In this paper, we have studied the characteristics of a perforated muzzle brake. The main purpose of a muzzle brake is to reduce the momentum being applied to the recoil system. Muzzle brake redirect a portion of the exiting gases to the side exerting a forward force on the brake, thus reducing recoil. So it also reduces the recoil force which acts on the turret and vehicle. First of all, we analyzed the flow-field characteristics of muzzle brake using RAMPANT software. Then we investigated the influence of design parameters of perforated muzzle brake. Sixteen muzzle brakes were tested and evaluated for analyzing their influence on the muzzle brake efficiency. The muzzle brakes were designed to fit on a 40mm gun barrel. The strong dependent parameters of muzzle brake efficiency were the wall thickness(L/d ratio) and the area ratio AR. We designed the perforated muzzle brakes which have 10-20% efficiency. And we proposed a design method of perforated muzzle brake.

A chamber enduring 3,000 bars and an electrical high voltage power system have been designed and installed for studying the characteristics of the plasma produced in electro-thermal chemical propulsion system. In order to test the structural characteristics, polyethylene injectors were used which have 4 or 6 mm inner diameter and several lengths from 15 to 70 mm. The capacitors were charged at the voltages of 5.2, 7.3 and 10.4 kV which correspond to 5.58, 11 and 22.3 kJ in charging energy. The observed resistivities of the plasma injector are close to those predicted by a theoretical model that describes the plasma resistivity according to high current density.

Airborne noise is one of the considerable environmental factors for navy ship personnel because of accomplishing their tasks on restricted ship spaces. In this study, the effects of airborne noise on personnel and existing criteria for acceptable airborne noise on ships are reviewed briefly. Statistic results of airborne noise levels of the Korean navy ships are analyzed according to the class of ships and are compared airborne noise levels of the US navy ships. These results can be used for proposing airborne noise criteria of the navy ship for the future.

Some signals, such as in radar system, are transmitted as periodic pulse trains. If more than one pulse train are transmitted over the same communication channel, a problem is to separate them for source identification and extract each pulse train at the receiver. This is known as pulse train deinterleaving. In this paper, we present an approach for deinterleaving the pulse trains and extracting their periods combining the estimation of the frequency of each pulse train by DFT, CDIF/SDIF histogram and Sequence Search technique. Also, we present the result of deinterleaving pulse trains and extracting PRI in the complex environment which multiple signals are interleaved.

For the purpose of the increase in the performance and thermal stability of PBX's, the mixed formal consisting of BDNPF, DNPBF and BDNBF were synthesized. In order to find out the optimal condition for the synthesis of energetic plasticizer, BDNPF, DNPBF and BDNBF, the synthetic procedures have been investigated. We synthesized DNP-OH and DNB-OH through oxidative nitration and controlled various composition of mixed formal by $H_{2}SO_{4}$ and s-trioxane to investigate optimal composition, and then characterized its thermo-physical properties.

본 연구는 굽힘 하중하에서 탄성평판 구조 해석을 위한 경계적분방법 구성을 주목적으로 하고 체계적인 모듈화시스템 개발의 첫 이론 부분을 확립하였다. 굽힘 문제에서의 4개의 고유변수인 처짐, 기울기, 굽힘모우멘트, 상당 전단력의 항으로 경계적분방정식을 구성하였다. 물리적인 의미를 갖는 두 새로운 핵함수 도입으로 구성된 이들 적분방정식은 경계요소 구성시 나타나는 특이거동의 문제점을 간단한 두 탄성해에 의해 정규화 시켰으며 수치 적분 과정도 Cauchy 주치 적분 수렴성에서의 특별취급과는 달리 효율적으로 일반화시켰다. 경계적분식의 수치해석방법을 서술하였으며 집중하중하의 비대칭문제의 근사수치해를 도시하였다.

This paper introduces the calibration results of the fatigue crack growth models for damage tolerance analysis of the aircraft structures. Generalized Willenborg model and Wheeler model are calibrated with experimental data tested under the load spectrum of a trainer. The retardation factors such as, shut-off ratio in Generalized Willenborg model and shaping exponent in Wheeler model, are evaluated for aluminum alloys AL2024-T3511, AL7050-T7451 and AL7075-T73511. It is shown that the retardation effect of the crack growth rate depends on the yield strength of material and the maximum stress in the load spectrum. Generalized Willenborg model and Wheeler model give satisfactory prediction of crack growth life but the calibration of the experimental parameters with test is required.

In this paper, the transonic aeroelastic behavior of the generic fighter model is investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects is conducted at the various conditions. The nonlinear aerodynamic effects are considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis is used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions are investigated.

The CSCM Upwind method and Material Transport Analysis(MTA) have been used to predict the thermal response and shape changes for charring/non-charring material which can be used as thermal protection material(TPM) on blunt-body nose tip. We performed intensive flight trajectory simulations to compare 1-D MTA results with those of 2-D/Axisymmetric MTA by using MTAs and Navier-Stokes code. Theheat-transfer rate and pressure distribution were predicted at selected altitudes and wall temperature along the flight trajectory and the shape changes of blunt-body nose tip were predicted subsequently by using current procedure.