Results 11 to 20 of about 370 (179)

Thermolysis and sensitivities of solid propellants using characterized nano oxidizers involving energy performance evaluation

FirePhysChem, 2022
This investigation was devoted to exploring the thermal decomposition and sensitivity characteristics of solid propellants using nano-AN and nano-AP as oxidizers.
Xiaolan Song, Xiaohui Gao, Yong Kou, Zhihong Yu, Yi Wang, Chongwei An, Fengsheng Li   +6 more
doaj   +1 more source

Effect of hexanitroethane (HNE) and hydrazinium nitroformate (HNF) on energy characteristics of composite solid propellants

FirePhysChem, 2021
This work deals with energy performance calculate results of new solid composite propellants based on Hexanitroethane (HNE) and Hydrazinium nitroformate (HNF).
Li-nan Zhang, Qun-qing Lin, Ben-duan Cheng, Peng-cheng Wang, Ming Lu, Qiu-han Lin   +5 more
doaj   +1 more source

Study on the interfacial interaction between ammonium perchlorate and hydroxyl-terminated polybutadiene in solid propellants by molecular dynamics simulation

e-Polymers, 2022
The interfacial interaction between the main oxidant filler ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene (HTPB) matrix in AP/HTPB propellants were studied via an all-atom molecular dynamics simulation.
Dong Ge, Liu Hengzhi, Deng Lei, Yu Haiyang, Zhou Xing, Tang Xianqiong, Li Wei   +6 more
doaj   +1 more source

A Viscometric study of mixtures with Hydroxyl-terminated polybutadiene (HTPB) and short chain diols used in the formulations of solid composite propellants

Anais da Academia Brasileira de Ciências, 2021
Hydroxyl-terminated polybutadiene (HTPB) is widely used in the formulations of solid propellants used in rocket motors. Furthermore, in general, chain extenders and short chain diols, such as 1,4-butanediol and 1,2-propanediol, can also be used in ...
BRUNO C.C. DA CUNHA, MARCELA G. DOMINGUES, JOSÉ A.F.F. ROCCO   +2 more
doaj   +1 more source

Development of a Solid, Low-Smoke Rocket Propellant – Smoke Generation Intensity Tests Using a Laser and Photodiode Setup [PDF]

Problemy Mechatroniki, 2023
The work completed and discussed in this paper was to determine the level of smoke generation intensity in a selection of solid rocket propellants developed to minimise the level of generated smoke.
Przemysław WOŹNIAK (przemyslaw.wozniak.dokt@pw.edu.pl), Jan KINDRACKI (Jan.Kindracki@pw.edu.pl), Krzysztof WACKO (krzysztof.wacko@pw.edu.pl), Tomasz GOŁOFIT (tomgol@ch.pw.edu.pl), Michał CHMIELAREK (michal.chmielarek@pw.edu.pl), Katarzyna CIEŚLAK (kcieslak@ch.pw.edu.pl), Sylwia KOZŁOWSKA (sylwia.kozlowska3.dokt@pw.edu.pl), Paweł MAKSIMOWSKI (pmaksimowski@ch.pw.edu.pl), Łukasz MĘŻYK (lukasz.mezyk@pw.edu.pl), Maciej KOŁODZIEJ (maciej.kolodziej.dokt@pw.edu.pl), Dominik ZDYBAŁ (dominik.zdybal.dokt@pw.edu.pl)   +10 more
doaj   +1 more source

Evolution of structural damage of solid composite propellants under slow heating and effect on combustion characteristics

Journal of Materials Research and Technology, 2023
Composite propellants are used to fabricate solid motors for space vehicles. The fundamental factor that affects motor safety is the structural damage in the propellant owing to slow heating in an abnormal storage or service environment.
Jianxin Nie, Jiahao Liang, Haijun Zhang, Yu Zou, Qingjie Jiao, Yingjun Li, Xueyong Guo, Shi Yan, Yanli Zhu   +8 more
doaj   +1 more source

Burning Properties of Uncured HTPB Propellant

Journal of the Korean Society of Propulsion Engineers, 2016
ABSTRACT In this study, we examined the burning rate of the uncured pr opellant (with and without a curing agent application) in order to inspect the process of the HTPB solid propellant. The burning rate of the uncured propellant, that did not contain the curing agent, was approximately 9.7 mm/s at 1000 psi. In relation to the curing time, the burning
Nakhyun Kim, Jungeun Kim, Myungpyo Hong
openaire   +2 more sources

Burning Characteristics of Ammonium-Nitrate-Based Composite Propellants with a Hydroxyl-Terminated Polybutadiene/Polytetrahydrofuran Blend Binder

International Journal of Aerospace Engineering, 2012
Ammonium-nitrate-(AN-) based composite propellants prepared with a hydroxyl-terminated polybutadiene (HTPB)/polytetrahydrofuran (PTHF) blend binder have unique thermal decomposition characteristics.
Makoto Kohga, Tomoki Naya, Kayoko Okamoto   +2 more
doaj   +1 more source

Combustion performance studies of aluminum and boron based composite solid propellants in sub-atmospheric pressure regimes

Propulsion and Power Research, 2019
The aim of present study is to investigate the burning rate, ignition delay, and flame characteristics of ammonium perchlorate (AP)-hydroxyl terminated poly-butadiene (HTPB) [AP/HTPB] based composite propellants (CSP's) in sub-atmospheric pressure ...
Pratim Kumar, Mayank Varshney, Aniket Manash   +2 more
doaj   +1 more source

Correlation between solid propellant failure and interface debonding in solid rocket motors

Polymer Testing, 2022
In the traditional integrity analysis of solid rocket motors, solid propellants failure and propellant-liner interface debonding were intentionally differentiated. This empirical distinction of failure regions based on the macroscopic phenomenon neglects
Ming Lei, Shuailong Ren, Erhao Chen, Zhenguo Zhang, Jinyou Xiao, Lihua Wen, Xiao Hou   +6 more
doaj   +1 more source