CN110986674B - A medium-sized solid launch vehicle launch method - Google Patents
A medium-sized solid launch vehicle launch method Download PDFInfo
- Publication number
- CN110986674B CN110986674B CN201911421803.3A CN201911421803A CN110986674B CN 110986674 B CN110986674 B CN 110986674B CN 201911421803 A CN201911421803 A CN 201911421803A CN 110986674 B CN110986674 B CN 110986674B
- Authority
- CN
- China
- Prior art keywords
- rocket
- launch
- medium
- sized solid
- launching
- 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
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Automatic Assembly (AREA)
- Conveying And Assembling Of Building Elements In Situ (AREA)
Abstract
The invention provides a medium-sized solid carrier rocket launching method, which belongs to the technical field of carrier rockets and comprises the following steps: transporting the rocket, and transporting the rocket to a specified position through a flat car; installing a transmitting device, and fixing the transmitting device on a transmitting field; turning over the rocket, fixedly connecting the rocket body of the rocket by using a turning device, and turning over and erecting the rocket body by using a truck crane; hoisting the rocket, and hoisting the rocket to the launching device by adopting a truck crane; the medium-sized solid carrier rocket launching method only needs a flat car to transport the rocket; the overturning device is fixed on the rocket body, the rocket body is overturned and erected through the truck crane, and the rocket is hoisted to the launching device, so that the integrally used tool is simple and reliable in structure and low in cost.
Description
Technical Field
The invention relates to the technical field of carrier rockets, in particular to a medium-sized solid carrier rocket launching method.
Background
Along with the development of economy in China, the demands of the economic parts of various nations and national defense modernization on various application satellites for communication, remote sensing and the like are increasing and urgent. Thus, the launch of medium-sized solid launch vehicles is increasing.
The launching vehicle is used for vertically supporting the rocket, adjusting the perpendicularity of the rocket according to the requirements of a rocket control system, and matching with aiming equipment to finish the aiming of the rocket and certain auxiliary work in the preparation and launching processes of the rocket.
However, the launching vehicle system is complex, high in cost, long in development period and needs to invest a large amount of capital. While requiring a dedicated launch site. The launching vehicle has long recovery period and many maintenance items in the later launching period.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of high cost of the launching vehicle in the prior art, and provide a middle-sized solid carrier rocket launching method.
The invention provides a medium-sized solid carrier rocket launching method, which comprises the following steps:
transporting the rocket, and transporting the rocket to a specified position through a flat car;
installing a transmitting device, and fixing the transmitting device on a transmitting field;
turning over the rocket, fixedly connecting the rocket body by using a turning device, and turning over and erecting the rocket body by using a truck crane;
and hoisting the rocket, namely hoisting the rocket to the launching device by adopting a truck crane.
Preferably, the flat car is provided with a transport bracket.
Preferably, a rubber plate is arranged between the flat car and the transportation bracket.
Preferably, the thickness of the rubber plate is 8-12 mm.
Preferably, the turning device includes:
the end shaft necks are arc-shaped, two end shaft necks are symmetrically arranged at two radial ends of the rocket body to form end shaft neck groups, and the end shaft neck groups are distributed at intervals along the axial direction of the rocket body;
the two connecting plates are symmetrically arranged at two radial ends of the rocket body and are arranged on the end journal group;
and at least two lifting ends of the lifting device are connected to the connecting plate.
Preferably, the turnover device further comprises a clamping device which is connected to the connecting plate and the end journal simultaneously so as to fix the connecting plate and the end journal.
Preferably, the clamping device includes an inner frame detachably disposed on the connecting plate, and a fastening device disposed on the inner frame and used for connecting the end journal.
Preferably, the transmitting device includes:
the foundation steel plate is suitable for being fixedly connected with the ground;
the launching platform is supported on the foundation steel plate through four height-adjustable supporting legs; the center of the launching platform is provided with a through hole;
and the flow guide cone is arranged on the foundation steel plate, and the top end of the flow guide cone faces the through hole of the launching platform.
As a preferred scheme, the levelness of the launching platform is adjusted by adjusting the launching platform through a quadrant instrument for cannons.
Preferably, the rocket is suitable for being fixedly connected with the launching platform through screws.
The technical scheme of the invention has the following advantages:
1. the invention provides a medium-sized solid carrier rocket launching method, which comprises the following steps: the method comprises the following steps: the method comprises the following steps of carrying a rocket, installing a launching device, turning the rocket and hoisting the rocket; in the method, only a flat car is needed to transport the rocket; the overturning device is fixed on the rocket body, the rocket body is overturned and erected through the truck crane, and the rocket is hoisted to the launching device, so that the integrally used tool is simple and reliable in structure and low in cost.
2. According to the method for launching the medium-sized solid carrier rocket, the flat car is provided with the transportation bracket, the structural size of the transportation bracket is designed according to the position of the main beam of the flat car, and the rocket body is convenient to place and fix.
3. According to the method for launching the medium-sized solid carrier rocket, the rubber plate is arranged between the flat car and the transportation bracket, the thickness of the rubber plate is 8-12mm, the friction force between the transportation bracket and the flat car is increased due to the arrangement of the rubber plate, and the rocket body is prevented from moving on the transportation car in the transportation process.
4. The invention provides a medium-sized solid carrier rocket launching method, wherein a turnover device comprises: the end journal, the connecting plate and the hoisting device; the rocket body overturning device disclosed by the invention can realize the overturning of the rocket body only by arranging the end shaft diameters on the rocket body and arranging the connecting plates on the end shaft diameters, hoisting the rocket body at two positions of the connecting plates by the hoisting device and adjusting the hoisting heights of two hoisting points, and is simple in structure and low in cost.
5. The invention provides a medium-sized solid carrier rocket launching method.
6. The invention provides a medium-sized solid carrier rocket launching method, wherein a launching device comprises: the device comprises a foundation steel plate, a launching platform and a diversion cone; the guide cone is used for discharging the gas flow of the flame of the engine in the takeoff stage of the rocket; the foundation steel plate is fixed without depending on a special launching site, and can be rapidly unfolded on a common cement field to launch the medium-sized solid carrier rocket. After the emission, the maintenance is simple and the period is short.
7. According to the method for launching the medium-sized solid carrier rocket, the heights of four supporting legs of a launching platform are adjusted through a quadrant for cannon, and the levelness of the launching platform is adjusted.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view of an installation structure of a launching device and a rocket body of the invention.
Fig. 2 is a schematic structural view of the arrow body overturning device.
Fig. 3 is a top view of the arrow inversion device.
Fig. 4 is a schematic structural diagram of the lifting device.
Fig. 5 is a schematic structural view of an end shaft diameter locking state.
Fig. 6 is a front view of the end shaft diameter.
FIG. 7 is a side view of the end shaft diameter.
Fig. 8 is a schematic view of the structure of the clamping device.
Description of reference numerals:
1. an end journal; 11. a connecting shaft; 12. a connecting member; 13. reinforcing ribs;
2. an arrow body;
3. a connecting plate; 31. an outer frame body; 32. adjusting the bolt; 33. fastening a bolt;
4. a hoisting device; 41. a sling; 42. a cross beam; 43. shackle dismounting;
5. a clamping device; 51. an inner frame body; 52. a fastening device; 521. jacking and pressing the bolt; 522. ejecting the head; 5211. jacking and pressing the screw; 5212. pressing the nut;
6. a launch pad;
7. a flow guide cone;
8. and (4) a foundation steel plate.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
The method for launching the medium-sized solid carrier rocket comprises the following steps,
transporting the rocket, and transporting the rocket to a specified position through a flat car; the flat car is a general flat car; the flat car is provided with a transportation bracket for supporting the rocket body 2, the structural size of the transportation bracket is designed and installed according to the position of a main beam of the flat car, and the fixing stability of the rocket and the flat car in the transportation process is ensured; meanwhile, in order to increase friction force, the rocket body 2 moves on the flat car in the process of placing and transporting, a rubber plate with the thickness of 80-12mm, preferably 10mm, is arranged between the flat car and the transporting bracket, and the stability between the rocket body 2 and the flat car in the process of transporting is guaranteed.
Installing a transmitting device, and fixing a foundation steel plate 8 on the transmitting device on a transmitting field according to the shot-to position as shown in figure 1; supporting the launching platform 6 on the foundation steel plate 8 through supporting legs to finish the adjustment of launching direction, and adjusting four supporting legs of the launching platform 6 by using a cannon quadrant to finish the adjustment of verticality; placing a diversion cone 7 on a foundation steel plate 8, wherein the top end of the diversion cone faces to a through hole in the center of the launching platform 6; the guide cone 7 is used for discharging and guiding the gas flow of the flame of the engine in the takeoff stage of the rocket.
The rocket body 2 can be overturned, the end shaft necks 1 on the overturning device are symmetrically arranged in the radial direction of the rocket body 2, the two end shaft necks 1 symmetrically arranged form an end shaft neck 1 group, the end shaft necks 1 are symmetrically fixed on the connecting plate 3 through the clamping device 5, and the truck crane is lifted at two positions of the connecting plate 3, so that the rocket body 2 can be overturned; the truck crane is a general truck crane for the market; and selecting a proper truck crane according to the lifting weight, the working amplitude and the height of the suspension arm of the rocket.
Hoisting the rocket, hoisting the rocket to the launching device by adopting a truck crane, fixedly connecting the rocket with the launching device through screws, and removing the screws before launching.
Example 2
This example details the turning device in example 1:
as shown in fig. 2-8, the arrow body turning device provided for this embodiment includes end journals 1, at least two end journals 1 are clamped on the outer circumferential surface of the arrow body 2 and are arranged at intervals along the axial direction of the arrow body 2; the connecting plate 3 is arranged along the axial direction of the arrow body 2 and is erected on the end journals 1; and the hoisting device 4 is connected with the connecting plate 3 at least at two hoisting ends.
As shown in fig. 2 and 3, the rocket body turning device in this embodiment turns the rocket body into a full rocket, and the turning requirement is to turn the rocket body horizontally placed into a vertical state to facilitate subsequent launching work, and the turning angle of the rocket body in this embodiment is about 90 °.
Because the whole rocket is overturned, the weight is large, the length of the rocket body is long, in order to better protect the rocket body 2 and the overturning stability, end shaft necks 1 are respectively and symmetrically arranged in the radial direction of the rocket body 2 in the embodiment, two end shaft necks 1 which are symmetrically arranged form an end shaft neck group, and six groups of the end shaft neck groups are arranged in the axial direction of the rocket body 2 in the embodiment.
Of course, in other embodiments, the number of end journals 1 is set according to the load requirements, depending on the object of the inverted arrow body.
In other embodiments, depending on the object of the arrow body to be turned, several end journals 1 may be arranged only on the same radial side of the arrow body 2, in order to save material and reduce the complexity of the construction.
As shown in FIG. 3, the lifting ends in the embodiment are arranged at four positions and are respectively arranged on the end journal groups at the two axial ends of the rocket body 2, so that the rocket lifting by adopting the design has good stability and is convenient for adjusting the turning angle.
As shown in fig. 4, the hoisting device 4 includes a cross beam 42 and slings 41 respectively connected to the upper and lower ends of the cross beam 42, the tail end of the sling 41 at the lower end of the cross beam 42 is connected to the hoisting end, the tail ends of the slings 41 at the upper end of the cross beam 42 are collected at the hoisting end of the external power device, and the cross beam 42 and the sling 41 at the upper end are in a triangular state in a tight hoisting state to provide a better hoisting strength.
It should be noted that the connection structure of the connection part related to the lifting device 4 is a conventional shackle 43 structure, so as to facilitate the detachment of the lifting device 4.
It should be noted that the power plant in this embodiment is a common truss crane, and the two truss cranes respectively act on the hoisting ends of the two sets of hoisting devices 4.
Through the explanation above, it is found that the rocket body turning device in the embodiment only needs to set up a plurality of end shaft necks 1 on the rocket body 2, the end shaft necks 1 are provided with the connecting plate 3, the lifting device 4 lifts at two positions of the connecting plate 3, and the turning of the rocket body can be realized by adjusting the lifting heights of two lifting points.
The specific construction of the end journal 1 and its mounting on the arrow body 2 is shown in fig. 5-7, which will be described in detail below to more clearly illustrate the present solution.
As shown in fig. 5, the fitting installation position of the end journal 1 and the arrow body 2 is configured as an arc surface, and the arc surface is attached to the outer peripheral surface of the arrow body 2 and matched with the outer peripheral surface of the arrow body 2, so that the effective action area of the outer peripheral surface of the arrow body is ensured, and the damage of surface deformation of the arrow body 2 caused by over-concentration of stress is prevented.
Further, the body of the end journal 1 is configured in an arc shape, and the end journal in an arc structure is easier to clamp than in an annular shape, so that the assembly efficiency can be improved.
As shown in fig. 6, in the present embodiment, eight fixing holes are provided on the body of the end journal 1, threaded holes are correspondingly provided on the arrow body 2, and the end journal 1 is locked to the arrow body 2 by bolts.
For the stability of connection, reduce the stress intensity of end journal 1 department, two connecting plates 3 symmetrical arrangement are in the radial both ends of arrow body 2 and set up on the end journal group, connect six end journals 1 of each side into an organic whole, strengthen holistic structural strength.
As shown in fig. 7, a connecting shaft 11 is provided on the outer circumferential surface of the end journal 1 in a protruding manner, and is used to cooperate with a clamping device below to fix the connecting plate 3 to the end journal 1, as will be explained in detail below.
Further, a reinforcing rib 13 is formed at the connecting shaft 11 to enhance the connecting strength between the connecting shaft 11 and the end journal 1 body.
The assembly of the end journal 1 and the arrow body 2 is explained above, and how the connecting plate 3 is connected to the end journal 1 is explained below.
As shown in fig. 8, the present embodiment further includes a clamping device 5, which is connected to the connecting plate 3 and the end journal 1 to fix the connecting plate 3 and the end journal 1. The clamping device 5 comprises an inner frame 51 detachably arranged on the connecting plate 3 and a fastening device 52 arranged on the inner frame 51 for connecting the end journal 1.
Because the rocket body length of rocket is big, there is the equipment error between the end journal fixed on it, can lead to the mounted position on the connecting plate can not be effectual and end journal 1 to realize accurate positioning fit, and lead to unable assembly, so fastener 52 in this embodiment includes top pressure bolt 521 that connects soon on inner frame 51 and sets up the top 522 at top pressure bolt 521 tip, under the rotary joint motion of top pressure bolt 521, top 522 butt is on end journal 1, through the precession stroke of adjusting radial and axial top pressure bolt, the different equipment errors of effectual adaptation, thereby guarantee the accurate equipment between connecting plate and end journal.
The inner frame body 51 in this embodiment is configured as a square frame body, four jacking bolts 521 are symmetrically arranged on four frame sides of the inner frame body 51 respectively, and in the preset mounting position, the frame sides of the inner frame body 51 are parallel to the axial direction and the radial direction of the arrow body 2 respectively. The four jacking bolts 521 can simultaneously realize the adjustment of radial and axial errors of the arrow body 2, the adjustment range is wider, the adaptability is better, and after jacking is in place, the fixing strength of the end journal 1 at the opposite end of the four jacking bolts 521 is better.
The pressing bolt 521 in this embodiment includes a pressing screw 5211 screwed to the frame of the inner frame 51, and a pressing nut 5212 screwed to the pressing screw 5211, and the pressing nut 5212 is pulled by an external force to drive the pressing screw 5211 to rotate so as to make the pressing head 522 close to or away from the connecting shaft 11.
In other embodiments, the above-mentioned press bolts 521 are symmetrically implemented only on two frame edges of the inner frame 51, which can only achieve axial or radial clamping fixation, but have a simple structure.
In other embodiments, the number of the press bolts 521 may be three, and in a specific embodiment, the three press bolts 521 are arranged at an included angle of 120 °.
Further, the abutting surface of the plug 522 and the connecting shaft 11 in the present embodiment is configured as a cambered surface structure. The design structure can ensure the full contact of the abutting surfaces, thereby ensuring the reliability of the fixation between the clamping device 5 and the end journal 1.
Further, a through hole is formed in the connecting plate 3, and the connecting shaft 11 penetrates through the through hole. The connecting plate 3 is welded with the outer frame 31 around the through hole, and the frame of the outer frame 31 is arranged in parallel corresponding to the frame of the inner frame 51.
Before the clamping device 5 is used for clamping the connecting shaft 11, the center of the outer frame body is required to be aligned as much as possible to ensure that the center of the outer frame body is coincident with the axis of the connecting shaft 11 as much as possible during initial assembly, so that the adjusting amount of the jacking bolt is reduced, the problem of assembly errors is solved better, and the adjusting efficiency is improved. Therefore, in this embodiment, the adjusting bolt 32 is installed on the frame of the outer frame 31 parallel to the radial direction of the arrow body 2, the end of the adjusting bolt 32 abuts against the frame of the inner frame 51, and the adjusting principle is basically the same as that of the jacking bolt, which is not described herein again.
When the inner frame is adjusted to the right position by the adjusting bolt 32, the fastening bolt 33 is mounted on the frame of the outer frame 31 parallel to the axial direction of the arrow body 2, and the end of the fastening bolt 33 abuts against the frame of the inner frame 51 to fix the inner frame 51.
The contact pressure adjusting screw is then locked to the connecting shaft 11, so that the connection plate 3 is fixed to the end journal 1.
It should be further noted that, in the present embodiment, the twelve end journals 1 and the connecting plates 3 are all connected by the above adjusting process, so as to ensure the accuracy of final installation of the connecting plates 3, and provide a good implementation basis for turning and overturning of the rocket.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911421803.3A CN110986674B (en) | 2019-12-31 | 2019-12-31 | A medium-sized solid launch vehicle launch method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911421803.3A CN110986674B (en) | 2019-12-31 | 2019-12-31 | A medium-sized solid launch vehicle launch method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110986674A CN110986674A (en) | 2020-04-10 |
| CN110986674B true CN110986674B (en) | 2021-02-09 |
Family
ID=70080292
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911421803.3A Active CN110986674B (en) | 2019-12-31 | 2019-12-31 | A medium-sized solid launch vehicle launch method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110986674B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461045A (en) * | 2020-11-26 | 2021-03-09 | 北京星途探索科技有限公司 | Detachable simple launching platform |
| CN112780445A (en) * | 2021-02-04 | 2021-05-11 | 北京星际荣耀空间科技股份有限公司 | Flow guide cone and launching platform |
| CN113154944A (en) * | 2021-04-29 | 2021-07-23 | 贵州航天天马机电科技有限公司 | Carrier rocket erection launching system without supporting transportation |
| CN114719678B (en) * | 2022-05-09 | 2023-09-19 | 鲁东大学 | A six-container type sea-launched rocket erecting device |
| CN118310370B (en) * | 2024-04-10 | 2025-02-07 | 中国科学院力学研究所 | A carrier suspension launch rack and a carrier suspension launch method |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05170198A (en) * | 1991-12-25 | 1993-07-09 | Mitsubishi Heavy Ind Ltd | Overturn preventing device for rocket |
| JPH0811800A (en) * | 1994-06-30 | 1996-01-16 | Mitsubishi Heavy Ind Ltd | Rocket air frame holding device |
| WO2007022300A2 (en) * | 2005-08-16 | 2007-02-22 | Theodore Chen Vora | Rocket rig drilling apparatus |
| CN201882471U (en) * | 2010-08-26 | 2011-06-29 | 浙江省火电建设公司 | Transportation bracket for heavy equipment |
| CN103542771B (en) * | 2012-07-10 | 2015-07-15 | 北京航天发射技术研究所 | Protection type cantilever launching platform with built-in water channel and manufacturing method thereof |
| CN107941085B (en) * | 2017-11-20 | 2019-12-20 | 中国运载火箭技术研究院 | Integral type launching pad |
| CN109019296A (en) * | 2018-08-30 | 2018-12-18 | 北京星际荣耀空间科技有限公司 | A kind of whole arrow lifting overturning system of carrier rocket |
| CN110375581B (en) * | 2019-06-13 | 2020-08-04 | 蓝箭航天空间科技股份有限公司 | Rocket launching method |
-
2019
- 2019-12-31 CN CN201911421803.3A patent/CN110986674B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110986674A (en) | 2020-04-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110986674B (en) | A medium-sized solid launch vehicle launch method | |
| US8596700B2 (en) | Tower erection lift kit tools | |
| US8678455B2 (en) | Lifting fitting | |
| CN101966965A (en) | Special hanger with guide cover wheel hub and turning and hanging method | |
| EP4264040B1 (en) | Adaptor for providing an adjustable connection between an endpiece of a lifting apparatus and a nacelle, and method of using same | |
| US8851859B2 (en) | Nacelle stand and a method for assembling and testing a nacelle for a wind turbine | |
| CN111593666A (en) | Bent cap hoop mounting platform and integral beam hoop mounting process | |
| CN108860450B (en) | Ship propeller blade assembling method | |
| CN103216103A (en) | Pre-deformation construction method for mounting oblique-arc-shaped combined steel-structured column of annular roof | |
| CN111071911B (en) | Rocket body flipping device and rocket hoisting system | |
| CN115285826A (en) | Wind power boosting rotor inner tower hoisting device | |
| CN111943014B (en) | Hanging device of aircraft engine starter and assembly method thereof | |
| CN211733584U (en) | Rocket body turning device and rocket lifting system | |
| CN219689087U (en) | Hoisting device with self-balancing adjusting function for nuclear power steam generator | |
| CN117735403A (en) | Light modularized fast-assembly portal frame and mounting process thereof | |
| CN117232325A (en) | Vertical platform, double-rocket aircraft launching installation method and launching system | |
| CN213838811U (en) | Support platforms, towers and wind turbines | |
| CN115638967A (en) | Underframe leg fatigue test device | |
| CN212925733U (en) | But rotation regulation's combination landing stage ramp | |
| CN115676625A (en) | Construction method for replacing driving flange on top of offshore wind power single pile | |
| CN110228748B (en) | Lifting beam and hoisting method for fan shell assembly of high-temperature gas cooled reactor steam generator | |
| CN202542748U (en) | Pin shaft connecting structure and tower crane | |
| CN108715408B (en) | Assembled adjustable anti-overturning device and method for standard section disassembly and assembly of tower crane | |
| CN221343583U (en) | Rocket overturning lifting sling | |
| CN218493727U (en) | Auxiliary device for accurate butt joint of fan and fan base and fan installation ship |
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 | ||
| CP03 | Change of name, title or address |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Beijing Star glory Space Technology Co.,Ltd. Patentee after: Beijing Star glory Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Patentee before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. Patentee before: Beijing Star glory Technology Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 100032 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Star Glory Aerospace Technology Group Co.,Ltd. Country or region after: China Patentee after: Beijing Star glory Technology Co.,Ltd. Address before: 1-14-214, 2nd Floor, 136 Xiwai Street, Xicheng District, Beijing Patentee before: Beijing Star glory Space Technology Co.,Ltd. Country or region before: China Patentee before: Beijing Star glory Technology Co.,Ltd. |
|
| CP03 | Change of name, title or address |