dc.contributor.author |
Alnasih, Mohammed Osman Abdelrahman Osman |
|
dc.contributor.author |
Supervisor, - Mohammed Altayeb Mansour |
|
dc.date.accessioned |
2018-07-15T08:18:14Z |
|
dc.date.available |
2018-07-15T08:18:14Z |
|
dc.date.issued |
2018-06-10 |
|
dc.identifier.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. |
en_US |
dc.identifier.uri |
http://repository.sustech.edu/handle/123456789/21117 |
|
dc.description |
Thesis |
en_US |
dc.description.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) |
en_US |
dc.description.sponsorship |
Sudan University of Science and Technology |
en_US |
dc.language.iso |
en |
en_US |
dc.publisher |
Sudan University of Science and Technology |
en_US |
dc.subject |
Power |
en_US |
dc.subject |
MECHANICAL ENGINEERING |
en_US |
dc.subject |
COMPOSITE PROPELLANT |
en_US |
dc.subject |
PERFORMANCE OF 107MM USING |
en_US |
dc.title |
DEVELOPMENT ROCKET PERFORMANCE OF 107MM USING COMPOSITE PROPELLANT |
en_US |
dc.title.alternative |
تطوير أداء الصاروخ 107 ملم بإستخدام الوقود الدفعي المركب |
en_US |
dc.type |
Thesis |
en_US |