A method for testing the mechanical performance parameters of the solid filler / matrix interface of solid propellants

Abstract

This proposal discloses a method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant. The method comprises the following steps: pressing the solid filler into a solid tablet by molding; producing a solid filler / matrix interface specimen by curing and bonding; obtaining a tensile curve of the solid filler / matrix interface through a uniaxial tensile test; and obtaining the mechanical performance parameters of the solid filler / matrix interface from the tensile curve. This method solves the problem of being unable to directly test the adhesion performance of the solid filler / matrix interface when using solid fillers such as ammonium perchlorate, octogenin, hexogen, and polymer materials in solid propellants, thereby achieving quantitative characterization of the adhesion performance of the solid filler / matrix interface.

Description

Technical Field

[0001] The present invention relates to the technical field of material performance testing, and in particular to a method for testing mechanical performance parameters of a solid filler / matrix interface of a solid propellant. Background Art

[0002] Composite solid propellants, the power source of solid rocket motors, are composed of solid fillers (ammonium perchlorate, octogen, and RDX) and a binder matrix. They are also a special type of energetic viscoelastic composite material. During their service, solid rocket motors are subjected to various loads, including temperature, vibration, and shock. These loads can cause microscopic damage to the solid propellant, and in severe cases, defects such as cracks may occur, compromising the proper operation of the solid motor. Research has shown that debonding at the filler / matrix interface is a major cause of microscopic damage in solid propellants. The particle size of fillers in solid propellants typically ranges from 10 μm to 300 μm. Due to this small size range, conventional mechanical testing equipment and instruments are unable to effectively and directly measure the adhesion properties of the filler / matrix interface. Instead, in situ observation techniques such as optical microscopy, scanning electron microscopy, and micro-CT can be used to observe the microcrack growth process on or within the solid propellant. Summary of the Invention

[0003] One purpose of this scheme is to provide a method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant. This method solves the problem that the bonding performance of the solid filler / matrix interface cannot be directly tested when one or more solids selected from ammonium perchlorate, octogenin, RDX and polymer materials are used as fillers in the solid propellant. This method realizes the quantitative characterization of the bonding performance of the solid filler / matrix interface and can be applied to the evaluation of the bonding performance of the filler / matrix interface when one or more solids selected from ammonium perchlorate, octogenin, RDX and polymer materials are used as fillers in the solid propellant.

[0004] To achieve the above objectives, this plan is as follows:

[0005] A method for testing mechanical performance parameters of a solid filler / matrix interface of a solid propellant, the method comprising the following steps:

[0006] 1. Press the solid filler into solid tablets by molding;

[0007] 2. Fabricate solid filler / matrix interface specimens by curing and bonding;

[0008] 3. Obtain the tensile curve of the solid filler / matrix interface through uniaxial tensile testing;

[0009] 4. Obtain the mechanical properties parameters of the solid filler / matrix interface through the tensile curve.

[0010] Preferably, the solid tablet is truncated cone-shaped, the volume compression ratio of the solid filler during the molding process is 2.8 to 3.5, the maximum loading force of the press during the molding process is 45,000 N to 60,000 N, and the loading time is 50 s to 90 s.

[0011] Preferably, in the process of manufacturing the solid filler / matrix interface specimen by curing and bonding, the curing and bonding is to cure and bond the solid filler and the matrix by an adhesive and a curing agent.

[0012] Preferably, during the curing and bonding process, the curing degree of the substrate is controlled by adjusting the curing parameters of the adhesive and the curing agent.

[0013] Preferably, the curing parameter of the adhesive and curing agent is 1.1 to 1.4:1.

[0014] Preferably, the curing temperature is 50° C. to 60° C., and the curing time is 4 to 7 days.

[0015] Preferably, the mechanical performance parameters include one or more of tensile strength, tensile debonding displacement, shear strength, shear debonding displacement and cohesive energy parameters.

[0016] Preferably, the solid filler includes one or more of ammonium perchlorate solid filler, octogen solid filler, RDX solid filler and polymer material solid filler.

[0017] The beneficial effects of this program are as follows:

[0018] The present application provides a method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant, thereby achieving quantitative characterization of the bonding performance of the solid filler / matrix interface of the solid propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the implementation of this solution, the following will briefly introduce the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of this solution. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0020] Figure 1 is the tensile curve of the AP filler / matrix interface tensile specimen in Example 1;

[0021] Figure 2 This is the tensile curve of the AP filler / matrix interface shear specimen in Example 2. DETAILED DESCRIPTION

[0022] The following is a further detailed description of the implementation of this solution. Obviously, the described embodiments are only a part of the embodiments of this solution, and are not an exhaustive list of all embodiments. It should be noted that the embodiments and features in the embodiments of this solution can be combined with each other unless they conflict.

[0023] The terms "first," "second," and the like (if any) in the specification and claims are used to distinguish similar objects and are not necessarily used to describe a particular order or sequential sequence. It should be understood that the terms used in this manner are interchangeable where appropriate so that the embodiments described herein can be implemented in sequences other than those illustrated or described herein. In addition, the terms "including" and "having," and any variations thereof, are intended to cover non-exclusive inclusions, e.g., a process, method, system, product, or apparatus that includes a series of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, product, or apparatus.

[0024] It should be understood that the character “ / ” used in this article indicates that the previous and next associated objects are in an “and” relationship.

[0025] The inventors of the present application propose a method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant, the method comprising:

[0026] 1. Press the ammonium perchlorate filler into a solid tablet by molding;

[0027] 2. Make tensile or shear specimens of the solid filler / matrix interface by curing and bonding;

[0028] 3. Obtain the tensile curve of the solid filler / matrix interface by uniaxial stretching;

[0029] 4. Obtain various mechanical properties parameters of the solid filler / matrix interface through tensile curves.

[0030] In one embodiment, the shape of the solid tablet is a truncated cone, the volume compression ratio of the solid filler during the molding process is 2.8 to 3.5, the maximum loading force of the press during the molding process is 45,000 N to 60,000 N, and the loading time is 50 s to 90 s.

[0031] In one embodiment, a solid filler / matrix interface specimen is fabricated by curing bonding, wherein the solid filler and the matrix are cured and bonded by an adhesive and a curing agent, and the curing degree of the matrix is ​​controlled by adjusting the curing parameters of the adhesive and the curing agent;

[0032] In one embodiment, the curing parameter of the adhesive and the curing agent is 1.1-1.4:1.

[0033] In one embodiment, the bonding temperature is 50° C. to 60° C., and the bonding time is 4 to 7 days.

[0034] In one embodiment, the mechanical performance parameters include one or more of tensile strength, tensile debonding displacement, shear strength, shear debonding displacement, and cohesive energy parameters.

[0035] In one embodiment, the solid filler includes one or more of ammonium perchlorate (AP) solid filler, octogen (HMX) solid filler, RDX solid filler and polymer material solid filler.

[0036] The present invention will be further described below through specific embodiments.

[0037] Example 1

[0038] A method for testing mechanical performance parameters of a solid filler / matrix interface of a solid propellant comprises the following steps:

[0039] 1. Press the AP filler into solid AP tablets by molding;

[0040] 2. Fabricate AP filler / matrix interface tensile test specimens by curing and bonding;

[0041] 3. Obtain the tensile curve of the AP filler / matrix interface tensile specimen by uniaxial tension;

[0042] 4. The mechanical properties of the AP filler / matrix interface are obtained through the tensile curve: tensile strength, tensile debonding displacement and cohesion parameters.

[0043] In this embodiment, the AP filler is pressed into a solid AP tablet by molding. The AP tablet is in the shape of a truncated cone with the following dimensions: upper base radius 3 mm, lower base radius 6 mm, and height 5 mm. The volume compression ratio of the AP filler during the molding process is 3.0. The loading force during the pressing of the press is 50,000 N, and the loading time is 60 s.

[0044] In this embodiment, the adhesive is HTPB glue and the curing agent is TDI during curing and bonding. The curing parameters of both are 1.3. The curing temperature is 50° C. and the curing time is 7 days.

[0045] In this embodiment, the tensile curve of the AP filler / matrix interface tensile specimen was obtained by uniaxial stretching at a pulling speed of 100 mm / min. Figure 1 Through the tensile curve, the maximum tensile load of the AP filler / matrix interface was obtained as 122.5N, and the tensile debonding displacement was 0.55mm.

[0046] In this embodiment, the tensile strength is calculated to be 4.34 MPa by the ratio of the maximum tensile load of the AP filler / matrix interface to the bonding area, and the tensile cohesive energy is calculated to be 67.4 mJ by half the product of the maximum tensile load of the AP filler / matrix interface and the tensile debonding displacement.

[0047] Example 2

[0048] A method for testing mechanical performance parameters of a solid filler / matrix interface of a solid propellant, the method comprising the following steps:

[0049] 1. Press the AP filler into solid AP tablets by molding;

[0050] 2. Fabricate AP filler / matrix interface shear specimens by curing and bonding;

[0051] 3. Obtain the tensile curve of the AP filler / matrix interface tensile specimen by uniaxial tension;

[0052] 4. The mechanical properties of the AP filler / matrix interface are obtained through the tensile curve: tensile strength, tensile debonding displacement and cohesion parameters.

[0053] In this embodiment, the AP filler is pressed into a solid AP tablet by molding. The AP tablet is in the shape of a truncated cone with the following dimensions: upper base radius 3 mm, lower base radius 6 mm, and height 5 mm. The volume compression ratio of the AP filler during the molding process is 3.0. The loading force during the pressing of the press is 50,000 N, and the loading time is 60 s.

[0054] In this embodiment, the adhesive is HTPB glue and the curing agent is TDI during curing and bonding. The curing parameters of both are 1.3. The curing temperature is 50° C. and the curing time is 7 days.

[0055] In this embodiment, the tensile curve of the AP filler / matrix interface shear specimen was obtained by uniaxial stretching at a pulling speed of 100 mm / min. Figure 2 Through the tensile curve, the maximum shear load of the AP filler / matrix interface was obtained as 148.6N, and the shear debonding displacement was 1.51mm.

[0056] In this embodiment, the shear strength is calculated to be 5.26 MPa by the ratio of the maximum shear load at the AP filler / matrix interface to the bonding area, and the shear cohesive energy is calculated to be 224.4 mJ by half the product of the maximum shear load at the AP filler / matrix interface and the shear debonding displacement.

[0057] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not limitations on the implementation methods of the present invention. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made based on the above description. It is impossible to list all the implementation methods here. All obvious changes or modifications derived from the technical solution of the present invention are still within the scope of protection of the present invention.

Claims

1. A method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant, characterized in that: The method comprises the following steps: Pressing the solid filler into a solid tablet by molding; A solid filler / matrix interface specimen is produced by curing and bonding, wherein the solid filler and the matrix are cured and bonded by an adhesive and a curing agent, and the curing degree of the matrix is ​​controlled by adjusting the curing parameters of the adhesive and the curing agent during the curing and bonding process; the solid filler comprises one or more of an ammonium perchlorate solid filler, an octogen solid filler, a RDX solid filler, and a polymer material solid filler; The tensile curve of the solid filler / matrix interface was obtained by uniaxial tensile test; The mechanical properties parameters of the solid filler / matrix interface are obtained through tensile curves; The mechanical performance parameters include tensile strength, tensile debonding displacement, shear strength, shear debonding displacement and cohesive energy parameters.

2. The method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant according to claim 1, characterized in that: The solid tablet is truncated cone-shaped. During the molding process, the volume compression ratio of the solid filler is 2.8 to 3.

5. During the molding process, the maximum loading force of the press is 45,000 N to 60,000 N, and the loading time is 50 s to 90 s.

3. The method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant according to claim 1, characterized in that: The curing bonding is to cure and bond the solid filler to the matrix through an adhesive and a curing agent, and the curing parameter of the adhesive and the curing agent is 1.1 to 1.4:

1.

4. The method for testing the mechanical performance parameters of the solid filler / matrix interface of a solid propellant according to claim 3, characterized in that: The curing temperature is 50℃~60℃; the curing time is 4 days to 7 days.

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