CN111136938B - Composite material breakable rod with controllable damage energy and manufacturing method thereof - Google Patents
Composite material breakable rod with controllable damage energy and manufacturing method thereof Download PDFInfo
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- CN111136938B CN111136938B CN201811314797.7A CN201811314797A CN111136938B CN 111136938 B CN111136938 B CN 111136938B CN 201811314797 A CN201811314797 A CN 201811314797A CN 111136938 B CN111136938 B CN 111136938B
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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
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
- B29C70/52—Pultrusion, i.e. forming and compressing by continuously pulling through a die
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- 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
- B29L2031/06—Rods, e.g. connecting rods, rails, stakes
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Abstract
The invention relates to a composite material breakable rod with controllable breakage energy and a manufacturing method thereof. The fragile rod comprises an inner structure layer, at least one abrupt change layer and an outer structure layer from inside to outside; the inner structure layer, the mutation layer and the outer structure layer are respectively and independently made of fiber reinforced composite materials, and the fiber reinforced composite materials comprise fiber reinforcements made of reinforced fibers and resin matrixes compounded in the fiber reinforcements; the reinforcing fibers contained in the inner structural layer and the outer structural layer are arranged along the axial direction of the fragile rod, and the reinforcing fibers contained in the abrupt change layer are arranged along the circumferential direction of the fragile rod. The manufacturing method comprises the steps of sequentially paving the fiber reinforcement bodies contained in the inner structural layer, the mutation layer and the outer structural layer to obtain a paving layer structure; placing the laying structure in a resin matrix material liquid for impregnation to obtain a prepreg; and curing and molding the prepreg through a pultrusion process to obtain the fragile rod. The fragile rod has the advantages of light structure, good environmental adaptability, simple forming process and the like.
Description
Technical Field
The invention belongs to the technical field of airport accessories, and particularly relates to a composite material breakable rod with controllable breakage energy and a manufacturing method thereof.
Background
The fragile pole (the fragile pole) is widely applied to main bearing structures of light poles and towers, instrument landing equipment poles and wind vane poles in various large airports. The structure of the fragile rod must meet the requirements of normal work under severe environments (jet airflow, earthquake, long-time solar radiation, natural wind, salt mist corrosion and the like) and being fragile when being accidentally impacted in any direction, so that the structural damage to the aircraft is reduced to the maximum extent. At present, no mature and reliable fragile rod product exists in China, and the fragile rods for civil airports are all metal aluminum products imported from two countries of Denmark and Norway. The aluminum alloy is an isotropic material, and when a certain impact load is applied, the load can be effectively and uniformly transmitted from the outer structural layer to the inner structural layer. However, such metal rods have high requirements for metal materials, complex processing technology, large specific gravity, high price and poor environmental suitability.
At present, the manufacturing process of the aluminum metal breakable bars is not disclosed internationally, and the production of the aluminum metal breakable bars is monopolized all the time, so that a large amount of foreign exchange imported aluminum metal breakable bars are needed to serve as airport accessories in China.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a composite material breakable rod with controllable breakage energy and a manufacturing method thereof. The fragile rod has the advantages of light structure, good environmental adaptability, simple forming process and the like.
In order to achieve the above object, the present invention provides in a first aspect a composite frangible rod with controllable breakage energy, comprising, in order from inside to outside, an inner structural layer, at least one strain layer and an outer structural layer; the inner structural layer, the mutant layer and the outer structural layer are each independently made of a fiber-reinforced composite material comprising a fiber reinforcement made of reinforcing fibers and a resin matrix compounded in the fiber reinforcement; the inner structure layer with reinforcing fiber who contains in the outer structure layer all follows the axial direction of fragile pole sets up, the reinforcing fiber who contains in the sudden change layer is followed the circumferential direction of fragile pole sets up.
Preferably, the fiber reinforcement comprised in the inner structural layer and the outer structural layer each consists of two fiber felt layers and at least one fiber layer sandwiched between the two fiber felt layers; the fiber reinforcement comprised in the mutation layer consists of at least one fiber layer.
Preferably, the fibrous mat layer is made of alkali-free glass fibers; the fiber layer is made of carbon fibers.
Preferably, the thickness of each fiber felt layer is 0.09-0.11 mm; and/or the thickness of each fiber layer is 0.11-0.13 mm.
Preferably, the fibre reinforcement comprised in the inner and outer structural layers consists of two fibre felt layers and 18 fibre layers sandwiched between the two fibre felt layers; the fiber reinforcement comprised in the mutation layer consists of one fiber layer.
Preferably, the thickness of each fiber felt layer is 0.09-0.11 mm, the thickness of each fiber layer is 0.11-0.13 mm, and the total thickness of the fragile rods is 4.43-5.25 mm.
Preferably, each of the fibrous batt layers has a thickness of 0.1mm, each of the fibrous layers has a thickness of 0.125mm, and the fragile rods have a total thickness of 5.025 mm.
Preferably, the resin matrix is an unsaturated polyester resin; preferably, the unsaturated polyester resin is selected from the group consisting of an ortho-benzene type unsaturated polyester resin, a meta-benzene type unsaturated polyester resin, a xylene type unsaturated polyester resin, a bisphenol a type unsaturated polyester resin, a halogenated unsaturated polyester resin, and a vinyl unsaturated polyester resin.
The present invention provides in a second aspect a method of manufacturing the frangible stems defined in the first aspect of the invention, the method comprising the steps of:
(1) sequentially laying the fiber reinforcement bodies contained in the inner structure layer, the mutation layer and the outer structure layer to obtain a laying structure;
(2) placing the layer structure obtained in the step (1) into a resin matrix material liquid for impregnation to obtain a prepreg;
(3) and (3) curing and molding the prepreg obtained in the step (2) through a pultrusion process to obtain the fragile rod.
Preferably, step (3) comprises the sub-steps of:
(a) placing the prepreg obtained in the step (2) in a preforming device for preforming into a preform;
(b) placing the prefabricated body obtained in the step (a) in a forming die for curing to obtain a fragile rod profile;
(c) naturally cooling the brittle rod section obtained in the step (b), thereby producing the brittle rod.
Compared with the prior art, the invention at least has the following beneficial effects:
(1) the invention adopts fiber reinforced composite material to manufacture the fragile rod for the first time, and an inner structure layer, a sudden change layer and an outer structure layer in the fragile rod are all made of the fiber reinforced composite material, wherein fiber reinforcements contained in the inner structure layer and the outer structure layer are arranged along the axial direction of the fragile rod, and fiber reinforcements contained in the sudden change layer are arranged along the circumferential direction of the fragile rod, so that the fragile rod can be automatically cracked under a triggering condition while having certain strength and rigidity; compared with the traditional metal material, the fragile rod has the advantages of light structure, good environmental adaptability, simple forming process and the like, can break the monopoly abroad, makes up the blank in China, and can save a large amount of foreign exchange.
(2) The frangible stems of the present invention fully meet the requirements of the international civil aviation organization standard, do not break and deform when exposed to wind or jet air at speeds up to 480km/h (260 knots), but are immediately breakable, bendable or yielding upon exposure to a sudden impact force of an aircraft weighing 3000kg, landing on a flight at 140km/h (75 knots) or taxiing on the ground at 50km/h (27 knots); the breakage energy of the fragile rod is controllable, the force applied to the aircraft at the moment of collision contact of the fragile rod and the aircraft is not more than 45kN, and the maximum energy applied to the aircraft is not more than 55 kJ.
(3) The manufacturing method of the fragile rod has the advantages that the manufacturing method is simple and controllable, and the fragile rods with various sizes can be manufactured according to the requirements; the manufacturing method of the invention can effectively save the cost of raw materials, effectively reduce the manufacturing time and further greatly reduce the production cost.
Drawings
The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the components in the drawings do not necessarily correspond to those of an actual product.
FIG. 1 is a perspective view of one embodiment of the frangible stems of the present invention.
Fig. 2 is an enlarged schematic view of a cross-section of the frangible stems of fig. 1.
In the figure: 1: an inner structural layer; 2: a mutant layer; 3: an outer structural layer.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The present invention provides in a first aspect a composite frangible stems having controlled failure energy, fig. 1 being a schematic perspective view of an embodiment of the frangible stem of the present invention, fig. 2 being an enlarged schematic cross-sectional view of the frangible stem of fig. 1; in the present invention, the cross section of the breakable bar means a cut plane cut perpendicular to the axis of the breakable bar.
The fragile rod comprises an inner structural layer 1, at least one mutation layer 2 and an outer structural layer 3 from inside to outside in sequence, for example, as shown in fig. 2, the fragile rod is in a round tube shape; the inner structural layer 1, the mutant layer 2 and the outer structural layer 3 are each independently made of a fiber-reinforced composite material comprising a fiber reinforcement made of reinforcing fibers and a resin matrix compounded in the fiber reinforcement; the inner structure layer with reinforcing fiber who contains in the outer structure layer all follows the axial direction of fragile pole sets up, the reinforcing fiber who contains in the sudden change layer is followed the circumferential direction of fragile pole sets up. In the present invention, the inside of the fragile rod may be, for example, a hollow structure or a solid structure, and preferably, the inside of the fragile rod is a hollow structure, for example, as shown in fig. 2; in the present invention, the inner structure layer 1, the mutation layer 2 and the outer structure layer 3 are each independently made of a fiber-reinforced composite material, which means that the types of the fiber-reinforced composite materials used for making the inner structure layer 1, the mutation layer 2 and the outer structure layer 3 may be the same or different, that is, the types of the fiber reinforcement included in the fiber-reinforced composite materials and the resin matrix compounded in the fiber reinforcement may be the same or different; in the present invention, the axial direction of the fragile rods is also referred to as the 0 ° direction, and the circumferential direction of the fragile rods is also referred to as the 90 ° direction; in the present invention, the breakable bars are also referred to as breakable bars.
Fiber-reinforced composites, such as carbon fiber-reinforced resin-based composites, have a specific stiffness of 5 times or more and a specific strength of 10 times or more that of aluminum alloy materials, and are commonly used as load-bearing structural materials. The invention adopts the fiber reinforced composite material to manufacture the fragile rod for the first time, and the inner structure layer, the abrupt change layer and the outer structure layer in the fragile rod are all made of the fiber reinforced composite material; the invention utilizes the characteristics that the fiber reinforced composite material has high tensile strength along the fiber direction and is easy to tear in the direction vertical to the fiber direction for the first time, reasonably designs the structure of the fragile rod, so that the fiber reinforcements contained in the inner structure layer and the outer structure layer are arranged along the axial direction of the fragile rod, and the fiber reinforcements contained in the mutation layer are arranged along the circumferential direction of the fragile rod, so that the fragile rod can be automatically cracked under a triggering condition while having certain strength and rigidity; specifically, the fragile rod in the invention adopts the inner structure layer and the outer structure layer with higher rigidity to realize a static bearing function, and the sudden change layer (rigidity sudden change layer) with lower rigidity is pre-embedded between the inner structure layer and the outer structure layer to realize a dynamic bearing function, so that stress is mainly concentrated on the outer surface of the fragile rod when the fragile rod is subjected to static loading, and stress is mainly concentrated on the rigidity sudden change layer after the fragile rod is subjected to certain impact load, so that the fragile rod can be quickly layered to form large-size interface cracks, thereby losing the bearing capacity to generate structural catastrophe and achieving the purpose of easy folding and frangibility.
Compared with the traditional metal material, the fragile rod has the advantages of light structure, good environmental adaptability, simple forming process, low cost and the like, can break the monopoly abroad, makes up the blank in China, and can save a large amount of foreign exchange.
According to some preferred embodiments, the frangible stems comprise a number of the tapered layers of 1 to 10 (e.g., 1, 2, 3, 4, 5, 6, 7, 8, 9, or 10).
According to some preferred embodiments, the fiber reinforcement comprised in the inner structural layer and the outer structural layer are both composed of two fiber felt layers and at least one fiber layer sandwiched between the two fiber felt layers; the fiber reinforcement comprised in the mutation layer consists of at least one fiber layer; that is, in the present embodiment, each of the inner structural layer and the outer structural layer includes two fiber felt layers, at least one fiber layer sandwiched between the two fiber felt layers, and a resin matrix compounded in the fiber felt layers and the fiber layer; the mutant layer comprises at least one fiber layer and a resin matrix compounded in the fiber layer. In the present invention, both the fibrous batt layer and the fibrous layer are made of reinforcing fibers; the fibrous mat layer and the reinforcing fibers contained in the fibrous layer are each independently selected from the group consisting of glass fibers, carbon fibers, and boron fibers.
According to some preferred embodiments, the fibrous mat layer is made of glass fibers (e.g., alkali-free glass fibers, chemical-resistant glass fibers, high alkali glass fibers, medium alkali glass fibers, etc.). In the present invention, when the fiber mat layer is made of glass fibers, the fiber mat layer is also referred to as a glass fiber mat layer or a glass mat layer.
According to some preferred embodiments, the fiber mat layer is made of alkali-free glass fibers (e.g., E-6-2400-386T glass fibers); the fiber layer is made of carbon fibers. In the present invention, the direction of the glass fibers contained in the fiber mat layer is set in the same direction as the arrangement direction of the carbon fibers contained in the fiber layers sandwiched between the two fiber mat layers.
According to some preferred embodiments, each of the fibrous batt layers has a thickness of 0.09 to 0.11mm (e.g., 0.09, 0.095, 0.1, 0.105, or 0.11 mm); and/or the thickness of each fiber layer is 0.11-0.13 mm (such as 0.11, 0.115, 0.12, 0.125 or 0.13 mm). In the invention, the thickness of each fiber felt layer is preferably 0.09-0.11 mm, and the thickness of each fiber layer is preferably 0.11-0.13 mm, and the inventor finds that the matching property between the fiber felt layer with the thickness and the fiber layer with the thickness is best, and the comprehensive advantages of the static bearing function and the dynamic bearing function of the fragile bar can be exerted to the maximum.
According to some preferred embodiments, the fiber reinforcement comprised in the inner and outer structural layers consists of two fiber felt layers and 1 to 30, preferably 10 to 20 (e.g. 10, 11, 12, 13, 14, 15, 16, 17, 18, 19 or 20) fiber layers sandwiched between the two fiber felt layers; the fiber reinforcement contained in the mutation layer consists of 1-5 (for example, 1, 2, 3, 4 or 5) fiber layers. In the invention, the fragile rods with different thicknesses can be obtained by arranging different fiber layers in the inner structural layer, the mutation layer and the outer structural layer according to different requirements.
According to some preferred real modes, the fiber reinforcement comprised in the inner structural layer and in the outer structural layer is composed of two fibrous batt layers and 18 fibrous layers sandwiched between the two fibrous batt layers; the fiber reinforcement comprised in the mutation layer consists of one fiber layer.
According to some preferred embodiments, each of the fiber felt layers has a thickness of 0.09 to 0.11mm, each of the fiber layers has a thickness of 0.11 to 0.13mm, and the fragile rods have a total thickness of 4.43 to 5.25 mm. In the present invention, it is preferable that the fiber layer sandwiched between two fiber felt layers is 18 layers, the fiber reinforcement included in the abrupt change layer is composed of one fiber layer, and the thickness of each of the fiber felt layers is 0.09 to 0.11mm, and the thickness of each of the fiber layers is 0.11 to 0.13mm, so that the total thickness (total wall thickness) of the fragile bar is 4.43 to 5.25 mm; the invention finds that the static bearing function and the dynamic bearing function of the fragile rod under the parameter are best, and the energy is more controllable when the fragile rod is damaged. In particular, the total thickness of the frangible stems referred to herein refers to the total thickness of the fiber reinforcement contained in the inner structural layer, the strain layer and the outer structural layer, with the resin matrix having negligible effect on the thickness of the frangible stems.
According to some preferred embodiments, each of the fibrous batt layers has a thickness of 0.1mm, each of the fibrous layers has a thickness of 0.125mm, and the fragile rods have a total thickness of 5.025 mm.
According to some preferred embodiments, the resin matrix is an unsaturated polyester resin; preferably, the unsaturated polyester resin is selected from the group consisting of an ortho-benzene type unsaturated polyester resin (e.g., 191 unsaturated polyester resin), a meta-benzene type unsaturated polyester resin, a xylene type unsaturated polyester resin, a bisphenol a type unsaturated polyester resin, a halogenated unsaturated polyester resin, and a vinyl unsaturated polyester resin; more preferably, the unsaturated polyester resin is an o-phenyl type unsaturated polyester resin or a vinyl type unsaturated polyester resin. In the invention, when the resin matrix in the fragile bar is the o-type unsaturated polyester resin or the vinyl unsaturated polyester resin, the force applied to the aircraft at the moment of collision and contact of the fragile bar with the aircraft can be more effectively reduced, and the maximum energy applied to the aircraft can be more effectively reduced, so that the breakage energy of the fragile bar is more controllable.
According to some preferred embodiments, the force applied to the aircraft at the moment of impact contact of the fragile bar with the aircraft is not greater than 45kN and the maximum energy applied to the aircraft is not greater than 55 kJ.
The fragile rods of the present invention fully meet the requirements of the international civil aviation organization standard, do not break and deform when exposed to wind or jet air at speeds up to 480km/h (260 knots), but are immediately breakable, bent or yielding upon exposure to a sudden impact force of an aircraft weighing 3000kg, flying to the ground at 140km/h (75 knots) or taxiing on the ground at 50km/h (27 knots); the breakage energy of the fragile rod is controllable, the force applied to the aircraft at the moment of collision contact of the fragile rod and the aircraft is not more than 45kN, and the maximum energy applied to the aircraft is not more than 55 kJ.
The present invention provides in a second aspect a method of manufacturing the frangible stems defined in the first aspect of the invention, the method comprising the steps of:
(1) sequentially laying the fiber reinforcement bodies contained in the inner structure layer, the mutation layer and the outer structure layer to obtain a laying structure;
(2) placing the layering structure obtained in the step (1) into a resin matrix feed liquid (such as an unsaturated polyester resin feed liquid) for impregnation to obtain a prepreg; wherein, the resin matrix material liquid can be resin or a solution containing the resin;
(3) and (3) curing and molding the prepreg obtained in the step (2) through a pultrusion process to obtain the fragile rod.
According to a particular embodiment, in step (1): use 0 orientation to be breakable pole axial direction, 90 orientations are breakable pole circumferential direction, and the scheme of laying of adoption is: glass mat layer/carbon fiber in 0 ° (18 layers)/glass mat layer/carbon fiber in 90 ° (1 layer)/glass mat layer/carbon fiber in 0 ° (18 layers)/glass mat layer; the thickness of each fiber layer is 0.125mm, the thickness of each glass mat layer is 0.1mm, and the total thickness of the fragile rod is 5.025 mm.
According to some preferred embodiments, step (3) comprises the following sub-steps:
(a) placing the prepreg obtained in the step (2) in a preforming device for preforming into a preform; for example, the preforming device comprises one or more groups of preforming dies, the whole preforming process is operated continuously, the prepreg is firstly pultruded by a pultrusion die to form an inner structural layer, then a 90-degree direction mutation layer is wound and formed on the outer surface of the inner structural layer, finally the inner structural layer is used as a pultrusion core die, the outer structural layer is pultruded to be gradually transited into a preform through the pultrusion-winding combined process;
(b) placing the preform obtained in the step (a) in a forming mold for curing (for example, curing according to the curing conditions of a resin system) to obtain a fragile rod profile;
(c) naturally cooling the fragile rod section obtained in the step (b), for example, naturally cooling the fragile rod section by natural wind (air cooling), thereby producing the fragile rod. In the present invention, the brittle rod profile is set after it has been completely cooled (e.g., to room temperature).
In the invention, the fragile rod is integrally molded by adopting a pultrusion process, a prefabricated body is prepared in a pultrusion system according to a preset layering system, and finally, the prefabricated body is subjected to co-curing molding in a molding mold. The manufacturing method of the fragile rod has the advantages that the manufacturing method is simple and controllable, and the fragile rods with various sizes can be manufactured according to the requirements; the manufacturing method of the invention can effectively save the cost of raw materials, can effectively reduce the manufacturing time, and further can greatly reduce the production cost.
According to some preferred embodiments, the method further comprises the step of removing excess resin from the preform obtained in step (a) before performing step (b).
According to some preferred embodiments, the method further comprises the step of cutting the produced frangible stems to form frangible stems of a desired length dimension.
According to some preferred embodiments, the method further comprises the step of spraying a three-proofing paint (e.g., a special three-proofing paint) after the obtained fragile rod is subjected to grinding and trimming.
According to some preferred embodiments, in step (b), the curing temperature is 120 to 150 ℃ (e.g., 120 ℃, 125 ℃, 130 ℃, 135 ℃, 140 ℃, 145 ℃ or 150 ℃), the curing pressure is 0.1 to 2MPa (e.g., 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8, 0.9, 1, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9 or 2MPa), and the curing time is 1 to 4 hours (e.g., 1, 1.5, 2, 2.5, 3, 3.5, or 4 hours).
The present invention will be further described with reference to the following examples. These examples are merely illustrative of preferred embodiments of the present invention and the scope of the present invention should not be construed as being limited to these examples.
Example 1
The method for manufacturing the composite material fragile rod with controllable damage energy comprises the following steps:
firstly, leading out glass fibers from a yarn bobbin, and uniformly and tidily arranging the glass fibers according to the laying sequence of a glass mat layer/carbon fibers (18 layers) in the 0-degree direction/glass mat layer/carbon fibers (1 layer) in the 90-degree direction/glass mat layer/carbon fibers (18 layers) in the 0-degree direction/glass mat layer to obtain a layering structure; wherein the glass mat layer is made of alkali-free glass fibers; the thickness of each fiber layer is 0.125mm, the thickness of each glass mat layer is 0.1mm, and the total thickness of the fragile rod is 5.025 mm.
Secondly, enabling the spreading layer structure (the fibers and the glass mat which are arranged orderly) to pass through a dipping tank filled with the vinyl unsaturated polyester resin matrix material liquid at a constant speed to ensure that the materials are uniformly dipped to obtain the prepreg.
Thirdly, the prepreg passes through a preforming device and continuously runs to ensure the corresponding positions of the prepreg and the preforming device; the prepreg is gradually transitioned into a preform in a preforming device while extruding excess resin.
And fourthly, placing the prefabricated body in a forming die for curing, wherein the curing temperature is 140 ℃, the curing pressure is 0.8MPa, and the curing time is 1.5h, so that the fragile rod section bar is obtained, and cooling and shaping are carried out on the obtained fragile rod section bar after curing is finished.
After cooling, the solidified section bar is pulled out from the die under the traction of a traction device, and then the section bar is cut according to the required section bar size, so as to obtain the fragile bar made of the composite material.
And sixthly, polishing and trimming the fragile rod, and spraying special three-proofing paint.
Exposing the fragile rods prepared in the embodiment to wind power and jet air flow with the speed of 480km/h (260 knots), wherein the fragile rods in the embodiment are not damaged and deformed; the fragile bar in this embodiment breaks immediately upon receiving a sudden impact force of an aircraft weighing 3000kg, flying at 140km/h (75 knots) for landing or taxiing on the ground at 50km/h (27 knots); through a ground simulation impact test, the force applied to the simulation piece at the moment of collision and contact of the fragile rod and the aircraft simulation piece in the embodiment is 29kN (less than 35kN), and the maximum energy applied to the simulation piece is 38kJ (less than 45 kJ); the specific gravity of the breakable bars described in this example is 2.05X 10-3kg/m3The specific gravity refers to a ratio of weight to volume of the fragile rod.
Example 2
Example 2 is essentially the same as example 1, except that:
in the formula I, the thickness of each fiber layer is 0.135mm, the thickness of each glass mat layer is 0.115mm, and the total thickness of the fragile rods is 5.455 mm.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Example 3
Example 3 is essentially the same as example 1, except that:
in the formula I, the thickness of each fiber layer is 0.105mm, the thickness of each glass mat layer is 0.085mm, and the total thickness of the fragile rods is 4.225 mm.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Example 4
Example 4 is essentially the same as example 1, except that:
firstly, leading out glass fibers from a yarn bobbin, and uniformly and tidily arranging the glass fibers according to the laying sequence of a glass mat layer/carbon fibers (15 layers) in the 0-degree direction/glass mat layer/carbon fibers (3 layers) in the 90-degree direction/glass mat layer/carbon fibers (15 layers) in the 0-degree direction/glass mat layer to obtain a layering structure; wherein the glass mat layer is made of alkali-free glass fibers; the thickness of each fiber layer is 0.125mm, the thickness of each glass mat layer is 0.1mm, and the total thickness of the fragile rod is 4.525 mm.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Example 5
Example 5 is essentially the same as example 1, except that:
firstly, leading out glass fibers from a yarn bobbin, and uniformly and tidily arranging the glass fibers according to the laying sequence of a glass mat layer/carbon fibers (20 layers) in the 0-degree direction/glass mat layer/carbon fibers (5 layers) in the 90-degree direction/glass mat layer/carbon fibers (20 layers) in the 0-degree direction/glass mat layer to obtain a layering structure; wherein the glass mat layer is made of alkali-free glass fibers; the thickness of each fiber layer is 0.125mm, the thickness of each glass mat layer is 0.1mm, and the total thickness of the fragile rod is 6.025 mm.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Example 6
Example 6 is essentially the same as example 1, except that:
secondly, enabling the spreading layer structure (the fibers and the glass mat which are arranged orderly) to pass through a dipping tank filled with the ortho-benzene unsaturated polyester resin matrix material liquid at a constant speed to ensure that the materials are uniformly dipped to obtain the prepreg.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Example 7
Example 7 is essentially the same as example 1, except that:
secondly, enabling the spreading layer structure (the fibers and the glass mat which are arranged orderly) to pass through a glue dipping tank filled with bisphenol A type unsaturated polyester resin matrix feed liquid at a constant speed to ensure that the materials are dipped uniformly to obtain the prepreg.
The brittle rods manufactured in this example were subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Comparative example 1
Easy-to-break rods of Norwegian LATTIX aluminum alloy were purchased and tested for performance using the same test method as in example 1, with the results of the performance tests shown in Table 1.
Comparative example 2
Comparative example 2 is substantially the same as example 1 except that:
firstly, leading out glass fibers from a yarn bobbin, and uniformly and tidily arranging the glass fibers according to the laying sequence of a glass mat layer/carbon fiber (18 layers) in the 0-degree direction/glass mat layer/carbon fiber (1 layer) in the 0-degree direction/glass mat layer/carbon fiber (18 layers) in the 0-degree direction/glass mat layer to obtain a layering structure; wherein the glass mat layer is made of alkali-free glass fibers; the thickness of each fiber layer is 0.125mm, the thickness of each glass felt layer is 0.1mm, and the total thickness of the rod piece is 5.025 mm.
The rod member manufactured in this comparative example was subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Comparative example 3
Comparative example 3 is substantially the same as example 1 except that:
firstly, leading out glass fibers from a yarn bobbin, and uniformly and tidily arranging the glass fibers according to the laying sequence of a glass mat layer/carbon fiber (18 layers) in the 90-degree direction/glass mat layer/carbon fiber (1 layer) in the 90-degree direction/carbon fiber (18 layers) in the 90-degree direction/glass mat layer, so as to obtain a layering structure; wherein the glass mat layer is made of alkali-free glass fibers; the thickness of each fiber layer is 0.125mm, the thickness of each glass felt layer is 0.1mm, and the total thickness of the rod piece is 5.025 mm.
The rod member manufactured in this comparative example was subjected to the performance test using the same test method as in example 1, and the results of the performance test are shown in table 1.
Table 1: the performance indexes of the brittle rods obtained in examples 1 to 7 and the rod members obtained in comparative examples 1 to 3.
As can be seen from the results in table 1, the brittle rod of the present invention has advantages of light weight structure, controllable breaking energy, etc., and can be immediately broken or immediately bent as required under a triggering condition while having certain strength and rigidity.
Finally, the description is as follows: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the embodiments can still be modified, or some technical features can be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the present invention in its spirit and scope.
Claims (11)
1. The utility model provides a controllable combined material fragile pole of breakage energy which characterized in that:
the fragile rod sequentially comprises an inner structural layer, at least one abrupt change layer and an outer structural layer from inside to outside;
the inner structural layer, the mutant layer and the outer structural layer are each independently made of a fiber-reinforced composite material comprising a fiber reinforcement made of reinforcing fibers and a resin matrix compounded in the fiber reinforcement;
the reinforcing fibers contained in the inner structural layer and the outer structural layer are arranged along the axial direction of the fragile rods, the inner structural layer and the outer structural layer realize a static bearing function, the reinforcing fibers contained in the mutation layer are arranged along the circumferential direction of the fragile rods, and the mutation layer realizes a dynamic bearing function;
when the fragile rods are subjected to static loading, stress is concentrated on the outer surfaces of the fragile rods so that the fragile rods are exposed to wind or jet air at a speed of up to 480km/h without being broken and deformed;
when the fragile rods are subjected to impact load, stress is concentrated on the abrupt change layer, so that the fragile rods lose bearing capacity and structural catastrophe occurs.
2. The frangible stem of claim 1, wherein:
the fiber reinforcement contained in the inner structural layer and the outer structural layer are both composed of two fiber felt layers and at least one fiber layer sandwiched between the two fiber felt layers;
the fiber reinforcement comprised in the mutation layer consists of at least one fiber layer.
3. The frangible stem of claim 2, wherein:
the fiber felt layer is made of alkali-free glass fibers;
the fiber layer is made of carbon fibers.
4. A frangible stem according to claim 2 or 3, wherein:
the thickness of each fiber felt layer is 0.09-0.11 mm; and/or
The thickness of each fiber layer is 0.11-0.13 mm.
5. A frangible stem according to claim 2 or 3, wherein:
the fiber reinforcement contained in the inner structural layer and the outer structural layer is composed of two fiber felt layers and 18 fiber layers sandwiched between the two fiber felt layers;
the fiber reinforcement comprised in the mutation layer consists of one fiber layer.
6. The frangible stem of claim 5, wherein:
the thickness of each layer of the fiber felt layer is 0.09-0.11 mm, the thickness of each layer of the fiber layer is 0.11-0.13 mm, and the total thickness of the fragile rods is 4.43-5.25 mm.
7. The frangible stem of claim 6, wherein:
each layer of the fiber felt layer has a thickness of 0.1mm, each layer of the fiber layer has a thickness of 0.125mm, and the total thickness of the fragile rods is 5.025 mm.
8. The frangible stem of claim 1 or 2, wherein:
the resin matrix is unsaturated polyester resin.
9. The frangible stem of claim 8, wherein:
the unsaturated polyester resin is selected from the group consisting of ortho-benzene type unsaturated polyester resin, meta-benzene type unsaturated polyester resin, xylene type unsaturated polyester resin, bisphenol a type unsaturated polyester resin, halogenated unsaturated polyester resin, and vinyl unsaturated polyester resin.
10. A method of manufacturing a frangible stem according to any one of claims 1 to 9, wherein the method includes the steps of:
(1) sequentially laying the fiber reinforcement bodies contained in the inner structure layer, the mutation layer and the outer structure layer to obtain a laying structure;
(2) placing the layer structure obtained in the step (1) into a resin matrix material liquid for impregnation to obtain a prepreg;
(3) and (3) curing and molding the prepreg obtained in the step (2) through a pultrusion process to obtain the fragile rod.
11. The manufacturing method according to claim 10, wherein the step (3) includes the substeps of:
(a) placing the prepreg obtained in the step (2) in a preforming device for preforming into a preform;
(b) placing the prefabricated body obtained in the step (a) in a forming die for curing to obtain a fragile rod profile;
(c) naturally cooling the brittle rod section obtained in the step (b), thereby producing the brittle rod.
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| CN201811314797.7A CN111136938B (en) | 2018-11-06 | 2018-11-06 | Composite material breakable rod with controllable damage energy and manufacturing method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01166937A (en) * | 1987-12-23 | 1989-06-30 | Toa Nenryo Kogyo Kk | Long-sized, light-weight and fiber-reinforced composite draw molding and its manufacture |
| CN102218836A (en) * | 2011-01-30 | 2011-10-19 | 刘伟 | Method for manufacturing large-scale composite tubular product by using prefabticated member |
| CN203097392U (en) * | 2013-02-21 | 2013-07-31 | 李长城 | Composite pole and tower |
| CN105952981A (en) * | 2016-05-20 | 2016-09-21 | 深圳市大疆创新科技有限公司 | Pultrusion pipe and manufacturing method and equipment thereof |
| CN107386752A (en) * | 2017-07-19 | 2017-11-24 | 天津工业大学 | A kind of fibre reinforced composites tower bar with anti-icing and deicing function |
| CN108263926A (en) * | 2018-03-01 | 2018-07-10 | 衡水通广通信导航设备有限公司 | Intelligent easy broken rod lifts navigational lighting aid Tower System |
-
2018
- 2018-11-06 CN CN201811314797.7A patent/CN111136938B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01166937A (en) * | 1987-12-23 | 1989-06-30 | Toa Nenryo Kogyo Kk | Long-sized, light-weight and fiber-reinforced composite draw molding and its manufacture |
| CN102218836A (en) * | 2011-01-30 | 2011-10-19 | 刘伟 | Method for manufacturing large-scale composite tubular product by using prefabticated member |
| CN203097392U (en) * | 2013-02-21 | 2013-07-31 | 李长城 | Composite pole and tower |
| CN105952981A (en) * | 2016-05-20 | 2016-09-21 | 深圳市大疆创新科技有限公司 | Pultrusion pipe and manufacturing method and equipment thereof |
| CN107386752A (en) * | 2017-07-19 | 2017-11-24 | 天津工业大学 | A kind of fibre reinforced composites tower bar with anti-icing and deicing function |
| CN108263926A (en) * | 2018-03-01 | 2018-07-10 | 衡水通广通信导航设备有限公司 | Intelligent easy broken rod lifts navigational lighting aid Tower System |
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| CN111136938A (en) | 2020-05-12 |
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