Research on the Application of Aluminum-lithium Alloy in HTPB Propellant

XIN Haoyue; REN Hui; JIAO Qingjie; YAN Shi

doi:10.12382/bgxb.2025.0589

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Research on the Application of Aluminum-lithium Alloy in HTPB Propellant

更新时间：2026-05-06

- Research on the Application of Aluminum-lithium Alloy in HTPB Propellant
- Acta Armamentarii Vol. 47, Issue 4, Pages: 250589(2026)
- 作者机构：
  
  北京理工大学爆炸科学与安全防护全国重点实验室，北京 100081
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2025.0589
  CLC： V512
- Received：01 July 2025，
  
  Online First：25 December 2025，
  
  Published：2026-04
- 稿件说明：
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XIN Haoyue, REN Hui, JIAO Qingjie, et al. Research on the Application of Aluminum-lithium Alloy in HTPB Propellant[J]. Acta Armamentarii, 2026, 47(4): 250589.
DOI：

XIN Haoyue, REN Hui, JIAO Qingjie, et al. Research on the Application of Aluminum-lithium Alloy in HTPB Propellant[J]. Acta Armamentarii, 2026, 47(4): 250589. DOI： 10.12382/bgxb.2025.0589.

摘要

为解决丁羟推进剂中铝粉燃烧不充分的问题，通过铝锂合金代替铝粉的方式，致力于改善燃料的燃烧效率，提高发动机比冲。采用激光粒度分布仪和扫描电子显微镜等仪器表征铝锂合金的粒度、形貌、物相及硬度，采用同步热分析仪和密闭点火装置测试其氧化及点火特性，通过浇注法制备丁羟推进剂，研究铝锂合金对丁羟推进剂的工艺性能、安全性能、燃烧性能和力学性能等综合性能的影响，并进行点火试车试验。研究结果表明：铝锂合金颗粒表面光滑，球形度达到0.92，点火温度在870℃左右，燃烧热值最高达到29.92kJ/g，燃烧效率达到96.89%。将铝锂合金代替铝粉后，丁羟推进剂的摩擦感度有所提升，燃烧热和燃烧速度提高，其他性能与对照配方基本相当。地面点火试车测试结果表明：引入铝锂合金后，推进剂的实测比冲提高了2s，具有明显的能量提升效果。总体而言，铝锂合金能够提高丁羟推进剂的燃烧效率和比冲，是替代微米铝粉作固相燃料的理想候选材料。

Abstract

To address the issue of incomplete combustion of aluminum powder in hydroxyl-terminated polybutadiene (HTPB) propellant

the combustion efficiency of fuel is improved to enhance the specific impulse of engine by replacing aluminum powder with aluminum-lithium alloy. The particle size

morphology

phase and hardness of aluminum-lithium alloy are characterized by using instruments such as laser particle size analyzer and scanning electron microscope

and its oxidation and ignition characteristics are tested by using simultaneous thermal analyzer and closed ignition device. HTPB propellant is prepared using the casting method to study the impact of aluminum-lithium alloy on the comprehensive properties of HTPB propellant

including processing performance

safety performance

combustion performance

and mechanical properties. Ignition test is also conducted on HTPB propellant. Experimental results indicate that the aluminum-lithium alloy particles have a smooth surface with a sphericity of 0.92

an ignition temperature of approximately 870℃

a maximum combustion calorific value of 29.92kJ/g

and a combustion efficiency of 96.89% .After replacing aluminum powder with aluminum-lithium alloy

the friction sensitivity of HTPB propellant is increased

while the combustion heat and combustion rate are improved. Other properties are basically the same as those of the reference formulation. Ground ignition test results demonstrate that the introduction of aluminum-lithium alloy increases the measured specific impulse of the propellant by 2s

indicating a significant energy enhancement effect. Overall

aluminumlithium alloy can be used to improve the combustion efficiency and specific impulse of HTPB propellant

making it an ideal candidate material to replace micron-sized aluminum powder as a solid-phase fuel.

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references

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