CN111023913A - Carrier rocket final-stage structure - Google Patents
Carrier rocket final-stage structure Download PDFInfo
- Publication number
- CN111023913A CN111023913A CN201911389997.3A CN201911389997A CN111023913A CN 111023913 A CN111023913 A CN 111023913A CN 201911389997 A CN201911389997 A CN 201911389997A CN 111023913 A CN111023913 A CN 111023913A
- Authority
- CN
- China
- Prior art keywords
- reinforcing
- instrument
- wall
- cabin
- reinforcing beam
- 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.)
- Pending
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
Abstract
The invention discloses a carrier rocket final-stage structure, which comprises: the power cabin provides an installation space for the last-stage power system; the instrument cabin is connected to the upper end of the power cabin, and the inner wall of the instrument cabin is provided with a plurality of installation interfaces for installing instruments; the reinforcing beam structure comprises at least two reinforcing beams which are arranged in parallel and two ends of each reinforcing beam are respectively connected with the inner wall of the instrument cabin; and connecting discs for providing connection interfaces for the final-stage power system are connected to the middle positions of at least two reinforcing beams. The reinforcing beam structure with the double-beam parallel structure is adopted in the instrument cabin, the dead weight of the reinforcing beam structure can be reduced on the premise of ensuring the stability of the mounting structure of the connecting disc, and the power cabin and the instrument cabin are respectively manufactured by adopting an integrated structure, so that the effect of reducing the self weight of the whole carrier rocket final-stage structure can be achieved; meanwhile, the inner wall of the instrument cabin can provide an installation interface for a large number of devices, so that the starting resistance of the rocket during launching is reduced, and the carrying efficiency of the rocket is improved.
Description
Technical Field
The invention relates to the technical field of aerospace and aviation, in particular to a carrier rocket final-stage structure.
Background
The carrier rocket is generally used as a transport vehicle to send payloads such as various satellites into space, and generally comprises two stages to four stages, wherein each stage comprises a rocket body structure, an engine and the like.
The last substage of the carrier rocket is generally provided with electric equipment of the whole rocket, including a guidance and control system, a remote measuring system, a safety system and the like, and the number of instrument installation interfaces is large. And a final-stage power system needs to be installed and bears larger load. Furthermore, the satellites are also typically mounted on the last substage, which is required to provide a reliable mounting interface.
The last son stage of the carrier rocket enters the orbit along with the satellite, and the structural efficiency of the carrier rocket directly influences the carrying capacity of the rocket. Therefore, the design of the last sub-stage is crucial, the structure weight is reduced, the carrying capacity is improved, the flight reliability of the carrier rocket is ensured, and the satellite is safely put into orbit with high precision.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the technical problems of unreasonable layout, complex assembly, high requirement, weak bearing capacity and larger weight of the carrier rocket final-stage structure in the prior art, thereby providing the carrier rocket final-stage structure.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a launch vehicle final sub-stage structure comprising:
the power cabin provides an installation space for the last-stage power system;
the instrument cabin is connected to the upper end of the power cabin, and the inner wall of the instrument cabin is provided with a plurality of installation interfaces for installing instruments;
the reinforcing beam structure comprises at least two reinforcing beams which are arranged in parallel and two ends of each reinforcing beam are respectively connected with the inner wall of the instrument cabin; and connecting discs for providing connection interfaces for the final-stage power system are connected to the middle positions of at least two reinforcing beams.
Furthermore, two ends of the reinforcing beam are respectively connected with the inner wall of the instrument cabin through reinforcing corner boxes.
Further, the power cabin, the instrument cabin, the reinforcing beam structure and the reinforcing corner box are all made of aluminum alloy.
Further, the cross section of the reinforcing beam is I-shaped; the stiffening beam comprises a web plate, an upper wing plate and a lower wing plate which are respectively connected to the upper end and the lower end of the web plate, and the connecting disc is connected to the bottom surfaces of at least two lower wing plates which are arranged in parallel.
Furthermore, the middle part of the lower wing plate connected with the connecting disc and the end part connected with the reinforcing corner box are provided with extension sections extending outwards; the part of the lower wing plate, which is correspondingly provided with the extension section, and a plurality of reinforcing rib plates which are arranged at intervals are connected between the upper wing plate and the web plate.
Further, the connection pad includes:
the upper connecting plate is connected to the lower end surfaces of at least two stiffening beams arranged in parallel;
the lower connecting plate is connected to one end face, opposite to the reinforcing beam, of the upper connecting plate through a connecting cylinder, and a plurality of mounting seats assembled with the last-stage power system are arranged on the lower end face of the lower connecting plate;
and the stiffening plates are connected among the upper connecting plate, the lower connecting plate and the connecting cylinders and are arranged corresponding to the mounting seats.
Furthermore, a plurality of first mounting holes for connecting the inner wall of the instrument chamber are formed in the side wall, close to the inner wall of the instrument chamber, of the reinforcing angle box; the bottom wall of the reinforcing corner box for bearing the reinforcing beam is provided with a plurality of second mounting holes for connecting the reinforcing beam; the bottom wall and the side wall of the reinforced corner box are perpendicular.
Furthermore, the lower end face of the bottom wall of the reinforced corner box is also connected with a reinforced corner block, the reinforced corner block is close to the side wall of the inner wall of the instrument chamber, and a plurality of third mounting holes used for connecting the inner wall of the instrument chamber are formed in the side wall of the inner wall of the instrument chamber.
Furthermore, a satellite support angle box used for providing support for the satellite support is connected to the upper portion of the inner wall of the instrument cabin.
Furthermore, the inner surfaces of the power cabin and the instrument cabin are provided with grid reinforced structures.
The technical scheme of the invention has the following advantages:
1. according to the carrier rocket final-stage structure provided by the invention, the inner wall of the instrument cabin can provide an installation interface for a large amount of equipment, the power cabin below the instrument cabin provides an installation space for a final-stage power system, meanwhile, a reinforcing beam structure formed by at least two reinforcing beams arranged in parallel is adopted between the inner walls of the instrument cabin to provide support for the final-stage power system, and the middle positions of the at least two reinforcing beams are connected with a structural design of a connecting disc for providing a connection interface for the final-stage power system; since the size of the last-stage power system is fixed, the connecting disc for installing the last-stage power system also needs to be designed to be a predetermined size to fit the fixed-size last-stage power system, and the corresponding reinforcing beam structure needs to have a sufficient width to ensure the stability of the connecting disc on the reinforcing beam structure. The existing stiffening beam structure generally adopts a single beam structure or a cross beam structure, and the stiffening beam structure formed by the single beam or the cross beam needs to be designed with enough width to ensure the stability of a connecting disc and a last-stage power system arranged on the connecting disc, so that the weight of the whole stiffening beam structure is increased, and the rocket carrying capacity is not improved; the reinforcing beam structure with the parallel double beams is adopted, so that the dead weight of the reinforcing beam structure can be reduced on the premise of ensuring the stability of the mounting structure of the connecting disc; and the carrier rocket final-stage structure with the structure has the advantages of simple structure, convenience in assembly, strong bearing capacity, light structure weight and capability of providing reliable support for an internal final-stage power system, and the carrying efficiency of the rocket is greatly improved.
2. According to the carrier rocket final-stage structure provided by the invention, the two ends of the stiffening beam are fixedly connected with the inner wall of the instrument cabin through the reinforcing corner boxes, so that on one hand, the firmness of the stiffening beam mounting structure can be improved, on the other hand, the stiffening beam is more convenient to mount, and the assembly difficulty is reduced.
3. According to the carrier rocket final-stage structure, the power cabin, the instrument cabin, the reinforcing beam structure and the reinforcing corner boxes are all made of aluminum alloy, so that the overall self weight of the carrier rocket final-stage structure can be reduced.
4. The reinforcing beam with the I-shaped cross section has the advantages of strong bearing capacity, light structure dead weight and convenience in mounting the connecting discs or other parts on the wing plates at the upper end and the lower end of the reinforcing beam.
5. According to the carrier rocket final-stage structure provided by the invention, the acting force applied to the middle part of the lower wing plate connected with the connecting disc and the end part connected with the reinforcing corner box is larger, the extension section is arranged at the corresponding position of the lower wing plate, and the plurality of reinforcing rib plates arranged at intervals are arranged between the part of the lower wing plate correspondingly provided with the extension section and the upper wing plate and the web plate, so that the structural strength of the part with stronger bearing capacity of the reinforcing beam can be improved, and the bearing capacity of the reinforcing beam structure can meet the design requirement under the condition of reducing the self weight of the reinforcing beam as much as possible.
6. The carrier rocket final-stage structure provided by the invention is a connecting disc consisting of an upper connecting plate, a lower connecting plate and a stiffening plate, and has the advantages of light dead weight and convenience in assembly under the condition of ensuring that the bearing capacity of the connecting disc can meet the design requirement.
7. According to the carrier rocket final-stage structure provided by the invention, the side wall, close to the inner wall of the instrument cabin, of the reinforcing corner box is provided with a plurality of first mounting holes for connecting the inner wall of the instrument cabin, the bottom wall, used for bearing the reinforcing beam, of the reinforcing corner box is provided with a plurality of second mounting holes for connecting the reinforcing beam, and the bottom wall and the side wall of the reinforcing corner box are vertical; the reinforcing corner box with the structure has the advantages of simple structure, high reliability and convenience in assembly.
8. According to the carrier rocket final-stage structure provided by the invention, the bottom of the reinforced corner box is connected with the reinforced corner block, and the reinforced corner block can be fixed on the inner wall of the instrument cabin through the connecting bolt, so that the stability of the reinforced corner box mounting structure can be further improved.
9. According to the carrier rocket tail-stage structure provided by the invention, the inner surfaces of the power cabin and the instrument cabin are arranged into grid reinforced structures, so that the structural strength and the bearing capacity of the power cabin and the instrument cabin can be improved; meanwhile, the grid reinforcement structure is convenient for reinforcing the installation of the corner box and the layout of the installation interface.
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 diagram of a final stage structure of a launch vehicle according to an embodiment of the present invention;
FIG. 2 is a schematic view of an instrument bay in a final sub-stage structure of a launch vehicle according to an embodiment of the present invention;
FIG. 3 is a schematic view of a reinforcing beam structure in the last substage of a launch vehicle according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a final stage power system assembled with a reinforcing beam structure according to an embodiment of the present invention
FIG. 5 is a schematic view of a power pod in a last-stage configuration of a launch vehicle according to an embodiment of the present invention;
fig. 6 is a schematic diagram of a separate spring bracket in a power pod according to an embodiment of the present invention.
Description of reference numerals: 1. a power compartment; 2. an instrument pod; 3. a stiffening beam structure; 31. a reinforcing beam; 311. a web; 312. an upper wing plate; 313. a lower wing plate; 314. an extension section; 315. reinforcing rib plates; 32. a connecting disc; 321. an upper connecting plate; 322. a lower connecting plate; 323. a stiffening plate; 324. a connecting cylinder; 325. a mounting seat; 4. a reinforcing corner box; 41. a side wall; 42. a bottom wall; 43. a reinforcing corner block; 5. explosion bolt cushions; 6. a camera fairing; 7. a satellite support corner box; 8. separating the spring support; 9. and a last-stage power system.
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.
The carrier rocket final-stage structure shown in figures 1-6 comprises a power cabin 1, an instrument cabin 2 and a reinforcing beam structure 3. Wherein, the power cabin 1 provides an installation space for the last-stage power system 9; the instrument cabin 2 is connected above the power cabin 1 through a reinforcing frame, and a plurality of installation interfaces for installing instruments are arranged on the inner wall of the instrument cabin 2; the reinforcing beam structure 3 is used for supporting the last-stage power system 9 so as to ensure that the last-stage power system 9 is stably and reliably connected. The reinforcing beam structure 3 comprises at least two reinforcing beams 31 which are arranged in parallel and two ends of which are respectively connected with the inner wall of the instrument cabin 2; and connecting discs 32 for providing connection interfaces for the final-stage power system 9 are connected to the middle positions of the at least two reinforcing beams 31. Specifically, the number of the reinforcing beams 31 is two in the present embodiment, and in other embodiments, three or more reinforcing beams 31 arranged in parallel may also be used as the reinforcing beam structure 3.
In the last-stage structure of the carrier rocket in the configuration, the inner wall of an instrument cabin 2 can provide installation interfaces for a large number of devices, a power cabin 1 below the instrument cabin 2 provides installation space for a last-stage power system 9, meanwhile, a reinforcing beam structure 3 formed by at least two reinforcing beams 31 arranged in parallel is adopted between the inner walls of the instrument cabin 2 to provide support for the last-stage power system 9, and the middle positions of the at least two reinforcing beams 31 are connected with a structural design of a connecting disc 32 for providing a connecting interface for the last-stage power system 9; since the size of the last sub-stage power system 9 is fixed, the connection disc 32 for mounting the last sub-stage power system 9 also needs to be designed to a predetermined size to accommodate the fixed size of the last sub-stage power system 9, and the corresponding reinforcing beam structure 3 needs to have a sufficient width to ensure the stability of the connection disc 32 on the reinforcing beam structure 3. The existing reinforcing beam structure 3 generally adopts a single beam structure or a cross beam structure, and the reinforcing beam structure 3 formed by the single beam or the cross beam needs to be designed with enough width to ensure the stability of the connecting disc 32 and the last-stage power system 9 arranged on the connecting disc, so that the weight of the whole reinforcing beam structure 3 is increased, and the improvement of the carrying capacity of the rocket is not facilitated; the reinforcing beam structure 3 with the parallel double beams is adopted, so that the self weight of the reinforcing beam structure 3 can be reduced on the premise of ensuring the stability of the mounting structure of the connecting disc 32; and the carrier rocket final-stage structure with the structure has the advantages of simple structure, convenience in assembly, strong bearing capacity, light structure weight and capability of providing reliable support for the internal final-stage power system 9, and the carrying efficiency of the rocket is greatly improved.
In the present embodiment, in order to facilitate the connection between the reinforcing beam 31 and the inner wall of the instrument chamber 2, the reinforcing corner boxes 4 capable of being fixed on the inner wall of the instrument chamber 2 are respectively disposed at two ends of the reinforcing beam 31. The mode that stiffening beam 31 passes through reinforcing angle box 4 to be fixed at instrument compartment 2 inner wall can improve stiffening beam 31 mounting structure's fastness on the one hand, and on the other hand also makes stiffening beam 31's installation more convenient, reduces stiffening beam structure 3's the assembly degree of difficulty.
In the present embodiment, the cross section of the reinforcing beam 31 is i-shaped; the reinforcing beam 31 includes a web 311, and an upper wing plate 312 and a lower wing plate 313 connected to the upper and lower ends of the web 311, respectively, and the connecting plate 32 is connected to the bottom surfaces of at least two lower wing plates 313 arranged in parallel. The reinforcing beam 31 with the I-shaped cross section has the advantages of strong bearing capacity, light structural dead weight and convenience for mounting the connecting disc 32 or other parts on wing plates at the upper end and the lower end of the reinforcing beam, and reduces the dead weight of the final stage structure of the whole carrier rocket on the premise of ensuring the flight reliability of the final stage structure of the carrier rocket.
Further, the middle part of the lower wing plate 313 connected with the connecting disc 32 and the end part connected with the reinforcing corner box 4 are provided with extension sections 314 extending outwards; a plurality of reinforcing rib plates 315 arranged at intervals are connected between the part of the lower wing plate 313 corresponding to the extension section 314 and the upper wing plate 312 and the web 311. Because the acting force on the middle part of the lower wing plate 313 connected with the connecting disc 32 and the end part connected with the reinforcing corner box 4 is relatively large, the extension section 314 is arranged at the corresponding position of the lower wing plate 313, and a plurality of reinforcing rib plates 315 which are arranged at intervals are arranged between the part of the lower wing plate 313 correspondingly provided with the extension section 314, the upper wing plate 312 and the web 311, the structural strength of the part with stronger bearing capacity of the reinforcing beam 31 can be improved, and the bearing capacity of the reinforcing beam structure 3 can meet the design requirement under the condition of reducing the self weight of the reinforcing beam 31 as much as possible.
In the present embodiment, the land 32 includes: an upper connecting plate 321 connected to the lower end surfaces of at least two reinforcing beams 31 arranged in parallel; a lower web 322 connected to an end surface of the upper web 321 opposite to the reinforcing beam 31 by a connecting cylinder 324; and a stiffening plate 323 integrally formed between the upper connecting plate 321, the lower connecting plate 322 and the connecting cylinder 324. The connecting disc 32 composed of the upper connecting plate 321, the lower connecting plate 322 and the stiffening plate 323 has the advantages of light dead weight and convenient assembly under the condition of ensuring that the bearing capacity of the connecting disc 32 can meet the design requirement.
Specifically, the upper connecting plate 321 and the lower connecting plate 322 are both disc-shaped, the upper connecting plate 321 is provided with a plurality of connecting holes for connecting and fixing with the reinforcing plate, the lower end face of the lower connecting plate 322 is integrally formed with four mounting seats 325, the four mounting seats 325 are circumferentially and uniformly arranged around the lower connecting plate 32 at intervals, and the four mounting seats 325 are all provided with assembling holes for assembling the final stage power system 9. The stiffening plates 323 correspond to the four mounting seats 325 one by one, and each mounting seat 325 corresponds to two stiffening plates 323. Because the mounting seat 325 needs to directly bear the weight of the final-stage power system 9 after the final-stage power system 9 is assembled, the pressure load on the position of the lower connecting plate 322 where the mounting seat 325 is arranged is relatively large, and the two stiffening plates 323 are arranged at the position, the bearing capacity of the lower connecting plate 322 can be improved.
In the embodiment, a plurality of uniformly arranged first mounting holes for connecting the inner wall of the instrument chamber 2 are arranged on the side wall 41 of the reinforcing corner box 4 close to the inner wall of the instrument chamber 2; the bottom wall 42 of the reinforcing corner box 4 for bearing the reinforcing beam 31 is provided with a plurality of second mounting holes which are uniformly arranged and are used for connecting the reinforcing beam 31; the bottom wall 42 and the side wall 41 of the corner box 4 are perpendicular. The reinforcing corner box 4 with the structure has the advantages of simple structure, high reliability and convenience in assembly.
Further, the lower end face of the bottom wall 42 of the reinforcing corner box 4 is further integrally connected with a reinforcing corner block 43, the reinforcing corner block 43 is of an angle-shaped structure, and a plurality of third mounting holes used for being connected with the inner wall of the instrument chamber 2 are formed in the side wall 41, close to the inner wall of the instrument chamber 2, of the reinforcing corner block 43. The reinforcing corner block 43 capable of being fixed on the inner wall of the instrument cabin 2 is added at the bottom of the reinforcing corner box 4, and the reinforcing corner block 43 can provide support for the reinforcing corner box 4, so that the stability of the mounting structure of the reinforcing corner box 4 is improved.
In this embodiment, the launch vehicle end sub-stage structure further comprises an explosive bolt bumper 5, a camera fairing 6, a satellite mount support angle box 7 and a breakaway spring mount 8. Wherein, the power compartment 1, the instrument compartment 2, the separation spring support 8, the stiffening beam structure 3 and the satellite support angle box 7 are made by aluminum alloy machining, the explosion bolt buffer 5 is made by aluminum alloy sheet metal, and the camera fairing 6 is made by titanium alloy 3D printing. After the power cabin 1, the instrument cabin 2, the separation spring support 8, the power system reinforcing beam 31, the explosion bolt cushion 5, the camera fairing 6, the satellite support supporting angle box 7 and the rocket body are formed independently, the carrier rocket final-stage structure is assembled in a screwing mode. The structure has simple structure, reliable connection, light weight and high bearing efficiency.
Specifically, the lower end of the power cabin 1 is used for being connected with a third sub-stage of the rocket, the instrument cabin 2 is located at the upper part of the last sub-stage, and the upper end of the instrument cabin 2 is used for being connected with a satellite support. The power cabin 1 is made of aluminum alloy through integral machining, the outer surface of the power cabin 1 is smooth and does not have protrusions, and the inner surface of the power cabin 1 is of a grid reinforced structure, so that the structural strength and the bearing capacity of the power cabin 1 are improved. The peripheral wall of the power compartment 1 is designed with four maintenance covering covers for internal equipment assembly and maintenance operation. The lower part of the power compartment 1 has six explosive bolt boxes for accommodating explosive bolt nuts connected with the third sub-stage.
Specifically, the root of the separation spring support 8 is connected with the power cabin 1 through four bolts, the tail end of the separation spring support 8 is provided with a conical groove, so that the end part of the spring ejector rod cannot slide out of the separation spring support 8 when the separation of the last secondary level and the third secondary level is ensured, and the back of the separation spring support 8 is provided with a reinforcing rib so as to ensure the supporting rigidity of the separation spring support 8 body.
Specifically, the lower end of the instrument cabin 2 is connected with the power cabin 1 through a reinforcing frame, and the instrument cabin 2 is internally loaded with final-stage instrument equipment. The explosion bolt buffer cushion 5 is positioned in an explosion bolt box of the instrument cabin 2, absorbs the impact energy of the explosion bolt and protects the cabin body from being damaged. The camera fairing 6 is located on the outer wall of the instrument cabin 2 and used for protecting the external camera from being damaged by aerodynamic force and airflow heating. The satellite support supporting angle box 7 is located at the upper part of the instrument cabin 2 and is used for connecting the satellite support and the instrument cabin 2, supporting the satellite support and bearing the whole load of the satellite support.
In a specific implementation manner of this embodiment, the bodies of the power pod 1 and the instrument pod 2 are of a revolving body structure with a wall thickness of 2mm, and the thickness of the end frames connecting the upper end and the lower end of the power pod 1 and the instrument pod 2 is 8 mm. The height of the grid ribs in the power cabin 1 and the instrument cabin 2 is 12mm, and the thickness of the grid ribs is 2 mm. The power cabin 1 and the instrument cabin 2 are made of aluminum alloy 2A14 forgings and are machined and formed.
The separated spring support 8, the reinforcing beam structure 3 and the satellite support supporting angle box 7 are made of aluminum alloy 2A14 plates and are machined and formed.
The material of explosion bolt blotter 5 is aluminum alloy 2A12 panel, the sheet metal shaping, and thickness is 3 mm.
The camera fairing 6 is made of titanium alloy TA15 powder, is formed by 3D printing and has the thickness of 2 mm.
And assembling the components after finishing processing respectively.
In the assembly process of the carrier rocket final-stage structure, firstly, the separation spring support 8 is arranged at the lower part of the power cabin 1, and the separation spring support and the power cabin are connected by four M6 bolts; then the reinforcing beam structure 3 is sequentially installed on the instrument cabin 2 through the four reinforcing corner boxes 4, the satellite support supporting corner box 7 is installed on the instrument cabin 22 through eight M8 bolts on each corner box, the six explosive bolt cushions 5 are installed on the instrument cabin 2 through twelve M5 pallet nuts, and the camera fairing 6 is installed on the instrument cabin 2 through nine M4 screws; and finally, combining the power cabin 1 and the instrument cabin 2 into a carrier rocket final sub-stage through sixteen M8 bolts on the reinforcing frame at the upper end of the power cabin 1 and the reinforcing frame at the lower end of the instrument cabin 2.
In other alternative embodiments of this embodiment, the number of the separation spring holders 8 may be four, or may be other numbers. The number of the satellite support angle boxes 7 can be three, and other numbers can also be adopted. The number of stud bumps may be six or other numbers.
A camera fairing 66 is designed outside the instrument pod 2. In the prior art, the cowling is usually made of stainless steel material, and the weight of the structure is heavy. However, in the embodiment of the invention, the camera fairing 66 is manufactured by adopting a titanium alloy 3D printing technology, so that the structural weight of the rocket tail sub-stage is reduced while the camera is protected from being ablated by high-temperature airflow.
In summary, the reinforced beam structure 3 with the double-beam parallel configuration is adopted in the instrument cabin 2, so that the self weight of the reinforced beam structure 3 can be reduced on the premise of ensuring the stability of the mounting structure of the connecting disc 32, and the power cabin 1 and the instrument cabin 2 are manufactured by integrated machining, so that the effect of reducing the self weight of the whole carrier rocket final-stage structure can be achieved; meanwhile, the inner wall of the instrument cabin 2 can provide mounting interfaces for a large number of devices, so that the starting resistance of the rocket during launching is reduced, and the carrying efficiency of the rocket is greatly improved.
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 (10)
1. A launch vehicle final substructure, comprising:
the power cabin (1) provides an installation space for the last-stage power system (9);
the instrument cabin (2) is connected to the upper end of the power cabin (1), and a plurality of installation interfaces for installing instruments are arranged on the inner wall of the instrument cabin;
the reinforcing beam structure (3) comprises at least two reinforcing beams (31) which are arranged in parallel and two ends of each reinforcing beam are respectively connected with the inner wall of the instrument cabin (2); and connecting discs (32) for providing connection interfaces for the final-stage power system (9) are connected to the middle positions of the at least two reinforcing beams (31).
2. A launch vehicle final stage structure according to claim 1, characterised in that the reinforcement beam (31) is connected at both ends to the inner wall of the instrument bay (2) by means of a reinforcement angle box (4), respectively.
3. A launch vehicle final stage structure according to claim 2, characterised in that the power pod (1), the instrument pod (2), the reinforcing beam structure (3) and the reinforcing corner boxes (4) are all made of aluminium alloy.
4. A launch vehicle final stage structure according to claim 3, characterised in that the cross section of the reinforcing beam (31) is i-shaped; the reinforcing beam (31) comprises a web plate (311), an upper wing plate (312) and a lower wing plate (313) which are respectively connected to the upper end and the lower end of the web plate (311), and the connecting disc (32) is connected to the bottom surfaces of at least two lower wing plates (313) which are arranged in parallel.
5. A launch vehicle end sub-stage structure according to claim 4, characterised in that the middle part of the lower wing (313) connected to the connection disc (32) and the end part connected to the reinforcing corner box (4) are each provided with an outwardly extending extension (314); and a plurality of reinforcing rib plates (315) arranged at intervals are connected between the part of the lower wing plate (313) correspondingly provided with the extension section (314) and the upper wing plate (312) and the web plate (311).
6. A launch vehicle final stage structure according to claim 1, characterised in that said connection disc (32) comprises:
an upper connecting plate (321) connected to the lower end surfaces of at least two reinforcing beams (31) arranged in parallel;
the lower connecting plate (322) is connected to one end face, opposite to the reinforcing beam (31), of the upper connecting plate (321) through a connecting cylinder (324), and a plurality of mounting seats (325) assembled with the final stage power system (9) are arranged on the lower end face of the lower connecting plate;
and the stiffening plate (323) is connected among the upper connecting plate (321), the lower connecting plate (322) and the connecting cylinder (324) and is arranged corresponding to the mounting seats (325).
7. The launch vehicle final stage structure according to claim 2, characterized in that the side wall (41) of the reinforcing corner box (4) close to the inner wall of the instrument pod (2) is provided with a plurality of first mounting holes for connecting the inner wall of the instrument pod (2); a plurality of second mounting holes for connecting the reinforcing beam (31) are formed in the bottom wall (42) of the reinforcing corner box (4) for bearing the reinforcing beam (31); the bottom wall (42) and the side wall (41) of the reinforcing corner box (4) are perpendicular.
8. The carrier rocket final stage structure according to claim 7, wherein a reinforcing corner block (43) is further connected to the lower end face of the bottom wall (42) of the reinforcing corner box (4), and a plurality of third mounting holes for connecting the inner wall of the instrument shelter (2) are formed in the side wall (41) of the reinforcing corner block (43) close to the inner wall of the instrument shelter (2).
9. A launch vehicle final stage structure according to claim 1, characterised in that a satellite support angle box (7) for providing support for a satellite support is connected to the upper part of the inner wall of the instrument pod (2).
10. A launch vehicle final stage structure according to claim 1, characterised in that the inner surfaces of the power pod (1) and the instrument pod (2) are provided with grid reinforcement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911389997.3A CN111023913A (en) | 2019-12-27 | 2019-12-27 | Carrier rocket final-stage structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911389997.3A CN111023913A (en) | 2019-12-27 | 2019-12-27 | Carrier rocket final-stage structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111023913A true CN111023913A (en) | 2020-04-17 |
Family
ID=70199306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911389997.3A Pending CN111023913A (en) | 2019-12-27 | 2019-12-27 | Carrier rocket final-stage structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111023913A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN112611269A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket |
| CN113022899A (en) * | 2020-12-09 | 2021-06-25 | 北京星际荣耀空间科技股份有限公司 | External camera mounting structure of carrier rocket |
| CN114061378A (en) * | 2021-11-03 | 2022-02-18 | 天津爱思达航天科技有限公司 | Cabin section split reinforcing structure |
-
2019
- 2019-12-27 CN CN201911389997.3A patent/CN111023913A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN113022899A (en) * | 2020-12-09 | 2021-06-25 | 北京星际荣耀空间科技股份有限公司 | External camera mounting structure of carrier rocket |
| CN112611269A (en) * | 2021-02-04 | 2021-04-06 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket |
| CN112611269B (en) * | 2021-02-04 | 2021-07-02 | 北京星际荣耀空间科技股份有限公司 | Carrier rocket |
| CN114061378A (en) * | 2021-11-03 | 2022-02-18 | 天津爱思达航天科技有限公司 | Cabin section split reinforcing structure |
| CN114061378B (en) * | 2021-11-03 | 2023-09-01 | 天津爱思达航天科技有限公司 | Cabin section split reinforcing structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111023913A (en) | Carrier rocket final-stage structure | |
| CN111703592B (en) | Large commercial remote sensing satellite platform configuration and assembly method | |
| CN101381003A (en) | Main load-carrying structure of spacecraft | |
| US8740150B2 (en) | Connection of a wing to a fuselage of an airplane | |
| RU2657650C1 (en) | Multicopter frame (options) | |
| US6758439B2 (en) | Apparatuses and methods for attaching engine nacelles to aircraft | |
| CN112611269B (en) | Carrier rocket | |
| KR20180041654A (en) | Subfloor structure with an integral hull for a rotary wing aircraft | |
| CN211696095U (en) | Carrier rocket final-stage structure | |
| US11220347B2 (en) | Modular subfloor arrangement for an aircraft | |
| CN110562499B (en) | Wall-mounted main frequency adjustable variable-section one-rocket multi-satellite launching moonlet structure | |
| CN117073471B (en) | Load cabin of satellite carrier rocket and satellite carrier rocket | |
| Mierheim et al. | A Trade of Study for the Structure of the CALLISTO Vehicle Equipment Bay | |
| CN211685683U (en) | Instrument mounting panel structure of carrier rocket | |
| US6499692B2 (en) | Suspension for air generation units in aircraft | |
| CN112455721B (en) | Large-bearing modular service cabin structure | |
| US20230278731A1 (en) | Airframe and motor assembly for an unmanned aircraft | |
| CN218368317U (en) | Power battery mounting structure and aircraft that has it | |
| CN218662354U (en) | Lower body assembly of multi-rotor aircraft and multi-rotor aircraft | |
| CN218578040U (en) | Full-frame satellite | |
| Watson | AV-$ B Composite Fuselage Design | |
| CN114537709B (en) | Load embedded type installation satellite platform configuration and assembly method thereof | |
| CN218258680U (en) | EVTOL aircraft wing connection structure | |
| CN111792056B (en) | Bearing and satellite-rocket connection integrated satellite structural slab | |
| US20230159179A1 (en) | Engine pylon for coupling a jet engine to a wing of an aircraft |
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 | ||
| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Applicant 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 Applicant before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. Applicant before: Beijing Star glory Technology Co.,Ltd. |
|
| CB02 | Change of applicant information |