CN109084969B - Integral static load test method for fluid director for missile launching - Google Patents
Integral static load test method for fluid director for missile launching Download PDFInfo
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- CN109084969B CN109084969B CN201810645309.4A CN201810645309A CN109084969B CN 109084969 B CN109084969 B CN 109084969B CN 201810645309 A CN201810645309 A CN 201810645309A CN 109084969 B CN109084969 B CN 109084969B
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Abstract
The invention discloses an integral static load test method of a fluid director for missile launching, which is characterized in that a strain sensor is arranged on the bottom surface of the fluid director to be tested, a vertical pull wire of a displacement sensor is adhered to a measuring point at the bottom of the fluid director to be tested, the fluid director to be tested is assembled in a surrounding frame at the top of a test support, a sand bag assembly is placed in a containing cavity formed by the fluid director to be tested and the surrounding frame, a pressing plate assembly is placed above the sand bag assembly and is connected with an oil cylinder system on the side surface of the test support, debugging is carried out before testing, and multiple full load tests. The integral static load test method for the fluid director for missile launching has the advantages of reliable and stable test data, low product quality risk, low test cost, easy realization of test conditions and no damage to non-metallic materials.
Description
Technical Field
The invention belongs to the technical field of static load tests of products, and particularly relates to an integral static load test method for a fluid director for missile launching.
Background
At present, the static load test of industrial and military products with force bearing application is mostly realized by a test press which belongs to rigid pressure application, can realize the simulation static load test under the working conditions of local loading and single pressure, and is suitable for the static load test of small products or local positions of products. The bearing surface of the fluid director for missile launching is large and is a streamline curved surface, the whole body bears the pressure of gas flow under the working condition, the bearing part is made of non-metal materials, the test process cannot be damaged, and the pressure applying mode of the test press machine cannot meet the test requirements. The military manufacturing enterprises of the fluid director generally adopt indirect modes such as finite element simulation analysis calculation or local static load test to verify the strength, and the reliability of the product strength is ensured by a large design safety factor. However, under the condition of the continuous increase of the thrust of the novel missile and the traction of the increasingly strict requirements on the quality of vehicle-mounted equipment, the fluid director must be designed in a lean way, and the integral bearing capacity of the fluid director is checked through a reliable integral static load test.
Disclosure of Invention
The invention aims to overcome the defects of the technology and provide a method for testing the integral static load of the deflector for missile launching, which has high reliability, low quality risk and low cost.
In order to achieve the aim, the invention designs a whole static load test method of the fluid director for missile launching, which comprises the following steps:
1) respectively installing a strain sensor on a plurality of measuring points on the bottom surface of the fluid director to be measured, respectively bonding a plurality of vertical pull wires of the displacement sensor to the plurality of measuring points at the bottom of the fluid director to be measured, and combining signal wires of all the strain sensors and signal wires of the displacement sensor and then accessing the signal wires and the signal wires into a data acquisition unit;
2) assembling the fluid director to be tested which completes the step 1) into an enclosure frame at the top of the test support, wherein the assembly state of the fluid director to be tested is consistent with the assembly state of the fluid director on the launching vehicle; the sandbag assembly is placed in a cavity formed by the fluid director to be measured and the surrounding frame; the pressing plate assembly is placed above the sand bag assembly and is connected with an oil cylinder system on the side face of the test bracket;
3) debugging is carried out before testing, no more than 30% of rated load is loaded in the debugging process, 5% of rated load is taken as a zero load state in the testing, and the testing equipment carries out calibration zero setting and starts to collect data in the zero load state;
4) and carrying out full load tests for multiple times, carrying out test loading in stages, increasing the loading to the maximum load by the amplitude of 10% of the rated load value, maintaining the pressure for 10-15 s after the feedback force is stable after each stage of load loading is finished, acquiring test data, continuing the loading after no abnormal phenomenon occurs, and maintaining the pressure for the maximum load for 20-30 s to acquire the test data.
Further, in the step 2), the surface of the fluid director to be tested along the diversion direction is fitted with the corresponding inner profile surface of the inner cavity of the enclosure frame, the corresponding outer side surface of the fluid director to be tested along the diversion direction is positioned by using the module beam on one side of the top of the test support, and the gaps between the rest surfaces of the fluid director to be tested and the corresponding inner profile surface of the inner cavity of the enclosure frame are not more than 30 mm.
Further, in the step 2), the sand bag assembly is completely wrapped by the tarpaulin, and the bottom surface and the side surface of the tarpaulin are both attached to the shape surface in the accommodating cavity.
Further, in the step 2), the sandbag assembly comprises a plurality of small sandbags which are closely arranged on the bottom layer side by side and a plurality of large sandbags which are closely arranged above the small sandbags on the bottom layer side by side in a multi-layer mode, and the height of the sandbag assembly is 50-150 mm higher than the upper end face of the surrounding frame.
Further, the size of each small sandbag is 150 × 150mm, the filling amount is 50-60%, and the size of each large sandbag is 500 × 300mm, and the filling amount is 70-80%.
Furthermore, the pressure plate assembly comprises a pressure plate and two pressure applying crossbeams which are symmetrically welded on the pressure plate, and two ends of each pressure applying crossbeam are respectively provided with a connecting pin with a nut;
correspondingly, the oil cylinder system comprises four oil cylinders, and the four oil cylinders are correspondingly connected with the four end connecting pins of the two pressing cross beams one by one.
Compared with the prior art, the invention has the following advantages: the integral static load test method for the fluid director for missile launching has the advantages of reliable and stable test data, low product quality risk, low test cost, easy realization of test conditions and no damage to non-metallic materials.
Drawings
FIG. 1 is a schematic view of an integral static load test of a deflector for missile launching according to the present invention;
FIG. 2 is a schematic view of the sandbag assembly of FIG. 1;
FIG. 3 is a schematic view of the platen assembly of FIG. 1;
FIG. 4 is a schematic view of the sensor of FIG. 1 mounted thereon;
FIG. 5 is a schematic view of the deflector for missile launching according to the present invention.
The components in the figures are numbered as follows:
the device comprises a fluid director 1 to be tested, a test support 2, a pressure plate assembly 3 (wherein, the pressure plate 3.1, a pressure applying beam 3.2, a connecting pin 3.3 and a nut 3.4), a surrounding frame 4, an oil cylinder system 5, a sand bag assembly 6 (wherein, a small sand bag 6.1 and a large sand bag 6.2), a module beam 7, tarpaulin 8, a strain sensor 9, a displacement sensor 10 (wherein, a vertical pull wire 10.1) and a data collector 11.
Detailed Description
The invention will be more clearly understood from the following detailed description of the invention taken in conjunction with the accompanying drawings and specific examples, which are not to be construed as limiting the invention.
The invention relates to an integral static load test method of a fluid director for missile launching, which comprises the following steps:
1) respectively installing a strain sensor 9 on a plurality of measuring points on the bottom surface of the fluid director 1 to be measured (namely, installing a strain sensor on one measuring point), respectively adhering a plurality of vertical pull wires 10.1 of the displacement sensor 10 to a plurality of measuring points on the bottom of the fluid director 1 to be measured (namely, adhering one vertical pull wire to one measuring point), and combining signal wires of all the strain sensors 9 and signal wires of the displacement sensor 10 and then accessing the combined signal wires into a data acquisition unit 11, as shown in fig. 4;
the strain sensor selected for the test is a three-way strain sensor, the type number of the strain sensor is BE120-4CA, the type number of the selected displacement sensor is C L MD2-AJ1A8P01500 type (ASM company), and the data acquisition unit is an EX1629 data acquisition system;
2) as shown in fig. 1, the fluid director 1 to be tested after the step 1) is assembled into the enclosure frame 4 at the top of the test support 2, the assembly state of the fluid director 1 to be tested is consistent with the assembly state of the fluid director on the launching vehicle, the surface of the fluid director 1 to be tested along the diversion direction (i.e. the surface with the lowest height) is attached to the inner profile surface corresponding to the inner cavity of the enclosure frame 4, the outer side surface of the fluid director 1 to be tested along the diversion direction is positioned by using the module beam 7 at one side of the top of the test support 2 to offset the horizontal guiding component force, and the gaps between the rest surfaces of the fluid director 1 to be tested and the inner profile surface corresponding to the inner cavity; the sandbag assembly 6 completely wrapped by the tarpaulin 8 is placed in a cavity formed by the fluid director 1 to be tested and the surrounding frame 4, and the bottom surface and the side surface of the tarpaulin 8 are both attached to the profile in the cavity, so that the condition of pressure release caused by upwelling of sand grains or overflow of gaps around the bottom surface can be effectively prevented; the pressing plate component 3 is placed above the sand bag component 6 completely wrapped by the tarpaulin 8 and is connected with the oil cylinder system 5 on the side surface of the test bracket 2;
in the embodiment, as shown in fig. 2, the sandbag assembly 6 comprises a plurality of small sandbags 6.1 which are closely arranged at the bottom layer side by side and a plurality of large sandbags 6.2 which are closely arranged at the top of the small sandbags at the bottom layer side by side, the final height of the sandbag assembly 6 is required to be 50-150 mm higher than the upper end surface of the enclosure frame 4, the sandbag size and the sand filling amount are determined by analyzing different variable combination verification test results and comprehensively considering the pressure uniform distribution detection condition and the sandbag filling workload, each small sandbag size at the bottom layer is 150 × 150mm, the filling amount is 50-60%, the deviation of pressure values at each part of the pressure bearing surface can be ensured to be less than 5%, each large sandbag size at the upper layer is 500 × 300mm, and the filling amount is 70-80%, and the sandbag filling workload can be effectively reduced under the condition that the pressure uniform distribution is not influenced;
referring to fig. 3, the pressing plate assembly 3 includes a pressing plate 3.1 (the size of the pressing plate is determined according to a simulated cloud chart of the working condition pressure of the fluid director, the size of the pressing plate needs to cover the highest order pressure area, but is not larger than the size of the surrounding frame, so as to prevent the occurrence of interference and pressure imbalance) and two pressing beams 3.2 symmetrically welded on the pressing plate 3.1 (namely, one pressing beam 3.2 is welded on one side of the pressing plate 3.1, the other pressing beam 3.2 is welded on the other side of the pressing plate 3.1, and the two pressing beams 3.2 are symmetrically distributed along the center line of the pressing plate 3.1), and both ends of each pressing beam 3.2 are equipped with connecting pins 3.3 with nuts 3.4. Correspondingly, the oil cylinder system 5 comprises four oil cylinders, two oil cylinders are assembled on one side surface of the test support 2, the other two oil cylinders are assembled on the other side surface of the test support 2, and the four oil cylinders are all connected with an FCS coordinated loading control system to perform synchronous and balanced pressure application; meanwhile, the four oil cylinders are correspondingly connected with four end connecting pins 3.3 of two pressing beams 3.2 one by one, namely, one end connecting pin 3.3 of one pressing beam is connected with one oil cylinder, the other end connecting pin 3.3 of one pressing beam is connected with a second oil cylinder, one end connecting pin 3.3 of the other pressing beam is connected with a third oil cylinder, and the other end connecting pin 3.3 of the other pressing beam is connected with a fourth oil cylinder. When the pressure applying beam 3.2 is assembled with the oil cylinder, the pressure plate assembly 3 is adjusted to be horizontal, the pressure plate assembly 3 is aligned with the fluid director 1 to be tested, and the oil cylinder applies pressure in a pull-down mode, so that stable pressure application can be ensured; in order to meet the requirement of 40t loading force, the parameters of the oil cylinder are as follows: maximum output load 15t, height 1500 mm.
3) Performing equipment joint debugging before a test, loading no more than 30% of rated load in the debugging process, taking 5% of rated load as a zero load state in the test, calibrating and zeroing the test equipment in the zero load state and starting to acquire data;
4) in order to ensure the reliability of data, a plurality of full load tests are carried out, the test loading is carried out in stages, the loading is increased to the maximum load by the amplitude of 10% of the rated load value, the pressure is maintained for 10-15 s after the feedback force is stable after each stage of loading is finished, the test data is collected, the loading is continued after no abnormal phenomenon occurs, and the test data is collected after the maximum load is maintained for 20-30 s.
Examples
A certain type of fluid director is of a single-side type fluid directing structure (see figure 5), the molded surface is a double-inflection point arc curved surface, the forward projection size is 1200 × 1200mm, the height is 370mm, the integral bearing capacity of 40t is required, the non-metal surface cannot be damaged in the test process, and the test method comprises the following steps:
1) respectively installing a strain sensor on fourteen measuring points on the bottom surface of the fluid director 1 to be measured, respectively bonding five vertical pull wires of the displacement sensor to the five measuring points at the bottom of the fluid director to be measured, and combining signal wires of all the strain sensors and signal wires of the displacement sensor and then accessing the signal wires into a data acquisition unit;
2) assembling the fluid director 1 to be tested which completes the step 1) into the enclosing frame 4 at the top of the test support 2, wherein the assembling state of the fluid director 1 to be tested is consistent with the assembling state of the fluid director on the launching vehicle, the surface of the fluid director 1 to be tested along the diversion direction (namely the surface with the lowest height) is attached to the corresponding inner molded surface of the inner cavity of the enclosing frame 4, the corresponding outer side surface of the fluid director 1 to be tested along the diversion direction is positioned by using a module beam at one side of the top of the test support 2 so as to offset the horizontal guiding component force, and the gaps between the rest surfaces of the fluid director 1 to be tested and the corresponding inner molded surface of the inner cavity; the sandbag assembly 6 completely wrapped by the tarpaulin 8 is placed in a cavity formed by the fluid director 1 to be tested and the surrounding frame 4, and the bottom surface and the side surface of the tarpaulin 8 are both attached to the profile in the cavity, so that the condition of pressure release caused by upwelling of sand grains or overflow of gaps around the bottom surface can be effectively prevented; the pressing plate assembly 3 is placed above the sandbag assembly 6 completely wrapped by the tarpaulin 8 and connected with the oil cylinder system 5 on the side face of the test support 2, and the oil cylinder system 5 is connected to an FCS (coordinated loading) control system;
in the embodiment, the size and the sand filling amount of the sandbag are determined by analyzing different variable combination verification test results and comprehensively considering the pressure uniform distribution detection condition and the sandbag filling workload, the size of each small sandbag on the bottom layer is 150 × 150mm, the filling amount is 60%, the deviation of the pressure value at each position of the pressure bearing surface can be ensured to be less than 5%, the size of each large sandbag on the upper layer is 500 × 300mm, the filling amount is 80%, and the sandbag filling workload can be effectively reduced under the condition that the pressure uniform distribution is not influenced;
the size of the pressing plate 3.1 is determined to be 800 × 800mm according to the simulated cloud picture of the pressure distribution of the working condition of the fluid director;
in order to meet the requirement of 40t loading force, the parameters of the oil cylinder are as follows: maximum output load 15t, height 1500 mm.
3) Performing equipment joint debugging before a test, loading no more than 30% of rated load in the debugging process, taking 5% of rated load as a zero load state in the test, calibrating and zeroing the test equipment in the zero load state and starting to acquire data;
4) in order to ensure the reliability of data, three full load tests are carried out, the test loading is carried out in stages, the loading is increased to the maximum load of 40T by the amplitude of 10 percent of the rated load value, the pressure is maintained for 15s after the feedback force is stable after the first-stage load loading is finished, the test data is collected, the loading is continued after no abnormal phenomenon occurs, and the maximum load pressure is maintained for 30s to collect the test data.
Tables 1 to 3 show data acquired by three full load tests, wherein 01a in the table indicates the direction of a strain measuring point No. 1, w1 indicates a displacement measuring point No. 1, CH1a/CH1a indicates the feedback force/control force of an oil cylinder No. 1, and the data of the three full load tests are basically consistent.
And the fluid director participating in the test subsequently participates in a certain type of missile launching task, the synchronous test is carried out on the strain and displacement measuring points at the same position, the fitting degree of the test data and the test data is high, and the load test scheme can effectively simulate the actual working condition state of the product.
TABLE 1 first full load test data
TABLE 2 second full load test data
TABLE 3 third full load test data
Claims (2)
1. A whole static load test method of a fluid director for missile launching is characterized by comprising the following steps: the integral static load test method comprises the following steps:
1) respectively installing a strain sensor (9) on a plurality of measuring points on the bottom surface of the fluid director (1) to be measured, respectively bonding a plurality of vertical pull wires (10.1) of a displacement sensor (10) to the plurality of measuring points at the bottom of the fluid director (1) to be measured, and jointly connecting signal wires of all the strain sensors (9) and signal wires of the displacement sensor (10) into a data acquisition unit (11) after stranding;
2) assembling the fluid director (1) to be tested which finishes the step 1) into an enclosure frame (4) at the top of the test support (2), wherein the assembling state of the fluid director (1) to be tested is consistent with the assembling state of the fluid director on the launching vehicle; the sandbag assembly (6) is placed in a containing cavity formed by the fluid director (1) to be tested and the surrounding frame (4); the pressing plate component (3) is placed above the sand bag component (6) and is connected with the oil cylinder system (5) on the side surface of the test bracket (2);
the surface of the fluid director (1) to be tested along the diversion direction is attached to an inner profile corresponding to the inner cavity of the enclosure frame (4), the fluid director (1) to be tested is positioned by a module beam (7) on one side of the top of the test support (2) along the corresponding outer side surface of the fluid director (1) to be tested along the diversion direction, gaps between the rest surfaces of the fluid director (1) to be tested and the inner profile corresponding to the inner cavity of the enclosure frame (4) are not more than 30mm, the sand bag assembly (6) is completely wrapped by the tarpaulin (8), the bottom surface and the side surfaces of the tarpaulin (8) are attached to the inner profile of the containing cavity, the sand bag assembly (6) comprises a plurality of small sand bags (6.1) which are closely placed at the bottom layer side by side and a plurality of large sand bags (6.2) which are closely placed above the small sand bags at the bottom layer side by side, the height of the sand bag assembly (6) is 50-150 mm higher than the upper end surface of the enclosure frame (4), the size of each small sand bag (6.1) is 150mm, and the filling amount is 50-60%, and the size of each large sand;
3) debugging is carried out before testing, no more than 30% of rated load is loaded in the debugging process, 5% of rated load is taken as a zero load state in the testing, and the testing equipment carries out calibration zero setting and starts to collect data in the zero load state;
4) and carrying out full load tests for multiple times, carrying out test loading in stages, increasing the loading to the maximum load by the amplitude of 10% of the rated load value, maintaining the pressure for 10-15 s after the feedback force is stable after each stage of load loading is finished, acquiring test data, continuing the loading after no abnormal phenomenon occurs, and maintaining the pressure for the maximum load for 20-30 s to acquire the test data.
2. The missile launching deflector integral static load test method according to claim 1, wherein the method comprises the following steps: the pressing plate assembly (3) comprises a pressing plate (3.1) and two pressing cross beams (3.2) symmetrically welded on the pressing plate (3.1), and two ends of each pressing cross beam (3.2) are respectively provided with a connecting pin (3.3) with a nut (3.4);
correspondingly, the oil cylinder system (5) comprises four oil cylinders, and the four oil cylinders are correspondingly connected with four end connecting pins (3.3) of the two pressure applying cross beams (3.2) one by one.
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| CN109104909B (en) * | 2008-11-18 | 2012-10-24 | 上海航天精密机械研究所 | Guided missile adapter static pressure test apparatus |
| CN109104908B (en) * | 2009-11-03 | 2013-07-10 | 上海航天精密机械研究所 | Guided missile buffer static pressure test apparatus |
| CN103674580B (en) * | 2013-11-27 | 2015-12-30 | 南车青岛四方机车车辆股份有限公司 | Vehicle body side wall load charger and load loading method |
| CN205506536U (en) * | 2016-03-07 | 2016-08-24 | 郑州大学 | Adopt rubber bag to realize loading device who evenly loads |
| CN107054692A (en) * | 2017-03-30 | 2017-08-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of hyperbolic surface parts ballast |
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