Development of solid rocket propellant / (Record no. 4238)

MARC details
000 -LEADER
fixed length control field 02379nam a2200241 a 4500
001 - CONTROL NUMBER
control field vtls000075712
003 - CONTROL NUMBER IDENTIFIER
control field KUKTEM
005 - DATE AND TIME OF LATEST TRANSACTION
control field 20251114204551.0
008 - FIXED-LENGTH DATA ELEMENTS--GENERAL INFORMATION
fixed length control field 131022t2012 my da f abm 000 0 eng d
020 ## - INTERNATIONAL STANDARD BOOK NUMBER
International Standard Book Number THE0007396(Local)
039 #9 - LEVEL OF BIBLIOGRAPHIC CONTROL AND CODING DETAIL [OBSOLETE]
Level of rules in bibliographic description 201905151148
Level of effort used to assign nonsubject heading access points fawwaz
-- 201310221529
-- nabilah
040 ## - CATALOGING SOURCE
Original cataloging agency UMP
090 ## - LOCALLY ASSIGNED LC-TYPE CALL NUMBER (OCLC); LOCAL CALL NUMBER (RLIN)
Classification number (OCLC) (R) ; Classification number, CALL (RLIN) (NR) TL783.3 .S55 2012 rs Bc.
100 0# - MAIN ENTRY--PERSONAL NAME
Personal name Mohammad Norshim Mohamed Hashim
245 10 - TITLE STATEMENT
Title Development of solid rocket propellant /
Statement of responsibility, etc. Mohammad Norshim Mohamed Hashim
260 ## - PUBLICATION, DISTRIBUTION, ETC.
Place of publication, distribution, etc. Kuantan, Pahang :
Name of publisher, distributor, etc. UMP,
Date of publication, distribution, etc. 2012
300 ## - PHYSICAL DESCRIPTION
Extent xvii, 60 p. :
Other physical details ill. ;
Dimensions 30 cm. +
Accompanying material 1 CD-ROM
502 ## - DISSERTATION NOTE
Dissertation note Project paper (Bachelor of Mechanical Engineering (Automotive Engineering)) -- Universiti Malaysia Pahang – 2012
504 ## - BIBLIOGRAPHY, ETC. NOTE
Bibliography, etc. note Bibliography : p. 48-49
520 3# - SUMMARY, ETC.
Summary, etc. This thesis presents a study on development of solid rocket propellant that was carried out at Universiti Malaysia Pahang. Rocket propellant has been identified as a component that played an important role in the development of rockets. The ejected material in rocket propulsion is due to material called propellant. Without propellant, a rocket cannot be launched. A solid rocket is a class of rocket in which the fuel, oxidizer and binder are mixed together and cast into a solid material. Objective of this thesis is to produce potassium nitrate sucrose based solid rocket propellant. Materials used to produce this propellant are potassium nitrate powder and sucrose powder. Potassium nitrate is an oxidizer in the propellant material and sucrose as a fuel in the propellant. This propellant is produce using the method of formation. This method was easy to operate and cost effective. Burning rate test was carried out at 1 atm and 7 atm pressure using a different oxidizer/fuel mass ratio. At 1 atm pressure, it was found that burning rate for the ratio of 65/35 was 2.184 mm/sec. At 7 atm, it was found that burning rate for the ratio 65/35 was 3.791 mm/sec. Propellant must be kept in a cool dry place like it in the refrigerator to prevent it become melt. From the result of this research, the burning rate test rig has been successfully designed, fabricated and tested. As a conclusion, oxidizer / fuel ratio and combustion pressure influence burning rate test.
650 #0 - SUBJECT ADDED ENTRY--TOPICAL TERM
Topical term or geographic name entry element Rockets (Aeronautics)
General subdivision Fuel
Holdings
Withdrawn status Lost status Damaged status Not for loan Home library Current library Date acquired Total checkouts Full call number Barcode Date last seen Copy number Price effective from Koha item type
  Not lost   Not for loan UMPLIB PEKAN UMPLIB PEKAN 04/09/2019   TL783.3 .S55 2012 rs Bc. 0000076175 04/09/2019 1 04/09/2019 Final Year Report
  Not lost   Not for loan UMPLIB PEKAN UMPLIB PEKAN 04/09/2019   CD 7349 | TL783.3 .S55 2012 rs Bc. 0000076176 04/09/2019 1 04/09/2019 Final Year Report

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