技术领域technical field
本发明属于固体火箭发动机推进剂技术领域，具体涉及到一种固体火箭发动机用复合固体推进剂药柱缺陷修补材料和该修补材料的制备方法。The invention belongs to the technical field of solid rocket motor propellants, and in particular relates to a composite solid propellant grain defect repairing material for solid rocket motors and a preparation method of the repairing material.
背景技术Background technique
固体火箭发动机装药在固化降温、长期贮存、运输、勤务处理过程中，因受到各种载荷及推进剂老化作用，可能产生裂纹、气孔等结构缺陷。这些缺陷破坏了原药型设计的燃烧规律，可能导致燃面增大、燃烧室压强快速升高，严重的可能导致发动机爆炸，造成人员和装备的损失。由于固体火箭发动机造价高，不应因局部裂纹等缺陷就予以报废，应力求修补后利用。Solid rocket motor charges may have structural defects such as cracks and pores due to various loads and propellant aging during solidification and cooling, long-term storage, transportation, and service processing. These defects destroy the combustion law of the original drug type design, which may lead to an increase in the combustion surface and a rapid increase in the pressure of the combustion chamber. In serious cases, it may cause the engine to explode, resulting in the loss of personnel and equipment. Due to the high cost of solid rocket motors, they should not be scrapped due to defects such as local cracks, and should be used after repairing.
发动机药柱裂纹修补材料应与推进剂材料基体相容，以保证修补材料有较高的粘接强度；具有良好的工艺流平性，便于操作和贮存；能量特性要与药柱相匹配，避免能量大幅度降低；与药柱界面具有良好的粘接性能，粘接强度接近药柱自身强度，修补区域延伸率要满足要求；修补材料升温固化后不应导致完好部位的药柱力学性能下降。The engine grain crack repair material should be compatible with the propellant material matrix to ensure that the repair material has a high bonding strength; it has good process leveling and is easy to operate and store; the energy characteristics should match the grain to avoid The energy is greatly reduced; the interface with the grain has good bonding performance, and the bonding strength is close to the strength of the grain itself, and the elongation of the repaired area must meet the requirements; after the repair material is heated and solidified, the mechanical properties of the grain in the intact part should not decrease.
目前针对采用端羟基聚丁二烯(HTPB)粘合剂体系的复合固体推进剂药柱缺陷，修补材料主要采用HTPB粘合剂体系。与固体推进剂药柱相比，修补材料大幅度降低了氧化剂高氯酸铵(AP)和金属燃料铝粉(Al)的含量，并添加了一些不能燃烧的氧化物，这导致修补材料的爆热值低于推进剂药柱的爆热值，从而使固体火箭发动机的比冲下降；已有修补材料配方高温固化也会导致推进剂药柱强度升高、延伸率下降。At present, for the defects of composite solid propellant grains using hydroxyl-terminated polybutadiene (HTPB) binder system, HTPB binder system is mainly used as repair material. Compared with solid propellant grains, the repair material greatly reduces the content of oxidant ammonium perchlorate (AP) and metal fuel aluminum powder (Al), and adds some incombustible oxides, which leads to the explosion of the repair material. The calorific value is lower than the detonation heat value of the propellant grain, thereby reducing the specific impulse of the solid rocket motor; the high-temperature curing of the existing repair material formula will also lead to an increase in the strength of the propellant grain and a decrease in elongation.
发明内容Contents of the invention
因此，本发明的目的是，提供一种复合固体推进剂药柱缺陷修补材料，以针对已固化端羟基聚丁二烯复合固体推进剂药柱的缺陷，解决现有修补材料配方高温固化导致推进剂药柱强度升高、延伸率下降、以及修补材料能量性能偏低的问题。Therefore, the purpose of the present invention is to provide a composite solid propellant grain defect repairing material, to solve the problem that the existing repair material formula is cured at high temperature and cause the propellant The strength of the agent column increases, the elongation decreases, and the energy performance of the repair material is low.
根据发明的一个方面，提供了一种复合固体推进剂药柱缺陷修补材料，它包括以下组份：端羟基聚丁二烯粘合剂；甲苯二异氰酸酯固化剂；癸二酸二辛酯增塑剂；高氯酸铵氧化剂；铝粉金属燃料，更为重要的是，还包括补强剂，且所述补强剂为多羟基化合物。According to one aspect of the invention, a composite solid propellant grain defect repair material is provided, which includes the following components: hydroxyl-terminated polybutadiene adhesive; toluene diisocyanate curing agent; dioctyl sebacate plasticizer agent; ammonium perchlorate oxidant; aluminum powder metal fuel, more importantly, also includes a reinforcing agent, and the reinforcing agent is a polyhydroxy compound.
进一步的，上述各组份的含量范围如下：端羟基聚丁二烯为15wt％-18wt％，高氯酸铵为55wt％-65wt％，铝粉为12wt％-16wt％，癸二酸二辛酯为4wt％-6wt％，甲苯二异氰酸酯为1wt％-2.5wt％，多羟基化合物为0.5wt％-3wt％。Further, the content ranges of the above components are as follows: hydroxyl-terminated polybutadiene is 15wt%-18wt%, ammonium perchlorate is 55wt%-65wt%, aluminum powder is 12wt%-16wt%, dioctyl sebacate The content of ester is 4wt%-6wt%, the content of toluene diisocyanate is 1wt%-2.5wt%, and the content of polyol is 0.5wt%-3wt%.
进一步的，上述多羟基化合物选自三羟甲基丙烷、三羟甲基乙烷、季戊四醇、丙三醇、甘露醇和丙烯醛季戊四醇树脂中的一种。Further, the polyhydroxy compound is selected from one of trimethylolpropane, trimethylolethane, pentaerythritol, glycerol, mannitol and acrolein pentaerythritol resin.
更进一步的，上述多羟基化合物为丙烯醛季戊四醇树脂。Furthermore, the above-mentioned polyhydroxy compound is acrolein pentaerythritol resin.
还进一步的，上述丙烯醛季戊四醇树脂的含量范围为0.5wt％-1.5wt％。Still further, the content range of the acrolein pentaerythritol resin is 0.5wt%-1.5wt%.
本发明还提供了一种上述复合固体推进剂药柱缺陷修补材料的制备方法，所述方法包括以下步骤：The present invention also provides a method for preparing the above composite solid propellant grain defect repairing material, the method comprising the following steps:
a)将高氯酸铵和铝粉分别过筛，放入温度为50-70℃的真空干燥箱内干燥，真空度1000Pa，干燥时间不少于2小时，自然降至室温后使用；a) Sieve the ammonium perchlorate and aluminum powder separately, put them into a vacuum drying oven at a temperature of 50-70°C, and dry them at a vacuum degree of 1000 Pa. The drying time is not less than 2 hours, and then use after naturally cooling down to room temperature;
b)将端羟基聚丁二烯称入不锈钢容器，再加入癸二酸二辛酯、多羟基化合物和步骤a)处理好的铝粉，预混后将预混物加入捏合机中混合，捏合机循环水浴温度为50℃；b) Weigh hydroxyl-terminated polybutadiene into a stainless steel container, then add dioctyl sebacate, polyol and aluminum powder treated in step a), premix and add the premix into a kneader for mixing, and knead The temperature of the machine circulating water bath is 50°C;
c)将步骤a)处理好的高氯酸铵分两次加入到捏合机中，混合均匀；c) the ammonium perchlorate processed in step a) is added into the kneader twice, and mixed uniformly;
d)将甲苯二异氰酸酯加入捏合机中，连续混合45min，得到复合固体推进剂药柱缺陷修补材料。d) adding toluene diisocyanate into a kneader, and continuously mixing for 45 minutes to obtain a composite solid propellant grain defect repairing material.
使用本发明复合固体推进剂药柱缺陷修补材料进行固体推进剂药柱缺陷修补的方法步骤如下：The method steps for repairing defects of solid propellant grains using the composite solid propellant grain defect repairing material of the present invention are as follows:
步骤一，用整形刀具将推进剂药柱缺陷部位修整到无尖角、修补材料药浆易于填充的形状，用浸泡了乙酸乙酯的纯棉布将推进剂药柱缺陷部位清理干净，然后放入浇注室；Step 1: Use a shaping cutter to trim the defective part of the propellant grain to a shape that has no sharp corners and is easy to fill with the repairing material slurry, clean up the defective part of the propellant grain with pure cotton cloth soaked in ethyl acetate, and then put into the pouring chamber;
步骤二，将按照本发明提供的制备方法获得的混合均匀的复合固体推进剂药柱缺陷修补材料的药浆真空浇注到推进剂药柱缺陷部位，真空除气30min，然后将推进剂药柱放入50℃的固化箱中固化7天；Step 2: Vacuum pour the slurry of the homogeneously mixed composite solid propellant grain defect repairing material obtained according to the preparation method provided by the present invention to the defective part of the propellant grain, vacuum degassing for 30 minutes, and then place the propellant grain Curing in a curing oven at 50°C for 7 days;
步骤三，推进剂药柱自然降温至室温后，对修复的推进剂药柱进行整形处理，缺陷在整形面的用整形刀将高出药柱型面的多余修补材料修正到与药柱型面平齐。Step 3: After the propellant grain is naturally cooled to room temperature, the repaired propellant grain is reshaped. If the defect is on the plastic surface, use a plastic knife to correct the excess repair material that is higher than the grain surface to match the grain surface. flush.
因为本发明复合固体推进剂药柱缺陷修补材料均匀性好，因此对缺陷药柱的修补工艺简单，比现有技术容易控制。Because the defect repairing material of the composite solid propellant grain of the invention has good uniformity, the repairing process for the defective grain is simple and easier to control than the prior art.
相比于现有技术，本发明的有益效果是：Compared with the prior art, the beneficial effects of the present invention are:
通过在修补材料配方中添加多羟基化合物，解决了修补材料配方高温固化导致推进剂药柱强度升高、延伸率下降的问题；采用高氯酸铵和铝粉做为固体填料，且修补材料配方中固体填料含量与有缺陷推进剂药柱配方含量相近，解决了修补材料能量性能偏低的问题；修补材料的制备工艺与推进剂药柱制备工艺一致，保证了修补材料混合的均匀性和性能的一致性。By adding polyhydroxyl compounds to the repair material formula, the problem of high-temperature curing of the repair material formula leads to an increase in the strength of the propellant grain and a decrease in elongation; ammonium perchlorate and aluminum powder are used as solid fillers, and the repair material formula The content of medium solid filler is similar to the content of the defective propellant grain formula, which solves the problem of low energy performance of the repair material; the preparation process of the repair material is consistent with the preparation process of the propellant grain, which ensures the uniformity and performance of the repair material mixing consistency.
本发明克服了现有固体推进剂药柱缺陷修补材料的不足，提供一种综合性能更好的修补材料，可用于修补已固化端羟基聚丁二烯复合固体推进剂药柱的缺陷。The invention overcomes the deficiency of the existing solid propellant grain defect repairing material and provides a repairing material with better comprehensive performance, which can be used for repairing the defects of the cured hydroxyl-terminated polybutadiene composite solid propellant grain.
附图说明Description of drawings
图1是断裂的复合固体推进剂试样及其断裂面的照片；Fig. 1 is the photograph of the composite solid propellant sample of fracture and fracture surface thereof;
图2是用本发明实施例复合固体推进剂药柱缺陷修补材料修补并固化完成后的复合固体推进剂试样照片；Fig. 2 is the photo of the composite solid propellant sample after repairing and solidifying the composite solid propellant grain defect repairing material according to the embodiment of the present invention;
图3是图2所示的修补并固化完成后复合固体推进剂试样完成单轴拉伸测试后的照片。Fig. 3 is a photo of the composite solid propellant sample shown in Fig. 2 after the uniaxial tensile test after repair and curing.
具体实施方式Detailed ways
为了使本领域技术人员更好地理解本发明，下面结合附图和具体实施方式对本发明作进一步详细说明。这里，需要注意的是，在附图中，将相同的附图标记赋予基本上具有相同或类似结构和功能的组成部分，并且将省略关于它们的重复描述。In order to enable those skilled in the art to better understand the present invention, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. Here, it is to be noted that, in the drawings, the same reference numerals are assigned to components having substantially the same or similar structures and functions, and repeated descriptions about them will be omitted.
实施例1：一种复合固体推进剂药柱缺陷修补材料Example 1: A Composite Solid Propellant Grain Defect Repairing Material
本实施例中，提供了一种复合固体推进剂药柱缺陷修补材料的配方组成及各组份含量(各组份含量按质量百分比计)，并与药柱有缺陷的待修补推进剂的配方组成及各组份含量进行了比较，示于表1中；下表1中列出了为本发明复合固体推进剂药柱缺陷修补材料和待修补推进剂的配方组成及各组份含量。In the present embodiment, the formula composition and the content of each component (the content of each component is calculated by mass percentage) of a composite solid propellant grain defect repairing material are provided, and the formula of the propellant to be repaired with a grain defect is provided. The composition and the content of each component are compared and are shown in Table 1; the formula composition and the content of each component of the composite solid propellant grain defect repairing material of the present invention and the propellant to be repaired are listed in Table 1 below.
表1待修补推进剂与本发明修补材料的配方组成和组份含量Formulation composition and component content of propellant to be repaired and repairing material of the present invention in table 1
实施例2：复合固体推进剂药柱缺陷修补材料的制备方法Embodiment 2: Preparation method of composite solid propellant grain defect repairing material
按实施例1的表1中所列的本发明修补材料配方组成及各组份含量，称取各组份，按以下步骤制备复合固体推进剂药柱缺陷修补材料：According to the composition of the repairing material formula and the content of each component listed in Table 1 of Example 1, each component is weighed, and the composite solid propellant grain defect repairing material is prepared according to the following steps:
a)将高氯酸铵和铝粉分别过筛，放入温度为50-70℃的真空干燥箱内干燥，真空度1000Pa，干燥时间不少于2小时，自然降至室温后使用；a) Sieve the ammonium perchlorate and aluminum powder separately, put them into a vacuum drying oven at a temperature of 50-70°C, and dry them at a vacuum degree of 1000 Pa. The drying time is not less than 2 hours, and then use after naturally cooling down to room temperature;
b)将端羟基聚丁二烯称入不锈钢容器，再加入癸二酸二辛酯、多羟基化合物和步骤a)处理好的铝粉，预混后将预混物加入捏合机中混合，捏合机循环水浴温度为50℃；b) Weigh hydroxyl-terminated polybutadiene into a stainless steel container, then add dioctyl sebacate, polyol and aluminum powder treated in step a), premix and add the premix into a kneader for mixing, and knead The temperature of the machine circulating water bath is 50°C;
c)将步骤a)处理好的高氯酸铵分两次加入到捏合机中，混合均匀；c) the ammonium perchlorate processed in step a) is added into the kneader twice, and mixed uniformly;
d)将甲苯二异氰酸酯加入捏合机中，连续混合45min，得到复合固体推进剂药柱缺陷修补材料。d) adding toluene diisocyanate into a kneader, and continuously mixing for 45 minutes to obtain a composite solid propellant grain defect repairing material.
实施例3：复合固体推进剂药柱缺陷修补材料对推进剂单轴拉伸力学性能影响Example 3: Influence of Composite Solid Propellant Grain Column Defect Repair Material on Propellant Uniaxial Tensile Mechanical Properties
根据实施例1、2的配方组成和方法步骤获得的复合固体推进剂药柱缺陷修补材料，采用修补材料对单轴拉伸断裂的3组复合固体推进剂试样(如附图1所示)进行修补，修补后的推进剂试样照片如图2所示，对用本发明复合固体推进剂药柱缺陷修补材料修补前后的推进剂试样进行单轴拉伸力学性能测试，测试按部标QJ924-85《复合固体推进剂单向拉伸试验方法》进行，测试温度为25±2℃，相对湿度不高于70％，拉伸速率为100mm·min-1，测试后的复合固体推进剂试样照片如附图3所示。测试结果示于下表2中。The composite solid propellant grain defect repairing material obtained according to the formula composition and method steps of embodiments 1 and 2, adopting the repairing material to 3 groups of composite solid propellant samples (as shown in Figure 1) of uniaxial tensile fracture Carry out repair, the photo of the propellant sample after repair is as shown in Figure 2, carry out uniaxial tensile mechanical performance test to the propellant sample before and after repairing with composite solid propellant grain defect repairing material of the present invention, test according to Ministry Standard QJ924-85 "Composite Solid Propellant Uniaxial Tensile Test Method", the test temperature is 25±2°C, the relative humidity is not higher than 70%, the tensile rate is 100mm·min-1 , the composite solid propellant after the test A photo of the sample is shown in Figure 3. The test results are shown in Table 2 below.
表2复合固体推进剂药柱缺陷修补材料修补前后Table 2 Composite solid propellant grain defect repair materials before and after repair
推进剂的单轴拉伸力学性能Uniaxial Tensile Mechanical Properties of Propellants
可以看出，采用本发明复合固体推进剂药柱缺陷修补材料修复后，推进剂的最大抗拉强度由0.57MPa降为0.55MPa，基本保持不变；最大延伸率由5.72％增加到15.91％，增加了178.1％，显著增加。It can be seen that after repairing with the composite solid propellant grain defect repairing material of the present invention, the maximum tensile strength of the propellant is reduced from 0.57MPa to 0.55MPa, which remains basically unchanged; the maximum elongation increases from 5.72% to 15.91%, An increase of 178.1%, a significant increase.
现有技术中的修补推进剂药柱缺陷方案包括改性HTPB胶、灌浆材料以及药浆胶粘剂材料等，对公开的文献进行分析研究，比较改性HTPB胶、灌浆材料以及药浆胶粘剂材料修补前后推进剂药柱的单轴拉伸力学性能测试数据，可以看出，经上述现有技术手段修补之后的推进剂药柱或者显著降低了原推进剂药柱的最大抗拉强度和延伸率，或者仅仅维持了原推进剂药柱的最大抗拉强度和延伸率数据。The solution for repairing propellant grain defects in the prior art includes modified HTPB glue, grouting materials, and slurry adhesive materials, etc. The published literature is analyzed and studied, and the modified HTPB glue, grouting materials, and slurry adhesive materials are compared before and after repair. From the test data of the uniaxial tensile mechanical properties of the propellant grain, it can be seen that the propellant grain repaired by the above-mentioned prior art means either significantly reduces the maximum tensile strength and elongation of the original propellant grain, or Only the maximum tensile strength and elongation data of the original propellant grains were maintained.
因此，本发明复合固体推进剂药柱缺陷修补材料能明显增大推进剂药柱的最大延伸率，提高了修补后推进剂药柱的力学性能，具有良好的修复效果。Therefore, the composite solid propellant grain defect repair material of the present invention can significantly increase the maximum elongation of the propellant grain, improve the mechanical properties of the repaired propellant grain, and have a good repair effect.
以上已经描述了本发明的各实施例，上述说明是示例性的，并非穷尽性的，并且也不限于所披露的各实施例。在不偏离所说明的各实施例的范围和精神的情况下，对于本技术领域的普通技术人员来说许多修改和变更都是显而易见的。因此，本发明的保护范围应该以权利要求的保护范围为准。Having described various embodiments of the present invention, the foregoing description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and alterations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. Therefore, the protection scope of the present invention should be determined by the protection scope of the claims.
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810204208.3ACN108456293B (en) | 2018-03-13 | 2018-03-13 | A kind of composite solid propellant grain defect repair material and preparation method thereof |
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810204208.3ACN108456293B (en) | 2018-03-13 | 2018-03-13 | A kind of composite solid propellant grain defect repair material and preparation method thereof |
| Publication Number | Publication Date |
|---|---|
| CN108456293Atrue CN108456293A (en) | 2018-08-28 |
| CN108456293B CN108456293B (en) | 2019-02-22 |
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810204208.3AActiveCN108456293B (en) | 2018-03-13 | 2018-03-13 | A kind of composite solid propellant grain defect repair material and preparation method thereof |
| Country | Link |
|---|---|
| CN (1) | CN108456293B (en) |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110907010A (en)* | 2019-12-16 | 2020-03-24 | 中国人民解放军国防科技大学 | Flow-induced resonance-based propellant residual quantity measuring device and measuring method in storage tank |
| KR20220031229A (en) | 2020-09-04 | 2022-03-11 | 주식회사 한화 | Solid propellant repair washcoat composition and solid propellant repair method |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105198681A (en)* | 2014-06-10 | 2015-12-30 | 湖北航天化学技术研究所 | Room-temperature-cured-type clean solid propellant |
| CN106632955A (en)* | 2016-12-18 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Hydroxy terminated polybutadiene propellant grain defect repairing material and application technique thereof |
| CN107420223A (en)* | 2017-07-24 | 2017-12-01 | 湖北三江航天江河化工科技有限公司 | A kind of solid propellant rocket prosthetic device and its restorative procedure |
| CN107512998A (en)* | 2017-07-26 | 2017-12-26 | 湖北航天化学技术研究所 | A kind of cold curing solid propellant |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105198681A (en)* | 2014-06-10 | 2015-12-30 | 湖北航天化学技术研究所 | Room-temperature-cured-type clean solid propellant |
| CN106632955A (en)* | 2016-12-18 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Hydroxy terminated polybutadiene propellant grain defect repairing material and application technique thereof |
| CN107420223A (en)* | 2017-07-24 | 2017-12-01 | 湖北三江航天江河化工科技有限公司 | A kind of solid propellant rocket prosthetic device and its restorative procedure |
| CN107512998A (en)* | 2017-07-26 | 2017-12-26 | 湖北航天化学技术研究所 | A kind of cold curing solid propellant |
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110907010A (en)* | 2019-12-16 | 2020-03-24 | 中国人民解放军国防科技大学 | Flow-induced resonance-based propellant residual quantity measuring device and measuring method in storage tank |
| CN110907010B (en)* | 2019-12-16 | 2020-12-08 | 中国人民解放军国防科技大学 | Device and method for measuring remaining propellant in tank based on flow-induced resonance |
| KR20220031229A (en) | 2020-09-04 | 2022-03-11 | 주식회사 한화 | Solid propellant repair washcoat composition and solid propellant repair method |
| KR102575547B1 (en) | 2020-09-04 | 2023-09-11 | 한화에어로스페이스 주식회사 | Solid propellant repair washcoat composition and solid propellant repair method |
| Publication number | Publication date |
|---|---|
| CN108456293B (en) | 2019-02-22 |
| Publication | Publication Date | Title |
|---|---|---|
| CN103711609B (en) | For improving the method for EPDM heat insulation layer, HTPB lining and NEPE propellant agent interfacial adhesion | |
| CN108456293A (en) | Composite solid propellant grain defect repairing material and preparation method thereof | |
| CN105801327A (en) | Composite solid propellant and preparation method thereof | |
| Manjari et al. | Structure‐property relationship of HTPB‐based propellants. II. Formulation tailoring for better mechanical properties | |
| CN109232848B (en) | DDI lining layer for solid rocket engine medicine loading and application method thereof | |
| CN106433143B (en) | A kind of material for repairing for repairing composite material and the method using the material for repairing repairing composite material | |
| CN107513000A (en) | A kind of composite solidpropellant and preparation method thereof | |
| CN110156547A (en) | A kind of high intensity low pressure index HTPB composite propellant and preparation method thereof | |
| CN103694923B (en) | A kind of method improving HTPB lining and NEPE high-energy propellant interfacial adhesion | |
| CN113402284B (en) | Method for solving sintering cracking of soft magnetic ferrite | |
| EP4332154A1 (en) | Syntactic foam | |
| US3943208A (en) | Method for binding solid propellant to rocket motor case | |
| US6679959B2 (en) | Propellant | |
| GB2305170A (en) | Propellant Compositions | |
| CN103351459A (en) | Ester plasticizing adhesive and preparation method thereof | |
| CN110423184B (en) | Propellant for solid rocket engine and preparation method thereof | |
| CN109628053A (en) | A kind of flammable liners formulation and its manufacturing method | |
| CN106632955A (en) | Hydroxy terminated polybutadiene propellant grain defect repairing material and application technique thereof | |
| Ramesh et al. | Development of a composite propellant formulation with a high performance index using a pressure casting technique | |
| CN110591043A (en) | A self-healing cross-linked azide adhesive and its preparation method | |
| CN116655444B (en) | High-solid-content low-viscosity thermoplastic propellant and preparation method thereof | |
| CN107384294A (en) | A kind of grouting material and preparation method thereof | |
| CA2988474C (en) | Ablative material with a polymeric phosphorylated amide | |
| CN111718226A (en) | A kind of paraffin-containing fuel formulation and preparation method | |
| CN115322064A (en) | Process method for rapidly mixing solid propellant through acoustic resonance and propellant |
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |