CN114953519B - Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method - Google Patents
Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method Download PDFInfo
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- CN114953519B CN114953519B CN202210309033.9A CN202210309033A CN114953519B CN 114953519 B CN114953519 B CN 114953519B CN 202210309033 A CN202210309033 A CN 202210309033A CN 114953519 B CN114953519 B CN 114953519B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C49/00—Blow-moulding, i.e. blowing a preform or parison to a desired shape within a mould; Apparatus therefor
- B29C49/071—Preforms or parisons characterised by their configuration, e.g. geometry, dimensions or physical properties
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/04—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/34—Layered products comprising a layer of synthetic resin comprising polyamides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C2949/00—Indexing scheme relating to blow-moulding
- B29C2949/07—Preforms or parisons characterised by their configuration
- B29C2949/0715—Preforms or parisons characterised by their configuration the preform having one end closed
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
Abstract
The invention provides a single-side crack enhancement simulation piece of an artificial debonding structure of a solid rocket engine and a forming method, wherein the enhancement simulation piece comprises a single-side crack test piece and a structure enhancement piece; a structural reinforcement is arranged at the front edge of the unilateral crack test piece; and the structural reinforcement and the installation end bevel of the unilateral crack test piece are in arc transition. The invention can effectively reduce the stress concentration at the manual release layer.
Description
Technical Field
The invention relates to the field of performance test of solid rocket engines, in particular to a single-side crack enhancement simulation piece of an artificial debonding structure of a solid rocket engine and a forming method.
Background
The rocket engine is a propulsion power device of a rocket aircraft system, and the solid rocket engine is widely applied to various tactical and strategic missiles due to the advantages of simple structure, reliable work, simple maintenance, strong quick reaction capability and the like. The solid rocket engine mainly comprises an engine combustion chamber shell, a solid propellant grain, a heat insulation layer, a lining layer, an artificial release layer, a spray pipe, a safe ignition device and the like.
In the process of long-term storage and transportation, the wall-attached cast solid engine may be damaged by ageing of propellant grains, heat insulating layers, lining layers and other materials, and the bonding interface of the charging combustion chamber is debonded. In the working process of the engine, the debonding is possibly further expanded under the influence of impact and vibration load, the structural integrity and the inner ballistic performance of the engine are affected slightly, and in severe cases, even fire penetration and combustion chamber pressure exceeding the use limit can be caused when the engine works, so that the engine explodes and other disastrous results are caused. The structural integrity is one of important research subjects of solid rocket engine technology, prevention of cracks and debonding of the grain is always one of focus of solid rocket engine research personnel, and the manual debonding structure effectively solves the debonding problem of the grain and an inner heat insulation layer. The manual debonding structure is a weak link (namely a free stretching interface) designed at the front end and the rear end or one end of a combustion chamber of the solid rocket engine, and the main functions of the manual debonding structure comprise three aspects: (1) Under the solidifying and cooling load, the stress level of the holes and the root parts of the wing grooves in the explosive column of the adhesive engine can be effectively reduced, and the stress level of the interface is reduced through the effect of the stress release ring; (2) Releasing internal stress of the heat insulation layers of the front and rear seal heads and the grain caused by external environment, load and other factors, ensuring that the grain is in a good stress state, and ensuring that the heat insulation layers and the shell have good bonding performance; (3) Under the pressure effect of ignition starting transient of the solid rocket engine, the stress state of the front seal head and the rear seal head is improved so as to relieve the stress caused by impact load and avoid the occurrence of sudden deformation impact, thereby causing the structural damage of the engine.
Due to the fact that under the factors of complex geometric configuration of solid charge, complex inner cavity surface of the explosive column and complex external load and the like, the requirement of the inner ballistic performance of an engine can be met by adopting the artificial debonding technology, and meanwhile the stress strain level of the explosive column can be effectively reduced. However, the artificial debonding layer can be regarded as a macroscopic crack, so that the stress state of the crack front edge is very bad, and a very high stress area appears on the front edge of the artificial debonding layer, so that debonding is likely to occur due to excessive interfacial normal stress. The problem of manual debonding structural integrity is also growing with increased engine diameter and length, increased operating pressures, and the long-term storage and cruising conditions that some solid rocket engines must experience.
The front edge of the root of the artificial release layer is in a Y-shaped structure, so that stress concentration is easy to generate, and damage is caused. In order to reduce the stress concentration at the tail end of the artificial debonding layer, the interface debonding and more serious consequences are avoided, the tail end of the artificial debonding layer is changed into a smooth circular arc as much as possible, and the stress concentration caused by the existence of a folding angle is reduced. The current stress state of the artificial debonding layer of the solid engine is simulated by adopting a circumferential crack test piece, because of the shape characteristics, the test piece cannot be provided with a structural reinforcing piece to reduce the stress concentration of the front edge of the artificial debonding structure, the field does not have a reinforcing simulation piece for a single-side crack of the artificial debonding structure of the solid rocket engine, the stress state of the front edge of the artificial debonding structure cannot be simulated in the actual working of the solid engine, and the stress concentration of the front edge of the artificial debonding structure is improved through the reinforcing simulation piece, so that the current research has some defects and limitations:
(1) The folding angle of the front edge of the manual debonding structure is changed into an arc shape, and the problem that the arc-shaped member deviates from the design state due to sliding in the manufacturing process possibly exists. The shape of the circular arc cannot be maintained, so that the grain is restored to a folded angle state again, and larger stress concentration is generated.
(2) The currently used circumferential crack test piece cannot be molded with the added structural reinforcement due to the shape and structural characteristics thereof, and the proper combination of the crack test piece and the reinforcement is required.
Disclosure of Invention
In view of the above, the invention provides a single-side crack enhancement simulation piece of an artificial debonding structure of a solid rocket engine and a forming method, which can effectively reduce stress concentration at an artificial debonding layer.
The technical scheme adopted by the invention is as follows:
a solid rocket engine artificial debonding structure unilateral crack enhancement simulator, the unilateral crack enhancement simulator comprising: a single-sided crack specimen and structural reinforcement;
the structural reinforcement is arranged at the front edge of the unilateral crack test piece; and the structural reinforcement and the installation end bevel of the unilateral crack test piece are in arc transition.
Further, the structural reinforcement comprises four layers of high-elasticity nylon cloth and a rubber rope; the rubber rope is fixed in a mode that a layer of high-elasticity nylon cloth is placed on the inner side of the rubber rope and three layers of high-elasticity nylon cloth are placed on the outer side of the rubber rope; gao Danni the tensile strength of the tarpaulin is more than 30Mpa, and the elongation is more than 100%.
Further, the single-side crack test piece heat insulation layer is formed by overlapping a layer of rubber sheets.
Further, in the range of 15mm or less from the front edge of the structural reinforcement, three layers of high-elastic nylon cloth on the outer side of the rubber rope are not bonded, and the rest of high-elastic nylon cloth is subjected to gum dipping and then is molded with the heat insulation layer.
Further, the Gao Danni tarpaul is a caprone cloth.
A method for forming a single-side crack enhancement simulation piece of an artificial debonding structure of a solid rocket engine comprises the following steps:
step one, brushing adhesive cement on four layers of bidirectional high-elastic nylon cloth in sequence, wrapping the rubber rope according to a placement mode of three layers on the outer side and one layer on the inner side, and enabling the bent part to be in arc transition, wherein the three layers of high-elastic nylon cloth on the outer side of the rubber rope are not adhered in a range below 15mm from the front edge of the edge, so that a structural reinforcing piece is formed;
step two, placing the structural reinforcement into a mold for prepressing and shaping;
and thirdly, cutting the pre-pressed and shaped structural reinforcement according to requirements, and carrying out compression molding on the structural reinforcement and the single-side crack test piece heat insulation layer.
Further, the single-side crack test piece heat insulation layer is formed by overlapping a layer of rubber sheets.
The beneficial effects are that:
1. the invention adopts a unilateral crack test piece, can be well compression molded with the structural reinforcement, can simulate the stress state of the front edge of the artificial debonding structure when the reinforcing simulation piece is applied to the solid engine in practice, enables the folded angle of the front edge of the artificial debonding structure to be in arc transition through the structural reinforcement, avoids abrupt change of the shape of the front edge of the artificial debonding structure, greatly reduces the risk of stress concentration, and improves the structural safety of the engine; the invention has simple structure and simple and convenient manufacturing process, can effectively reduce the stress concentration at the manual debonding layer, improves the safety coefficient of the front edge of the manual debonding structure, reduces the risk of interface debonding and also ensures the working efficiency.
2. According to the invention, through four layers of caprone cloth, the positions of the rubber ropes are fixed by adopting a mode of placing one layer on the inner side and three layers on the outer side, so that the possible deviation of the rubber ropes in the manufacturing process is avoided, and the shape of the arc is kept.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a partial schematic view of a structural reinforcement;
FIG. 3 is a schematic structural diagram of a caprone test fixture used in the molding of the invention;
FIG. 4 is a schematic structural diagram of a sample fixture used in the molding of the present invention;
wherein, 1-structure reinforcement, 2-unilateral crack test piece, 3-rubber rope, 4-carpron cloth.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The embodiment provides a single-side crack enhancement simulation piece of an artificial debonding structure of a solid rocket engine, which comprises a single-side crack test piece 2 and a structural enhancement piece 1 as shown in fig. 1.
The front edge of the unilateral crack test piece 2 is provided with a structural reinforcement 1 which can improve the stress concentration phenomenon of the front edge of the artificial debonding structure; the installation end angle of the structural reinforcement 1 and the unilateral crack test piece 2 is in arc transition.
As shown in fig. 2, the tail end of the structural reinforcement 1 is fixed with a rubber rope 3 through four layers of caprone cloth 4, the folding angle of the structural reinforcement 1 is changed into arc transition through the arc surface of the rubber rope 3, and meanwhile, the rubber rope 3 is fixed in a mode that the three layers of caprone cloth 4 are wrapped on the outer side of the rubber rope 3 and one layer of caprone cloth 4 is placed on the inner side of the rubber rope, so that the rubber rope 3 cannot deviate from a design state due to sliding in the manufacturing process of the artificial debonding structure, the stress concentration of the artificial debonding layer is avoided, the risk of failure of a solid engine is reduced, and the safety and reliability of the solid propellant are improved. Meanwhile, in the range of less than 15mm from the front edge of the structural reinforcement 1, three layers of high-elastic nylon cloth on the outer side of the rubber rope 3 are not bonded, and after the rest high-elastic nylon cloth is dipped, the rubber cloth is molded with a heat insulation layer of the unilateral crack test piece 2. The heat insulation layer of the unilateral crack test piece 2 is formed by overlapping a layer of rubber sheets.
The caprone cloth can also adopt other high-elasticity nylon cloth with the tensile strength of more than 30Mpa and the elongation percentage of more than 100 percent.
In this example, the external dimensions of the single-sided crack specimen 2 were 200×25×24mm: the structural reinforcement 1 with the thickness of 2.4mm on one side is adopted, and is subjected to gum dipping and folding and then is subjected to die pressing with the heat insulation layer.
Rubber ropes 3 with the diameter D less than or equal to 6mm are placed on the front edge of the folding edge, wherein one layer of caprone cloth 4 is arranged on the inner side of the rubber ropes 3 (layer a in fig. 2), and three layers of caprone cloth 4 are arranged on the outer side (layer b in fig. 2). The three layers of the caprone cloth 4 outside the rubber rope 3 are not dipped in glue within the range of less than or equal to 15mm from the front edge L of the edge, and the caprone cloth 4 of each layer is not bonded.
According to the design of the test scheme, the corresponding caprone cloth tool and the sample tool are newly processed, as shown in fig. 3 and 4. The front end inside the capron cloth tool is in a fusiform shape, and the fusiform front end is provided with a groove. The sample tool is of an upper layer structure and a lower layer structure, a threaded hole is formed in the upper layer, and an empty interlayer is arranged between the upper layer and the lower layer and is used for forming a single-side crack enhancement simulation piece of the artificial debonding structure of the solid rocket engine; positioning structures are arranged on two sides.
The method for forming the single-side crack enhancement simulation piece of the artificial debonding structure of the solid rocket engine comprises the following specific steps:
step one, brushing mucilage on four layers of bidirectional caprone cloth 4 in sequence, wrapping the rubber rope 3 according to a placement mode of three layers on the outer side and one layer on the inner side, ensuring that the caprone cloth 4 is stretched, enabling a bending part to be in arc transition, and enabling the three layers of high-elasticity nylon cloth on the outer side of the rubber rope 3 not to be bonded within a range of less than 15mm from the front edge of the edge, so as to form a preformed structural reinforcement 1;
step two, placing the preformed structural reinforcement 1 into a caprone cloth tool for prepressing and shaping;
and thirdly, cutting the pre-pressed and shaped structural reinforcement 1 according to the requirement, and sequentially placing the structural reinforcement 1 and the heat insulation layer into a test piece tool for compression molding.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A solid rocket engine manual debonding structural unilateral crack enhancement simulator, characterized in that the unilateral crack enhancement simulator comprises: a single-sided crack specimen and structural reinforcement;
the structural reinforcement is arranged at the front edge of the unilateral crack test piece; the structural reinforcement and the mounting end folded angle of the unilateral crack test piece are in arc transition;
the structural reinforcement comprises four layers of high-elasticity nylon cloth and a rubber rope; the rubber rope is fixed in a mode that a layer of high-elasticity nylon cloth is placed on the inner side of the rubber rope and three layers of high-elasticity nylon cloth are placed on the outer side of the rubber rope; gao Danni the tensile strength of the tarpaulin is more than 30Mpa, and the elongation is more than 100%.
2. The solid rocket engine artificial debonding structure single-sided crack enhancement simulator of claim 1, wherein the single-sided crack test piece heat insulation layer is formed by overlapping a layer of rubber sheets.
3. The artificial debonding structural unilateral crack enhancement simulator of the solid rocket motor of claim 2, wherein the three layers of high-elastic nylon cloth outside the rubber rope are not bonded within the range of less than 15mm from the front edge of the structural reinforcement, and the rest of high-elastic nylon cloth is molded with the heat insulation layer after being impregnated with glue.
4. A solid rocket motor artificial debonding structure unilateral crack growth simulator as recited in any one of claims 2-3, wherein said Gao Danni tarpaul is a caprone cloth.
5. The method for forming the single-side crack enhancement simulation piece of the artificial debonding structure of the solid rocket engine is characterized by comprising the following steps of:
step one, brushing adhesive cement on four layers of bidirectional high-elastic nylon cloth in sequence, wrapping the rubber rope according to a placement mode of three layers on the outer side and one layer on the inner side, and enabling the bent part to be in arc transition, wherein the three layers of high-elastic nylon cloth on the outer side of the rubber rope are not adhered in a range below 15mm from the front edge of the edge, so that a structural reinforcing piece is formed;
step two, placing the structural reinforcement into a mold for prepressing and shaping;
and thirdly, cutting the pre-pressed and shaped structural reinforcement according to requirements, and carrying out compression molding on the structural reinforcement and the single-side crack test piece heat insulation layer.
6. The method for forming the single-sided crack enhancement simulation piece of the artificial debonding structure of the solid rocket engine as claimed in claim 5, wherein the single-sided crack test piece heat insulation layer is formed by overlapping a layer of rubber sheets.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210309033.9A CN114953519B (en) | 2022-03-27 | 2022-03-27 | Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method |
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| CN202210309033.9A CN114953519B (en) | 2022-03-27 | 2022-03-27 | Single-side crack enhancement simulation piece of artificial debonding structure of solid rocket engine and forming method |
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| CN114953519A CN114953519A (en) | 2022-08-30 |
| CN114953519B true CN114953519B (en) | 2023-09-15 |
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| CN114953519A (en) | 2022-08-30 |
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