Please use this identifier to cite or link to this item: https://repository.sustech.edu/handle/123456789/21117
Title: DEVELOPMENT ROCKET PERFORMANCE OF 107MM USING COMPOSITE PROPELLANT
Other Titles: تطوير أداء الصاروخ 107 ملم بإستخدام الوقود الدفعي المركب
Authors: Alnasih, Mohammed Osman Abdelrahman Osman
Supervisor, - Mohammed Altayeb Mansour
Keywords: Power
MECHANICAL ENGINEERING
COMPOSITE PROPELLANT
PERFORMANCE OF 107MM USING
Issue Date: 10-Jun-2018
Publisher: Sudan University of Science and Technology
Citation: Alnasih, Mohammed Osman Abdelrahman Osman . DEVELOPMENT ROCKET PERFORMANCE OF 107MM USING COMPOSITE PROPELLANT / Mohammed Osman Abdelrahman Osman Alnasih ; Mohammed Altayeb Mansour .- Khartoum: Sudan University of Science and Technology, college of Engineering, 2018 .- 103p. :ill. ;28cm .-PhD.
Abstract: The design of 107mm solid rocket motor using hydroxyl-telechelic polybutadiene (HTPB) propellant to improve the rocket performance of 107mm and to have a details study of the internal ballistic affecting performance of the motor using solid propellant will be analyzed. Both approaches computational and experimental have been used to calculate the internal ballistic parameters and performance. The objective of the study will be achieved using the grain configuration design, propellant formulation design, small batches of propellant and firing test. The basic solid rocket motor (107mm) is the double base propellant. In this study composite propellant were used instead of double base and designed by two formulations. First RMD-107-1 formulation giving low burning rate 11.8 mm/s. The result is not suitable for requested design. Second RMD-107-2 formulation giving high burning rate 31.41mm/s. The formulation high burning rate is adopted according to the requirement design. Six degree of freedom (6DOF) is used to calculate the range of the original motor and modified one, experiment test carried out for the two motors. The original motor represent the performance that was designed for double base propellant while the modified motor was designed by using composite propellant. Therefore the original motor and the modified one were designed for same combustion chamber and nozzle. In the original motor total impulse found 6.97 KN and that of modified motor was found 7.31KN, the total impulse of the modified was increased than the original motor .The other v internal ballistic parameters results showed the modified motor is better than the original motor , the maximum thrust of original motor was 24.01KN while for the modified one was 37.26 KN which is greater than the original motor by about 13%,.The burning time for the original motor was 0.54sec and that for the modified one 0.498sec. Finally the range of original motor was 7.09KM and that for the modified motor range of 9KM , which is greater than the original motor by about 2KM (28% improved)
Description: Thesis
URI: http://repository.sustech.edu/handle/123456789/21117
Appears in Collections:PhD theses : Engineering

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