1. UTM's Missiles Technical Capabilities By Wan Khairuddin Wan Ali

2. UTM started its Rocket research activities in late 1988
The first three years were dedicated to finding the right research methods.
In 1991, a study was conducted to find the suitable type of rocket that UTM should concentrate its research effort
Resulting in the research on solid propellant rockets
In 1992, Experimental testing was conducted on ammonium perchloride base composite propellant
60 kg thrust rocket motor was developed

3. Early Research (1992 – 1999) Test rig
60 Kg Rocket motor (1992)
Early research :- A Very Primitive, Risky and Dangerous
Business

4. From 1993 – 1999, The research approach was split into 3 main research areas
Nozzle technology
Ceramic Nozzle Material
Metal alloy Nozzle
Solid propellant technology
Ammonium perchloride base solid propellant
Potassium Nitrite base solid propellant
Instrumentation and test equipment
Telemetry
Antenna development (1 MS Patent)
Digital data acquisition system
Analog sensor
Measuring rig
Burning rate test rig (1 MS patent)
Static thrust test rig (1 MS patent)

5. Nozzle technology Destructive testing of Alloy Material
Ceramic Material For Rocket Nozzle

6. Instrumentation and test equipment
Instrumentation set - up
Static thrust test

7. Research (from )
With financial support through IRPA grant, better instrumentation was established
90% of all the instruments were locally made.
In housed measurement equipments
Burning rate stand
Burning rate chambers
Static trust test rig

8. Burning rate tests

9. The Propellant
The actual burning
Burning rate Characteristic

10. Static Trust set up and result

11. Rocket motors
Standard rocket motors

12. The thrust
Static trust test

13. The missiles
The missiles been developed
Propellant used

14. The launching

15. Comparison CRV7 Rocket motor C18 (RLU-5005/B) Rocket Motor
uses 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 signatures
features HEPI system, minimal FOD, HERO and ESD protection
asbestos-free insulation and liner materials used throughout rocket motor
incorporates the shear pin rocket retention system
offers the performance of C17 rocket motor for helicopter and ground launch applications
compatible with LAU-5002, LAU-5003, SUU-5003 and LAU-5005 launcher types

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

17. Current Facilities Development
27 Apr 2007
Current Facilities Development
Propulsion Laboratory (Blast proof room)
Test volume:1 X 1 X 0.5 m
Blast proof capable to withstand 200 gram of equivalent explosive
Designed to meet US TM /NAVFAC P-397/AFR 88-22
Equipped with Crawford Bomb, Static thrust test bed and Data acquisition system

18. Current Facilities Development
Propulsion Laboratory (preparation room)
Working area: 20ft X 10ft
Equip with propellant grain casting machine
Fume cabinet for mixing toxic compound
Rolling drum mixer

19. Current Facilities Development
UTM Low Speed Wind Tunnel
Working section:1.5 X 2 X 2.5 m
High quality flow pattern
Maximum wind velocity 80m/s (Mach 0.23)

20. Current Facilities Development
Strength of Material Laboratory
Equipped with several universal testing machines:
50 ton universal testing machine
5 ton universal testing machine
Cupping test machine

21. Current Facilities Development
Composite Laboratory
Capable of making short and medium range rocket bodies

22. Current Facilities Development
Mersing runway
UTM is the official runway operator (According to DCA’s AIP).
Capable of launching short range rocket for dynamic testing

23. Current Facilities Development
60m dynamic testing rail
Can be used to test rocket motor
Capable of testing short range rocket motor for dynamic testing

24. Current Facilities Development
Facilities not shown:
Static thrust test bed
Electronics / Avionics laboratory
CNC manufacturing laboratory
Open area testing facility for antenna characterization
Solid Mechanic simulation laboratory
Material sciences laboratory

25. Current Research Personnel
Researcher
Dr. Ir. Wan Khairuddin Wan Ali
Dr. Mohammad Nazri Mohd Jaafar
En. Md Nizam Dahalan
En. Ainulllotfi Abdul Latif
Engineer
En. Abdul Basid Abdul Rahman
Research Officers
Cik Zuriana Mariati Mat Yajid
Cik Intan Noryanah Mohd Kimsin
En Mohammad Noor Ezwan Abdullah

26. Ongoing Research Projects
Development of Stable Composite Solid Propellant.
Development of Liquid Mono-Propellant.
A Study of Odd Shape Electromagnetic Structures.
Development of Single base Solid Propellant.

27. Conclusion
Since late 1989, UTM has pursued to localize the rocket technology in Malaysia.
Experience has been gained from this exercise and a number of useful facilities have been established.
Now, UTM is in a better position to further develop the technology and pass the knowledge to the rest of the country

28. Acknowledgement
The authors would like to thank UTM for providing financial support as well as human resource. Special thanks also toward MOSTI for the first project grant in 1999.