CN110736394B - Assembling process for tail section of split rocket - Google Patents
Assembling process for tail section of split rocket Download PDFInfo
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- CN110736394B CN110736394B CN201911028175.2A CN201911028175A CN110736394B CN 110736394 B CN110736394 B CN 110736394B CN 201911028175 A CN201911028175 A CN 201911028175A CN 110736394 B CN110736394 B CN 110736394B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
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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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Abstract
The invention discloses a split rocket tail section assembly process, which comprises the steps of providing a lower half cover and an upper half cover, and enabling the lower half cover and the upper half cover to move to a preset position from the tail end of a rocket engine along the outer side of the rocket in the axial direction; and butting the upper half cover and/or the lower half cover with the adjacent end surface of the rocket tail section, and butting the two half covers with each other. Compared with the prior art, the whole process has the advantages that the tail end is divided into the lower half cover and the upper half cover to be independent parts, the lower half cover and the upper half cover are butted, the two half covers are butted with the adjacent end faces of the rocket, the form is novel, the operation is simple, the tail section structure does not need to be greatly adjusted, the engine can be ingeniously avoided, and the problem that when a plurality of rocket engine machines are connected in parallel, and the maximum envelope size of the engine is large, the tail section can not be normally butted integrally is solved.
Description
Technical Field
The invention relates to the field of rocket assembly, in particular to a split rocket tail section assembly process.
Background
Large launch vehicles are heavy and large in size, and usually their bodies are manufactured in sections, and then the sections are assembled and connected to each other.
At present, the carrier rocket assembly in China mostly adopts single-section horizontal assembly. Namely, the rocket single section is placed on the copying bracket vehicle, and the driving is carried out the butt joint of all the sections through the slide rail below. Because the maximum size envelope of an engine does not exceed 3350 size in the traditional domestic rocket model with 3350 size, the tail section assembly and other sections all adopt an integral butt joint mode. In some rockets under study, in order to improve the carrying capacity of the rocket, a plurality of rocket engine machines are required to be connected in parallel, so that the maximum size envelope of the engine exceeds 3350 size, and the tail section cannot be butted in a conventional mode.
The invention provides a split rocket tail section assembly process, which is novel in form and simple in operation, does not need to greatly adjust the tail section structure, can skillfully avoid an engine, and well solves the problems.
Disclosure of Invention
The invention aims to provide a split rocket tail section assembly process, which is novel in form and simple to operate, does not need to greatly adjust the tail section structure, and can skillfully avoid an engine.
In order to achieve the purpose, the invention provides the following technical scheme: a split rocket tail section assembly process comprises the following steps:
providing a lower half cover and an upper half cover, and enabling the lower half cover and the upper half cover to move to a preset position from the tail end of the rocket engine along the outer side of the rocket axial direction;
and butting the upper half cover and/or the lower half cover with the adjacent end surface of the rocket tail section, and butting the two half covers with each other.
Further, before moving the lower half cowl and the upper half cowl from the aft end of the rocket engine to a predetermined position, respectively, outside in the rocket circumferential direction, the method includes: and performing mutual pre-butt joint treatment on the lower half cover and the upper half cover on the outer side of the engine in the rocket body axis direction.
Further, the rocket to be assembled is provided with four engines which are arranged in parallel, when the rocket is in a state to be assembled, the first engine and the second engine are located below the third engine and the fourth engine, when the lower half cover and the upper half cover are in pre-butt joint with each other, the lower half cover is located at the lower parts of the first engine and the second engine, the upper half cover is located at the upper parts of the third engine and the fourth engine, the outer end surfaces of the nozzles of the first engine and the second engine and the outer end surfaces of the nozzles of the third engine and the fourth engine are symmetrical to each other relative to a symmetry line, an included angle between the symmetry line and the butt joint surface of the lower half cover and the upper half cover is A, and A is more than 10 degrees and less than 12 degrees.
Further, pre-docking the lower half cover and the upper half cover to each other includes: moving the lower half cover and the upper half cover away from each other; moving the upper half cover and/or the lower half cover to a predetermined position along the axial direction of the rocket; moving the upper half cover and/or the lower half cover to the adjacent end surface to be attached at the preset position; and butting the upper half cover and/or the lower half cover with the adjacent end face, and butting the two half covers with each other.
Further, the lower half cover is placed on the driving, and the position of the lower half cover is adjusted by moving the driving.
Further, the method also comprises the following steps: after the lower half cover is placed on the car rack, the height of the driving support is adjusted to fall by a safe distance N; driving to drive the lower half cover to horizontally move along the rocket axis direction to a position with the axial distance M from the adjacent end surface and stop moving; the driving bracket moves upwards, and the moving height is N; and driving the rocket body to horizontally move along the axial direction of the rocket body so as to ensure that the end surface of the lower half cover is attached to the adjacent end surface.
Furthermore, the safe distance N is more than or equal to 300mm and less than or equal to 400 mm.
Furthermore, M is more than or equal to 100mm and less than or equal to 400 mm.
Further, the upper half cover is moved and adjusted in position by the crane.
Further, one end of the upper half cover is connected with a lifting machine, and the lifting machine is used for lifting the upper half cover upwards by a height N' through a rope; along the axial direction of the rocket, the crane drives the upper half cover to horizontally move to a position with the axial distance M' from the adjacent end face and stop moving; the upper half cover is descended downwards by the crane by a rope to a height N'; so that the end face of the upper half cover is attached to the adjacent end face, N 'is more than or equal to 300mm and less than or equal to 400mm, and M' is more than or equal to 100mm and less than or equal to 400 mm.
Compared with the prior art, the invention has the beneficial effects that: the assembling process of the tail section of the split rocket comprises the steps of providing a lower half cover and an upper half cover, and enabling the lower half cover and the upper half cover to move to a preset position from the tail end of a rocket engine along the outer side of the rocket in the axial direction; and butting the upper half cover and/or the lower half cover with the adjacent end surface of the rocket tail section, and butting the two half covers with each other. The whole assembly process is novel in form and simple in operation, does not need to greatly adjust the tail section structure, can skillfully avoid the engine, and solves the problem that when a plurality of rocket engine machines are connected in parallel, the tail section can not be normally butted integrally when the maximum size envelope of the engine exceeds 3350 size.
Drawings
FIG. 1 is a right side view of the lower and upper housing halves of the present invention shown in a displaced position;
FIG. 2 is a front view of the rocket of the present invention;
FIG. 3 is a perspective view of the upper half shell of the present invention;
FIG. 4 is a perspective view of the lower cover half of the present invention;
FIG. 5 is a right side view of the upper half shell and the lower half shell of the present invention abutting each other;
FIG. 6 is a front view of the connection of the upper half shell to the lower half shell of the present invention;
fig. 7 is a schematic structural view of the connector of the present invention.
Description of reference numerals:
1 lower half cover 2 upper half cover
3 adjacent end faces 4 first engine
5 second engine 6 third engine
7 fourth engine 8-frame vehicle
9 crane 10 butt joint face
11 symmetrical line 12 connecting piece
13 fixing bolt
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc., do not denote any order or sequence, nor are they used to limit the present invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
The embodiment of the invention provides a split rocket tail section assembly process, which comprises the steps of providing a lower half cover 1 and an upper half cover 2, wherein the lower half cover 1 is provided with a first half cover and the upper half cover 2 is provided with a second half cover; moving the lower half cover 1 and the upper half cover 2 to a predetermined position from the side of the tail end of the rocket engine respectively; the lower half cover 1 and the upper half cover 2 are butted with each other and with the adjacent end face 3 of the rocket.
Specifically, the method comprises the following steps: the assembling process of the tail section of the split rocket comprises the steps of providing a lower half cover 1 and an upper half cover 2; moving the lower half cover 1 and the upper half cover 2 from the tail end of the rocket engine to a predetermined position along the outer side of the rocket axial direction; the upper half-cowl 2 and/or the lower half-cowl 1 are butted against the adjacent end faces of the rocket tail section, and the two half-cowls are butted against each other.
The whole process comprises the steps of dividing the tail end into a lower half cover 1 and an upper half cover 2 (for example, the two half covers can be divided into two independent components which are divided into two parts and are divided into two parts, namely the two parts and the two parts, relative to the tail end, and the plane which passes through the axis is divided into two parts, and adjusting the positions of the lower half cover 1 and the upper half cover 2 to enable the lower half cover 1 and the upper half cover 2 to respectively move to a preset position from the tail end of a rocket engine along the outer side of the rocket body in the axial direction, so that the lower half cover 1 and the upper half cover 2 are butted and then butted with the adjacent end faces of the rocket, and the tail end faces of the rocket are butted.
As shown in fig. 3, 4 and 5, before moving the lower half cowl 1 and the upper half cowl 2 from the side of the tail end of the rocket engine to the predetermined positions, respectively, the method includes: in order to ensure that the lower half cover 1 and the upper half cover 2 are connected more accurately, the lower half cover 1 and the upper half cover 2 are subjected to mutual pre-butt joint treatment on the outer side of the engine in the arrow body axis direction, so that the butt joint effect of the upper half cover and the lower half cover can be reliably tested, and the butt joint efficiency is improved.
It is further noted that the rocket to be assembled has four engines arranged in parallel, as shown in figure 5. And the first engine 4 and the second engine 5 are positioned below the third engine 6 and the fourth engine 7 when the rocket is in a state of waiting to be assembled. When the lower half cowl 1 and the upper half cowl 2 are pre-butted against each other, the lower half cowl 1 is located below the first engine and the second engine 5 (i.e., located outside the rocket engine in the axial direction and corresponding to a spatial position of a formal butt position of the lower half cowl, which corresponds to a translation from a final butt position of the lower half cowl to an outer side of the rocket body in the axial direction of the rocket body), and the upper half cowl 2 is located above the third engine 6 and the fourth engine 7 (i.e., located outside the rocket engine in the axial direction and corresponding to a spatial position of a formal butt position of the upper half cowl, which corresponds to a translation from a final butt position of the upper half cowl to an outer side of the rocket body in the axial direction of the rocket body).
For convenience of installation, the condition that the lower half cover 1 and the upper half cover 2 touch a rocket engine pipeline in the installation process is avoided, and the angle of the butt joint surface of the upper half cover and the lower half cover needs to be set. The rocket of an embodiment of the application is provided with four engines in parallel, wherein the outer end surfaces of the nozzles of the first engine 4 and the second engine 5, the outer end surfaces of the nozzles of the third engine 6 and the fourth engine 7 are symmetrical with each other relative to a symmetry line 11 (in a plane where the outer end surfaces of the nozzles of the engines are located, the four engines are distributed in quadrants, the symmetry line 11 is coincident with one coordinate axis, the first engine and the second engine are located on the lower side of the symmetry line, and the third engine and the fourth engine are located on the upper side of the symmetry line). For example, through simulation research on the upper half cover, the lower half cover and four engines, when the included angle a between the symmetry line 11 and the abutting surface 10 of the lower half cover 1 and the upper half cover 2 is 11.5 °, the half cover installation process can be simplified, and the installation efficiency can be improved. In addition, according to the size of the rocket engine and the installation mode thereof, the angle formed by the butt joint surface 10 of the lower half cover 1 and the upper half cover 2 and the symmetry line 11 can be adjusted adaptively, and A is more than or equal to 10 degrees and less than or equal to 12 degrees through calculation.
Further, as shown in fig. 2, 3 and 4, the pre-joining of the lower half shell 1 and the upper half shell 2 to each other, and the pre-joining of the lower half shell 1 and the upper half shell 2 to each other, includes: moving the lower half shell 1 and the upper half shell 2 away from each other, for example, may be away from each other in a vertical direction; moving the upper half cover 2 and/or the lower half cover 1 to a preset position along the axial direction of the rocket; moving the upper half cover 2 and/or the lower half cover 1 to the adjacent end face 3 to be attached at a preset position; and butting the upper half cover 2 and/or the lower half cover 1 with the adjacent end face 3, and butting the two half covers with each other.
Specifically, as shown in fig. 1 and 2, the lower half cover 1 is placed on the driver, and the position of the lower half cover 1 is adjusted by moving the driver 8, so that the lower half cover 1 is attached to the adjacent end face 3.
It should be noted that after the lower half cover 1 is placed on the car shelving 8, the height of the driving support can be adjusted to fall by a safe distance N (the height is relative to the final mounting position of the lower half cover at the tail section); driving 8 to drive the lower half cover 1 to horizontally move along the rocket axis direction to a position with the axial distance M from the adjacent end face 3 to stop moving; the bracket of the driving 8 moves upwards, and the moving height is N; and the driving vehicle horizontally moves along the axial direction of the rocket body so that the end surface of the lower half cover 1 is attached to the adjacent end surface 3. In the moving process of the driving support, the levelness of the driving support is detected through the level meter, and the levelness of the two ends of the driving support 8 can meet the preset requirement through adjustment of the support. It should be mentioned that, in order to ensure the installation progress and facilitate observation, the safe distance N is 300mm or more and N is 400mm or less, and M is 100mm or more and M is 400mm or less through multiple measurement and calculation.
Specifically, as shown in fig. 1 and 2, the upper half shell 2 may be moved by a crane, and the position of the upper half shell 2 may be adjusted so that the upper half shell 2 is butted against the adjacent end face 3. Specifically, one end of the upper half shell 2 is connected to a crane 9, and the crane 9 lifts the upper half shell 2 by a rope by a height N' (with respect to the final position of the upper half shell at the rocket); along the axial direction of the rocket, the hoisting machine 9 drives the upper half cover 2 to horizontally move to a position with the axial distance M' from the adjacent end face 3 and stop moving; the upper half cover 2 is descended downwards by the crane 9 by a height N' through a rope; the crane 9 drives the upper half cover 2 to move horizontally along the arrow body axis direction, so that the end surface of the upper half cover 1 is attached to the adjacent end surface, N 'is more than or equal to 300mm and less than or equal to 400mm, and M' is more than or equal to 100mm and less than or equal to 400 mm.
That is, the lower half cover is driven, the upper half cover is lifted by a crane, and the two move away from each other (for example, the lower half cover moves downwards by N, and the upper half cover moves upwards by N ') before overlapping with the engine structure, then move towards the engine side along the rocket body axis direction, and move to the position where the maximum envelope outer dimension of the engine can be avoided, move to the opposite direction by the distance (namely, the upper half cover descends by N', the lower half cover ascends by N), and continue to move along the rocket body axis direction until the lower half cover is attached to the adjacent end face.
In the process of hoisting the upper half-cover 2 by the hoisting machine 9, the two ends of the hoisting machine 9 are provided with pressure sensors to measure the pressure of the ropes at the two ends of the hoisting machine 9, so that the upper half-cover 2 can be ensured to move stably under the driving of the hoisting machine.
It should be particularly noted that, for convenience of operation and recording, when taking values, N ' or M ' may be designed, for example, N ' or 350mm or N350 mm; m' is 200mm, M is 200 mm.
It is noted that, in order to improve the installation efficiency, the lower half shell 1 and the upper half shell 2 may be moved simultaneously after the pre-butt process of the lower half shell 1 and the upper half shell 2.
In addition, as shown in fig. 3, 4, 6 and 7, in order to ensure that the lower half cover 1 and the upper half cover 2 are connected more tightly, the lower half cover 1 and the upper half cover 2 are provided with mutually matched connecting pieces 12. The lower half cover 1 and the upper half cover 2 are mutually butted by adopting the fixing bolts 13, after the mutual butt joint is completed, the gap at the joint of the lower half cover 1 and the upper half cover 2 needs to be detected by a crack width detector, when the gap is not qualified (too large or too small), the fixing bolts 13 need to be adjusted, so that the gap is qualified, the stress of each fixing bolt 13 is ensured to be kept consistent, and then the lower half cover 1 and the upper half cover 2 are tightly connected, thereby being convenient for the stability of the rocket.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (9)
1. A split rocket tail section assembly process is characterized by comprising the following steps:
providing a lower half cover and an upper half cover;
performing mutual pre-butt joint treatment on the lower half cover and the upper half cover on the outer side of the engine in the rocket body axis direction;
moving the lower half cowl and the upper half cowl from a rocket engine aft end to a predetermined position outside in a rocket axial direction;
and butting the upper half cover and/or the lower half cover with the adjacent end surface of the rocket tail section, and butting the two half covers with each other.
2. The split rocket tail section assembling process according to claim 1, wherein the rocket to be assembled has four engines arranged in parallel, and when the rocket is in a state to be assembled, the first engine and the second engine are positioned below the third engine and the fourth engine, when the lower half cover and the upper half cover are pre-butted with each other, the lower half cover is positioned at the lower part of the first engine and the second engine, the upper half cover is positioned at the upper part of the third engine and the fourth engine, the outer nozzle end faces of the first engine and the second engine and the outer nozzle end faces of the third engine and the fourth engine are symmetrical to each other relative to a symmetry line, and the angle between the symmetry line and the butting face of the lower half cover and the upper half cover is A, wherein A is more than 10 degrees and less than 12 degrees.
3. The assembly process of a split rocket tail section according to claim 1, wherein pre-docking the lower half-cap and the upper half-cap to each other comprises:
moving the lower half cover and the upper half cover away from each other;
moving the upper half cover and/or the lower half cover to a predetermined position along the axial direction of the rocket;
moving the upper half cover and/or the lower half cover to the adjacent end surface to be attached at the preset position; and
and abutting the upper half cover and/or the lower half cover with the adjacent end face, and abutting the two half covers with each other.
4. The assembly process of a split rocket tail section according to claim 3, further comprising: and placing the lower half cover on the driving, and adjusting the position of the lower half cover by moving the driving.
5. The assembly process of a split rocket tail section according to claim 4, further comprising:
after the lower half cover is placed on the car rack, the height of the driving support is adjusted to fall by a safe distance N;
driving to drive the lower half cover to horizontally move along the rocket axis direction to a position with the axial distance M from the adjacent end surface and stop moving;
the driving bracket moves upwards, and the moving height is N;
and driving the rocket body to horizontally move along the axial direction of the rocket body so as to ensure that the end surface of the lower half cover is attached to the adjacent end surface.
6. The assembly process of the tail section of a split rocket according to claim 5, wherein the safe distance N is 300mm or more and 400mm or less.
7. The assembly process of the tail section of a split rocket according to claim 5, wherein M is 100mm or more and 400mm or less.
8. A process of assembling a split rocket tail section according to claim 5, wherein the upper half-cover is moved and adjusted in position by a crane.
9. The assembly process of the tail section of a split rocket according to claim 8, wherein one end of the upper half casing is connected with a crane, and the crane lifts the upper half casing upwards by a height N' through a rope;
along the axial direction of the rocket, the crane drives the upper half cover to horizontally move to a position with the axial distance M' from the adjacent end face and stop moving;
the upper half cover is descended downwards by the crane by a rope to a height N';
and driving the upper half cover to horizontally move along the axis direction of the arrow body by a crane so as to ensure that the end surface of the upper half cover is attached to the adjacent end surface, wherein N 'is more than or equal to 300mm and less than or equal to 400mm, and M' is more than or equal to 100mm and less than or equal to 400 mm.
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| CN201911028175.2A CN110736394B (en) | 2019-10-28 | 2019-10-28 | Assembling process for tail section of split rocket |
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| CN201911028175.2A CN110736394B (en) | 2019-10-28 | 2019-10-28 | Assembling process for tail section of split rocket |
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| CN110736394B true CN110736394B (en) | 2020-11-06 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4023355A (en) * | 1972-02-24 | 1977-05-17 | Thiokol Corporation | Combination diffuser, thermal barrier, and interchamber valve for rockets |
| CN203949576U (en) * | 2014-05-29 | 2014-11-19 | 北京宇航系统工程研究所 | A kind of minor diameter rocket rear separates with falling impact housing |
| CN106078190B (en) * | 2016-07-07 | 2018-09-21 | 上海航天设备制造总厂 | The total Butt Assembling device and method of rocket level segment flexible digitalization |
| CN208070450U (en) * | 2018-02-27 | 2018-11-09 | 蓝箭航天技术有限公司 | A kind of packing case section for rocket |
| CN108871110B (en) * | 2018-05-28 | 2020-05-05 | 北京航空航天大学 | Rocket and assembling method thereof |
| CN113607006A (en) * | 2019-02-13 | 2021-11-05 | 蓝箭航天空间科技股份有限公司 | Pneumatic separation system for interstage separation in launch vehicles |
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