CN109084969A - MISSILE LAUNCHING air deflector entirety Static Load Test Method - Google Patents
MISSILE LAUNCHING air deflector entirety Static Load Test Method Download PDFInfo
- Publication number
- CN109084969A CN109084969A CN201810645309.4A CN201810645309A CN109084969A CN 109084969 A CN109084969 A CN 109084969A CN 201810645309 A CN201810645309 A CN 201810645309A CN 109084969 A CN109084969 A CN 109084969A
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- Prior art keywords
- air deflector
- load
- test
- measured
- sandbag
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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
- G01M13/00—Testing of machine parts
Abstract
The invention discloses a kind of MISSILE LAUNCHING air deflector entirety Static Load Test Methods, strain transducer is installed in air deflector bottom surface to be measured, the vertical stays of displacement sensor are bonded in the peripheral frame that air deflector to be measured is assembled at the top of test bracket by air deflector bottom to be measured measurement point-, in the cavity that sandbag component is placed on air deflector to be measured and peripheral frame is formed, Anchor plate kit is placed on above sandbag component and carries out debugging-carrying out multiple full and down test before being connected-test with the cylinder system of test bracket side.MISSILE LAUNCHING of the present invention is reliable and stable with air deflector entirety Static Load Test Method test data, product quality risk is low, and experimentation cost is low, experimental condition is easily achieved, and will not cause to damage to nonmetallic materials.
Description
Technical field
The invention belongs to product Static Test Technique fields, try in particular to a kind of MISSILE LAUNCHING air deflector entirety static load
Proved recipe method.
Background technique
The static test of the industry with load purposes and military use product passes through test pressure machine mostly and realizes at present, tests
Press machine belongs to rigidity pressure, it can be achieved that simulation static test under local loading, single pressure working condition, be suitble to small sized product or
The static test of product local location.MISSILE LAUNCHING is larger with air deflector loading end, is streamlined curved surface, integrally bears under operating condition
Combustion gas flowing pressure, and carrying position is nonmetallic materials, test process must not generate damage, and test pressure machine presses mode cannot
Meet the above test requirements document.Air deflector military project manufacturing enterprise generally uses Finite Element Simulation Analysis calculating or local static test etc.
Indirect mode carries out strength modification, and the reliability of product strength is ensured with larger design safety factor (DSF).However it is pushed away in newer versions of these missiles
Power constantly increases, and under the more and more harsh demand pull of car kits quality requirement, air deflector must carry out lean design, passes through
Reliable entirety static test examines its integrated carrying ability.
Summary of the invention
Present invention aim to the deficiencies of the above-mentioned technology of needle, provide a kind of with high reliability, low quality risk
And the MISSILE LAUNCHING air deflector entirety Static Load Test Method of low cost.
To achieve the above object, the MISSILE LAUNCHING air deflector entirety Static Load Test Method designed by the present invention, including such as
Lower step:
1) strain transducer is installed respectively in multiple measurement points of air deflector bottom surface to be measured, by displacement sensor
More vertical stays are bonded to multiple measurement points of air deflector bottom to be measured, the signal wire of all strain transducers and displacement respectively
Data collector is accessed together after the signal wire plying of sensor；
2) air deflector to be measured for completing step 1) is assembled in the peripheral frame at the top of test bracket, and the dress of air deflector to be measured
It is consistent with assembled state of the air deflector on car launcher with state；The appearance that sandbag component is placed on air deflector to be measured and peripheral frame is formed
It is intracavitary；Anchor plate kit is placed on above sandbag component and is connected with the cylinder system of test bracket side；
3) it is debugged before testing, load is no more than 30% rated load in debugging process, and test takes 5% rated load to make
It is zero load state, test equipment carries out calibration zeroing under zero load state and starts to acquire data；
4) multiple full and down test is carried out, test load classification carries out, and load is increased with the amplitude of 10% rated load value
To maximum load, every completion level-one load load, 10~15s of pressure maintaining after power to be feedback is stablized acquires test data, without exception
Phenomenon continues to load after occurring, and 20~30s of maximum load pressure maintaining acquires test data.
Further, in the step 2), face with peripheral frame inner cavity corresponding inner mold of the air deflector to be measured along water conservancy diversion direction
Face paste is closed, and air deflector to be measured is corresponded to lateral surface along the face in water conservancy diversion direction and positioned using the module beam of test bracket top side,
Its lap inner mold corresponding with peripheral frame inner cavity face gap of air deflector to be measured is no more than 30mm.
Further, in the step 2), sandbag component is fully wrapped around by tarpaulin, and the bottom surface of tarpaulin and side with
Cavity inner mold face paste is closed.
Further, in the step 2), sandbag component includes one layer of several little Sha for being closely placed on bottom side by side
Bag and multilayer are closely placed on several big sandbags above the small sandbag of bottom side by side, and the height of the sandbag component is higher than and encloses
50~150mm of frame upper surface.
Further, each small sandbag is having a size of 150 × 150mm, loading 50~60%, each big sandbag
Having a size of 500 × 300mm, loading 70~80%.
Further, the Anchor plate kit includes pressing plate and two pressure crossbeams being symmetrically welded on pressing plate, and each
The both ends of root application pressure crossbeam are each equipped with the connecting pin with nut；
Accordingly, the cylinder system includes four oil cylinders, and four oil cylinders are connect with four ends of two root applications pressure crossbeam
Pin is in connect one to one.
Compared with prior art, the present invention having the advantage that MISSILE LAUNCHING air deflector entirety static test of the present invention
Method test data are reliable and stable, product quality risk is low, and experimentation cost is low, experimental condition is easily achieved, and will not be to non-gold
Belong to material to cause to damage.
Detailed description of the invention
Fig. 1 is MISSILE LAUNCHING air deflector entirety static test schematic diagram of the present invention；
Fig. 2 is sandbag component diagram in Fig. 1；
Fig. 3 is Anchor plate kit schematic diagram in Fig. 1；
Fig. 4 is sensor scheme of installation in Fig. 1；
Fig. 5 is MISSILE LAUNCHING air deflector schematic diagram of the present invention.
Each part numbers are as follows in figure:
Air deflector 1 to be measured, test bracket 2, Anchor plate kit 3 are (wherein: pressing plate 3.1, pressure crossbeam 3.2, connecting pin 3.3, spiral shell
It is female 3.4), peripheral frame 4, cylinder system 5, sandbag component 6 (wherein: small sandbag 6.1, big sandbag 6.2), module beam 7, tarpaulin 8, strain
Sensor 9, displacement sensor 10 (wherein: vertical stays 10.1), data collector 11.
Specific embodiment
The following further describes the present invention in detail with reference to the accompanying drawings and specific embodiments, convenient for more clearly understanding this
Invention, but they limiting the invention.
MISSILE LAUNCHING of the present invention air deflector entirety Static Load Test Method, includes the following steps:
1) strain transducer 9 (i.e. measurement point is installed respectively in multiple measurement points of 1 bottom surface of air deflector to be measured
One strain transducer is installed), more vertical stays 10.1 of displacement sensor 10 are bonded to 1 bottom of air deflector to be measured respectively
Multiple measurement points (i.e. a vertical stays be bonded a measurement point), the signal wire and displacement sensing of all strain transducers 9
Data collector 11 is accessed together after the signal wire plying of device 10, as shown in Figure 4；
The strain transducer that test is selected is three-dimensional strain transducer, model BE120-4CA, the displacement sensing of selection
Device model CLMD2-AJ1A8P01500 type (ASM company), data collector are EX1629 data collection system；
2), as shown in Figure 1, the air deflector to be measured 1 for completing step 1) is assembled in the peripheral frame 4 at 2 top of test bracket, and
The assembled state of air deflector 1 to be measured is consistent with assembled state of the air deflector on car launcher, and air deflector 1 to be measured is along water conservancy diversion direction
Face (i.e. the most face of bottom height) inner mold face paste corresponding with 4 inner cavity of peripheral frame is closed, and air deflector to be measured 1 is faced along water conservancy diversion direction
It answers lateral surface to position using the module beam 7 of 2 top side of test bracket, is oriented to component to offset by the level of, air deflector 1 to be measured
Its lap inner mold corresponding with 4 inner cavity of peripheral frame face gap is no more than 30mm；It is placed by the fully wrapped around sandbag component 6 of tarpaulin 8
In the cavity that air deflector 1 to be measured is formed with peripheral frame 4, and the bottom surface of tarpaulin 8 and side are closed with cavity inner mold face paste, can be effective
It prevents from gushing on the grains of sand or excessive in bottom surface surrounding gap location and then generate pressure release situation；Anchor plate kit 3 is placed on complete by tarpaulin 8
6 top of sandbag component of package is simultaneously connected with the cylinder system 5 of 2 side of test bracket；
In the present embodiment, as shown in connection with fig. 2, sandbag component 6 include one layer be closely placed on side by side bottom several are small
Sandbag 6.1 and multilayer are closely placed on several big sandbags 6.2 above the small sandbag of bottom side by side, it is desirable that sandbag component 6 is most
Height is higher than 4 50~150mm of upper surface of peripheral frame eventually；Sandbag size and to fill out husky amount be to combine verification tests by analyzing different variables
As a result, comprehensively consider uniform pressure distribution detection case and sandbag filling workload and determination, the small sandbag of each of bottom having a size of
150 × 150mm, loading 50~60%, it can be ensured that pressure value deviation is less than 5% everywhere for pressure-bearing surface, the big sandbag in each of upper layer
Having a size of 500 × 300mm, loading 70~80%, sandbag filling work can be effectively reduced when not influencing uniform pressure distribution
Amount；
As shown in connection with fig. 3, Anchor plate kit 3 include pressing plate 3.1 (pressing plate size according to air deflector working condition pressure emulate cloud atlas into
Row determines that pressing plate size, which need to cover, belongs to maximum quantity stage pressure region, but is not greater than peripheral frame size, to prevent occurring interfering and
Imbalance of pressure situation) and two be symmetrically welded on pressing plate 3.1 pressure crossbeams 3.2 (i.e. a root application pressure crossbeam 3.2 be welded on pressure
The side of plate 3.1, another root application pressure crossbeam 3.2 is welded on the other side of pressing plate 3.1, and two root applications pressure crossbeam 3.2 is along pressing plate 3.1
Center line it is symmetrical), and each root application pressure crossbeam 3.2 both ends be each equipped with the connecting pin 3.3 with nut 3.4.It is corresponding
Ground, cylinder system 5 include four oil cylinders, and two oil cylinders are assemblied in the one side of test bracket 2, other two oil cylinder is assemblied in examination
The another side of bracket 2 is tested, four oil cylinders are connected with FCS coordinated loading control system, play sync equalizing pressure；Meanwhile
Four end connection pins 3.3 of four oil cylinders and two root applications pressure crossbeam 3.2 are in connect one to one, i.e. a root application presses the one of crossbeam
End connection pins 3.3 connect an oil cylinder, and a root application presses the other end connecting pin 3.3 of crossbeam to connect second oil cylinder, another
Root application presses the one end connecting pin 3.3 of crossbeam to connect third oil cylinder, and the other end connecting pin 3.3 of another root application pressure crossbeam connects
Connect the 4th oil cylinder.Pressure crossbeam 3.2 and oil cylinder when being assembled adjustment Anchor plate kit 3 until horizontal, and make Anchor plate kit 3 with
To just, oil cylinder is pressed air deflector 1 to be measured using pull-down pattern, it can be ensured that stablizes pressure；Force request is loaded to meet 40t, is selected
Oil cylinder parameter are as follows: maximum output load 15t, height 1500mm.
3) equipment joint debugging is carried out before test, load is no more than 30% rated load in debugging process, and test takes 5% specified load
Lotus carries state as zero, and test equipment carries out calibration zeroing under zero load state and starts to acquire data；
4) it is the reliability for ensuring data, carries out multiple full and down test altogether, test load classification is carried out, loaded with 10%
The amplitude of rated load value increases to maximum load, and every completion level-one load loads, 10~15s of pressure maintaining after power to be feedback is stablized,
Test data is acquired, continues to load after phenomenon without exception generation, 20~30s of maximum load pressure maintaining acquires test data.
Embodiment
Certain type air deflector is unilateral pattern flow-guiding structure (see Fig. 5), and type face is crutches null circle arc surface, forward projection's size
For 1200 × 1200mm, height 370mm, it is desirable that have 40t integrated carrying ability, test process must not damage nonmetallic surface,
Test method includes the following steps:
1) strain transducer is installed respectively in 14 measurement points of 1 bottom surface of air deflector to be measured, by displacement sensing
Five vertical stays of device are bonded to five measurement points of air deflector bottom to be measured respectively, the signal wire of all strain transducers with
Data collector is accessed together after the signal wire plying of displacement sensor；
2) air deflector to be measured 1 for completing step 1) is assembled in the peripheral frame 4 at 2 top of test bracket, and air deflector to be measured 1
Assembled state it is consistent with assembled state of the air deflector on car launcher, (i.e. most bottom is high along the face in water conservancy diversion direction for air deflector 1 to be measured
The face of degree) corresponding with 4 inner cavity of peripheral frame inner mold face paste closes, and along the face in water conservancy diversion direction correspond to lateral surface sharp for air deflector to be measured 1
Positioned with the module beam of 2 top side of test bracket, be oriented to component to offset by the level of, its lap of air deflector 1 to be measured with enclose
The corresponding inner mold face in 4 inner cavity of frame gap is no more than 30mm；Water conservancy diversion to be measured is placed on by the fully wrapped around sandbag component 6 of tarpaulin 8
In the cavity that device 1 and peripheral frame 4 are formed, and the bottom surface of tarpaulin 8 and side are closed with cavity inner mold face paste, can be effectively prevent on the grains of sand
Gush or it is excessive in bottom surface surrounding gap location so that generate pressure release situation；Anchor plate kit 3 is placed on the sandbag fully wrapped around by tarpaulin 8
6 top of component is simultaneously connected with the cylinder system 5 of 2 side of test bracket, and cylinder system 5 accesses FCS coordinated loading control system；
In the present embodiment, sandbag size and to fill out husky amount be to combine verification tests as a result, synthesis is examined by analyzing different variables
Consider uniform pressure distribution detection case and sandbag filling workload and determination, the small sandbag of each of bottom having a size of 150 × 150mm,
Loading 60%, it can be ensured that pressure-bearing surface everywhere pressure value deviation less than 5%, the big sandbag in each of upper layer having a size of 500 ×
300mm, loading 80% can effectively reduce sandbag filling workload when not influencing uniform pressure distribution；
3.1 size of pressing plate is determined as 800 × 800mm according to air deflector working condition pressure distributed simulation cloud atlas；
Force request, the oil cylinder parameter of selection are as follows: maximum output load 15t, height 1500mm are loaded to meet 40t.
3) equipment joint debugging is carried out before test, load is no more than 30% rated load in debugging process, and test takes 5% specified load
Lotus carries state as zero, and test equipment carries out calibration zeroing under zero load state and starts to acquire data；
4) it is the reliability for ensuring data, carries out full and down three times altogether and test, test load classification carries out, and loads with 10%
The amplitude of rated load value increases to maximum load 40T, every completion level-one load load, and pressure maintaining 15s after power to be feedback is stablized is adopted
Collect test data, continues to load after phenomenon without exception generation, maximum load pressure maintaining 30s acquires test data.
1~table of table 3 is that full and down test acquires data three times, wherein 01a refers to No. 1 direction strain measurement point a, w1 in table
Refer to that No. 1 displacement measurement point, CH1a/CH1a refer to No. 1 oil cylinder feedback force/control force, full and down test data is almost the same three times.
And this participate in test air deflector it is subsequent takes part in certain type MISSILE LAUNCHING task, strain to same position and
The synchronism detection that displacement measurement point carries out, test data and test data fitting degree are higher, which can effective mould
Quasi- product actual condition state.
Table 1 first time full-load test data
Second of the full-load test data of table 2
3 third time full-load test data of table
Claims (6)
1. a kind of MISSILE LAUNCHING air deflector entirety Static Load Test Method, it is characterised in that: the entirety Static Load Test Method packet
Include following steps:
1) strain transducer (9) is installed respectively in multiple measurement points of air deflector to be measured (1) bottom surface, by displacement sensor
(10) more vertical stays (10.1) are bonded to multiple measurement points of air deflector to be measured (1) bottom, all strain sensings respectively
Data collector (11) are accessed together after the signal wire of device (9) and the signal wire plying of displacement sensor (10)；
2) air deflector to be measured (1) for completing step 1) is assembled to the peripheral frame (4) at the top of test bracket (2) Nei, and water conservancy diversion to be measured
The assembled state of device (1) is consistent with assembled state of the air deflector on car launcher；Sandbag component (6) is placed on air deflector to be measured
(1) in the cavity formed with peripheral frame (4)；Anchor plate kit (3) be placed on above sandbag component (6) and with test bracket (2) side
Cylinder system (5) be connected；
3) it is debugged before testing, load is no more than 30% rated load in debugging process, and test takes 5% rated load as zero
Load state, test equipment carry out calibration zeroing under zero load state and start to acquire data；
4) multiple full and down test is carried out, test load classification carries out, and load is increased to most with the amplitude of 10% rated load value
Big load, every completion level-one load load, 10~15s of pressure maintaining after power to be feedback is stablized acquire test data, in phenomenon without exception
Continue to load after generation, 20~30s of maximum load pressure maintaining acquires test data.
2. MISSILE LAUNCHING air deflector entirety Static Load Test Method according to claim 1, it is characterised in that: the step 2)
In, face with peripheral frame (4) inner cavity corresponding inner mold face paste of the air deflector (1) to be measured along water conservancy diversion direction is closed, and air deflector to be measured (1)
It corresponds to lateral surface along the face in water conservancy diversion direction to position using the module beam (7) of test bracket (2) top side, air deflector (1) to be measured
Its lap inner mold corresponding with peripheral frame (4) inner cavity face gap no more than 30mm.
3. MISSILE LAUNCHING air deflector entirety Static Load Test Method according to claim 1, it is characterised in that: the step 2)
In, sandbag component (6) is fully wrapped around by tarpaulin (8), and the bottom surface of tarpaulin (8) and side are closed with cavity inner mold face paste.
4. MISSILE LAUNCHING air deflector entirety Static Load Test Method according to claim 1, it is characterised in that: the step 2)
In, sandbag component (6) includes that one layer of several small sandbag (6.1) for being closely placed on bottom side by side and multilayer are closely placed side by side
Several big sandbags (6.2) above the small sandbag of bottom, and the height of the sandbag component (6) is higher than peripheral frame (4) upper surface
50~150mm.
5. MISSILE LAUNCHING air deflector entirety Static Load Test Method according to claim 4, it is characterised in that: each described small
Sandbag (6.1) having a size of 150 × 150mm, loading 50~60%, each big sandbag (6.2) having a size of 500 × 300mm,
Loading 70~80%.
6. MISSILE LAUNCHING air deflector entirety Static Load Test Method according to claim 1, it is characterised in that: the pressing plate group
Part (3) includes pressing plate (3.1) and two pressure crossbeams (3.2) being symmetrically welded on pressing plate (3.1), and each root application presses crossbeam
(3.2) both ends are each equipped with the connecting pin (3.3) with nut (3.4)；
Accordingly, the cylinder system (5) includes four oil cylinders, four ends of four oil cylinders and two root applications pressure crossbeam (3.2)
Connecting pin (3.3) is in connect one to one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810645309.4A CN109084969B (en) | 2018-06-21 | 2018-06-21 | Integral static load test method for fluid director for missile launching |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810645309.4A CN109084969B (en) | 2018-06-21 | 2018-06-21 | Integral static load test method for fluid director for missile launching |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109084969A true CN109084969A (en) | 2018-12-25 |
| CN109084969B CN109084969B (en) | 2020-08-04 |
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ID=64840121
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810645309.4A Active CN109084969B (en) | 2018-06-21 | 2018-06-21 | Integral static load test method for fluid director for missile launching |
Country Status (1)
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| CN (1) | CN109084969B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113092233A (en) * | 2021-03-10 | 2021-07-09 | 上海复合材料科技有限公司 | Static load test system suitable for cartridge adapter and test method thereof |
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| CN101101249A (en) * | 2007-07-31 | 2008-01-09 | 中铁二局股份有限公司 | 32m/900t prestressed concrete pretension box beam static loading test method |
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| CN109084969B (en) | 2020-08-04 |
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