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CN-121974769-A - High-performance HTPB propellant and preparation method thereof

CN121974769ACN 121974769 ACN121974769 ACN 121974769ACN-121974769-A

Abstract

The invention belongs to the technical field of solid propellants, and particularly relates to a high-performance HTPB propellant and a preparation method thereof, wherein the propellant consists of aluminum powder, ammonium perchlorate, hydroxyl-terminated polybutadiene HTPB, toluene diethyl cyanate and aluminum fibers, the aluminum powder comprises nano aluminum powder with an average particle size of 0.1-0.5 mu m and micro aluminum powder with an average particle size of 5-50 mu m, and the mass ratio of the nano aluminum powder to the micro aluminum powder is 1-10:1. By the design of specific components, the invention improves the fatigue resistance of the propellant and the stability of a system network, can effectively disperse external stress and prolongs the fatigue resistance life. Meanwhile, the interface bonding strength between the aluminum fiber and the HTPB adhesive can be enhanced through physical anchoring and chemical bonding, under long-term storage or alternating load, the fiber network can resist creep deformation of the matrix, maintain the structural stability of the propellant, and is particularly suitable for aerospace solid propulsion systems with extremely high requirements on reliability.

Inventors

  • GAO BO
  • YA RUHAN
  • LIU YONGMAO
  • LIU XIONG
  • WANG ZHANFENG
  • ZHANG JIANJUN

Assignees

  • 内蒙古科学技术研究院

Dates

Publication Date
20260505
Application Date
20250401

Claims (10)

  1. 1. The HTPB propellant consists of aluminum powder, ammonium perchlorate, hydroxyl-terminated polybutadiene HTPB, toluene diethyl cyanate and aluminum fibers, and is characterized in that the aluminum fibers have diameters of 0.01-1 μm and lengths of 10-100 μm.
  2. 2. The HTPB propellant of claim 1 wherein the aluminum powder comprises two of nano aluminum powder having an average particle size of 0.1 to 0.5 μm and micro aluminum powder having an average particle size of 5 to 50 μm, wherein the mass ratio of nano aluminum powder to micro aluminum powder is 1 to 10:1.
  3. 3. The HTPB propellant according to claim 1, wherein the propellant comprises, by mass, 10% of aluminum powder, 70-74% of ammonium perchlorate, 10% of hydroxyl-terminated polybutadiene HTPB, 5% of toluene diethyl cyanate and 1-5% of aluminum fibers.
  4. 4. The HTPB propellant of claim 3 wherein the aluminum powder comprises two of nano aluminum powder having an average particle size of 0.1 to 0.5 μm and micro aluminum powder having an average particle size of 5 to 50 μm, wherein the mass ratio of nano aluminum powder to micro aluminum powder is 2 to 5:1.
  5. 5. The HTPB propellant of any of claims 1 to 4 wherein the aluminum powder is coated with hydroxyl-terminated polybutadiene HTPB.
  6. 6. The HTPB propellant as claimed in claim 5, wherein the hydroxyl-terminated polybutadiene coated on the surface of the aluminum powder is prepared by dissolving hydroxyl-terminated polybutadiene HTPB in toluene to obtain a dispersion, taking the aluminum powder and slowly adding the dispersion into an HTPB toluene solution, simultaneously shearing and stirring at a high speed for 1-5 hours to completely wet the aluminum powder by the HTPB solution, placing the mixed system in a vacuum oven, preserving heat for 5-10 hours at 115 ℃ to sufficiently remove toluene and obtain the HTPB-coated aluminum powder.
  7. 7. A preparation method of the HTPB propellant as claimed in any one of claims 1 to 6, wherein the propellant comprises, by mass, 10% of aluminum powder, 70 to 74% of ammonium perchlorate, 10% of hydroxyl-terminated polybutadiene HTPB, 5% of toluene diethyl cyanate and 1 to 5% of aluminum fibers, and is characterized by comprising the following steps: 1) Weighing raw materials, namely weighing aluminum powder, ammonium perchlorate, hydroxyl-terminated polybutadiene HTPB, toluene diethyl cyanate and aluminum fibers according to the mass fraction, dissolving 25wt% of hydroxyl-terminated polybutadiene HTPB into toluene to obtain 10-20wt% of dispersion liquid, dividing the aluminum powder into two parts according to the mass ratio of 1-10:1, and respectively performing ball milling and crushing on the two parts of aluminum powder to obtain nano aluminum powder with the average particle size of 0.1-0.5 mu m and micron aluminum powder with the average particle size of 5-50 mu m; 2) Slowly adding nano aluminum powder into HTPB toluene solution, simultaneously shearing and stirring at a high speed for 1h to uniformly disperse the nano aluminum powder, slowly adding micro aluminum powder into the system, and shearing and stirring at a high speed for 2-4 h to completely wet the micro aluminum powder by the HTPB solution; 3) Mixing the obtained HTPB coated aluminum powder, the rest 75wt% hydroxyl-terminated polybutadiene HTPB and aluminum fibers, then putting into a VKM-5 type vertical mixer, introducing 60 ℃ circulating hot water in the mixing process, preserving heat for 30-60 min, putting ammonium perchlorate into the mixer for 3 times within 15min for material mixing, adding toluene diethyl cyanate for continuous mixing for 60min after 30-60 min, discharging, vacuum casting into square billets, and curing for 5-10 d in a 70 ℃ oven.
  8. 8. The method for preparing the HTPB propellant as claimed in claim 7, wherein the aluminum fiber has a diameter of 0.01 to 1 μm and a length of 10 to 100. Mu.m.
  9. 9. The preparation method of the HTPB propellant as claimed in claim 7, wherein the mass ratio of the nano aluminum powder to the micro aluminum powder is 2-5:1.
  10. 10. Use of an HTPB propellant as claimed in any of claims 1 to 6, wherein the propellant has a service life of not less than 5 years under space environmental conditions when used in a solid rocket thruster.

Description

High-performance HTPB propellant and preparation method thereof Technical Field The invention belongs to the technical field of HTPB solid propellant, in particular to a high-performance HTPB propellant and a preparation method thereof, which are prepared by using aluminum powder with different particle diameters in a matching way and introducing HTPB coating and aluminum fibers, realizes high energy release, excellent fatigue resistance and long-life stability, and is particularly suitable for aerospace solid propulsion systems with extremely high requirements on reliability. Background The propellant is widely paid attention to at home and abroad as an important substance for providing energy for carrier rockets, satellite aerospace and weapon propulsion systems. The solid propellant is a composite material with certain performance and a large amount of energy, and has the advantages of low cost, simple structure, safe operation and the like, and is used in various propulsion system fields. The solid propellant mainly comprises a binder, a curing agent, a metal filler, an additive and the like. The curing reaction between the binder and the curing agent can fully bond the components such as the metal filler, the additive and the like together to form the solid propellant with certain bonding property, energy property and mechanical property. The solid propellant has obvious mechanical properties and memory materials, the memory properties of the solid propellant are related to the materials of the propellant, such as temperature, humidity and the like, mechanical load conditions, such as grain dead weight, transportation vibration and the like, chemical load conditions, such as macromolecular chain thermal motion of high polymer materials of the propellant, a heat insulation layer and the like, the effects of the loads can possibly influence the working reliability of the propellant, in order to reduce the influence, the good mechanical properties of the solid propellant are maintained, the reliable operation of an engine under various load conditions is ensured, the solid propellant is required to have good strength, elongation and modulus and lower vitrification temperature in the whole service period, the adhesive used by the solid propellant at the present stage is mostly hydroxyl-terminated polybutadiene (HTPB) as a viscoelastic plastic material, the propellant is also influenced by alternating loads of vibration, impact and the like in the storage and transportation processes, the deformation and recovery processes under the alternating stress effect of the matrix polymer molecules are required to overcome the elasticity of the molecular chains, the interaction between the macromolecular chains and the HTPB and the interaction between the solid propellant and the HTPB can be used for the solid propellant, and the fatigue resistance can be improved, and the fatigue resistance can be further improved, and the fatigue resistance can be caused by the necessary life-cycle. Because the HTPB main chain structure only contains a small amount of hydroxyl groups, the polarity of the whole molecule is lower, and powder fillers such as Ammonium Perchlorate (AP), aluminum powder and the like are all high-polarity substances, so that a strong interface bonding effect is difficult to form at the positions of the adhesive matrix and the filler surface, the phenomenon of interface dehumidification is easy to occur under the action of external force, and the mechanical property of the propellant is further seriously influenced. At present, researches for solving the problems are mainly focused on various bonding additives for enhancing the interfacial adhesion effect of a filler and an adhesive matrix and optimizing the mixing uniformity of raw materials, for example, CN103084571B discloses a nano Al/Ni/HTPB core-shell structure energetic composite particle for a solid propellant, wherein the composite particle is a three-layer core-shell structure composite material, firstly, al powder is taken as a core, ni is taken as a shell to coat the Al powder for one time to prepare nano Al/Ni composite particles, and then HTPB is used for carrying out secondary coating on the nano Al/Ni composite particles to prepare the nano Al/Ni/HTPB composite particles. According to the invention, ni and HTPB are adopted to carry out double-layer coating on nano Al powder, coating materials are all formula components of the propellant, the energetic particle structure is optimized, the problem of poor propellant compatibility in the application process is solved, CN116655441A discloses a layer-by-layer self-assembled energetic aluminum powder, an energetic adhesive, namely, the poly azide glycidyl ether, is introduced into an aluminum powder system, so that the energy of the aluminum powder system can be obviously improved, the combustion speed of the propellant is improved, and the thermal decomposition products of 1H,2H, 3H-perfluor