CN111380423B - Eccentric hoop structure and installation mode thereof - Google Patents
Eccentric hoop structure and installation mode thereof Download PDFInfo
- Publication number
- CN111380423B CN111380423B CN202010207953.0A CN202010207953A CN111380423B CN 111380423 B CN111380423 B CN 111380423B CN 202010207953 A CN202010207953 A CN 202010207953A CN 111380423 B CN111380423 B CN 111380423B
- Authority
- CN
- China
- Prior art keywords
- warhead
- hoop
- cabin body
- eccentric
- eccentric hoop
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an eccentric hoop structure and an installation mode thereof, wherein a structural part can arrange a warhead in a cabin body by utilizing the eccentric hoop structure, and the eccentric hoop structure is connected with the cabin body through a connecting piece; the shape structure of the warhead is matched with the eccentric hoop structure, so that the warhead can be arranged at a designated position in the cabin body through the eccentric hoop structure; under the action of the eccentric hoop structure, the axis of the warhead arranged in the cabin body is not coincident with the axis of the cabin body. The invention provides an eccentric hoop structure, which enables a warhead to be eccentrically arranged in a cabin body and leaves a space for installing large-size equipment on a missile. Due to the adoption of the eccentric hoop structure, the warhead is eccentrically arranged in the cabin, the gravity center of the missile is not on the axis of the missile, the missile can be restrained from rolling in the flying process, and the flying stability is improved.
Description
Technical Field
The invention relates to the field of tactical missile structure design, in particular to an eccentric hoop structure and an installation mode thereof, and particularly relates to a device and a method for fixedly installing a warhead in a cabin with limited space by adopting the eccentric front and rear hoop structures.
Background
At present, the warhead at home and abroad mostly adopts a structural mode that the warhead and the cabin body are concentrically arranged.
Patent document CN104567561B discloses a special-shaped missile cabin section connecting structure suitable for a split missile cover. The connecting structure comprises a guiding cabin metal shell, a fighting cabin metal shell and a cabin body adapter ring, wherein the cabin body adapter ring is of a stepped cylindrical structure and is fixedly connected with the guiding cabin metal shell through a threaded structure, and the left side cylinder wall of the cabin body adapter ring is fixedly connected with the guiding cabin metal shell through an anti-loosening pin; the warhead cabin metal casing matches with the end face of the guide cabin metal casing, the inner wall of the warhead cabin metal casing matches with the right side cylinder wall of the cabin body adapter ring, and the warhead cabin metal casing is fixedly connected with the cabin body adapter ring through the connecting pin.
With the increasing demand for missile destruction capability, the volume of the warhead is increased. The space between the warhead and the cabin is reduced. Meanwhile, as modern battlefield environments are increasingly complex, more electronic equipment needs to be installed in the cabin, so that more cabin space is needed. To solve the contradiction, the warhead can only be eccentrically installed in the cabin, the internal space structure of the warhead is optimized, and the side with large space can be provided with the popup device with larger volume.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an eccentric hoop structure and an installation mode thereof.
According to the eccentric hoop structure provided by the invention, the warhead can be arranged in the cabin body by utilizing the eccentric hoop structure, and the eccentric hoop structure is connected with the cabin body through a connecting piece; the shape structure of the warhead is matched with the eccentric hoop structure, so that the warhead can be arranged at a designated position in the cabin body through the eccentric hoop structure;
under the action of the eccentric hoop structure, the axis of the warhead arranged in the cabin body is not coincident with the axis of the cabin body.
Preferably, the eccentric hoop structure comprises a front hoop and a rear hoop; the front anchor ear and the rear anchor ear are both of annular structures;
for the front hoop, a thread structure is arranged on the inner contour of the annular structure, and the shape of the inner contour is matched with the shape of the warhead in the direction;
and the warhead is provided with threads matched with the thread structure on the inner contour of the front hoop.
Preferably, the eccentric hoop structure is an annular structure, and the geometric center of the outer contour of the annular structure is not coincident with the geometric center of the inner contour.
Preferably, the side of the axis of the cabin body far away from the axis of the warhead is provided with a designated pop-up device.
Preferably, the section of the eccentric hoop structure is an I-shaped structure.
Preferably, the eccentric hoop structure is provided with lightening holes.
Preferably, the inner and outer profiles are both circular structures.
Preferably, the arrangement position of the front hoop relative to the warhead is matched with the position of the mass center of the warhead, so that the front hoop can limit the bending moment and the shearing force generated in the flying process of the warhead.
Preferably, 2 hoisting spokes are arranged on the front hoop; the center of mass of the combined warhead and the front hoop is positioned on the connecting line of the 2 hoisting spokes.
The invention discloses an installation method of an eccentric hoop structure, which comprises the following steps:
the installation step of the front hoop: firstly, erecting the warhead on a platform vertically, and then screwing the front hoop on the external thread of the warhead;
a rear hoop mounting step: the rear anchor ear is pushed into the cabin body, and the cabin body and the rear anchor ear are fixed into a whole by adopting a connecting piece;
hoisting: the hanging belt is adopted to penetrate through the hoisting spokes, and the center of mass after the warhead and the front hoop are fixed is hoisted right after the connecting line of the two hoisting spokes passes through;
mounting and fixing: the warhead is vertically hoisted and slowly placed in the cabin body, and after the rear end surface of the warhead contacts the mounting surface of the rear anchor ear, the circumferential position of the warhead is finely adjusted; after the adjustment is in place, the connecting piece is used for axially connecting the rear hoop and the warhead, and then the connecting piece is used for radially connecting the cabin body and the front hoop.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention aims to solve the problems that the internal space is insufficient after the missile warhead is installed and the equipment is difficult to install.
2. The invention provides an eccentric hoop structure, which enables a warhead to be eccentrically arranged in a cabin body and leaves a space for installing large-size equipment on a bullet.
3. The invention adopts the eccentric hoop structure, so that the warhead is eccentrically arranged in the capsule, the gravity center of the missile is not on the axis of the missile, the missile can be inhibited from rolling in the flying process, and the flying stability is improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic view of a warhead structure of an eccentric hoop structure provided by the present invention;
FIG. 2 is a schematic view of a front hoop structure of the eccentric hoop structure provided in the present invention;
FIG. 3 is a schematic view of a rear hoop structure of the eccentric hoop structure provided in the present invention;
FIG. 4 is a schematic view of the connection between the warhead and the front hoop of the eccentric hoop structure of the present invention;
FIG. 5 is a schematic view of the connection between the cabin and the rear hoop of the eccentric hoop structure according to the present invention;
FIG. 6 is a schematic top view of the vertical hoisting of the front hoop and the warhead of the eccentric hoop structure provided in the present invention;
fig. 7 is a schematic view of the warhead of the eccentric hoop structure provided by the invention after being installed in place.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will aid those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any manner. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
According to the eccentric hoop structure provided by the invention, the warhead can be arranged in the cabin body by utilizing the eccentric hoop structure, and the eccentric hoop structure is connected with the cabin body through a connecting piece; the shape structure of the warhead is matched with the eccentric hoop structure, so that the warhead can be arranged at a designated position in the cabin body through the eccentric hoop structure; under the action of the eccentric hoop structure, the axis of the warhead arranged in the cabin body is not coincident with the axis of the cabin body. The eccentric hoop structure comprises a front hoop and a rear hoop; the front hoop and the rear hoop are both of annular structures; for the front hoop, a thread structure is arranged on the inner contour of the annular structure, and the shape of the inner contour is matched with the shape of the warhead in the direction; and the warhead is provided with threads matched with the thread structures on the inner profile of the front hoop. The eccentric hoop structure is an annular structure, and the geometric center of the outer contour of the annular structure is not coincident with the geometric center of the inner contour. And one side of the axis of the cabin body, which is far away from the axis of the warhead, is provided with appointed equipment for popping up. The cross section of the eccentric hoop structure is of an I-shaped structure. The eccentric hoop structure is provided with lightening holes. The inner contour and the outer contour are both circular structures. The front hoop is matched with the center of mass of the warhead relative to the position where the warhead is arranged, so that the front hoop can limit the bending moment and the shearing force generated in the flying process of the warhead. 2 hoisting spokes are arranged on the front hoop; the center of mass of the combined warhead and the front hoop is positioned on the connecting line of the 2 hoisting spokes.
The invention discloses an installation method of an eccentric hoop structure, which comprises the following steps:
the installation step of the front hoop: erecting the warhead on the platform vertically, and screwing the front hoop on the external thread of the warhead;
a rear hoop mounting step: the rear anchor ear is pushed into the cabin body, and the cabin body and the rear anchor ear are fixed into a whole by adopting a connecting piece;
hoisting: hanging straps are adopted to penetrate through the hoisting spokes, and the center of mass of the fixed warhead and the front hoop is hoisted right after passing through the connecting line of the two hoisting spokes;
mounting and fixing: the warhead is vertically hoisted and slowly placed in the cabin body, and after the rear end surface of the warhead contacts the mounting surface of the rear anchor ear, the circumferential position of the warhead is finely adjusted; after the adjustment is in place, the connecting piece is used for axially connecting the rear hoop and the warhead, and then the connecting piece is used for radially connecting the cabin body and the front hoop.
Specifically, the invention provides a warhead eccentric hoop structure and a mounting mode. The eccentric hoop structure is composed of a front hoop and a rear hoop, and the large-mass warhead is installed in the cabin body through the eccentric hoop structure. The front hoop is connected with the front end of the warhead through large-caliber threads and is radially connected with the cabin body through two rows of screws. The rear anchor ear is axially connected with the rear end face of the warhead part through screws and is radially connected with the cabin body through a single row of screws. The invention adopts the eccentric hoop structure, so that the warhead is eccentrically arranged in the cabin, the internal space of the warhead is optimized, and the side with large space can be provided with the spring equipment with larger volume; meanwhile, the missile gravity center is not on the missile axis due to the eccentric installation of the warhead, the missile can be restrained from rolling in the flying process, and the flying stability is improved.
More specifically, the technical solution of the preferred embodiment of the present invention is as follows:
an eccentric staple bolt structure of warhead and mounting means: the front hoop and the rear hoop adopt the design that the outer ring and the inner ring are not concentric, so that the axis of the warhead and the axis of the cabin body can generate an eccentric amount. The front anchor ear is connected with the front end of the warhead through large-caliber threads and is connected with the cabin body through radial screws; the rear anchor ear is connected with the rear end face of the warhead part through an axial screw and is connected with the cabin body through a radial screw. The warhead is eccentrically arranged in the cabin, so that the internal space of the warhead is optimized, and the side with large space can be provided with the popup equipment with larger volume; meanwhile, the missile gravity center is not on the missile axis due to the eccentric installation of the warhead, the missile can be restrained from rolling in the flying process, and the flying stability is improved.
The front hoop and the rear hoop are arranged eccentrically, so that the warhead is eccentrically arranged in the cabin body.
The warhead is eccentrically installed, the space in the cabin is optimized, and the side with large space can be provided with the popup equipment with larger volume, so that the reasonable layout of the popup equipment is facilitated;
due to the fact that the warhead is eccentrically installed, the rotational inertia of the missile rotating around the missile axis is increased, and disturbance suppression of the rolling of the missile body is facilitated;
the warhead is connected by adopting a front large thread, and the warhead is restrained by adopting a rear axial screw structure, so that the reliable connection of the warhead in an airborne environment can be met;
the front hoop is fixed near the center of mass of the warhead and is mainly used for bearing bending moment and shearing force generated by the warhead in the flight process;
the rear hoop is mainly used for restraining the axial movement of the warhead and bearing the axial force borne by the warhead in the flight process;
the center of mass of the fit body of the warhead and the front hoop is located on the connecting line of the two hoisting spokes, so that the warhead can be perpendicular to the platform in the hoisting process, and the warhead can be conveniently butted with the cabin body.
Further, the eccentric hoop structure provided by the invention is realized by the following technical scheme: the front hoop and the rear hoop adopt the design that the outer ring and the inner ring are not concentric, so that the axis of the warhead and the axis of the cabin body can generate an eccentric amount. The front anchor ear is connected with the front end of the warhead through large-caliber threads and is connected with the cabin body through radial screws; the rear anchor ear is connected with the rear end face of the warhead part through an axial screw and connected with the cabin body through a radial screw. At this time, the eccentric installation of the warhead in the cabin body is completed.
The structure of the warhead is shown in figure 1; the front end of the warhead is close to the center of mass, and is provided with a circle of large threads, the number of the threads is 30, and the threads are used for being connected with a front hoop; the rear end face is provided with 8 threaded holes for being connected with a rear hoop.
The front hoop structure is shown in figure 2, the outer circle is matched with the interface on the cabin body, the inner circle is connected with the interface at the front end of the fighting part, and the front hoop structure plays a main bearing role for the fighting part. The inner circle and the outer circle of the front hoop adopt a non-concentric design, so that the warhead is eccentrically fixed in the cabin body; in order to reduce the weight of the front anchor ear, an I-shaped section is adopted, and lightening holes are additionally formed; in the threaded connection part, in order to increase the connection strength, local thickening and reinforcing treatment is carried out on the threaded connection part; considering that the connection strength of the single-row screws is not enough, two rows of mounting holes are designed on the front hoop, and meanwhile, the holes of each row are arranged in a staggered mode.
The structure of the rear anchor ear is shown in figure 3, the outer circle is matched with the interface on the cabin body, 8 bosses on the inner circle are matched with the rear end interface of the fighting part, the unthreaded holes on the bosses are used for penetrating screws, and the rear anchor ear is mainly used for restraining the axial movement of the fighting part and bearing the axial force borne by the fighting part in the flight process.
The connection form of the warhead and the front hoop is shown in fig. 4, the warhead is erected on the platform, and then the front hoop is screwed on the external thread of the warhead.
The connection form of the cabin body and the rear anchor ear is shown in fig. 5, the rear anchor ear is pushed into the cabin body, and the cabin body and the rear anchor ear are fixed into a whole by a row of screws. Because back staple bolt has the directionality, need pay attention to its phase place during the installation.
The vertical hoisting top view of the front hoop and the warhead is shown in fig. 6, the hanging straps are arranged on the hoisting spokes shown in fig. 6 in a penetrating manner, the center of mass of the fixed warhead and the front hoop is just connected with the connecting line of the two spokes by hoisting, and thus the warhead can be hoisted, and the warhead can be ensured to be a vertical table top and is convenient to be butted with a cabin body.
The warhead is installed in place as shown in fig. 7, the warhead is vertically hoisted and slowly placed in the cabin, and after the rear end surface of the warhead contacts the rear hoop installation surface, the circumferential position of the warhead is finely adjusted. After the adjustment is in place, the screws are axially connected with the rear anchor ear and the warhead, and the screws are radially connected with the cabin body and the front anchor ear in two rows.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (6)
1. An eccentric hoop structure is characterized in that a warhead can be arranged in a cabin body by utilizing the eccentric hoop structure, and the eccentric hoop structure is connected with the cabin body through a connecting piece; the shape structure of the warhead is matched with the eccentric hoop structure, so that the warhead can be arranged at a designated position in the cabin body through the eccentric hoop structure;
under the action of the eccentric hoop structure, the axis of a warhead arranged in the cabin body is not coincident with the axis of the cabin body;
the eccentric hoop structure comprises a front hoop and a rear hoop; the front hoop and the rear hoop are both of annular structures;
the geometric center of the outer contour of the annular structure is not coincident with the geometric center of the inner contour;
for the front hoop, a thread structure is arranged on the inner contour of the annular structure, and the shape of the inner contour is matched with the shape of the warhead;
the warhead is provided with threads matched with the thread structure on the inner profile of the front hoop;
the arrangement position of the front hoop relative to the warhead is matched with the mass center position of the warhead, so that the front hoop can limit the bending moment and the shearing force generated in the flight process of the warhead;
2 hoisting spokes are arranged on the front hoop; the center of mass of the combined warhead and the front hoop is positioned on the connecting line of the 2 hoisting spokes;
the rear anchor ear is connected with the rear end face of the warhead part through an axial screw and is connected with the cabin body through a radial screw.
2. The eccentric hoop structure of claim 1, wherein the side of the axis of the cabin body away from the axis of the warhead is provided with designated pop-up equipment.
3. The eccentric hoop structure of claim 1, wherein the cross section of the eccentric hoop structure is an I-shaped structure.
4. The eccentric hoop structure of claim 1, wherein the eccentric hoop structure is provided with lightening holes.
5. The eccentric hoop structure of claim 1, wherein the inner and outer contours are both circular structures.
6. An eccentric hooping structure mounting method according to any one of claims 1-5, comprising the steps of:
the installation step of the front hoop: erecting the warhead on the platform vertically, and screwing the front hoop on the external thread of the warhead;
a rear hoop mounting step: the rear anchor ear is pushed into the cabin body, and the cabin body and the rear anchor ear are fixed into a whole by adopting a connecting piece;
hoisting: hanging straps are adopted to penetrate through the hoisting spokes, and the center of mass of the fixed warhead and the front hoop is hoisted right after passing through the connecting line of the two hoisting spokes;
installing and fixing: the warhead is vertically hoisted and slowly placed in the cabin, and after the rear end surface of the warhead contacts the rear hoop mounting surface, the circumferential position of the warhead is finely adjusted; after the adjustment is in place, the connecting piece is used for axially connecting the rear hoop and the warhead, and then the connecting piece is used for radially connecting the cabin body and the front hoop.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010207953.0A CN111380423B (en) | 2020-03-23 | 2020-03-23 | Eccentric hoop structure and installation mode thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010207953.0A CN111380423B (en) | 2020-03-23 | 2020-03-23 | Eccentric hoop structure and installation mode thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111380423A CN111380423A (en) | 2020-07-07 |
| CN111380423B true CN111380423B (en) | 2022-09-13 |
Family
ID=71221678
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010207953.0A Active CN111380423B (en) | 2020-03-23 | 2020-03-23 | Eccentric hoop structure and installation mode thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111380423B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114061379B (en) * | 2021-11-16 | 2023-07-14 | 天津爱思达新材料科技有限公司 | Front cabin T-shaped frame reinforcing structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2540903C1 (en) * | 2013-10-29 | 2015-02-10 | Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Guided missile |
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| CN105115367A (en) * | 2015-08-04 | 2015-12-02 | 北京航天长征飞行器研究所 | Partition plate type warhead cabin capable of carrying recovery storage devices |
| CN105466288A (en) * | 2015-11-20 | 2016-04-06 | 江西长江化工有限责任公司 | Cabin of conical rotary body structure and manufacturing method of cabin |
| CN205940308U (en) * | 2016-07-18 | 2017-02-08 | 中国人民解放军总参谋部工程兵科研三所 | A prefabricated angle of attack device for high -speed penetration test of body |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9010009B2 (en) * | 2010-11-01 | 2015-04-21 | The Otis Patent Trust | Eccentric rail nut and eccentric rail mounting system |
| CN110451399B (en) * | 2019-08-08 | 2020-07-17 | 西安近代化学研究所 | Large-diameter warhead hanging device |
-
2020
- 2020-03-23 CN CN202010207953.0A patent/CN111380423B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| RU2540903C1 (en) * | 2013-10-29 | 2015-02-10 | Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Guided missile |
| CN105115367A (en) * | 2015-08-04 | 2015-12-02 | 北京航天长征飞行器研究所 | Partition plate type warhead cabin capable of carrying recovery storage devices |
| CN105466288A (en) * | 2015-11-20 | 2016-04-06 | 江西长江化工有限责任公司 | Cabin of conical rotary body structure and manufacturing method of cabin |
| CN205940308U (en) * | 2016-07-18 | 2017-02-08 | 中国人民解放军总参谋部工程兵科研三所 | A prefabricated angle of attack device for high -speed penetration test of body |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111380423A (en) | 2020-07-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111380423B (en) | Eccentric hoop structure and installation mode thereof | |
| CN103673786B (en) | Impact reducing tail-section linear explosion separating device for small-diameter assisted takeoff rocket | |
| CN104567561A (en) | Special-shape missile bay section connecting structure for sectional fairing deploying | |
| CN206329586U (en) | A kind of band bushing pyramidal structure interference fit connector | |
| CN103527608B (en) | Bolt anti-rotation device and the installation method of bolt pair | |
| CN203127144U (en) | Quick mounting structure of rotor wing of unmanned aerial vehicle and unmanned aerial vehicle | |
| CN207740558U (en) | A kind of pipeline road fixing hoop | |
| CN104457447A (en) | Device for accelerating separation of head and body of aircraft | |
| CN209445883U (en) | A kind of gun barrel detection device | |
| CN107191745B (en) | A kind of generating set installation pedestal protection mechanism | |
| CN207470585U (en) | pneumatic self-unlocking separation nut and spacecraft | |
| CN208265037U (en) | A kind of oil storage tank convenient for transporting safely | |
| CN207976064U (en) | Detachable fuse structure | |
| CN206494633U (en) | A kind of attachment structure of escalator handrail | |
| CN107588061B (en) | A kind of locking-adjustable power quick-locking device | |
| CN206595831U (en) | Motor and the compressor with it | |
| CN217440214U (en) | Transitional connecting mechanism for tower of wind driven generator | |
| CN117781784A (en) | Fuze room for penetration warhead | |
| CN106184827B (en) | The active-passive integrated whole star isolation mounting of formula | |
| CN105115367B (en) | Partition plate type warhead cabin capable of carrying recovery storage devices | |
| CN218329570U (en) | Instrument cabin structure made of composite material | |
| CN212296468U (en) | Centralized control on-duty automatic flameproof robot system | |
| CN112081803B (en) | Device for improving coaxiality based on laser range finder | |
| CN212509148U (en) | Stud convenient for mounting and dismounting parts | |
| CN220745381U (en) | Fastening assembly for oil supply tank and oil supply system of gas station |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |