CN113324846A - Accelerated aging test method and device for solid propellant - Google Patents
Accelerated aging test method and device for solid propellant Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/18—Performing tests at high or low temperatures
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0003—Steady
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0075—Strain-stress relations or elastic constants
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0226—High temperature; Heating means
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- G—PHYSICS
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0658—Indicating or recording means; Sensing means using acoustic or ultrasonic detectors
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
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- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
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- G01N2203/06—Indicating or recording means; Sensing means
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Abstract
The application relates to an accelerated aging test method and device for solid propellant, wherein the method comprises the following steps: respectively adhering two stress joints to the waist lines on two sides of a flat solid propellant sample with a set shape; stretching the solid propellant sample to a preset position from two sides where the stress joint is located to carry out strain stepless loading; installing the stretched solid propellant sample on a tool of an aging chamber, connecting a high-temperature constant-temperature heat source to one stress joint, and connecting a low-temperature constant-temperature heat source to the other stress joint; respectively starting a high-temperature constant-temperature heat source and a low-temperature constant-temperature heat source after the aging chamber is vacuumized, carrying out temperature stepless loading on the solid propellant sample, and stabilizing the solid propellant sample to a constant temperature gradient; respectively measuring the elastic modulus of a plurality of positions of the solid propellant sample at different set time nodes and storing the measured data; the measurement data were used to determine the accelerated aging test results for the solid propellant specimens. The test efficiency is greatly improved.
Description
Technical Field
The application relates to the technical field of accelerated aging tests, in particular to an accelerated aging test method and device for a solid propellant.
Background
With the development of solid rocket technology, the accelerated aging test requirements of solid propellants are higher and higher. At present, the methods adopted for carrying out accelerated aging tests on solid propellants at home and abroad mainly comprise the following types: one is 71 degree method: see initiating explosive device test method 71 ℃ test method (GJB 763.8-1990), which is a truncated end life test method, wherein the default reaction rate temperature coefficient is 2.7, 3 test time nodes are set, and a minimum of 30 samples are needed in 84 days. Secondly, multi-temperature accelerated aging: referring to the initiating explosive device test method-constant temperature stress test method (GJB 736.13-1991) and composite solid propellant high temperature accelerated aging test method (QJ 2328A-2005), the acceleration temperature is generally set to 3 to 4 or 8 points, so as to obtain the approved acceleration coefficient and aging life without obtaining the acceleration coefficient of the material, and each stress is 175 to 210 at least. And the third method is a temperature-constant strain aging method: on the basis of the second method, the influence of strain on the aging performance of the material is considered, the test piece is pre-applied to a plurality of strain levels through a clamp and then placed into aging test boxes at different temperatures for aging, so that the change of the mechanical property of the material along with the aging time at different temperatures and different strains is obtained, and the number of the test pieces is 3-4 times that of the second method.
However, in the process of implementing the present invention, the inventor finds that the conventional accelerated aging test method for the solid propellant has the technical problems of large propellant usage amount and low test efficiency.
Disclosure of Invention
In view of the above, it is necessary to provide a method for accelerated aging test of a solid propellant with high efficiency using a small amount of propellant and an apparatus for accelerated aging test of a solid propellant.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
in one aspect, an embodiment of the present invention provides an accelerated aging test method for a solid propellant, including the steps of:
respectively adhering two stress joints to the waist lines on two sides of a flat solid propellant sample with a set shape;
stretching the solid propellant sample to a preset position from two sides where the stress joint is located to carry out strain stepless loading;
installing the stretched solid propellant sample on a tool of an aging chamber, connecting a high-temperature constant-temperature heat source to one stress joint, and connecting a low-temperature constant-temperature heat source to the other stress joint;
respectively starting a high-temperature constant-temperature heat source and a low-temperature constant-temperature heat source after the aging chamber is vacuumized, carrying out temperature stepless loading on the solid propellant sample, and stabilizing the solid propellant sample to a constant temperature gradient;
respectively measuring the elastic modulus of a plurality of positions of the solid propellant sample at different set time nodes and storing the measured data; the measurement data were used to determine the accelerated aging test results for the solid propellant specimens.
In one embodiment, the flat solid propellant samples of a given shape comprise isosceles trapezoid flat samples or sector flat samples.
In one embodiment, the method further comprises the steps of:
and (3) preparing a flat solid propellant sample with a set shape by adopting a mechanical cutting mode.
In one embodiment, the stress joint is bonded to the solid propellant coupon by an adhesive; the adhesive strength of the adhesive is higher than that of the solid propellant sample.
In one embodiment, both stress joints are copper joints.
In one embodiment, the high-temperature constant-temperature heat source and the low-temperature constant-temperature heat source are respectively controlled by a temperature control module of the aging chamber.
In one embodiment, a process for making elastic modulus measurements at a plurality of locations on a solid propellant sample comprises:
the elastic modulus at a plurality of different positions is respectively measured on two main planes of a solid propellant sample by adopting an ultrasonic longitudinal wave transmission measurement method.
In one embodiment, the coupling mode used in the measurement by ultrasonic longitudinal wave transmission measurement comprises a non-adhesive coupling agent coupling mode or a dry coupling mode.
In one embodiment, a process for making elastic modulus measurements at a plurality of locations on a solid propellant sample comprises:
the modulus of elasticity is measured at a plurality of different locations on two main planes of the solid propellant sample, respectively, using indentation measurements.
On the other hand, the accelerated aging test device for the solid propellant comprises a solid propellant sample with a set shape, two stress joints, a clamp, an aging chamber, a high-temperature constant-temperature heat source, a low-temperature constant-temperature heat source and modulus measuring equipment; the set shape comprises an isosceles trapezoid flat plate or a fan-shaped flat plate;
the two stress joints are respectively bonded to the waist lines on the two sides of the solid propellant sample, and the clamps are clamped on the two sides of the stress joint on the solid propellant sample and used for stretching the solid propellant sample to a preset position for strain stepless loading;
the testing tool is arranged in the aging chamber and used for installing the stretched solid propellant sample, the high-temperature constant-temperature heat source is connected to one stress joint, the low-temperature constant-temperature heat source is connected to the other stress joint, and the high-temperature constant-temperature heat source and the low-temperature constant-temperature heat source are respectively used for carrying out temperature stepless loading on the solid propellant sample after the aging chamber is vacuumized, so that the solid propellant sample is stabilized to be in a constant temperature gradient;
the modulus measuring equipment is used for respectively measuring the elastic modulus of a plurality of positions of the solid propellant sample at different set time nodes after the test is started and outputting measured data; the measurement data were used to determine the accelerated aging test results for the solid propellant specimens.
One of the above technical solutions has the following advantages and beneficial effects:
according to the accelerated aging test method and device for the solid propellant, the flat solid propellant sample with the set shape is used as an aging sample, corresponding stress joints are bonded on the waist lines on the two sides of the sample, then stretching treatment is carried out, and strain stepless loading is carried out on the sample; the test sample is installed in an aging chamber, the aging chamber is vacuumized, and then a high-temperature constant-temperature heat source and a low-temperature constant-temperature heat source which are respectively connected to two stress joints are started, the solid propellant sample is subjected to temperature stepless loading, and is stabilized to be in a constant temperature gradient, so that the temperature and strain loading modes on the sample are simultaneously loaded in a temperature gradient and strain gradient mode in the test process. And then, measuring the mechanical properties (namely elastic modulus) of the solid propellant sample at a plurality of positions (corresponding to different temperatures and strains) of the solid propellant sample at different set time nodes for a plurality of times, storing the measured data, obtaining the change relation of the mechanical properties of the propellant along with the temperature, the strain and the aging time according to the stored measured data, and determining the accelerated aging test result of the solid propellant sample. Compared with the traditional accelerated aging test method in the field, the test method has the advantages of shorter test period, less test equipment consumption, low equipment capacity requirement, less propellant material consumption in the test, low material processing cost, good sample consistency, small data discreteness and high test safety, and greatly improves the test efficiency.
Drawings
FIG. 1 is a schematic flow chart of a method for accelerated aging testing of a solid propellant in one embodiment;
FIG. 2 is a schematic flow chart of a method for accelerated aging testing of a solid propellant in another embodiment;
FIG. 3 is a schematic diagram of an apparatus for accelerated aging testing of solid propellants in one embodiment;
FIG. 4 is a schematic diagram of an efficient test of mechanical properties of a propellant in one embodiment;
FIG. 5 is a graphical representation of ultrasonic measurements of the modulus of a propellant in one embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application. It will be understood that when an element is referred to as being "connected" to another element, it can be directly connected to the other element and integrated therewith or intervening elements may be present, i.e., indirectly connected to the other element.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should be considered to be absent and not within the protection scope of the present invention.
In practice, the inventors have found that although the conventional accelerated aging method is already in use, there are disadvantages in terms of range of use, safety, cycle time, and cost: for example, the 71 degree method, the temperature coefficient of the reaction rate of the propellant is not necessarily 2.7, the performance obtained by the aging test performance has larger deviation, and only the influence of the temperature on the aging is considered. For example, the multi-temperature accelerated aging only considers the influence of temperature on aging, different temperature tests need a plurality of aging devices or aging tests need to be carried out for a plurality of times, and the test consumes more samples and has large test quantity. For another example, the temperature-constant strain aging method needs to put the strain tensile test bed into an aging test box, so that the requirement on the capacity of the test equipment is high, more samples are consumed in the test, and the test quantity is larger.
In summary, the present invention provides an accelerated aging test method for a solid propellant, which utilizes the highly correlated characteristics of modulus and elongation of the solid propellant during aging, and prepares an aging sample with gradient distribution on the same sample by applying dual stress loading of temperature gradient and strain gradient to the same sample. The method utilizes the highly-correlated characteristic of modulus and elongation rate of the solid propellant during aging, rapidly tests the modulus of the propellant sample at different positions in situ on line, obtains the distribution and the change of the modulus performance of the sample in the aging process of the sample, and further establishes a solid propellant aging model taking the elongation rate as a characterization parameter.
Referring to fig. 1, in one embodiment, the present invention provides a method for accelerated aging test of solid propellant, including the following steps S12 to S20:
and S12, respectively adhering two stress joints to the waist lines on two sides of the flat solid propellant sample with the set shape.
It is understood that the stress joint means a joint member capable of effectively transmitting a stress (e.g., temperature stress) to be applied to the solid propellant sample to the sample, and may be any of various metal joints having excellent heat conductivity, and the shape thereof may be determined according to the shape of the waistline of the sample, as long as the joint member can match the waistline of the sample. The set shape refers to a shape which can load the strain applied to the solid propellant sample in a gradient distribution when the solid propellant sample is stretched on two sides, such as a trapezoid, a fan or other shapes. In the same way, the stress joints are adhered to the waist lines on the two sides of the solid propellant sample, and the temperature applied to the solid propellant sample can be loaded in a gradient distribution in a gradual change manner when the solid propellant sample is connected with a constant-temperature heat source through the stress joints after being stretched.
Preferably, the flat solid propellant sample of the set shape comprises an isosceles trapezoid flat sample or a sector flat sample.
And S14, stretching the solid propellant sample to a preset position from two sides of the stress joint for strain stepless loading.
It is understood that the predetermined position refers to the magnitude of the tensile deformation required by the solid propellant sample, and can be determined by pre-calculation according to the strain magnitude required to be loaded in the actual test. The solid propellant sample may be subjected to a stretching process using a jig.
And S16, mounting the stretched solid propellant sample on a tool of an aging chamber, connecting a high-temperature constant-temperature heat source to one stress joint, and connecting a low-temperature constant-temperature heat source to the other stress joint.
It can be understood that the high-temperature constant-temperature heat source (also called a hot-end heat source) and the low-temperature constant-temperature heat source (also called a cold-end heat source) can be respectively arranged on the tool of the aging chamber, and the solid propellant sample is arranged on the tool and is respectively connected with the cold-end heat source and the hot-end heat source through stress joints.
And S18, respectively starting a high-temperature constant-temperature heat source and a low-temperature constant-temperature heat source after the aging chamber is vacuumized, carrying out temperature stepless loading on the solid propellant sample, and stabilizing the solid propellant sample to a constant temperature gradient.
It can be understood that after the solid propellant sample is installed, the vacuum pump needs to be started to vacuumize the aging chamber, so as to avoid the influence of convection on the temperature gradient; the high and low temperature constant temperature heat sources are then turned on, for example, in some embodiments, controlled by the temperature control module of the aging chamber. And starting the heat source by starting a temperature control module of the aging chamber, so that the solid propellant sample is heated and reaches a state of constant temperature gradient. At this point, a test timer may be started.
S20, respectively measuring the elastic modulus of the solid propellant sample at a plurality of positions at different set time nodes and storing the measured data; the measurement data were used to determine the accelerated aging test results for the solid propellant specimens.
It is understood that the different time nodes are preset time points of a plurality of data measurements according to data points required to be collected in the test process. The elastic modulus of the solid propellant sample at a plurality of different positions (corresponding to different temperatures and strains) is measured at different set time nodes, and the measurement mode can be ultrasonic measurement, indentation measurement or other measurement modes suitable for elastic modulus measurement in the field, as long as the elastic modulus of the solid propellant sample at different positions can be measured at different set time nodes. The measured data can be stored by a special monitoring computer, a data storage device or a general storage terminal, so that the data can be read for analysis and evaluation after the test.
Specifically, the solid propellant sample is a flat plate sample with a set shape, and is pre-stretched in the direction of a waist line (understood by referring to the waist line of a trapezoid or a fan) of the sample to carry out strain gradient loading; and respectively connecting the waist of the stretched solid propellant sample with two constant-temperature heat sources with constant temperature difference in a vacuum environment to carry out temperature gradient loading. In the aging process of the sample, the mechanical properties (namely the elastic modulus) of the solid propellant sample are measured for many times at different positions (corresponding to different temperatures and strains) according to the set time node, so that the change relation of the mechanical properties of the solid propellant along with the temperature, the strain and the aging time, namely the test result, is obtained.
According to the accelerated aging test method of the solid propellant, a flat solid propellant sample with a set shape is used as an aging sample, corresponding stress joints are bonded on the waist lines on two sides of the sample, then stretching treatment is carried out, and strain stepless loading is carried out on the sample; the test sample is installed in an aging chamber, the aging chamber is vacuumized, and then a high-temperature constant-temperature heat source and a low-temperature constant-temperature heat source which are respectively connected to two stress joints are started, the solid propellant sample is subjected to temperature stepless loading, and is stabilized to be in a constant temperature gradient, so that the temperature and strain loading modes on the sample are simultaneously loaded in a temperature gradient and strain gradient mode in the test process. And then, measuring the mechanical properties (namely elastic modulus) of the solid propellant sample at a plurality of positions (corresponding to different temperatures and strains) of the solid propellant sample at different set time nodes for a plurality of times, storing the measured data, obtaining the change relation of the mechanical properties of the propellant along with the temperature, the strain and the aging time according to the stored measured data, and determining the accelerated aging test result of the solid propellant sample. Compared with the traditional accelerated aging test method in the field, the test method has the advantages of shorter test period, less test equipment consumption, low equipment capacity requirement, less propellant material consumption in the test, low material processing cost, good sample consistency, small data discreteness and high test safety, and greatly improves the test efficiency.
Referring to fig. 2, in an embodiment, the method for testing accelerated aging of a solid propellant may further include the following processing step S10:
and S10, preparing a flat solid propellant sample with a set shape by adopting a mechanical cutting mode.
Optionally, in this embodiment, the set shape may be a trapezoid, and the surface of the trapezoid flat-plate-shaped solid propellant sample may be machined and manufactured in a mechanical cutting manner, so that the machining and manufacturing manner is simple and high in safety.
In one embodiment, the stress joint is bonded to the solid propellant coupon by an adhesive; the adhesive strength of the adhesive is higher than that of the solid propellant sample. Optionally, in this embodiment, the flat solid propellant sample and the stress joint are connected by using an adhesive, and the adhesive strength of the adhesive is higher than that of the propellant, so that stress is stably loaded while the stress joint is prevented from loosening and falling off.
In one embodiment, both stress joints are copper joints. Preferably, in this embodiment, two red copper joints are used to respectively realize the connection of two heat sources, so that the temperature loading efficiency is higher and the cost is more controllable.
In an embodiment, regarding the process of measuring the elastic modulus of the solid propellant sample at the plurality of positions in step S20, the process may specifically include the following processing steps:
the elastic modulus at a plurality of different positions is respectively measured on two main planes of a solid propellant sample by adopting an ultrasonic longitudinal wave transmission measurement method.
It can be understood that, in this embodiment, the ultrasonic device is used to set different time nodes, and the transmitting probe and the receiving probe of the ultrasonic device are respectively disposed on the surfaces of the solid propellant sample at two axial sides, so that the non-adhesive couplant can be used for the measurement. The measuring efficiency is high and the precision is good.
In one embodiment, the coupling means used in the measurement using ultrasonic longitudinal wave transmission measurement includes a non-adhesive coupling agent coupling means or a dry coupling means.
Optionally, when the elastic modulus of the solid propellant sample is measured by an ultrasonic longitudinal wave transmission measurement method, the coupling mode may be a wet coupling mode of a non-adhesive coupling agent, or may be a dry coupling mode, as long as the modulus measurement can be achieved.
In an embodiment, regarding the process of measuring the elastic modulus of the solid propellant sample at the plurality of positions in step S20, the process may specifically include the following processing steps:
the modulus of elasticity is measured at a plurality of different locations on two main planes of the solid propellant sample, respectively, using indentation measurements.
It can be understood that, in the present embodiment, the elastic modulus at a plurality of different positions of the solid propellant sample is not measured with low accuracy by using the indentation measurement method to set different time nodes.
Referring to fig. 3, in another aspect, an apparatus 100 for accelerated aging test of solid propellant is provided, which includes a solid propellant sample 12 with a set shape, two stress joints 13, a fixture 14, an aging chamber 15, a high temperature and constant temperature heat source 16, a low temperature and constant temperature heat source 17, and a modulus measuring device 18. The set shape comprises an isosceles trapezoid flat plate or a fan-shaped flat plate. The two stress joints 13 are respectively adhered to the waist lines on the two sides of the solid propellant sample 12, and the clamps 14 are clamped on the two sides of the solid propellant sample 12 where the stress joints 13 are located and used for stretching the solid propellant sample 12 to a preset position for strain stepless loading. The aging chamber 15 is internally provided with a testing tool, the testing tool is used for installing the stretched solid propellant sample 12, the high-temperature constant-temperature heat source 16 is connected to one stress joint 13, the low-temperature constant-temperature heat source 17 is connected to the other stress joint 13, and the high-temperature constant-temperature heat source 16 and the low-temperature constant-temperature heat source 17 are respectively used for carrying out temperature stepless loading on the solid propellant sample 12 after the aging chamber 15 is vacuumized, so that the solid propellant sample 12 is stabilized to a constant temperature gradient. The modulus measuring device 18 is used for measuring the elastic modulus of the solid propellant sample 12 at a plurality of positions at different set time nodes after the test is started and outputting measurement data; the measurement data was used to determine the accelerated aging test results for the solid propellant sample 12.
It is understood that, regarding the specific limitations of the apparatus 100 for testing accelerated aging of solid propellant, reference may be made to the corresponding limitations of the method for testing accelerated aging of solid propellant, and the detailed description thereof is omitted here. It should be noted that all the components of the accelerated aging test apparatus 100 for solid propellant described above are not necessarily added all the time to the test, and they may be selectively added or removed according to the actual use requirements before, during and after the test. In this example, the sample shown in fig. 3 is an example of an isosceles trapezoidal flat plate-like sample, and the same is understood for samples of other shapes.
In the accelerated aging test device 100 for the solid propellant, a flat solid propellant sample 12 with a set shape is used as an aging sample, corresponding stress joints 13 are bonded on the waist lines on two sides of the sample, and then stretching treatment is carried out, so that strain stepless loading is carried out on the sample; the test sample is installed in an aging chamber 15, the aging chamber 15 is vacuumized, then a high-temperature constant-temperature heat source 16 and a low-temperature constant-temperature heat source 17 which are respectively connected to two stress joints 13 are started, the solid propellant test sample 12 is subjected to temperature stepless loading, the solid propellant test sample 12 is stabilized to be in a constant temperature gradient, and therefore the temperature and strain loading mode on the test sample is simultaneously loaded in a temperature gradient and strain gradient mode in the test process. And then, measuring the mechanical properties of the solid propellant sample 12 for multiple times at different set time nodes respectively, storing the measured data, obtaining the variation relation of the mechanical properties of the propellant along with the temperature, the strain and the aging time according to the stored measured data, and determining the accelerated aging test result of the solid propellant sample 12. Compared with the traditional accelerated aging test method in the field, the test method has the advantages of shorter test period, less test equipment consumption, low equipment capacity requirement, less propellant material consumption in the test, low material processing cost, good sample consistency, small data discreteness and high test safety, and greatly improves the test efficiency.
In one embodiment, the modulus measurement device 18 is an ultrasonic device. The transmitting probe and the receiving probe of the ultrasonic equipment are respectively arranged on the surfaces of two sides of the solid propellant sample 12 in the axial direction, and non-adhesive couplant can be adopted for measurement in cooperation during measurement. In this embodiment, it can be understood that, the elastic modulus is measured by ultrasonic waves by a longitudinal wave penetration method, and the measurement efficiency is high and the accuracy is good.
In one embodiment, in order to more intuitively and fully illustrate the accelerated aging test method of the solid propellant, the method provided by the invention is illustrated and verified by taking an accelerated aging test of an HTPB propellant to which the method is applied as an example. It should be noted that the embodiments given in this specification are only illustrative and not the only limitations of the specific embodiments of the present invention, and those skilled in the art can implement the accelerated aging test of the solid propellant of different solid rocket engines by using the above-mentioned accelerated aging test method of the solid propellant in the same manner as the embodiments provided in the present invention.
Accelerated aging test of HTPB propellant:
(1) the propellant was cut into test pieces as shown in fig. 4, the dimensions of the propellant test pieces being: h10 mm, W1 100mm, W2 80mm, L100 mm;
(2) bonding the two bevel edges (waist lines) of the propellant sample piece with red copper joints (the joint size is h is 20mm, and w is 10mm) by using adhesives respectively;
(3) the two sides of the bonding joint of the propellant sample piece are stretched by a clamp 14 to a state of 100mm multiplied by 100mm, and the stepless loading of 0-20% strain is realized. And installing the stretched propellant sample piece on a tool, connecting the propellant sample piece with a cold end heat source and a hot end heat source, setting the high temperature of the heat source to be 70 ℃ and the low temperature to be 40 ℃, and realizing the stepless loading at the temperature of 40-70 ℃.
(4) Starting a vacuum pump of the aging chamber 15 to enable the vacuum degree of the aging chamber 15 to reach 80KPa, and avoiding the influence of convection on the temperature gradient;
(5) starting a temperature control module to enable the propellant sample piece to be heated and reach a constant temperature gradient;
(6) as shown in fig. 5, the elastic modulus of the sample at multiple positions is measured by a 1MHz ultrasonic longitudinal wave transmission measurement method at different sampling time nodes, and the test measurement data is stored and the test is finished. The measurement of the transmitting probe 182 and receiving probe 184 of the ultrasonic apparatus at one of the locations on the propellant sample is illustrated in fig. 5.
Through test result verification and analysis, compared with the traditional accelerated aging test method in the field, the test method has the advantages of shorter test period, less test equipment consumption, low equipment capacity requirement, less propellant material consumption in the test, low material processing cost, good sample consistency, small data discreteness and high test safety, and greatly improves the test efficiency.
It should be understood that although the steps in the flowcharts of fig. 1 and 2 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps of fig. 1 and 2 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above examples only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the spirit of the present application, and all of them fall within the scope of the present application. Therefore, the protection scope of the present patent should be subject to the appended claims.
Claims (10)
1. An accelerated aging test method for a solid propellant, characterized by comprising the steps of:
respectively adhering two stress joints to the waist lines on two sides of a flat solid propellant sample with a set shape;
stretching the solid propellant sample to a preset position from two sides where the stress joint is located to carry out strain stepless loading;
installing the stretched solid propellant sample on a tool of an aging chamber, connecting a high-temperature constant-temperature heat source to one stress joint, and connecting a low-temperature constant-temperature heat source to the other stress joint;
respectively starting the high-temperature constant-temperature heat source and the low-temperature constant-temperature heat source after the aging chamber is vacuumized, carrying out temperature stepless loading on the solid propellant sample, and stabilizing the solid propellant sample to a constant temperature gradient;
respectively measuring the elastic modulus of a plurality of positions of the solid propellant sample at different set time nodes and storing measurement data; the measurement data is used to determine the accelerated aging test results for the solid propellant test specimens.
2. The method for accelerated aging testing of solid propellants according to claim 1, wherein the flat plate-like solid propellant specimens of a set shape include isosceles trapezoid flat plate-like specimens or sector flat plate-like specimens.
3. The method for accelerated aging testing of solid propellants according to claim 1 or 2, further comprising the steps of:
and manufacturing a flat-plate-shaped solid propellant sample with a set shape by adopting a mechanical cutting mode.
4. The method for accelerated aging testing of solid propellants according to claim 1, wherein the stress joint is bonded to the solid propellant coupon by an adhesive; the adhesive has a bond strength higher than the strength of the solid propellant sample.
5. The method of accelerated aging testing of solid propellants according to claim 4, wherein both of the stress joints are copper joints.
6. The accelerated aging test method for solid propellant according to claim 1, wherein the high temperature constant temperature heat source and the low temperature constant temperature heat source are respectively controlled by a temperature control module of the aging chamber.
7. The method for accelerated aging testing of solid propellants according to claim 1, wherein the process of measuring the modulus of elasticity at a plurality of positions of the solid propellant sample comprises:
and respectively measuring the elastic modulus at a plurality of different positions on two main planes of the solid propellant sample by adopting an ultrasonic longitudinal wave transmission measurement method.
8. The method for accelerated aging testing of solid propellants according to claim 7, wherein the coupling method used in the measurement by the ultrasonic longitudinal wave transmission measurement method includes a non-adhesive coupling agent coupling method or a dry coupling method.
9. The method for accelerated aging testing of solid propellants according to claim 1, wherein the process of measuring the modulus of elasticity at a plurality of positions of the solid propellant sample comprises:
the modulus of elasticity is measured at a plurality of different locations on the two main planes of the solid propellant sample, respectively, using indentation measurements.
10. The accelerated aging test device for the solid propellant is characterized by comprising a solid propellant sample with a set shape, two stress joints, a clamp, an aging chamber, a high-temperature constant-temperature heat source, a low-temperature constant-temperature heat source and modulus measuring equipment; the set shape comprises an isosceles trapezoid flat plate or a fan-shaped flat plate;
the two stress joints are respectively bonded to the waist lines on the two sides of the solid propellant sample, and the clamps are clamped on the two sides of the solid propellant sample where the stress joints are located and used for stretching the solid propellant sample to a preset position for strain stepless loading;
the testing tool is arranged in the aging chamber and used for installing the stretched solid propellant sample, the high-temperature constant-temperature heat source is connected to one stress joint, the low-temperature constant-temperature heat source is connected to the other stress joint, and the high-temperature constant-temperature heat source and the low-temperature constant-temperature heat source are respectively used for carrying out temperature stepless loading on the solid propellant sample after the aging chamber is vacuumized, so that the solid propellant sample is stabilized to be in a constant temperature gradient;
the modulus measuring equipment is used for measuring the elastic modulus of the solid propellant sample at a plurality of positions at different set time nodes after the test is started and outputting measured data; the measurement data is used to determine the accelerated aging test results for the solid propellant test specimens.
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