06 | Aircraft safety seat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103818557B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4819987A (en) * | 1987-11-18 | 1989-04-11 | Weber Aircraft | Aircraft seat leg support release device |
| CN2140880Y (en) * | 1992-12-21 | 1993-08-25 | 于建康 | Seat specially adapted for civil passenger plane |
| CN103153787A (en) * | 2010-11-18 | 2013-06-12 | 赵恒敏 | Seat structure for an airplane |
| CN103223882A (en) * | 2012-01-27 | 2013-07-31 | 贝尔直升机德事隆公司 | Vehicle crewstation seat assembly |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU5527899A (en) * | 1998-08-22 | 2000-03-14 | Zoltan Pal | Seat-operating system |
| KR20100071962A (en) * | 2007-07-16 | 2010-06-29 | 웨버 에어크래프트 엘엘씨 | Vehicle seat assemblies |
-
2014
- 2014-03-06 CN CN201410079297.5A patent/CN103818557B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4819987A (en) * | 1987-11-18 | 1989-04-11 | Weber Aircraft | Aircraft seat leg support release device |
| CN2140880Y (en) * | 1992-12-21 | 1993-08-25 | 于建康 | Seat specially adapted for civil passenger plane |
| CN103153787A (en) * | 2010-11-18 | 2013-06-12 | 赵恒敏 | Seat structure for an airplane |
| CN103223882A (en) * | 2012-01-27 | 2013-07-31 | 贝尔直升机德事隆公司 | Vehicle crewstation seat assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103818557A (en) | 2014-05-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201572458U (en) | Slit small-caliber vertical shaft lifesaving device | |
| CN203408391U (en) | High-place operation buffer | |
| CN103818557B (en) | Aircraft safety seat | |
| CN107351804A (en) | A kind of security against fire fire fighting hammer | |
| CN205198743U (en) | Emergency device falls in high altitude | |
| CN104399207A (en) | Deep well rescue device | |
| CN105501169A (en) | Car window breaker | |
| CN204502171U (en) | A kind of bus breaks window slow descending device | |
| CN207469258U (en) | A kind of excavation of foundation pit escape cage assembly | |
| CN205502134U (en) | Anti -collision fire hydrant | |
| CN205484969U (en) | Steel strand wires protective case | |
| CN203438973U (en) | Security window breaker | |
| CN205013036U (en) | High resistance to compression survival capsule of high strength body | |
| CN103434474A (en) | Safety winder breaker | |
| CN204073176U (en) | A kind of fall arrest mark of safety belt | |
| CN205108791U (en) | Buffering formula high safe lifesaving umbrella of standing | |
| CN206178348U (en) | Needle structure is prevented falling by tower clock core | |
| CN103306615A (en) | Novel safety elevator pin | |
| CN205154239U (en) | Survival capsule with antiknock impact property | |
| CN205382954U (en) | Survival capsule internal separation formula rescue bedstead is rescued perpendicularly in mine | |
| CN204136924U (en) | A kind of escape device for bus | |
| CN104100283B (en) | Mine anchorage cable end apparatus for shaping | |
| CN205591864U (en) | Special fisher of beam -pumping unit polished rod | |
| CN210014903U (en) | Safety pressure test plug device | |
| CN210416525U (en) | Truck tire inflation protection mechanism |
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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 Termination date: 20180306 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |