CN111113023A - Auxiliary device for assembling monopropellant liquid rocket engine and assembling method - Google Patents
Auxiliary device for assembling monopropellant liquid rocket engine and assembling method Download PDFInfo
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- CN111113023A CN111113023A CN202010011024.2A CN202010011024A CN111113023A CN 111113023 A CN111113023 A CN 111113023A CN 202010011024 A CN202010011024 A CN 202010011024A CN 111113023 A CN111113023 A CN 111113023A
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- rocket engine
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- liquid rocket
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
- B23P21/002—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control the units stationary whilst being composed
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Abstract
The invention provides an auxiliary device for assembling a single-component liquid rocket engine and an assembling method, wherein the auxiliary device comprises the following components: the device comprises a guide needle, an auxiliary bracket and a top block; the upper side of the top block is used for placing a collector of the head of the single-component thrust chamber; the height of the auxiliary support is higher than that of a head support of the head of the single-component thrust chamber, the lower part of the auxiliary support is detachably connected to the top block, and the upper part of the auxiliary support is used for supporting a head jetting plate of the head of the single-component thrust chamber; the guide needle is used for being respectively inserted into the mounting hole and the injection pipe of the head part of the single-component thrust chamber corresponding to the mounting hole. The ejector block effectively avoids the work of adjusting the extending heights of a large number of injection pipes after the original single-component liquid rocket engine is assembled, and is beneficial to improving the production efficiency. According to the invention, the mounting gap between the injection pipe and the injection plate mounting hole is manufactured through the height design of the auxiliary support, and the mounting guidance is realized through the guide needle, so that the phenomenon that the injection pipe is bent or damaged due to the undersize assembly gap is effectively avoided.
Description
Technical Field
The invention relates to the field of rocket assembly, in particular to an auxiliary device for assembling a single-component liquid rocket engine and an assembling method.
Background
The single-component engine has the characteristics of simple composition system, high single-machine working reliability and the like, and is widely applied to attitude control power systems in the fields of satellites, carrying, missile weapons and the like at present. With the continuous and deep exploration of outer space by human beings, the single-component engine is used as a part of power composition, and the great improvement is also realized. As the single-component engine has various thrust varieties and the thrust range is 1N-1000N, the single-component engine relates to nearly dozens of structural types, and a large-scale automatic production line mode is not suitable for processing and assembling the single-component engine. The manual operation of independent personnel, production efficiency is low, and manual assembly process easily produces the part damage simultaneously. Meanwhile, in the manual assembly process, due to the fact that the number of the injection pipes is too large, the injection pipes are prone to assembly dislocation, bending is caused in the injection pipe assembly process due to assembly, and the like.
Patent document CN104907809A discloses an adjustable assembly vehicle for assembling a liquid rocket engine rotor, which is mainly used for assembling the liquid rocket engine rotor and cannot solve the problem in the assembly process of a jet tube.
At present, no description or report of similar technologies to the technology of the invention is found at home, and similar data at home and abroad is not collected.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an auxiliary device for assembling a single-component liquid rocket engine and an assembling method.
According to the present invention, there is provided an auxiliary device for assembling a single-component liquid rocket engine, comprising: the device comprises a guide needle, an auxiliary bracket and a top block;
the upper side of the top block is used for placing a collector of a single-component thrust chamber head;
the height of the auxiliary support is higher than that of a head support of the head of the single-component thrust chamber, the lower part of the auxiliary support is detachably connected to the top block, and the upper part of the auxiliary support is used for supporting a head injection plate of the head of the single-component thrust chamber;
the guide needle is used for being respectively inserted into the mounting hole and the injection pipe of the head of the single-component thrust chamber corresponding to the mounting hole.
Preferably, the secondary support is located at the periphery of the collector.
Preferably, the guide needle is conical, the minimum outer diameter position of the guide needle is smaller than the inner diameter of the injection pipe, and the maximum outer diameter position of the guide needle is larger than the inner diameter of the injection pipe and smaller than the inner diameter of the mounting hole of the head injection plate.
Preferably, the auxiliary support is a split structure and comprises a first part and a second part.
Preferably, the height of the auxiliary support is 10-30mm higher than that of the head support of the single-component thrust chamber head.
Preferably, the top block is of a two-stage boss-shaped structure and comprises a substrate, a first-stage bump and a second-stage bump, the first-stage bump is arranged on the upper side of the substrate, and the second-stage bump is arranged on the upper side of the first-stage bump;
the collector is sleeved and positioned on the secondary convex block, and the lower part of the auxiliary support is detachably connected on the substrate outside the primary convex block.
Preferably, the height of the secondary projection is equal to the length of the injection tube which needs to extend out of the mounting hole.
According to the assembling method of the single-component liquid rocket engine provided by the invention, the auxiliary device for assembling the single-component liquid rocket engine is adopted, and the execution steps comprise:
s1, placing a collector on the upper side of the top block;
s2, assembling one end of the injection tube into the assembling hole of the collector;
s3, assembling a head support on the collector;
s4, placing a head injection plate on the upper part of the auxiliary bracket;
s5, inserting the guide needle into the mounting hole of the head injection plate and the corresponding injection tube from top to bottom;
s6, detaching the auxiliary bracket, and inserting the injection tube into the corresponding mounting hole of the injection plate of the injection part by utilizing the self gravity or the pressing action of the injection plate and the guiding action of the guide needle;
and S7, removing the guide needle.
Compared with the prior art, the invention has the following beneficial effects:
the ejector block effectively avoids the work of adjusting the extending heights of a large number of injection pipes after the original single-component liquid rocket engine is assembled, and is beneficial to improving the production efficiency.
According to the invention, the mounting gap between the injection pipe and the injection plate mounting hole is manufactured through the height design of the auxiliary support, and the mounting guidance is realized through the guide needle, so that the phenomenon that the injection pipe is bent or damaged due to the undersize assembly gap is effectively avoided.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a side view of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the present invention provides an auxiliary device for assembling a single-component liquid rocket engine, comprising: the device comprises three parts, namely a guide needle 1, an auxiliary bracket 2 and a top block 3. The upper side of the top block 3 is used for placing a collector 41 of the single-component thrust chamber head 4, the height of the auxiliary support 2 is higher than that of a head support 43 of the single-component thrust chamber head 4, the lower part of the auxiliary support 2 is detachably connected to the top block 3, the upper part of the auxiliary support 2 is used for supporting a head injection plate 44 of the single-component thrust chamber head 4, and the guide pins are respectively inserted into the mounting holes and injection pipes 42 of the single-component thrust chamber head 4 corresponding to the mounting holes.
The auxiliary bracket 2 is positioned at the periphery of the collector 41, and an accommodating space is formed inside the auxiliary bracket and is used for accommodating the components of the single-component thrust chamber head 4 except for the head injection plate 44. The height of the auxiliary bracket 2 is 10-30mm higher than that of the head bracket of the single-component thrust chamber head 4, so that the installation clearance of the injection pipe and the injection plate installation hole is formed. The auxiliary support 2 is of a split structure and comprises a first part and a second part, and the first part and the second part are respectively pulled out towards two sides when being detached.
The guide needle 1 is conical, the minimum outer diameter position is smaller than the inner diameter of the injection tube 42, and the maximum outer diameter position is larger than the inner diameter of the injection tube 42 and smaller than the inner diameter of the mounting hole of the head injection plate 44. The end with the smaller outer diameter is inserted into the mounting hole and the corresponding injection tube 42 of the single-component thrust chamber head 4 from top to bottom, so as to prevent the guide needle 1 from continuously sliding downwards from the mounting hole.
The top block 3 is of a two-stage boss-shaped structure and comprises a substrate, a first-stage lug and a second-stage lug, the first-stage lug is arranged on the upper side of the substrate, and the second-stage lug is arranged on the upper side of the first-stage lug. The collector 41 is sleeved and positioned on the secondary bump, and the secondary bump forms an installation positioning structure of the collector 41 to prevent the position deviation; the lower part of the auxiliary support 2 is detachably connected to the substrate on the outer side of the first-level bump, the auxiliary support 2 is limited by the side wall of the first-level bump to further move inwards, and the collector 41 is prevented from being damaged by the auxiliary support 2. The height of the secondary projection is equal to the length of the injector tube 42 that needs to extend through the mounting hole.
The assembly method of the invention is as follows:
s1, the collector 41 is placed on the upper side of the top block 3 so as to be positioned on the secondary bump.
S2, fitting one end of the injection tube 42 into the fitting hole of the manifold 41.
S3, assembling the head mount 43 to the collector 41.
S4, the head injection plate 44 is placed on the upper portion of the auxiliary stand 2.
And S5, inserting the guide needle 1 into the mounting hole of the head injection plate 44 and the corresponding injection tube 42 from top to bottom.
And S6, removing the auxiliary bracket 2, and inserting the injection tube 42 into the corresponding mounting hole of the injection plate 44 by utilizing the gravity or the pressing action of the injection plate 44 and the guiding action of the guide needle 1.
And S7, removing the guide needle 1.
The method is used for testing the single-component 300N thrust magnitude engine and the single-component 40N thrust magnitude engine, the assembly efficiency is improved by 20% compared with the prior art, and the product qualification rate is improved by 1% through product brazing and subsequent testing work. And can be suitable for cattle, hundred-cattle and thousand-cattle single-component liquid rocket engines.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (8)
1. An auxiliary device for assembling a single-component liquid rocket engine, comprising: the device comprises a guide needle (1), an auxiliary bracket (2) and a top block (3);
the collector (41) is used for placing the single-component thrust chamber head (4) on the upper side of the top block (3);
the height of the auxiliary support (2) is higher than that of a head support (43) of a single-component thrust chamber head (4), the lower part of the auxiliary support (2) is detachably connected to the top block (3), and the upper part of the auxiliary support (2) is used for supporting a head injection plate (44) of the single-component thrust chamber head (4);
the guide needle is used for being respectively inserted into the mounting hole and an injection tube (42) of the single-component thrust chamber head (4) corresponding to the mounting hole.
2. Auxiliary device for assembly of a mono-component liquid rocket engine according to claim 1, wherein said auxiliary support (2) is located at the periphery of said collector (41).
3. Auxiliary device for assembly of a mono-component liquid rocket engine according to claim 1, wherein the guiding needle (1) is tapered with the smallest outer diameter smaller than the inner diameter of the injection tube (42) and the largest outer diameter larger than the inner diameter of the injection tube (42) and smaller than the inner diameter of the mounting hole of the head injection plate (44).
4. Auxiliary device for assembly of a mono-component liquid rocket engine according to claim 1, wherein said auxiliary bracket (2) is a split structure comprising a first part and a second part.
5. Auxiliary device for assembly of a mono-component liquid rocket engine according to claim 4, wherein the height of the auxiliary support (2) is 10-30mm higher than the head support (43) of the mono-component thrust chamber head (4).
6. The auxiliary device for assembling a mono-component liquid rocket engine according to claim 1, wherein the top block (3) is a two-stage boss-shaped structure comprising a base, a first-stage projection and a second-stage projection, the first-stage projection is disposed on the upper side of the base, and the second-stage projection is disposed on the upper side of the first-stage projection;
the collector (41) is sleeved and positioned on the secondary bump, and the lower part of the auxiliary support (2) is detachably connected to the substrate on the outer side of the primary bump.
7. Auxiliary device for assembly of a mono-component liquid rocket engine according to claim 6, wherein the height of said secondary protrusions is equal to the length of said injector tube (42) that needs to protrude through said mounting hole.
8. A method of assembling a single component liquid rocket engine, using the auxiliary device for assembling a single component liquid rocket engine according to any one of claims 1 to 7, the method comprising the steps of:
s1, placing a collector (41) on the upper side of the top block (3);
s2, fitting one end of the injection tube (42) into the fitting hole of the collector (41);
s3, assembling a head support (43) on the collector (41);
s4, placing a head injection plate (44) on the upper part of the auxiliary bracket (2);
s5, inserting the guide needle (1) into the mounting hole of the head injection plate (44) and the corresponding injection tube (42) from top to bottom;
s6, detaching the auxiliary bracket (2), and inserting the injection tube (42) into the corresponding mounting hole of the injection plate (44) by utilizing the self gravity or pressing action of the injection plate (44) and the guiding action of the guide needle (1);
s7, removing the guide needle (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010011024.2A CN111113023B (en) | 2020-01-06 | 2020-01-06 | Auxiliary device for assembling monopropellant liquid rocket engine and assembling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010011024.2A CN111113023B (en) | 2020-01-06 | 2020-01-06 | Auxiliary device for assembling monopropellant liquid rocket engine and assembling method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111113023A true CN111113023A (en) | 2020-05-08 |
| CN111113023B CN111113023B (en) | 2021-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010011024.2A Active CN111113023B (en) | 2020-01-06 | 2020-01-06 | Auxiliary device for assembling monopropellant liquid rocket engine and assembling method |
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| CN (1) | CN111113023B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112177798A (en) * | 2020-09-28 | 2021-01-05 | 上海空间推进研究所 | Heat insulation structure suitable for spacecraft engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002070513A (en) * | 2000-08-29 | 2002-03-08 | Mitsubishi Automob Eng Co Ltd | Press fitting device for valve guide and press fitting method for valve guide |
| CN101757815A (en) * | 2009-03-30 | 2010-06-30 | 江苏新中环保股份有限公司 | Centering and correcting device for arranging injection pipe in bag-type dust collector |
| CN202780441U (en) * | 2012-07-23 | 2013-03-13 | 深圳市东方亮彩精密技术有限公司 | Nut implantation device with dredging structure |
| CN203055866U (en) * | 2012-12-28 | 2013-07-10 | 贵州雅光电子科技股份有限公司 | A device used for assembling diodes on a rectifier substrate |
| CN104907809A (en) * | 2014-03-12 | 2015-09-16 | 北京航天动力研究所 | Adjustable assembly trolley used for liquid-propellant rocket engine rotor assembly |
| CN204772325U (en) * | 2015-08-03 | 2015-11-18 | 陶琴封 | Perforation seeker |
| CN206029262U (en) * | 2016-07-20 | 2017-03-22 | 梁启明 | Pipe assembly quality of vein needle |
| CN207656225U (en) * | 2017-12-14 | 2018-07-27 | 昆山利禾时精密工业有限公司 | Sealing ring installing mechanism |
-
2020
- 2020-01-06 CN CN202010011024.2A patent/CN111113023B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002070513A (en) * | 2000-08-29 | 2002-03-08 | Mitsubishi Automob Eng Co Ltd | Press fitting device for valve guide and press fitting method for valve guide |
| CN101757815A (en) * | 2009-03-30 | 2010-06-30 | 江苏新中环保股份有限公司 | Centering and correcting device for arranging injection pipe in bag-type dust collector |
| CN202780441U (en) * | 2012-07-23 | 2013-03-13 | 深圳市东方亮彩精密技术有限公司 | Nut implantation device with dredging structure |
| CN203055866U (en) * | 2012-12-28 | 2013-07-10 | 贵州雅光电子科技股份有限公司 | A device used for assembling diodes on a rectifier substrate |
| CN104907809A (en) * | 2014-03-12 | 2015-09-16 | 北京航天动力研究所 | Adjustable assembly trolley used for liquid-propellant rocket engine rotor assembly |
| CN204772325U (en) * | 2015-08-03 | 2015-11-18 | 陶琴封 | Perforation seeker |
| CN206029262U (en) * | 2016-07-20 | 2017-03-22 | 梁启明 | Pipe assembly quality of vein needle |
| CN207656225U (en) * | 2017-12-14 | 2018-07-27 | 昆山利禾时精密工业有限公司 | Sealing ring installing mechanism |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112177798A (en) * | 2020-09-28 | 2021-01-05 | 上海空间推进研究所 | Heat insulation structure suitable for spacecraft engine |
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| Publication number | Publication date |
|---|---|
| CN111113023B (en) | 2021-06-04 |
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