CN116907274A - Multifunctional carrier rocket erection frame and installation method - Google Patents
Multifunctional carrier rocket erection frame and installation method Download PDFInfo
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- CN116907274A CN116907274A CN202311067271.4A CN202311067271A CN116907274A CN 116907274 A CN116907274 A CN 116907274A CN 202311067271 A CN202311067271 A CN 202311067271A CN 116907274 A CN116907274 A CN 116907274A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000009434 installation Methods 0.000 title claims description 17
- 230000007246 mechanism Effects 0.000 claims description 26
- 210000001503 joint Anatomy 0.000 claims description 13
- 241000282326 Felis catus Species 0.000 claims description 12
- 230000009193 crawling Effects 0.000 claims description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 5
- 230000009194 climbing Effects 0.000 claims description 4
- 238000004378 air conditioning Methods 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 9
- 239000003380 propellant Substances 0.000 abstract description 6
- 238000001514 detection method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 description 3
- 238000001914 filtration Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Conveying And Assembling Of Building Elements In Situ (AREA)
Abstract
The invention relates to the field of aerospace ground launching equipment, and provides a multifunctional carrier rocket erection frame, which comprises a erection frame front section, a erection frame middle section and a erection frame tail section which are connected from front to back; the tail section of the erection frame and the middle section of the erection frame are connected and fastened through a double-end stud, and the connecting end surfaces of the middle section of the erection frame and the front section of the erection frame are positioned and butted by rectangular concave flange and convex flange profiles; the sections of the tail section of the erection frame, the middle section of the erection frame and the front section of the erection frame are concave structures. The invention also provides a method for installing the multifunctional erection frame of the carrier rocket. The invention has strong rigidity and strength, can realize large tonnage reliable bearing and erection, can meet the requirement of horizontal support and rocket loading erection of a rocket in functional application, and also has the basic functional requirements of interface detection, test, propellant filling and other work on a fixed launching tower; the method has the advantages of rapid assembly, rapid test and rapid emission.
Description
Technical Field
The invention relates to a multifunctional carrier rocket erection frame and an installation method thereof, and belongs to the field of aerospace ground launching equipment.
Background
At present, the medium-sized and large-sized liquid carrier rocket launching mode generally needs to be launched at a fixed launching station by depending on a ground fixed launching tower, and the mode is that the carrier rocket is transported to the launching tower in a segmented or integral manner, and the fixed launching tower provides corresponding ground assembly, rocket body support and other functions.
However, the fixed launching tower has long infrastructure period, complex functions, high maintenance cost, complex launching process, poor flexibility and high requirements on the launching site of a launching zone, and the launching period is generally 15-25 days from rocket sectional assembly to preparation work such as rocket test, aiming, propellant filling and the like.
In recent years, at home and abroad, the fixed towers on the ground of the launching array are cancelled in a conventional launching mode, a three-flat one-vertical launching mode is adopted, and the lifting frames can meet the requirements of carrying, transporting and transporting the arrow, quickly and integrally lifting, and have the simple launching function. As the main structure of novel space ground launching equipment, the main structure of the novel space ground launching equipment is mainly provided with a celiac box structure, steel plates are welded to form the novel space ground launching equipment, splicing welding seams are more, dead weight and complexity of the novel space ground launching equipment are more than those of other truss structures, the novel space ground launching equipment is also provided with a truss structure at home and abroad, but the novel space ground launching equipment is single in function, only plays the role of carrying and transporting the arrow, is fast and integrally erected, and has simple launching function requirements, and after the liquid carrier rocket is erected, the working requirements of the fixed tower for testing, checking, aiming, propellant filling and the like of the rocket cannot be met.
Along with the rapid development of the aerospace technology, the requirements on the length and the quality of the rocket core stage are higher and higher, the rocket core stage is increased and the quality is increased, so that the erection frame is prolonged, the length of a cantilever and the weight of the cantilever are correspondingly increased in the erection process, the winding degree is difficult to control when the erection frame carries the rocket to erect, and therefore larger additional bending moment is generated on the rocket.
Disclosure of Invention
In order to solve the technical problems, the invention provides the multifunctional carrier rocket erection frame and the installation method thereof, which have strong enough rigidity and strength, can realize large-tonnage reliable bearing and erection, can meet the basic functional requirements of rocket horizontal support and rocket erection in function application, and also have the basic functional requirements of interface detection, test, propellant filling and the like on a fixed launching tower.
The invention is realized by the following technical scheme.
The invention provides a multifunctional carrier rocket erection frame, which comprises an erection frame front section, an erection frame middle section and an erection frame tail section which are connected from front to back; the tail section of the erection frame and the middle section of the erection frame are connected and fastened through a double-end stud, and the connecting end surfaces of the middle section of the erection frame and the front section of the erection frame are positioned and butted by rectangular concave flange and convex flange profiles; the sections of the tail section of the erection frame, the middle section of the erection frame and the front section of the erection frame are concave structures.
The concave flange and the convex flange are fastened by adopting opposite insertion type connection and double-end studs.
The tail section of the erection frame, the middle section of the erection frame and the front section of the erection frame are rectangular steel pipe welding truss structures, filling pipelines and cable laying installation spaces are arranged on two sides of the tail section of the erection frame, a crawling ladder installation space is arranged in the inner cavity of the tail section of the erection frame, and a crawling ladder is arranged in the crawling ladder installation space.
The tail section body of the tail section of the vertical frame and the middle section body of the middle section of the vertical frame are connected with each other through a convex flange, the middle section body of the middle section of the vertical frame and the front section body of the front section of the vertical frame are connected with each other through a convex flange, and the tail section body of the tail section of the vertical frame and the front section body of the front section of the vertical frame are connected with each other through a concave flange.
The tail section of the erection frame is integrated with a tail section body, a crawling ladder, a rear end locking mechanism, an operation platform, an auxiliary supporting mechanism, an oil cylinder starting support and a tail section filling pipeline.
The middle section of the erection frame is integrated with the middle section body, the holding clamp mechanism, the main supporting device, the middle section filling pipeline, the operating platform and the climbing ladder.
The front section of the erection frame is integrated with a front section body, an air conditioner filtering box, an operation platform and a ladder stand.
The invention also provides a method for installing the multifunctional erection frame of the carrier rocket, which comprises the following steps:
s1, single-section assembly: assembling the tail section, the middle section and the front section of the vertical frame into a single module respectively;
s2, splicing and assembling: butt-jointing and fastening the tail section of the erection frame, the middle section of the erection frame and the front section of the erection frame into a whole of the erection frame;
s3, hoisting and fastening: the whole vertical frame is connected and fastened with other equipment of ground emission equipment through the vehicle-mounted motorized reversing or lifting;
s4, connecting pipelines: the front section of the erection frame, the tail section of the erection frame and the middle section of the erection frame are respectively connected by bolts, a filling pipeline and an air-conditioning pipeline butt flange are added, and a rocket connecting interface is accessed;
s5, connecting cables: and (3) quickly inserting each cable of the front section of the erection frame, the middle section of the erection frame and the tail section of the erection frame into the connector, and accessing the connector into a corresponding connection interface of the rocket.
The step S1 specifically comprises the following steps:
s1.1, assembling a tail section of an erection frame: the crawling ladder, the rear-end locking mechanism, the operating platform, the auxiliary supporting mechanism, the oil cylinder starting support and the tail section filling pipeline are respectively installed on the tail section body to integrate an integrated module;
s1.2, assembling the middle section of the vertical frame: the clamp holding mechanism, the main supporting device, the middle section filling pipeline, the operating platform and the climbing ladder are respectively integrated into an integrated module, and are installed on the middle section body to be integrated into an integrated module;
s1.3, assembling the front section of the vertical frame: the air conditioner filter box, the operation platform and the cat ladder are respectively installed on the front section body to be integrated into an integral module.
The step S2 specifically includes the following steps:
s2.1, assembling a tail section of the erection frame and a middle section of the erection frame: lifting the tail section of the vertical frame, inserting the convex flange of the tail section into the profile of the concave flange at the middle section of the vertical frame for positioning and butt joint, and then connecting and fastening by using a double-end stud;
s2.2, assembling the front section of the erection frame and the middle section of the erection frame: and (3) lifting the front section of the vertical frame, inserting the convex flange of the front section into the profile positioning butt joint of the concave flange at the middle section of the vertical frame, and then connecting and fastening by using a double-end stud.
The invention has the beneficial effects that: the device has strong rigidity and strength, can realize large-tonnage reliable bearing and erection, can meet the requirement of horizontal support and rocket loading erection of a rocket in functional application, and also has the basic functional requirements of interface detection, test, propellant filling and other works on a fixed launching tower; the method has the advantages of rapid assembly, rapid test and rapid emission.
Drawings
FIG. 1 is a schematic structural view of at least one embodiment of the present invention;
FIG. 2 is a schematic view of the structure of the tail section of the erection block of FIG. 1;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is a front view of FIG. 2;
FIG. 5 is a schematic view of the overall three-dimensional structure of FIG. 2;
FIG. 6 is a schematic view of the structure of the middle section of the erection frame in FIG. 1;
FIG. 7 is a front view of FIG. 6;
FIG. 8 is a top view of FIG. 6;
FIG. 9 is a schematic view of the front section of the upright frame of FIG. 1;
FIG. 10 is a schematic view of the clasping mechanism of FIG. 6;
fig. 11 is a schematic structural view of the rear end locking mechanism of fig. 2.
In the figure: the device comprises a 1-lifting frame tail section, a 11-tail section body, a 12-rear end locking mechanism, a 13-operating platform, a 14-auxiliary supporting mechanism, a 15-oil cylinder starting support, a 16-cat ladder, a 17-tail section filling pipeline, a 2-lifting frame middle section, a 21-middle section body, a 22-holding clamp mechanism, a 23-main supporting device, a 24-middle section filling pipeline, a 3-lifting frame front section, a 31-front section body and a 32-air conditioner filter box.
Detailed Description
The technical solutions of the present invention are further described below, but the scope of the claims is not limited thereto.
Example 1
A multifunctional carrier rocket erection frame as shown in fig. 1 to 11 comprises a erection frame front section 3, a erection frame middle section 2 and a erection frame tail section 1 which are connected from front to back; the tail section 1 of the erection frame and the middle section 2 of the erection frame are connected and fastened through studs, and the connecting end surfaces of the middle section 2 of the erection frame and the front section 3 of the erection frame are positioned and butted by rectangular concave flanges and convex flange profiles; the sections of the tail section 1, the middle section 2 and the front section 3 of the vertical frame are concave structures.
Furthermore, the concave flange and the convex flange are fastened by adopting opposite insertion type connection and double-end studs.
Example 2
Based on embodiment 1, play and erect frame tail section 1, play and erect frame middle section 2 and play and erect frame anterior segment 3 and be rectangle steel pipe welding truss structure, both sides are provided with filling line and cable laying installation space, and the inner chamber is provided with cat ladder installation space, installs cat ladder 16 in the cat ladder installation space.
Further, the connection section of the tail section body 11 of the tail section 1 of the erection frame and the middle section body 21 of the middle section 2 of the erection frame is a convex flange, the connection section of the middle section body 21 of the middle section 2 of the erection frame and the front section body 31 of the front section 3 of the erection frame is a convex flange, and the connection section of the tail section body 11 of the tail section 1 of the erection frame and the front section body 31 of the front section 3 of the erection frame is a concave flange.
Example 3
Based on embodiment 1, the erection frame tail section 1 is integrated with a tail section body 11, a cat ladder 16, a rear end locking mechanism 12, an operation platform 13, an auxiliary supporting mechanism 14, an oil cylinder starting support 15 and a tail section filling pipeline 17.
Further, the middle section 2 of the erection frame is integrated with the middle section body 21, the holding clamp mechanism 22, the main supporting device 23, the middle section filling pipeline 24, the operation platform 13 and the crawling ladder 16.
Further, the front section 3 of the erection frame is integrated with the front section body 31, the air conditioner filtering box 32, the operation platform 13 and the ladder stand 16.
Example 4
Based on the embodiment, in order to meet the requirements of highway transportation and the stress conditions of all actions, the three-section equal-section integrated truss structure is designed to be formed by a vertical frame tail section, a vertical frame middle section and a vertical frame front section. The whole of each section with equal section is designed into a concave structure; the end sections of the erection frame and the middle section of the erection frame, the connecting end surfaces of the middle section of the erection frame and the front section of the erection frame are in positioning butt joint with the profiles of the rectangular concave flange and the convex flange, the concave flange and the convex flange are in butt joint with each other through butt joint connection and stud fastening, shearing force and torque are born and transferred through the positioning butt joint blocks with the concave-convex profiles, the stud plays a role in connecting and fastening, mainly bears axial force, ensures the connecting strength between the sections and improves the shearing resistance between the sections.
The whole of the erection frame is a rectangular steel pipe welding truss structure (33904 mm multiplied by 4400mm multiplied by 3069 mm), the tail section of the erection frame, the middle section of the erection frame and the front section of the erection frame are space truss structures mainly formed by 8 main beams and 4 auxiliary main beams, and the whole is designed into a concave structure. Each section both sides are provided with filling line and cable laying installation space (480 mm x 1076 mm), and the inner chamber is provided with cat ladder installation space (2260 mm x 916 mm), and in the vertical state of setting up the frame, set up the frame from top to bottom through cat ladder installation passageway and provide the staff in order to realize artifical work operation on setting up the frame.
The connecting section of the tail section body and the middle section body is a convex flange, the length is 13370mm (including a 25mm rectangular convex flange), the width is 4400mm, and the height is 3069mm; the length of the middle section body is 14155mm, the width is 4400mm, the height is 3069mm, and the connecting section of the middle section body and the tail section body and the front section body is designed into a concave flange; the front section body and the middle section body are connected with each other by a convex flange, the length is 6430mm (including 25mm rectangular convex flange), the width is 4400mm, and the height is 1869mm.
The tail section of the erection frame is formed by integrating a tail section body, a ladder stand, a rear end locking mechanism, an operation platform, an auxiliary supporting mechanism, an oil cylinder starting support and a tail section filling pipeline into an integrated module; the middle section of the erection frame is integrated into an integrated module by a middle section body, a clamp holding mechanism, a main supporting device, a middle section filling pipeline, an operation platform and a climbing ladder; the front section of the erection frame is integrated into an integral module by a front section body, an air conditioner filter box, an operation platform and a cat ladder. The filling pipeline and the connecting cable at the butt joint positions of the three module sections are provided with quick connection or disassembly interfaces, when the transition transportation is needed, the three modules can be transported to a designated site in a vehicle-mounted mobile mode, and the normal starting or closing of functions of all equipment can be realized only by quickly butt-jointing and assembling or disassembling the mechanical, filling pipeline and the cable connection interfaces among the sections.
The end sections of the erection frame are connected with the middle section of the erection frame, the connecting end surfaces of the middle section of the erection frame and the front section of the erection frame through the rectangular concave flange and the convex flange profile positioning butt joint double-end studs, the filling pipeline flanges of the sections are quickly connected, and the cables are quickly inserted through connectors, so that the detection and the debugging of each functional condition of the erection frame and the horizontal testing of a rocket can be realized, and after the testing is correct, the rocket is carried by the erection frame to erect and butt joint with the launching array ground launching platform.
After the vertical frame carries the rocket and is erected, staff can reach each section of operation platform through the crawling ladder so as to meet the working requirements of the fixed launching tower on the operation of interface detection, fairing air supply, propellant filling pipelines and the like on the rocket.
Example 5
A method for installing a multifunctional standing frame of a launch vehicle according to any one of embodiments 1 to 4, comprising the steps of:
s1, single-section assembly: the tail section 1, the middle section 2 and the front section 3 of the vertical frame are assembled into a single module respectively;
s2, splicing and assembling: the tail section 1, the middle section 2 and the front section 3 of the erection frame are butt-jointed and fastened into a whole;
s3, hoisting and fastening: the whole vertical frame is connected and fastened with other equipment of ground emission equipment through the vehicle-mounted motorized reversing or lifting;
s4, connecting pipelines: the front section 3 of the erection frame, the tail section 1 of the erection frame and the middle section 2 of the erection frame are respectively connected by bolts, and a filling pipeline and an air-conditioning pipeline butt flange are added and connected into a rocket connecting interface;
s5, connecting cables: and (3) quickly inserting the cables of the front section 3, the middle section 2 and the tail section 1 of the vertical frame into connectors, and accessing the connectors into corresponding connection interfaces of rockets.
Further, the step S1 specifically includes the following steps:
s1.1, assembling a tail section of an erection frame: the cat ladder 16, the rear end locking mechanism 12, the operation platform 13, the auxiliary supporting mechanism 14, the oil cylinder starting support 15 and the tail section filling pipeline 17 are respectively installed on the tail section body 11 to form an integrated module;
s1.2, assembling the middle section of the vertical frame: the clamp holding mechanism 22, the main supporting device 23, the middle section filling pipeline 24, the operating platform 13 and the cat ladder 16 are respectively integrated into an integral module, and the integral module is arranged on the middle section body 21;
s1.3, assembling the front section of the vertical frame: the air conditioner filter box 32, the operation platform 13 and the ladder stand 16 are respectively mounted on the front section body 31 to be integrated into an integral module.
Further, the step S2 specifically includes the following steps:
s2.1, assembling a tail section of the erection frame and a middle section of the erection frame: lifting the tail section 1 of the vertical frame, inserting the convex flange of the tail section into the profile positioning butt joint of the concave flange of the middle section 2 of the vertical frame, and then connecting and fastening by using a double-end stud;
s2.2, assembling the front section of the erection frame and the middle section of the erection frame: and lifting the front section 3 of the vertical frame, inserting the convex flange of the front section into the profile positioning butt joint of the concave flange of the middle section 2 of the vertical frame, and then connecting and fastening by using a double-end stud.
Based on the above, through practical inspection, the invention can directly fill the movable sled and the tank wagon after the rocket is erected in actual use, and the quick response capability of the work of the launching area can be shortened to 48 hours after entering the launching process.
Claims (10)
1. The utility model provides a multi-functional play of carrier rocket erects frame, includes from the front to the back with this linking play erect frame anterior segment (3), play erect frame middle section (2), play to erect frame tail section (1), its characterized in that: the tail section (1) of the erection frame and the middle section (2) of the erection frame are connected and fastened through studs, and the connecting end surfaces of the middle section (2) of the erection frame and the front section (3) of the erection frame are positioned and butted by rectangular concave flange and convex flange profiles; the sections of the tail section (1), the middle section (2) and the front section (3) of the erection frame are concave structures.
2. A launch vehicle multifunctional riser as recited in claim 1, wherein: the concave flange and the convex flange are fastened by adopting opposite insertion type connection and double-end studs.
3. The launch vehicle multifunctional erection and installation method of claim 1, wherein: the automatic vertical frame comprises a vertical frame tail section (1), a vertical frame middle section (2) and a vertical frame front section (3), wherein the vertical frame tail section, the vertical frame middle section and the vertical frame front section (3) are rectangular steel pipe welding truss structures, filling pipelines and cable laying installation spaces are arranged on two sides of the vertical frame tail section, a ladder stand installation space is arranged in an inner cavity of the vertical frame tail section, and a ladder stand (16) is arranged in the ladder stand installation space.
4. A launch vehicle multifunctional riser as recited in claim 1, wherein: the tail section body (11) of the erection frame tail section (1) and the middle section body (21) of the erection frame middle section (2) are connected with a convex flange, the connecting section of the middle section body (21) of the erection frame middle section (2) and the front section body (31) of the erection frame front section (3) is a convex flange, and the connecting section of the tail section body (11) of the erection frame tail section (1) and the front section body (31) of the erection frame front section (3) is a concave flange.
5. A launch vehicle multifunctional riser as recited in claim 1, wherein: the lifting frame tail section (1) is integrated with a tail section body (11), a cat ladder (16), a rear end locking mechanism (12), an operating platform (13), an auxiliary supporting mechanism (14), an oil cylinder starting support (15) and a tail section filling pipeline (17).
6. A launch vehicle multifunctional riser as recited in claim 1, wherein: the middle section (2) of the erection frame is integrated with a middle section body (21), a holding clamp mechanism (22), a main supporting device (23), a middle section filling pipeline (24), an operating platform (13) and a crawling ladder (16).
7. A launch vehicle multifunctional riser as recited in claim 1, wherein: the front section (3) of the erection frame is integrated with a front section body (31), an air conditioner filter box (32), an operation platform (13) and a cat ladder (16).
8. A method for installing a multifunctional erection frame of a carrier rocket is characterized by comprising the following steps of: mounting a multifunctional lifting frame of a carrier rocket according to any one of claims 1 to 9, comprising the steps of:
s1, single-section assembly: the tail section (1), the middle section (2) and the front section (3) of the vertical frame are assembled into a single module respectively;
s2, splicing and assembling: the tail section (1), the middle section (2) and the front section (3) of the erection frame are butt-jointed and fastened to form a whole erection frame;
s3, hoisting and fastening: the whole vertical frame is connected and fastened with other equipment of ground emission equipment through the vehicle-mounted motorized reversing or lifting;
s4, connecting pipelines: the front section (3) of the erection frame, the tail section (1) of the erection frame and the middle section (2) of the erection frame are respectively connected by bolts, and a filling pipeline and an air-conditioning pipeline butt flange are added and connected into a rocket connecting interface;
s5, connecting cables: and (3) the front section (3), the middle section (2) and the tail section (1) of the erection frame are quickly inserted into the connectors and are connected into corresponding connecting interfaces of the rocket.
9. The method for installing the multifunctional lifting frame of the carrier rocket according to claim 1, wherein the method comprises the following steps: the step S1 specifically comprises the following steps:
s1.1, assembling a tail section of an erection frame: the crawling ladder (16), the rear-end locking mechanism (12), the operating platform (13), the auxiliary supporting mechanism (14), the oil cylinder starting support (15) and the tail section filling pipeline (17) are respectively installed on the tail section body (11) to form an integrated module;
s1.2, assembling the middle section of the vertical frame: the clamp holding mechanism (22), the main supporting device (23), the middle section filling pipeline (24), the operating platform (13) and the climbing ladder (16) are respectively integrated into an integral module, and the integral module is arranged on the middle section body (21);
s1.3, assembling the front section of the vertical frame: the air conditioner filter box (32), the operation platform (13) and the crawling ladder (16) are respectively installed on the front section body (31) to be integrated into an integral module.
10. The method for installing the multifunctional lifting frame of the carrier rocket according to claim 1, wherein the method comprises the following steps: the step S2 specifically includes the following steps:
s2.1, assembling a tail section of the erection frame and a middle section of the erection frame: lifting a tail section (1) of the vertical frame, inserting a convex flange of the tail section into a concave flange molded surface of a middle section (2) of the vertical frame for positioning and butt joint, and then connecting and fastening by using a double-end stud;
s2.2, assembling the front section of the erection frame and the middle section of the erection frame: and lifting the front section (3) of the vertical frame, inserting the convex flange of the front section into the concave flange molded surface of the middle section (2) of the vertical frame for positioning and butt joint, and then connecting and fastening by using a double-end stud.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311067271.4A CN116907274A (en) | 2023-08-23 | 2023-08-23 | Multifunctional carrier rocket erection frame and installation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311067271.4A CN116907274A (en) | 2023-08-23 | 2023-08-23 | Multifunctional carrier rocket erection frame and installation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116907274A true CN116907274A (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311067271.4A Pending CN116907274A (en) | 2023-08-23 | 2023-08-23 | Multifunctional carrier rocket erection frame and installation method |
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| Country | Link |
|---|---|
| CN (1) | CN116907274A (en) |
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2023
- 2023-08-23 CN CN202311067271.4A patent/CN116907274A/en active Pending
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