Results 1 to 10 of about 38,024 (216)

Research on Grain Burnback and Internal Ballistic Performance of Solid Rocket Motor under High Overload Conditions Based on Minimum Distance Function [PDF]

Hangkong bingqi, 2022
The accurate calculation of the burning surface during the grain burnback is the basis for the ballistic performance calculation of solid rocket motor. The overload conditions of the motor can significantly affect the burning surface area, grain burnback
Lin Lin, Shang Yongteng, Li Chongchong, Bai Tao, Guo Mengfei
doaj   +1 more source

Investigations on the thermal response of a solid rocket motor with complex charge structure using CL-20/GAP propellant

Case Studies in Thermal Engineering, 2022
The thermal safety of a solid rocket motor with a complex charge structure using CL-20 (Hexanitrohexaazaisowurtzitane)/GAP (Glycidyl Azide Polymer) propellant was evaluated. The morphology and thermal decomposition properties of the propellant were first
Yiyao Wang, Junjie Wen, Junsen Yang, Guanglong Zhang, Ningfei Wang, Yi Wu   +5 more
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Study on Size Distribution and Flow Characteristics of Condensed Products in Solid Rocket Motor

International Journal of Aerospace Engineering, 2021
The size distribution of condensed products during the combustion of aluminized propellants and flow characteristics of the gas-solid two-phase flow in solid rocket motor were studied in this paper.
Mengying Liu, Zhu Liu, Shipeng Li, Wenhao Yu, Jian Cao, Ningfei Wang   +5 more
doaj   +1 more source

Coupled Thermo-Structural Analysis Model of Solid Rocket Motor Nozzle considering the Variation of Friction Coefficient under Operating Conditions

International Journal of Aerospace Engineering, 2022
Multi-interface is a typical feature of solid rocket motor nozzles, and the interface evolution law is an important aspect to analyze the thermo-structural response of solid rocket motor nozzles.
Lin Sun, Huiyin Jia, Nan Zhang, Yu Zhao, Futing Bao   +4 more
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Hydrogen peroxide – A promising oxidizer for rocket propulsion and its application in solid rocket propellants

FirePhysChem, 2022
This paper discusses the potential use of hydrogen peroxide as oxidizer for solid rocket propulsion. While hydrogen peroxide is a liquid in normal conditions, it may be used in solid rocket motor grains.
Wioleta Kopacz, Adam Okninski, Anna Kasztankiewicz, Paweł Nowakowski, Grzegorz Rarata, Pawel Maksimowski   +5 more
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Development of Technology and Ballistic Research of the Propulsion Unit for 122 mm Rocket Missile with an Extended Range [PDF]

Problemy Mechatroniki, 2015
The paper presents the results of ballistic studies on the demonstrator missile 122 mm rocket motor of an extended range with the heterogeneous solid propellant.
Bogdan FLORCZAK, Andrzej CHOLEWIAK, Marek BIAŁEK   +2 more
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Ablation characteristics of insulator under high-temperature gas dual-pulse erosion

Defence Technology, 2022
This study numerically simulated and investigated the flow field characteristics of a typical dual-pulse solid rocket motor with a soft pulse separation device through thermal insulation ablation under high-temperature dual-pulse erosion.
Yang Liu, Xiao-cong Li, Peng-fei Zhu, Kun Xi   +3 more
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Experimental research on accelerated aging of solid propellant under alternating temperature

FirePhysChem, 2022
The storage environment of solid rocket motor charge is always alternating. In order to study its effect on the performance of solid rocket motor charge, the accelerated aging experiments under different temperature range, temperature change period and ...
Yufeng Wang, Gaochun Li, Jinfei Li, Yundong Xiao, Zhuqing Liu, Kai Qu   +5 more
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Computational analysis of rocket-assisted projectile trajectory [PDF]

Scientific Technical Review
A computational analysis was carried out in order to study the effect of solid rocket motor operating parameters on the trajectory elements of 155mm rocket-assisted projectile. Two numericalsolutions have been programmed for this purpose.
Ferfouri Abdellah, Jerković Damir D., Kari Aleksandar V., Živković Saša, Karić Mirko   +4 more
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CFD Analysis of a Solid Propellant Retro Rocket Motor using Ansys Fluent [PDF]

E3S Web of Conferences, 2020
A Solid propellant Retro Rocket Motor with a C-D Nozzle is analyzed using Ansys Fluent 17.1 .Steady State analysis of a retro rocket motor has been done for Viscous models like Inviscid and k-ɛ (Realizable) with air and gas as working fluids.
Anil Hemanth Varada, Jyothi U.S
doaj   +1 more source