CN107063007A - A kind of carrier rocket boost motor tank structure for biasing concentrated force - Google Patents
A kind of carrier rocket boost motor tank structure for biasing concentrated force Download PDFInfo
- Publication number
- CN107063007A CN107063007A CN201710356685.7A CN201710356685A CN107063007A CN 107063007 A CN107063007 A CN 107063007A CN 201710356685 A CN201710356685 A CN 201710356685A CN 107063007 A CN107063007 A CN 107063007A
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- CN
- China
- Prior art keywords
- biasing
- concentrated force
- stiffened panel
- tank structure
- material stiffened
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Classifications
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The present invention provides a kind of carrier rocket boost motor tank structure for biasing concentrated force, the structure includes preceding brevicone, preceding bottom, cylinder section, rear cabinet bottom and rear brevicone, five parts constitute whole tank structure by circumferential welded seam, and formation can store propellant and bear the sealing container of various load.It is integral that preceding brevicone is just putting outer Material Stiffened Panel welding by one piece of outer Material Stiffened Panel of radiation and two pieces；Cylinder section Material Stiffened Panel and tilting interior Material Stiffened Panel in the mixing with concentrated force diffusion function [are constituted.The present invention solves carrying and diffusion problem of the carrier rocket boost motor tank to biasing concentrated force, so that biasing concentrated force becomes even distributed force by tank structure diffusion, good mechanical environment, the features such as tank structure of the invention has strong bearing capacity, high structure efficiency and good concentrated force diffusion effect are provided for nacelle behind tank.
Description
Technical field
The present invention relates to carrier rocket tank construction applications, more particularly to a kind of carrier rocket boost motor for biasing concentrated force
Tank structure.
Technical background
Carrier rocket tank is mainly used in the propellant needed for tank rocket flight, and bears the various load of rocket.Often
Advise tank structure erect on ground and flight course in generally by the active force being distributed uniformly and circumferentially, therefore conventional storage
The structures such as brevicone, the cylinder section of case generally use symmetrical Material Stiffened Panel structure.And the XX high thrusts binding delivery fire of domestic a new generation
Arrow, using core level plus the configuration of four liquid boosters, liquid booster is bundled in the surrounding of core level, each boost motor top side
Wall carries out structure with core level by single binding point and is connected, the tank of boost motor front end due to close to binding by larger
Concentrated force is biased, in order to provide good mechanical environment to nacelle below, it is desirable to which boost motor tank allows for expanding concentrated force
Dissipating turns into even distributed force, and carrying and diffusion that conventional tank structure can not meet above-mentioned biasing concentrated force are required.Current country's nothing
The tank structure of requirement of similarity, also not yet collects abroad similar data.
To overcome above mentioned problem, the characteristic of biasing concentrated force, pin must be taken into full account in boost motor tank structure design
Diffusion to each position requires design corresponding construction, it is intended to realize carrying and diffusion of the biasing concentrated force on boost motor tank
It is required that.
The content of the invention
The present invention provides a kind of carrier rocket boost motor tank structure for biasing concentrated force, by preceding brevicone, preceding bottom, cylinder
Section, rear cabinet bottom and the part of rear brevicone five composition, five part constitute whole tank structure by circumferential welded seam, and formation can store
Deposit propellant and bear the sealing container of various load, biasing concentrated force gradually spreads to tank circumferencial direction from front to back, real
Now biasing concentrated force gradually diffuses into the function of even distributed force.
Further, the preceding brevicone is just being put outer Material Stiffened Panel and constituted by one piece of outer Material Stiffened Panel of radiation and two pieces, wallboard week
It is identical to width, it is integral by being welded to connect；
Wherein, the outer Material Stiffened Panel of the radiation of preceding brevicone is arranged in the side for bearing to bias concentrated force, by radiating outer reinforcement
Wallboard realizes the preliminary diffusion along the circumferential direction of biasing concentrated force, and two pieces are just being put outer Material Stiffened Panel to be arranged in radiation additional
The both sides of muscle wallboard, for bearing other even distributed forces.
Further, the cylinder section is used in the side of biasing concentrated force just puts reinforcement in muscle and the combined mixing of tilting muscle
Wallboard, for bearing and spreading biasing concentrated force, remaining position uses tilting interior Material Stiffened Panel, for bearing even distributed force.
Wherein, the circumferential width of Material Stiffened Panel gradually increases along the direction away from biasing concentrated force in the mixing of cylinder section
Greatly, the complete diffusion of biasing concentrated force along the circumferential direction is realized.
Arranged moreover, the longitudinal seam of cylinder section interlocks 45 ° with circumferential welded seam, the reliability for improving weld seam.
As can be seen here, a kind of carrier rocket boost motor tank structure for biasing concentrated force that the present invention is provided can solve the problem that storage
The carrying of biasing concentrated force and diffusion problem on case so that biasing concentrated force becomes uniform by the tank structure diffusion of the present invention
Power, good mechanical environment is provided for nacelle behind tank, and the tank structure has that bearing capacity is strong, structure efficiency is high and concentrates
The features such as power diffusion effect is good.
Brief description of the drawings
Fig. 1 and Fig. 2 are a kind of carrier rocket boost motor tank structural representations of biasing concentrated force of the present invention.
Wherein：1 is preceding bottom；2 be preceding brevicone；3 be cylinder section；4 be rear cabinet bottom；5 be rear brevicone；6 be the outer reinforcement wall of radiation
Plate；7 be just to put outer Material Stiffened Panel；8 be circumferential welded seam；9 be longitudinal seam；10 be Material Stiffened Panel in mixing；11 be to add in tilting
Muscle wallboard；12 is just put muscle, and 13 be tilting muscle.
Embodiment
In order to be fully clear from disclosing present invention, the present invention is further elaborated below in conjunction with the accompanying drawings.
The present invention provides a kind of carrier rocket boost motor tank structure for biasing concentrated force, and the structure includes preceding brevicone 2, preceding
Bottom 1, cylinder section 3, rear cabinet bottom 4 and rear brevicone 5, as shown in Figure 1.Five parts constitute whole tank structure, shape by circumferential welded seam 8
Into can store propellant and bear the sealing container of various load.
Brevicone is just being put outer Material Stiffened Panel 7 and is being welded integral by one piece of outer Material Stiffened Panel 6 of radiation and two pieces before described in Fig. 1,
The outer Material Stiffened Panel arrangement 6 of radiation is bearing the side of biasing concentrated force, passes through and radiates the outer realization of Material Stiffened Panel 6 biasing concentrated force edge
The preliminary diffusion of circumferencial direction, and two pieces are just being put outer Material Stiffened Panel 7 and are being arranged in the both sides for radiating outer Material Stiffened Panel 6, are used for
Bear other even distributed forces.
The section of cylinder described in Fig. 1 uses just to put in muscle 12 and the combined mixing of tilting muscle 13 in the side of biasing concentrated force to be added
Muscle wallboard 10, for bearing and spreading biasing concentrated force, remaining position uses tilting interior Material Stiffened Panel 11, uniform for bearing
Power.
Wherein, the circumferential width of Material Stiffened Panel 10 gradually increases along the direction away from biasing concentrated force in the mixing of cylinder section
Greatly, the complete diffusion of biasing concentrated force along the circumferential direction is realized, diffusion schematic diagram is as shown in Figure 2.
The longitudinal seam 9 of cylinder section 3 interlocks 45 ° with circumferential welded seam 8 arranges, the reliability for improving weld seam.
The foregoing is only a preferred embodiment of the present invention, but protection scope of the present invention be not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with scope of the claims
It is defined.
Claims (6)
1. a kind of carrier rocket boost motor tank structure for biasing concentrated force, it is characterised in that：By preceding brevicone, preceding bottom, cylinder section,
Rear cabinet bottom and the part of rear brevicone five composition, five part constitute whole tank structure by circumferential welded seam, and formation can be stored
Propellant and the sealing container for bearing various load, biasing concentrated force gradually spread to tank circumferencial direction from front to back, realize
Biasing concentrated force gradually diffuses into the function of even distributed force.
2. the carrier rocket boost motor tank structure of biasing concentrated force according to claim 1, it is characterised in that：Before described
Brevicone is just being put outer Material Stiffened Panel and constituted by one piece of outer Material Stiffened Panel of radiation and two pieces, and wallboard circumferential width is identical, passes through the company of welding
It is connected into entirety.
3. the carrier rocket boost motor tank structure of biasing concentrated force according to claim 2, it is characterised in that：It is described to put
Penetrate outer Material Stiffened Panel and be arranged in the side for bearing to bias concentrated force, biasing concentrated force is realized circumferentially by radiating outer Material Stiffened Panel
The preliminary diffusion in direction, and two pieces are just being put outer Material Stiffened Panel and are being arranged in the both sides for radiating outer Material Stiffened Panel, for bearing it
His even distributed force.
4. the carrier rocket boost motor tank structure of biasing concentrated force according to claim 1, it is characterised in that：The cylinder
Section uses in the side of biasing concentrated force and just puts Material Stiffened Panel in muscle and the combined mixing of tilting muscle, for bearing and spreading partially
Concentrated force is put, remaining position uses tilting interior Material Stiffened Panel, for bearing even distributed force.
5. the carrier rocket boost motor tank structure of biasing concentrated force according to claim 4, it is characterised in that：Described
The circumferential width of Material Stiffened Panel gradually increases along the direction away from biasing concentrated force in mixing, realizes biasing concentrated force edge
The complete diffusion of circumferencial direction.
6. the carrier rocket boost motor tank structure of biasing concentrated force according to claim 4, it is characterised in that：The cylinder
The longitudinal seam of section interlocks 45 ° with circumferential welded seam arranges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710356685.7A CN107063007A (en) | 2017-05-19 | 2017-05-19 | A kind of carrier rocket boost motor tank structure for biasing concentrated force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710356685.7A CN107063007A (en) | 2017-05-19 | 2017-05-19 | A kind of carrier rocket boost motor tank structure for biasing concentrated force |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107063007A true CN107063007A (en) | 2017-08-18 |
Family
ID=59609439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710356685.7A Pending CN107063007A (en) | 2017-05-19 | 2017-05-19 | A kind of carrier rocket boost motor tank structure for biasing concentrated force |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107063007A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN109854413A (en) * | 2019-03-13 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Tank cylinder section, tank and rocket |
| CN110901955A (en) * | 2019-12-06 | 2020-03-24 | 上海宇航系统工程研究所 | Storage box with frame and truss structure |
| CN111173645A (en) * | 2019-11-27 | 2020-05-19 | 上海宇航系统工程研究所 | Liquid rocket storage tank binding structure |
| CN111762343A (en) * | 2020-06-09 | 2020-10-13 | 上海宇航系统工程研究所 | Throwing-off double-component annular storage tank for spacecraft |
| CN112832927A (en) * | 2021-01-21 | 2021-05-25 | 江苏深蓝航天有限公司 | Fuel storage tank |
| CN115783313A (en) * | 2022-11-09 | 2023-03-14 | 上海空间推进研究所 | Annular on-orbit propellant screen collector surface and tension storage tank |
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| RU2412088C1 (en) * | 2009-11-30 | 2011-02-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Rocket booster |
| CN103455644A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Liquid propellant dynamics analogy method based on coupling quality |
| RU2561154C2 (en) * | 2014-06-11 | 2015-08-27 | Александр Тимофеевич Корабельников | Method of carrying out acceleration of carrier-rockets |
| CN105834028A (en) * | 2015-01-13 | 2016-08-10 | 上海航天设备制造总厂 | Automatic spray system and method for heat insulating layer of cryogenic tank of rocket |
| CN106481483A (en) * | 2016-10-01 | 2017-03-08 | 北京宇航系统工程研究所 | A kind of have big concentration power, the tank of integrated diffusion structure |
| CN106528928A (en) * | 2016-10-01 | 2017-03-22 | 北京宇航系统工程研究所 | Wave distribution radial type storage box short shell |
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- 2017-05-19 CN CN201710356685.7A patent/CN107063007A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2412088C1 (en) * | 2009-11-30 | 2011-02-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Rocket booster |
| CN103455644A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Liquid propellant dynamics analogy method based on coupling quality |
| RU2561154C2 (en) * | 2014-06-11 | 2015-08-27 | Александр Тимофеевич Корабельников | Method of carrying out acceleration of carrier-rockets |
| CN105834028A (en) * | 2015-01-13 | 2016-08-10 | 上海航天设备制造总厂 | Automatic spray system and method for heat insulating layer of cryogenic tank of rocket |
| CN106481483A (en) * | 2016-10-01 | 2017-03-08 | 北京宇航系统工程研究所 | A kind of have big concentration power, the tank of integrated diffusion structure |
| CN106528928A (en) * | 2016-10-01 | 2017-03-22 | 北京宇航系统工程研究所 | Wave distribution radial type storage box short shell |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107676194A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| CN107676195A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of cover plate connection |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN107676196B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of connection of cover board can blocking type rocket engine propellant bias spray panel |
| CN107676194B (en) * | 2017-09-12 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of modularization rocket engine propellant biasing spray panel of threaded connection |
| CN108569422A (en) * | 2018-02-11 | 2018-09-25 | 浙江兆华机械制造有限公司 | A kind of rocket segmental structure |
| CN109854413A (en) * | 2019-03-13 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Tank cylinder section, tank and rocket |
| CN109854413B (en) * | 2019-03-13 | 2024-03-01 | 北京星际荣耀空间科技股份有限公司 | Tank section, tank and rocket |
| CN111173645A (en) * | 2019-11-27 | 2020-05-19 | 上海宇航系统工程研究所 | Liquid rocket storage tank binding structure |
| CN111173645B (en) * | 2019-11-27 | 2022-08-26 | 上海宇航系统工程研究所 | Liquid rocket storage tank binding structure |
| CN110901955A (en) * | 2019-12-06 | 2020-03-24 | 上海宇航系统工程研究所 | Storage box with frame and truss structure |
| CN111762343A (en) * | 2020-06-09 | 2020-10-13 | 上海宇航系统工程研究所 | Throwing-off double-component annular storage tank for spacecraft |
| CN111762343B (en) * | 2020-06-09 | 2023-09-08 | 上海宇航系统工程研究所 | Throwable double-component annular storage tank for spacecraft |
| CN112832927A (en) * | 2021-01-21 | 2021-05-25 | 江苏深蓝航天有限公司 | Fuel storage tank |
| CN112832927B (en) * | 2021-01-21 | 2022-05-31 | 江苏深蓝航天有限公司 | Fuel storage tank |
| CN115783313A (en) * | 2022-11-09 | 2023-03-14 | 上海空间推进研究所 | Annular on-orbit propellant screen collector surface and tension storage tank |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170818 |