UTM's Missiles Technical Capabilities By Wan Khairuddin Wan Ali

UTM's Missiles UTM's Missiles Technical CapabilitiesTechnical Capabilities

ByBy

Wan Khairuddin Wan AliWan Khairuddin Wan Ali

UTM started its Rocket research UTM started its Rocket research activities in late 1988activities in late 1988

The first three years were dedicated to The first three years were dedicated to finding the right research methods.finding the right research methods.• In 1991, a study was conducted to find In 1991, a study was conducted to find

the suitable type of rocket that UTM the suitable type of rocket that UTM should concentrate its research effortshould concentrate its research effort

Resulting in the research on solid propellant Resulting in the research on solid propellant rocketsrockets

• In 1992, Experimental testing was In 1992, Experimental testing was conducted on ammonium perchloride conducted on ammonium perchloride base composite propellantbase composite propellant

60 kg thrust rocket motor was developed60 kg thrust rocket motor was developed

60 Kg Rocket 60 Kg Rocket motor (1992)motor (1992)

Test rig

Early Research (1992 – 1999)

Early research :- A Very Primitive, Risky and Dangerous

Business

From 1993 – 1999, The research approach From 1993 – 1999, The research approach was split into 3 main research areaswas split into 3 main research areas• Nozzle technologyNozzle technology

Ceramic Nozzle MaterialCeramic Nozzle Material Metal alloy NozzleMetal alloy Nozzle

• Solid propellant technologySolid propellant technology Ammonium perchloride base solid propellantAmmonium perchloride base solid propellant Potassium Nitrite base solid propellantPotassium Nitrite base solid propellant

• Instrumentation and test equipmentInstrumentation and test equipment TelemetryTelemetry

• Antenna development (1 MS Patent)Antenna development (1 MS Patent)• Digital data acquisition systemDigital data acquisition system• Analog sensorAnalog sensor

Measuring rigMeasuring rig• Burning rate test rig (1 MS patent)Burning rate test rig (1 MS patent)• Static thrust test rig (1 MS patent)Static thrust test rig (1 MS patent)

Nozzle technologyNozzle technology

Ceramic Material For Rocket Nozzle

Destructive testing of Alloy Material

Instrumentation and test equipmentInstrumentation and test equipment

Instrumentation set - up

Static thrust test

Research (from 1999 - 2006)Research (from 1999 - 2006)

In housed measurement equipments

Burning rate chambers

Burning rate stand

Static trust test rig

• With financial support through IRPA grant, better instrumentation was established

• 90% of all the instruments were locally made.

Burning rate tests

The Propellant

Burning rate Characteristic

The actual burning

Static Trust set up and result

Rocket motorsRocket motors

Standard rocket motors

The thrust Static trust test

The missiles been developed

The missiles

Propellant used

The launchingThe launching

ComparisonComparison

C18 (RLU-5005/B) Rocket Motoruses fast-burning non-aluminized HTBP/AP composite propellant (Hazard Class 1.3) to achieve a nominal total impulse of 1905 lbf-sec.nominal action time of 0.96 seconds produces burnout ranges and velocities of approximately 447 m and 944 m/s respectively when used with 10 lb. class warheads non-aluminized propellant results in reduced smoke and thermal signaturesfeatures HEPI system, minimal FOD, HERO and ESD protectionasbestos-free insulation and liner materials used throughout rocket motorincorporates the shear pin rocket retention systemoffers the performance of C17 rocket motor for helicopter and ground launch applicationscompatible with LAU-5002, LAU-5003, SUU-5003 and LAU-5005 launcher types

CRV7 Rocket motor

UTM launched Rocket

Rocket Motoruses fast-burning non-aluminized KNO3 / C12H22O11 composite propellant (Hazard Class 1.3) to achieve a nominal total impulse of 150.04 Ns.nominal action time of 0.6 seconds produces burnout ranges and velocities of approximately 300 m and 700 m/s respectivelyasbestos-free insulation

27 Apr 2007

Propulsion Laboratory Propulsion Laboratory (Blast proof room)(Blast proof room)• Test volume:1 X 1 X 0.5 mTest volume:1 X 1 X 0.5 m• Blast proof capable to Blast proof capable to

withstand 200 gram of withstand 200 gram of equivalent explosiveequivalent explosive

• Designed to meet US TM 5-Designed to meet US TM 5-1300/NAVFAC P-397/AFR 1300/NAVFAC P-397/AFR 88-2288-22

• Equipped with Crawford Equipped with Crawford Bomb, Static thrust test bed Bomb, Static thrust test bed and Data acquisition and Data acquisition systemsystem

Current Facilities DevelopmentCurrent Facilities Development

Propulsion Laboratory Propulsion Laboratory (preparation room)(preparation room)• Working area: 20ft X Working area: 20ft X

10ft10ft• Equip with propellant Equip with propellant

grain casting machinegrain casting machine• Fume cabinet for Fume cabinet for

mixing toxic compoundmixing toxic compound• Rolling drum mixerRolling drum mixer



UTM Low Speed Wind UTM Low Speed Wind Tunnel Tunnel • Working section:1.5 X Working section:1.5 X

2 X 2.5 m2 X 2.5 m• High quality flow High quality flow

patternpattern• Maximum wind Maximum wind

velocity 80m/s (Mach velocity 80m/s (Mach 0.23)0.23)


Strength of Material Strength of Material Laboratory Laboratory • Equipped with several Equipped with several

universal testing universal testing machines:machines:

50 ton universal testing 50 ton universal testing machinemachine

5 ton universal testing 5 ton universal testing machinemachine

Cupping test machineCupping test machine


Composite Laboratory Composite Laboratory • Capable of making Capable of making

short and medium short and medium range rocket bodiesrange rocket bodies


Mersing runwayMersing runway• UTM is the official runway operator UTM is the official runway operator

(According to DCA’s AIP).(According to DCA’s AIP).• Capable of launching short range rocket Capable of launching short range rocket

for dynamic testingfor dynamic testing


60m dynamic testing rail60m dynamic testing rail• Can be used to test rocket motorCan be used to test rocket motor• Capable of testing short range rocket Capable of testing short range rocket

motor for dynamic testingmotor for dynamic testing

Current Facilities DevelopmentCurrent Facilities Development Facilities not shown:Facilities not shown:

• Static thrust test bedStatic thrust test bed• Electronics / Avionics laboratoryElectronics / Avionics laboratory• CNC manufacturing laboratoryCNC manufacturing laboratory• Open area testing facility for Open area testing facility for

antenna characterizationantenna characterization• Solid Mechanic simulation Solid Mechanic simulation

laboratorylaboratory• Material sciences laboratoryMaterial sciences laboratory

Current Research PersonnelCurrent Research Personnel ResearcherResearcher

• Dr. Ir. Wan Khairuddin Wan AliDr. Ir. Wan Khairuddin Wan Ali• Dr. Mohammad Nazri Mohd JaafarDr. Mohammad Nazri Mohd Jaafar• En. Md Nizam Dahalan En. Md Nizam Dahalan • En. Ainulllotfi Abdul LatifEn. Ainulllotfi Abdul Latif

EngineerEngineer• En. Abdul Basid Abdul RahmanEn. Abdul Basid Abdul Rahman

Research OfficersResearch Officers• Cik Zuriana Mariati Mat YajidCik Zuriana Mariati Mat Yajid• Cik Intan Noryanah Mohd KimsinCik Intan Noryanah Mohd Kimsin• En Mohammad Noor Ezwan AbdullahEn Mohammad Noor Ezwan Abdullah

Ongoing Research ProjectsOngoing Research Projects

Development of Stable Composite Development of Stable Composite Solid Propellant.Solid Propellant.

Development of Liquid Mono-Development of Liquid Mono-Propellant.Propellant.

A Study of Odd Shape Electromagnetic A Study of Odd Shape Electromagnetic Structures.Structures.

Development of Single base Solid Development of Single base Solid Propellant.Propellant.

ConclusionConclusion

Since late 1989, UTM has pursued to Since late 1989, UTM has pursued to localize the rocket technology in Malaysia. localize the rocket technology in Malaysia.

Experience has been gained from this Experience has been gained from this exercise and a number of useful facilities exercise and a number of useful facilities have been established. have been established.

Now, UTM is in a better position to further Now, UTM is in a better position to further develop the technology and pass the develop the technology and pass the knowledge to the rest of the countryknowledge to the rest of the country

AcknowledgementAcknowledgement The authors would like to thank UTM The authors would like to thank UTM

for providing financial support as well for providing financial support as well as human resource. Special thanks as human resource. Special thanks also toward MOSTI for the first also toward MOSTI for the first project grant in 1999.project grant in 1999.

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UTM's Missiles Technical Capabilities By Wan Khairuddin Wan Ali