CN112100763B - Missile cover root connection thermal matching evaluation method - Google Patents
Missile cover root connection thermal matching evaluation method Download PDFInfo
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- CN112100763B CN112100763B CN202010875827.2A CN202010875827A CN112100763B CN 112100763 B CN112100763 B CN 112100763B CN 202010875827 A CN202010875827 A CN 202010875827A CN 112100763 B CN112100763 B CN 112100763B
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- test piece
- missile
- quartz ceramic
- evaluation method
- thermal matching
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- 238000011156 evaluation Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 108
- 239000010453 quartz Substances 0.000 claims abstract description 56
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 56
- 239000000919 ceramic Substances 0.000 claims abstract description 55
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 43
- 239000010959 steel Substances 0.000 claims abstract description 43
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 27
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 27
- 239000011888 foil Substances 0.000 claims abstract description 27
- 239000000853 adhesive Substances 0.000 claims abstract description 25
- 230000001070 adhesive effect Effects 0.000 claims abstract description 25
- 238000000034 method Methods 0.000 claims abstract description 17
- 238000004519 manufacturing process Methods 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000010438 heat treatment Methods 0.000 claims abstract description 7
- 238000005303 weighing Methods 0.000 claims abstract description 4
- 229910001374 Invar Inorganic materials 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 2
- 238000005498 polishing Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 10
- 239000000463 material Substances 0.000 description 6
- 229910010293 ceramic material Inorganic materials 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 238000005259 measurement Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/08—Thermal analysis or thermal optimisation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention discloses a missile cover root connection thermal matching evaluation method, which comprises the following steps of: according to index requirements, designing a typical structure of the missile radome; step 2: processing a quartz ceramic test block and a tile steel test block, and weighing a certain amount of high-temperature adhesive; step 3: manufacturing a test piece; step 4: measuring the section thickness and the side length of the test piece, recording the measured value, and calculating the section circumference of the test piece; step 5: designing a thin-wall aluminum foil sleeve; step 6: sleeving a thin-wall aluminum foil sleeve outside the test piece to form a test piece combined structure; step 7: heating the test piece combined structure at high temperature; step 8: the method for evaluating the thermal matching of the root part designed by the invention can conveniently detect and correct the thermal matching design of the root part of the missile radome and guide the thermal matching design of the root part of the missile radome.
Description
Technical Field
The invention belongs to the technical field of experimental mechanics, and particularly relates to a missile cover root connection thermal matching evaluation method.
Background
At present, the missile speed is continuously improved, the electrical performance requirement on the missile radome is also continuously improved, and the missile radome is required to meet high electromagnetic property requirements and high-temperature resistance requirements brought by high speed. In order to meet the requirements, the missile antenna housing is generally designed into a quartz ceramic nose cone and a metal ring made of tile steel, the nose cone and the metal ring are bonded by adopting an adhesive, and due to different thermal expansion coefficients of a quartz ceramic material and a metal ring material, a serious deformation mismatch phenomenon exists between structures after the quartz ceramic material and the metal ring material are expanded at high temperature, so that the ceramic structure is cracked. Therefore, when the missile radome is designed, the design clearance between the quartz ceramic nose cone and the root of the tile steel is very critical, the design clearance at the present stage stays at the theoretical stage, the rationality of the specific design clearance can be checked only by an integral missile radome thermal test, other interference influence factors can be inevitably introduced by adopting a whole radome checking mode, and the condition of thermal matching cannot be conveniently evaluated.
Disclosure of Invention
The purpose of the invention is that:
the method can be used for detecting the problems of the thermal matching of the ceramic material of the missile radome, the bonding of the tile steel material and the welding height Wen Cunzai, and is simple and visual, so that the rationality of the adopted thermal connection mode is evaluated, and the thermal connection design of the root of the missile radome is guided.
The technical scheme of the invention is as follows:
a missile cover root connection heat matching evaluation method comprises the following steps:
step 1: according to index requirements, designing a typical structure of the missile radome;
step 2: machining a quartz ceramic test block (1) and a invar steel test block (2), and weighing a certain amount of high-temperature adhesive;
step 3: manufacturing a test piece;
step 4: measuring the section thickness and the side length of the test piece, recording the measured value, and calculating the section circumference of the test piece;
step 5: designing a thin-wall aluminum foil sleeve (4);
step 6: sleeving a thin-wall aluminum foil sleeve (4) outside the test piece to form a test piece combined structure;
step 7: heating the test piece combined structure at high temperature;
step 8: the fracture gap of the thin-wall aluminum foil sleeve (4) is measured, and the thermal expansion level of the test piece combined structure is evaluated through the size of the fracture gap.
Further, the index requirements in the step 1 include electromagnetic wave transmission performance, high temperature resistance performance, bearing performance and weight index requirements of the missile radome.
Furthermore, the missile radome typical structure in the step 1 comprises a quartz ceramic nose cone part, a tile steel connecting ring part and a high-temperature-resistant adhesive for connecting the quartz ceramic nose cone with the tile steel connecting ring.
Furthermore, the thickness of the quartz ceramic test block (1) in the step 2 is the same as that of the quartz ceramic at the joint of the quartz ceramic nose cone and the invar steel connecting ring in the actual missile radome;
the thickness of the tile steel test block (2) is the same as that of a tile steel connecting ring at the joint of a quartz ceramic nose cone and the tile steel connecting ring in an actual missile radome;
the weight of the weighed high-temperature adhesive (3) is the same as that of the adhesive used at the bonding part of the quartz ceramic nose cone and the tile steel connecting ring in the actual missile antenna housing.
Furthermore, the processing precision of the quartz ceramic test block (1) and the invar steel test block (2) is better than-0.001 mm.
Further, the test piece is manufactured in the step 3, according to the bonding process requirement of the adhesive at the bonding position of the quartz ceramic nose cone and the tile steel connecting ring, the quartz ceramic test block (1) and the tile steel test block (2) are polished, the thickness precision of the high-temperature adhesive (3) is better than-0.001 mm, the flatness treatment is carried out on the bonding surface of the quartz ceramic test block (1) and the tile steel test block (2), and the flatness of the bonding surface of the quartz ceramic test block (1) and the tile steel test block (2) is better than-0.001 mm.
Further, the measuring tool adopted in the step 4 is a dial indicator with accuracy better than 0.001.
Further, the thickness of the thin-wall aluminum foil sleeve (4) in the step 5 is 0.1mm, the thickness precision is better than +0.001mm, and the perimeter precision is better than +0.001mm.
And (3) the heating temperature in the step (7) is 300-400 ℃, and the actual environment temperature of the bonding part of the quartz ceramic nose cone of the missile antenna housing and the connection ring of the invar steel is the same.
Further, in the step 8, a dial gauge with the precision being better than +0.001mm is adopted to measure the rupture gap of the thin-wall aluminum foil sleeve (4).
The invention has the beneficial effects that:
the root thermal matching evaluation method of the missile radome root connection is provided, can conveniently detect and correct the thermal matching design of the missile radome root, and guides the thermal matching design of the missile radome root.
Drawings
FIG. 1 is a schematic view of the combined structure of the test piece of the present invention;
wherein: 1. quartz ceramic test block 2, tile steel test block 3, high temperature adhesive 4, thin wall aluminum foil sleeve.
Detailed Description
The following detailed description of the embodiments of the present invention, such as the shape and construction of the components, the mutual positions and connection relationships between the components, the roles and working principles of the components, the manufacturing process and the operation and use method, etc., is provided to help those skilled in the art to more fully and accurately understand the concept, technical solution of the present invention by describing the embodiments in the following drawings:
one embodiment of the invention:
a missile cover root connection heat matching evaluation method comprises the following steps:
the first step: according to index requirements, designing a typical structure of the missile radome;
and a second step of: processing a quartz ceramic test block 1 and a invar steel test block 2, and weighing a certain amount of high-temperature adhesive;
and a third step of: manufacturing a test piece;
fourth step: measuring the section thickness and the side length of the test piece, recording the measured value, and calculating the section circumference of the test piece;
fifth step: designing a thin-wall aluminum foil sleeve 4;
sixth step: sleeving a thin-wall aluminum foil sleeve 4 outside the test piece to form a test piece combined structure;
seventh step: heating the test piece combined structure at high temperature;
eighth step: the breaking gap of the thin-wall aluminum foil sleeve 4 was measured, and the thermal expansion level of the test piece assembly structure was evaluated by the breaking gap size.
A second embodiment of the invention:
a missile cover root connection heat matching evaluation method comprises the following steps:
first, a missile radome typical structure is designed. According to the electromagnetic wave transmission performance, high temperature resistance, bearing performance and weight index requirements of the missile radome, comprehensively developing the typical structural design of the missile radome, wherein the typical structure of the radome comprises a quartz ceramic nose cone part, a tile steel connecting ring part and a high temperature resistant adhesive for connecting the quartz ceramic nose cone and the tile steel connecting ring, and the three parts are used as main parts of the typical structure of the missile radome and are significant in evaluating the thermal matching performance of the main parts;
and secondly, preparing a test piece. Grinding the quartz ceramic test block 1 according to the thickness of the quartz ceramic at the joint of the quartz ceramic nose cone and the tile steel connecting ring in the actual missile radome, so that the thickness of the quartz ceramic test block 1 is the same as the thickness of the actual quartz ceramic; processing a tile steel test block 2 according to the thickness of a tile steel connecting ring at the bonding position in the actual missile radome, so that the thickness of the tile steel test block 2 is the same as the thickness of the actual tile steel connecting ring; according to the using amount of the high-temperature adhesive 3 in the actual missile radome, the high-temperature adhesive 3 with the same weight is weighed and configured and is used for connecting the quartz ceramic test block 1 and the tile steel test block 2, and the processing precision of the quartz ceramic test block 1 and the processing precision of the tile steel test block 2 are better than-0.001 mm.
And thirdly, manufacturing a test piece. According to the bonding process of the adhesive at the bonding position of the quartz ceramic nose cone and the tile steel connecting ring, polishing the quartz ceramic test block 1 and the tile steel test block 2 to enable the surfaces of the quartz ceramic test block 1 and the tile steel test block 2 to be smooth, bonding the quartz ceramic test block 1 and the tile steel test block 2 by using the high-temperature adhesive 3 (the thickness of the high-temperature adhesive 3 is limited by a limiting tool, the thickness precision is superior to-0.001 mm), and processing the bonding surface by using a tool to ensure that the flatness of the exposed bonding surface of the high-temperature adhesive 3 is superior to-0.001 mm.
Fourth, the test piece is measured. And measuring the section thickness and the side length of the test piece at a plurality of positions from top to bottom or from bottom to top by adopting a measuring instrument with the precision being better than 0.001mm, such as a dial indicator, recording the measured value, and calculating the section circumference of the test piece.
And fifthly, designing a thin-wall aluminum foil sleeve 4. According to the section perimeter of the typical structure of the bonded quartz ceramic test block 1+the tile steel test block 2, a thin-wall aluminum foil sleeve 4 matched with the quartz ceramic test block 1+the tile steel test block is designed, the thickness of the thin-wall aluminum foil sleeve 4 is 0.1mm, the thickness precision is better than +0.001mm, and the perimeter precision is better than +0.001mm.
And fifthly, manufacturing a test piece combined structure. Manufacturing a thin-wall aluminum foil sleeve 4 according to the thickness, the length and the circumference of each side of a test piece, sleeving the thin-wall aluminum foil sleeve 4 on a test piece combined structure consisting of a quartz ceramic test block 1 plus a tile steel test block 2 plus a high-temperature adhesive 3, wherein the sleeving position precision is better than +/-0.001 mm;
and sixthly, heating the test piece combined structure at high temperature. According to the working environment temperature (300-400 ℃) of the bonding part of the quartz ceramic nose cone of the actual missile radome and the connection ring of the steel-in-steel, the test piece combined structure is heated to 300-400 ℃ at high temperature, and a gap is generated by high-temperature cracking of the thin-wall aluminum foil sleeve 4 outside the test piece combined structure;
and seventhly, measuring and evaluating, namely measuring the breaking gap of the thin-wall aluminum foil sleeve 4 by using a measuring instrument with the precision being better than 0.001mm, such as a dial gauge, and evaluating the thermal expansion level of the test piece combined structure through the size of the breaking gap.
In the embodiment of the invention, as shown in fig. 1, the quartz ceramic test block 1 and the tile steel test block 2 are rectangular block test pieces with certain thickness, the two test pieces are identical in shape, the thickness of the two test pieces is designed according to the thickness of quartz ceramic and the tile steel connecting ring in an actual missile radome, the two test pieces are bonded together through the high-temperature adhesive 3, and the two test pieces can be bonded through resin, generally one or more of phenolic resin, epoxy resin and cyanate resin is adopted, so that the contact surface connection of the quartz ceramic test block 1 and the tile steel test block 2 is ensured to be firm.
Meanwhile, as shown in fig. 1, the thin-wall aluminum foil sleeve 4 made of aluminum foil material is sleeved outside the test piece combined structure, as shown in fig. 1, the thin-wall aluminum foil sleeve 4 is of a cross-shaped structure, two edges of the cross-shaped structure in the length direction are sleeved in the length direction of the test piece combined structure, two edges of the cross-shaped structure in the width direction are sleeved in the width direction of the test piece combined structure, sleeving in the length direction and the width direction of the test piece combined structure is achieved, and connecting bayonets are designed on the two edges of the cross-shaped structure in the length direction and the two edges of the width direction, so that assembly and disassembly are facilitated.
Meanwhile, in the embodiment of the invention, the micrometer is adopted to measure the rupture gap of the thin-wall aluminum foil sleeve 4, the micrometer precision is better than 0.001mm, the higher measurement precision is realized, the accuracy of a measurement structure can be ensured, and the measurement error is reduced.
The missile radome root connection thermal matching evaluation method provided by the invention can be used for aiming at the problem of thermal matching of the missile radome ceramic material, the tile steel material glue joint and the welding high temperature, and the missile radome root thermal matching can be detected by adopting a simple and visual means by simulating the actual running condition of the missile radome, and the tile steel material glue joint and the welding high Wen Cunzai thermal matching, so that the rationality of the adopted thermal connection mode is evaluated, and the missile radome root thermal connection design is guided.
While the invention has been described above with reference to the accompanying drawings, it will be apparent that the invention is not limited to the above embodiments, but is capable of being modified or applied directly to other applications without modification, as long as various insubstantial modifications of the method concept and technical solution of the invention are adopted, all within the scope of the invention.
Claims (10)
1. A missile cover root connection heat matching evaluation method is characterized in that: the method comprises the following steps:
step 1: according to index requirements, designing a typical structure of the missile radome;
step 2: machining a quartz ceramic test block (1) and a invar steel test block (2), and weighing a certain amount of high-temperature adhesive;
step 3: manufacturing a test piece;
step 4: measuring the section thickness and the side length of the test piece, recording the measured value, and calculating the section circumference of the test piece;
step 5: designing a thin-wall aluminum foil sleeve (4);
step 6: sleeving a thin-wall aluminum foil sleeve (4) outside the test piece to form a test piece combined structure;
step 7: heating the test piece combined structure at high temperature;
step 8: the fracture gap of the thin-wall aluminum foil sleeve (4) is measured, and the thermal expansion level of the test piece combined structure is evaluated through the size of the fracture gap.
2. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: the index requirements in the step 1 comprise the index requirements of electromagnetic wave transmission performance, high temperature resistance, bearing performance and weight of the missile radome.
3. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: the missile antenna housing typical structure in the step 1 comprises a quartz ceramic nose cone part, a tile steel connecting ring part and a high-temperature-resistant adhesive for connecting the quartz ceramic nose cone with the tile steel connecting ring.
4. The missile cover root connection thermal matching evaluation method according to claim 3, wherein the method comprises the following steps: the thickness of the quartz ceramic test block (1) in the step 2 is the same as the thickness of the bonding part of the quartz ceramic nose cone and the invar steel connecting ring in the actual missile radome;
the thickness of the tile steel test block (2) is the same as that of a tile steel connecting ring at the joint of a quartz ceramic nose cone and the tile steel connecting ring in an actual missile radome;
the weight of the weighed high-temperature adhesive (3) is the same as that of the adhesive used at the bonding part of the quartz ceramic nose cone and the tile steel connecting ring in the actual missile antenna housing.
5. The missile cover root connection thermal matching evaluation method according to claim 4, wherein the method comprises the following steps: the processing precision of the quartz ceramic test block (1) and the invar steel test block (2) is better than-0.001 mm.
6. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: and 3, manufacturing a test piece, namely polishing the quartz ceramic test piece (1) and the invar steel test piece (2) according to the bonding process requirement of the adhesive at the bonding position of the quartz ceramic nose cone and the invar steel connecting ring, bonding the quartz ceramic test piece (1) and the invar steel test piece (2), wherein the thickness precision of the high-temperature adhesive (3) is better than-0.001 mm, and performing flatness treatment on the bonding surface of the quartz ceramic test piece (1) and the invar steel test piece (2), so that the flatness of the bonding surface of the quartz ceramic test piece (1) and the invar steel test piece (2) is better than-0.001 mm.
7. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: the measuring tool adopted in the step 4 is a dial indicator with the accuracy better than 0.001.
8. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: the thickness of the thin-wall aluminum foil sleeve (4) in the step 5 is 0.1mm, the thickness precision is better than +0.001mm, and the perimeter precision is better than +0.001mm.
9. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: and 7, heating at 300-400 ℃, wherein the actual ambient temperature of the bonding part of the quartz ceramic nose cone of the missile antenna housing and the connection ring of the invar steel is the same as that of the actual ambient temperature of the bonding part of the quartz ceramic nose cone of the missile antenna housing and the connection ring of the invar steel.
10. The missile cover root connection thermal matching evaluation method according to claim 1, wherein the method comprises the following steps: and step 8, measuring the rupture gap of the thin-wall aluminum foil sleeve (4) by adopting a dial indicator with the precision being better than +0.001mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010875827.2A CN112100763B (en) | 2020-08-26 | 2020-08-26 | Missile cover root connection thermal matching evaluation method |
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| CN202010875827.2A CN112100763B (en) | 2020-08-26 | 2020-08-26 | Missile cover root connection thermal matching evaluation method |
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| CN112100763B true CN112100763B (en) | 2024-02-13 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103293179A (en) * | 2013-05-20 | 2013-09-11 | 江家嘉 | Device and method for testing early thermal expansion coefficient of concrete based on suspension method |
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| US9702676B1 (en) * | 2013-10-04 | 2017-07-11 | Washington State University | High strength munitions structures with inherent chemical energy |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103293179A (en) * | 2013-05-20 | 2013-09-11 | 江家嘉 | Device and method for testing early thermal expansion coefficient of concrete based on suspension method |
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