UTM's Missiles Technical Capabilities By Wan Khairuddin Wan Ali

1. UTM's Missiles Technical CapabilitiesByWan 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 set - up • Instrumentation and test equipment Static thrust test

7. Research (from 1999 - 2006) • 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 150.04 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. 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 5-1300/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.