• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1996.05a
• /
• pp.177-184
• /
• 1996

We have developed a polysilicon semiconductor bridge (SCB) igniter which produces a plasma discharge that ignites explosive materials pressed against the bridge. Our experiments have demonstrated that the SCB produces a hot plasma that ignites explosives, when driven with a short, low energy peak. The SCB, a heavily-doped film, typically 100 $\mu\textrm{m}$long by 300 $\mu\textrm{m}$ wide 5 $\mu\textrm{m}$ thick, is 30 times smaller in volume than a conventional bridge. We described the SCB operation and processing, and the requirement of obtaining a plasma discharge in order to ignite the explosive material.

• Journal of Ocean Engineering and Technology
• /
• v.35 no.3
• /
• pp.238-246
• /
• 2021

The survivability of a naval ship is the ability of the ship and its onboard systems to remain functional and continue a designated mission in man-made hostile environments. A passive decoy system is primarily used as a weapon system for improving the survivability of a naval ship. In this study, an engagement scenario-based simulation program was developed for decoy effectiveness assessments against an anti-ship missile (ASM), which tracks a target with sea-skimming and active radar homing. The program can explain the characteristics of a target ship, such as the radar cross section and evasive maneuvers, as well as the operational performance of the onboard decoy system, the guidance method of the ASM, and the engagement environment's wind speed and direction. This paper describes the theory and formulations, configuration, and user interface of the developed program. Numerical examples of a decoy effect assessment of a virtual naval ship against an ASM are presented.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.35 no.11B
• /
• pp.1659-1666
• /
• 2010

The High maneuver missiles use various interfaces and high speed guidance and control loop. Hardware-in-the-Loop(HWIL) simulation control system, therefore, should have high performance computing power and hardware interface capabilities, and should be developed using IT technology with which real time operating system, embedded system, data communication technology, and real time hardware control are integrated. This paper suggests the control system design techniques, such as a system hardware configuration, a job distribution algorithm for high performance multi-processors, a real time calculation and control mechanism, inter-processor communication mechanism, and a real time data acquisition technique, to perform the HWIL simulation for high maneuver missile system.

• 한국전산유체공학회:학술대회논문집
• /
• 2001.05a
• /
• pp.21-29
• /
• 2001

For rapid and abrupt control of a missile in supersonic flight, side jet on a missile body is found to be a useful devise as evidenced by recent missile development at several nations. The magnitude of the side jet and the duration of it decide the level of control of such a missile system. In this paper, the aerodynamic characteristics of the side jet devise itself are examined in terms of key parameters such as the side jet nozzle contour, the chamber pressure and temperature. Specifically attention is focused on the effect of the chamber shape between the straight nozzle and the bended nozzle by 90 degrees. The flow properties as well as the thrust level are compared between the two shapes. Particular attention is paid at the way the nozzle is bended at the joint. Effects of the length and the divergence angle of the nozzle on the thrust magnitude are also quantified among the three different side jet nozzles.

• 제어로봇시스템학회:학술대회논문집
• /
• 1996.10b
• /
• pp.1496-1499
• /
• 1996

A nonlinear tracking control technique developed for the control of nonlinear systems has been applied to the autopilot design of missile system. The difficulties in the application of inversion based control methods such as input-output feedback linearization and sliding mode control due to nonminimum phase characteristics are discussed. To avoid the stability problem associated with unstable zero dynamics, the input-output feedback linearization is applied with output-redefinition method to normal acceleration control. The output-redefinition method gives an indirect way to apply the nonlinear controls to nonminimum phase plants by redefining the plant output such that the tracking control of the modified output ensures the asymptotic tracking of the original output. The numerical simulation shows satisfactory results both for nominal and for slightly perturbed missile systems adopting the sliding mode control technique. However, the robustness problem in this method is briefly investigated and verified with the simulation.

• Journal of computational fluids engineering
• /
• v.6 no.3
• /
• pp.27-31
• /
• 2001

For rapid and abrupt control of a missile in supersonic flight, side jet on a missile body is found to be a useful device as evidenced by recent missile development at several nations. The magnitude of the side jet and the duration of it decide the level of control of such a missile system. In this paper, the aerodynamic characteristics of the side jet device itself are examined in terms of key parameters such as the side jet nozzle geometry, the chamber pressure and temperature. Specifically attention is paid to the effect of the chamber shape between the straight nozzle and the bent nozzle by 90 degrees on the nozzle flow properties. The thrust magnitudes are compared between the two shapes. Whether the way the nozzle is bent at the joint affects the nozzle performance is also investigated. Effects of the length and the divergence angle of the nozzle on the thrust are also quantified among three different side jet nozzles.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.20 no.11
• /
• pp.1171-1177
• /
• 2009

A missile warning radar is an essential sensor for active protection system to detect antitank missile in all weather environments. This paper introduces missile warning radar for main battle tank and presents the results of the design and implementation of the radar signal processor using high speed multi-DSP. The key algorithms include adaptive CF AR, weighted linear fitting algorithm, S/W tracking capability, and threat decision and present test result.

• Proceedings of the KIEE Conference
• /
• 2006.04a
• /
• pp.219-221
• /
• 2006

The recently developed autopilot controller can make the input-output (I/O) dynamic characteristics of the nonlinear missile dynamics linear and independent of flight conditions. However, significant fin actuator dynamics can degenerate the I/O dynamic performance of the overall system. In this paper, we propose a singular perturbation-like method to compensate the effect of significant fin actuator dynamics in nonlinear missile control. The proposed compensation method does not require the time derivatives of fin angles but can maintain the linear I/O dynamic characteristics provided by the recently developed autopilot controller.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.7 no.3 s.18
• /
• pp.30-37
• /
• 2004

For a proper operation of portable air defense IR terminal homing missile to the rapid intruding target, the boresight of an IR seeker of the missile should be accurately aligned with the gunner's aiming sight. Before a gunner fires the missile, he tries to keep the target within the circle of ASU ensuring the seeker to lock on the target correctly. In this paper, using an electrical seeker caging loop and IR detector signal characteristics, a precise aligning method between the seeker boresight and the LOS(Line of Sight) of ASU(Aiming Sight Unit) was studied. Although every seeker has slightly different SLA (Signal of Look Angle) output, we can get negligible alignment error through a fine tuning method of electrical caging signal. This alignment procedure was also adopted in K-PSAM system.

• Journal of the Korean Professional Engineers Association
• /
• v.42 no.3
• /
• pp.35-40
• /
• 2009

After the yield of North Korea conducted underground the first nuclear test in 2006, which was less than a kiloton, it launched a vehicle on this April 9 again, which is believed to be a Taepo-dong 2 missile, defying international warnings that the move would violate U.N. resolutions, from Musudan-ni, North Korea. Its development and proliferation of ballistic missile and nuclear bomb technology pose a threat to the northeast Asian region and to international peace and security. In the other launching the missile, a newspaper reported that "While the launch was dubbed a failure by the U.S., it was an improvement over the North Koreans' July 2006 test of the Taepodong-2, said Green of the Center for Strategic and International Studies. "It was definitely better than last time, but it's still not an operational system," Green said.