Results 1 to 10 of about 17,155 (237)

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
doaj   +1 more source

Structural response analysis of a solid rocket motor with HTPB propellant grain under vertical storage condition

Xibei Gongye Daxue Xuebao, 2022
Aiming at the structural response characteristics of solid rocket motor (SRM) under vertical storage conditions, the creep tests of HTPB propellant under different stress levels were carried out, and the creep constitutive model of the propellant was ...
CHEN Ke, REN Quanbin, CHENG Jiming, WANG Jianru, LEI Jiahao   +4 more
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Launching to an orbit with a chemical propellant staged rocket systems

MANAS: Journal of Engineering, 2022
There is one way to explore space by using the space launch vehicles, which is known as rockets, and it can carry useful load named simply as payload of satelite from Earth into Space.
Erk İnger
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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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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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Agglomerate Size Evolution in Solid Propellant Combustion under High Pressure

Aerospace, 2023
Solid propellant combustion and flow are significantly affected by condensed combustion products (CCPs) in solid rocket motors. A new aluminum agglomeration model is established using the discrete element method, considering the burning rate and ...
Songchen Yue, Lu Liu, Huan Liu, Yanfeng Jiang, Peijin Liu, Aimin Pang, Guangxue Zhang, Wen Ao   +7 more
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Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Aerospace, 2023
This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works ...
Jihyoung Cha
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A Study on Ultra-Low-Pressure Ratio Technology on the Basis of 3D-Printed Propellant for a Solid Rocket Motor

Aerospace, 2023
Fused deposition technology (FDM), as an additive manufacturing (AM) technology, holds immense potential in the field of solid grain manufacturing. It can accomplish complex grain shaping with ultra-low-pressure ratios, which are challenging to achieve ...
Shixiong Song, Quanbin Ren, Min Tang, Jiawei Shi, Jiawei Wang   +4 more
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Studies on composite solid propellant with tri-modal ammonium perchlorate containing an ultrafine fraction

Defence Technology, 2017
Composite solid propellant is prepared using tri-modal Ammonium perchlorate (AP) containing coarse, fine and ultrafine fractions of AP with average particle size (APS) 340, 40 and 5 μm respectively, in various compositions and their rheological ...
K.V. Suresh Babu, P. Kanaka Raju, C.R. Thomas, A. Syed Hamed, K.N. Ninan   +4 more
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THE PROBLEM OF THE OPTIMIZATION THE DESIGN PARAMETERS AND CONTROL PROGRAMS OF THE CONTROLLED ROCKET WITH SOLID PROPELLANT ROCKET ENGINE

Авіаційно-космічна техніка та технологія, 2017
The complex problem of the simultaneous optimization of the control programs and design parameters of the controlled single-stage rocket with cruise solid propellant rocket engine is formulated.
Светлана Васильевна Сюткина-Доронина
doaj   +1 more source