CN106644488A - Large rocket engine and support integral overturn fixture - Google Patents
Large rocket engine and support integral overturn fixture Download PDFInfo
- Publication number
- CN106644488A CN106644488A CN201610835738.9A CN201610835738A CN106644488A CN 106644488 A CN106644488 A CN 106644488A CN 201610835738 A CN201610835738 A CN 201610835738A CN 106644488 A CN106644488 A CN 106644488A
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- China
- Prior art keywords
- engine
- mounting surface
- fixture
- frame
- main frame
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a large rocket engine and support integral overturn fixture, which comprises an engine connection main frame and is characterized in that a main body of the engine connection main frame is of a cylindrical structure and comprises a plurality of annular plates which are coaxially arranged at intervals and a plurality of connecting rods which are uniformly arranged at intervals in the axial direction and connect the annular plates together, both ends of the engine connection main frame are connected with two lifting ropes through detachable clamping apparatuses, each two of the lifting ropes are detachably connected with a lifting beam, a rack mounting surface of the engine main frame is provided with a plurality of rack mounting surface cushion blocks, and the inner side and the outer side of each rack mounting cushion block are detachably provided with a rack mounting surface connecting flange and a rack mounting surface reverse-side connecting flange respectively. The fixture disclosed by the invention realizes integral single-arm overturn of a large-size high-mass rocket engine and a support thereof, the overturn process is stable and controllable, and the safety of the engine is ensured. The large rocket engine and support integral overturn fixture has the advantages of high operability and low cost.
Description
Technical field
The invention belongs to Large Spacecraft technical field of mechanical environmental test, and in particular to a kind of large rocket engine and
Support entirety turnover fixture.
Background technology
When rocket engine carries out dynamic environmental test examination, because the factors such as vibratory equipment thrust deficiency are normally only adopted
The relatively less unit of quality and size is used as testpieces.With high thrust shake table development and vibration test technology into
Ripe, the border of dynamic environmental test examination is truer, and certain large rocket multi-machine parallel connection engine and support need entirety to carry out power
Learn environmental test examination.In process of the test, engine and support need using the back-off form contrary with rocket body installation direction with
Shake table clamp connects, and needs engine and support to be overturn to back-off state from normal condition.Due to engine and support it is whole
Body size reaches 3500mm × 3500mm × 3000mm, quality about 3000kg, realizes producing without applicable turnover fixture and method
The upset of product.
For the type rocket engine is typically based on applying working condition design specialized fixture, but vibration examination is carried out in engine
Before testing, applying working condition is engine and changes into horizontality from vertical state or go to vertical state from horizontality, and vibrates
In process of the test, engine need to go to back-off state from vertical state, and need to ensure engine bracket mounting face under back-off state
Can install with vibration tong.
At present, it is to ensure the reliability and versatility in engine switching process, large rocket engine turnover fixture one
As adopt motor overturning, cost is of a relatively high, and for rocket engine turnover fixture in the present invention, operating mode is special, usage frequency
It is low, it is considered to design it is a set of meet large rocket engine mounting interface requirement, be capable of achieving the upset of engine 180 degree, possess safety
Coefficient is big, the turnover fixture of low cost feature is very important.
The content of the invention
It is an object of the invention to solve above-mentioned technical problem and provide a kind of large rocket engine and support entirety
Turnover fixture.
For achieving the above object, the present invention is adopted the following technical scheme that：
A kind of large rocket engine and support entirety turnover fixture, including：
Engine connects main frame, and it is cylinder-like structure that the engine connects the main body of main frame, including it is multiple it is coaxial in the heart
It is described to start every the connecting rod that the annular slab for arranging and multiple axial uniform intervals for coupling together the annular slab are arranged
Machine connects the two ends of main frame respectively by respectively by removable fixture two lifting ropes of connection, removable per lifting rope described in two
One hanging beam of connection, is laid with multiple frame mounting surface cushion blocks, the frame peace on the frame mounting surface for starting owner's frame
The inner and outer of dress cushion block is detachably arranged respectively organic frame mounting surface adpting flange, frame mounting surface and tosses about connection method
It is blue.
The fixture is connected by bolt with the annular endplate, and the fixture on each annular endplate is 180 ° symmetrical
Install.
The frame mounting surface adpting flange, frame mounting surface adpting flange of tossing about installs surface side with the frame respectively
The engine is connected the annular endplate and mounting surface cushion block of main frame and is connected by bolt.
The hanging beam adopts I-beam welding structure, hanging beam span to exceed engine and connect main frame and fixture outer envelope
Size；The upper end center of the hanging beam is provided with the circular hole being connected with crane, described to hang in the case where the hanging beam and crane hang naturally
Beam is the level of state；The hanging beam lower end is uniformly used to meet multiple lifting hole(eyelet)s of different size product lifting requirements.
The lifting rope adopts steel wire rope, two ends compacting steel wire loop to be simultaneously cased with capel, the chicken of described lifting rope one end
Thimble is connected by shackle with the hanging beam and the capel of the other end is directly connected with the fixture.
The engine is connected main frame and is formed using welding for steel structure.
Present invention achieves the overall single armed upset of the big quality rocket engine of large scale and support, and switching process is steady
It is controllable, it is ensured that the security of engine, possess strong operability, the advantage of low cost.
Description of the drawings
Fig. 1 is that the stereochemical structure of the large rocket engine and support entirety turnover fixture switching process of the present invention is illustrated
Figure；
Fig. 2 is the local structural graph of Fig. 1 of the present invention；
Fig. 3 is the structural representation before Fig. 1 upsets of the present invention；
Fig. 4 is the structural representation after the completion of Fig. 3 upsets of the present invention.
In figure：1. hanging beam, 2. lifting rope, 3. fixture, 4. engine connect main frame, 5. frame mounting surface cushion block, 6. frame peace
Dress face adpting flange, 7 frame mounting surfaces are tossed about adpting flange, 8. engine and its frame.
Specific embodiment
Below, the substantive distinguishing features and advantage of the present invention are further described with reference to example, but the present invention not office
It is limited to listed embodiment.
Referring to shown in Fig. 1-4, a kind of large rocket engine and support entirety turnover fixture, including：
Engine connects main frame 4, and it is cylinder-like structure that the engine connects the main body of main frame, including it is multiple it is coaxial in the heart
It is described every the connecting rod 42 that the annular slab 41 for arranging and multiple axial uniform intervals for coupling together the annular slab are arranged
Engine connects the two ends of main frame and connects two lifting ropes 2 by removable fixture 3 respectively, removable per lifting rope described in two 2
One hanging beam 1 of connection, the engine to connect and be laid with multiple frame mounting surface cushion blocks 5 on the frame mounting surface of main frame 4, described
The inner and outer of frame installation cushion block 5 is detachably arranged respectively organic frame mounting surface adpting flange 6, frame mounting surface and tosses about
Adpting flange 7.
Described frame mounting surface cushion block 5, frame mounting surface adpting flange 6 and frame mounting surface are tossed about adpting flange 7, main
It is used for connection and dismounting that engine and support 8 and engine connect between main frame 4；Hanging beam 1, lifting rope 2 are used for real with fixture 3
Existing engine and support 8 are connected the overall upset of main frame 4 with engine.
Wherein, the lifting rope is four, and the frame mounting surface cushion block 5, frame mounting surface adpting flange 6 are installed with frame
Face toss about adpting flange 7 be respectively 8, the hanging beam be 2, the fixture 3 be 4.
Wherein, the fixture is connected by the way that bolt is dismountable with the annular endplate, and on each annular endplate
Fixture is symmetrically installed for 180 °.
Specifically, when being used, the frame mounting surface adpting flange, frame mounting surface toss about adpting flange difference
The engine for installing surface side with frame is connected the annular endplate and mounting surface cushion block of main frame and is connected by bolt.
Implement, the hanging beam adopts the span of I-beam welding structure, the hanging beam to exceed engine connection master
Frame and fixture outer envelope size；The upper end center of the hanging beam is provided with and the circular hole being connected for crane, in the hanging beam
Under hanging naturally with crane, the hanging beam is the level of state；The hanging beam lower end is uniformly used to meet the lifting of different size product
Desired multiple lifting hole(eyelet)s.
The hanging beam bears engine, engine under rollover states and connects main frame, frame mounting surface pad in installation crane
Block, frame mounting surface adpting flange, frame mounting surface are tossed about the mass loadings such as adpting flange.
Implement, the lifting rope adopts steel wire rope, two ends compacting steel wire loop to be simultaneously cased with capel, the lifting rope
The capel of one end is connected by shackle with the hanging beam and the capel of the other end is directly connected with the fixture,
And prevent capel from sliding using measure.
The lifting rope can meet and bear 2.5 times of safety coefficients of load and require, length connects main frame not less than 2 times of engines
Highly；During rollover states, lifting rope is in vertical state.
The engine connects the inside installation dimension of main frame 4 and should exceed external engine envelope size, highly should meet
Do not contact with ground under engine vertical state；And engine connects main frame and should be able to bear maximum load under rollover states.
Implement, the engine is connected main frame 4 and formed using welding for steel structure, the frame mounting surface cushion block 5,
Frame mounting surface adpting flange 6, frame mounting surface is tossed about and adpting flange 7 and fixture 3 and is processed using steel plate
In the present invention, the engine connects the main load-carrying construction part of main frame 4, connects organic frame mounting surface cushion block 5, frame
Mounting surface adpting flange 6, frame mounting surface toss about adpting flange 7 annular endplate be engine support interface, surface plane
Degree has high demands, and plane error degree is less than 0.1mm.
The step of the present embodiment carries out upset operation using turnover fixture is as follows：
The first step：Each frame mounting surface adpting flange 7 of tossing about is connected in engine and connects main frame 4 by screw respectively
On, then the whole machine of engine is hung to into frame mounting surface with suspender and is tossed about the upside of adpting flange 7, by screw by engine and machine
Toss about adpting flange 7, frame mounting surface cushion block 5 of frame 8 and frame mounting surface is connected, and disconnects the connection of entablature and suspender,
As shown in Figure 3；
Second step：Respectively each frame mounting surface adpting flange 6 is connected in into engine by screw to connect on main frame 4,
Frame mounting surface adpting flange 6 is connected with frame mounting surface cushion block 5 by tightening screw；Fixture 3 is consolidated respectively by screw
It is connected in engine to connect on main frame 4, fixture 3 connects respectively the hanging beam 1 of crane before and after twin hood crane by lifting rope 2；
3rd step：By the upper and lower distance of crane before and after control, realize that the whole machine of engine and frame are connected main frame with engine
Overall upset, switching process schematic diagram is as shown in Figure 1.After engine integrally overturns 180 ° (as shown in Figure 4), remove by fixture
3rd, the engine reversal hanger of lifting rope 2 and the composition of hanging beam 1；
4th step：Frame mounting surface adpting flange 6 is removed, engine and frame 8 is connected into the entirety of main frame 4 with engine and is hung
It is transported at vibration tong, removes frame mounting surface and toss about adpting flange 7, hangs engine and connect main frame 4.
Present invention achieves the overall single armed upset of the big quality rocket engine of large scale and support, and switching process is steady
It is controllable, it is ensured that the security of engine, possess strong operability, the advantage of low cost.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (6)
1. a kind of large rocket engine and support entirety turnover fixture, it is characterised in that include：
Engine connects main frame, and it is cylinder-like structure that the engine connects the main body of main frame, including multiple coaxial heart septums set
The connecting rod that the annular slab and multiple axial uniform intervals for coupling together the annular slab put is arranged, the engine connects
The two ends of main frame are connect respectively by respectively by removable fixture two lifting ropes of connection, per the removable connection of lifting rope described in two
One hanging beam, is laid with multiple frame mounting surface cushion blocks on the frame mounting surface for starting owner's frame, the frame installs pad
The inner and outer of block is detachably arranged respectively organic frame mounting surface adpting flange, frame mounting surface and tosses about adpting flange.
2. according to claim 1 large rocket engine and support entirety turnover fixture, it is characterised in that the fixture lead to
Cross bolt to be connected with the annular endplate, and the fixture on each annular endplate is symmetrically installed for 180 °.
3. according to large rocket engine described in claim 1 and support entirety turnover fixture, it is characterised in that the frame
Mounting surface adpting flange, frame mounting surface toss about adpting flange respectively with the frame install surface side the engine be connected master
The annular endplate and mounting surface cushion block of frame is connected by bolt.
4. according to large rocket engine described in claim 1 and support entirety turnover fixture, it is characterised in that the hanging beam
Using I-beam welding structure, hanging beam span exceedes engine and connects main frame and fixture outer envelope size；The hanging beam
Upper end center is provided with the circular hole being connected with crane, and in the case where the hanging beam and crane hang naturally, the hanging beam is the level of state；Institute
Stating hanging beam lower end is uniformly used to meet multiple lifting hole(eyelet)s of different size product lifting requirements.
5. according to large rocket engine described in claim 1 and support entirety turnover fixture, it is characterised in that the lifting rope
Using steel wire rope, two ends compacting steel wire loop is simultaneously cased with capel, and the capel of described lifting rope one end is by shackle and institute
State hanging beam connection and the capel of the other end is directly connected with the fixture.
6. according to large rocket engine described in any one of claim 1-5 and support entirety turnover fixture, it is characterised in that
The engine is connected main frame and is formed using welding for steel structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610835738.9A CN106644488B (en) | 2016-09-20 | 2016-09-20 | Large rocket engine and support integral overturning clamp |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610835738.9A CN106644488B (en) | 2016-09-20 | 2016-09-20 | Large rocket engine and support integral overturning clamp |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106644488A true CN106644488A (en) | 2017-05-10 |
| CN106644488B CN106644488B (en) | 2020-03-10 |
Family
ID=58853145
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610835738.9A Active CN106644488B (en) | 2016-09-20 | 2016-09-20 | Large rocket engine and support integral overturning clamp |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106644488B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107986147A (en) * | 2017-12-01 | 2018-05-04 | 天津航天瑞莱科技有限公司 | A kind of reversal hanger of list skirt engine |
| CN108000448A (en) * | 2017-12-05 | 2018-05-08 | 内蒙古航天红峡化工有限公司 | A kind of solid propellant rocket support roller protective device and application method |
| CN108007659A (en) * | 2017-11-17 | 2018-05-08 | 天津航天瑞莱科技有限公司 | A kind of dynamic environmental test Universal clamp of space flight tank |
| CN109387997A (en) * | 2017-08-04 | 2019-02-26 | 北京空间机电研究所 | A kind of high rigidity lightweight space camera lens barrel and its vibrostability test method |
| CN109406153A (en) * | 2018-12-14 | 2019-03-01 | 中国航发沈阳发动机研究所 | Aero-engine support device, experimental rig |
| CN109580150A (en) * | 2018-12-03 | 2019-04-05 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket vibration test standard frock |
| CN110961820A (en) * | 2019-12-28 | 2020-04-07 | 天津航天长征火箭制造有限公司 | Assembly welding process and turnover tool for storage box body with common-bottom structure |
| CN111114834A (en) * | 2019-12-17 | 2020-05-08 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
| CN112943482A (en) * | 2021-01-26 | 2021-06-11 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
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| CN103567739A (en) * | 2013-08-12 | 2014-02-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Universal horizontal overturn assembly platform and assembly process for aero-engine |
| CN203513077U (en) * | 2013-09-22 | 2014-04-02 | 西安航天化学动力厂 | Lifting turnover tool for nonmetallic combustor |
| CN206208527U (en) * | 2016-09-20 | 2017-05-31 | 天津航天瑞莱科技有限公司 | A kind of large rocket engine and frame entirety turnover fixture |
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| JPH07196284A (en) * | 1994-01-06 | 1995-08-01 | Penta Ocean Constr Co Ltd | Suspension having hydraulic cylinder |
| JP3113208B2 (en) * | 1996-06-21 | 2000-11-27 | 三菱重工業株式会社 | Hanging posture control device using gyroscope and control method thereof |
| KR20130080275A (en) * | 2012-01-04 | 2013-07-12 | 두산중공업 주식회사 | Turn over device |
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| CN203048387U (en) * | 2012-11-15 | 2013-07-10 | 广西玉柴机器股份有限公司 | Marine engine intercooler assembling and overturning lifting appliance |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109387997A (en) * | 2017-08-04 | 2019-02-26 | 北京空间机电研究所 | A kind of high rigidity lightweight space camera lens barrel and its vibrostability test method |
| CN109387997B (en) * | 2017-08-04 | 2021-03-26 | 北京空间机电研究所 | High-rigidity light space camera lens barrel and anti-vibration stability testing method thereof |
| CN108007659A (en) * | 2017-11-17 | 2018-05-08 | 天津航天瑞莱科技有限公司 | A kind of dynamic environmental test Universal clamp of space flight tank |
| CN108007659B (en) * | 2017-11-17 | 2023-09-22 | 天津航天瑞莱科技有限公司 | Universal clamp for mechanical environment test of aerospace storage box |
| CN107986147A (en) * | 2017-12-01 | 2018-05-04 | 天津航天瑞莱科技有限公司 | A kind of reversal hanger of list skirt engine |
| CN107986147B (en) * | 2017-12-01 | 2024-04-30 | 天津航天瑞莱科技有限公司 | Overturning lifting appliance of single-skirt engine |
| CN108000448A (en) * | 2017-12-05 | 2018-05-08 | 内蒙古航天红峡化工有限公司 | A kind of solid propellant rocket support roller protective device and application method |
| CN109580150A (en) * | 2018-12-03 | 2019-04-05 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket vibration test standard frock |
| CN109406153A (en) * | 2018-12-14 | 2019-03-01 | 中国航发沈阳发动机研究所 | Aero-engine support device, experimental rig |
| CN111114834B (en) * | 2019-12-17 | 2021-05-04 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
| CN111114834A (en) * | 2019-12-17 | 2020-05-08 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
| CN110961820A (en) * | 2019-12-28 | 2020-04-07 | 天津航天长征火箭制造有限公司 | Assembly welding process and turnover tool for storage box body with common-bottom structure |
| CN112943482A (en) * | 2021-01-26 | 2021-06-11 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
| CN112943482B (en) * | 2021-01-26 | 2022-08-12 | 西安航天动力研究所 | Integral frame of liquid rocket engine |
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| CN106644488B (en) | 2020-03-10 |
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