The development of projectile guidance requires consideration of a large number of
possible flight scenarios with various system parameters. In this paper, the
Monte-Carlo parametric study for a 160 mm artillery rocket equipped with a set of
34 small, solid propellant lateral thrusters located before the center of mass was
evaluated to reduce projectile dispersion and collateral damage. The novelty of this
paper lies in the functionality of modifying the shape of the trajectory in the
terminal phase using lateral thrusters only. A six degree of freedom mathematical
model implemented in MATLAB/Simulink was used to investigate the influence of
numerous parameters on the resulting accuracy at several launch elevation angles.
Augmented impact point prediction guidance was applied in the descending portion
of the flight trajectory to achieve the trajectory shaping functionality. The
optimum combination of thruster magnitude and algorithm parameters was
obtained. The real data from the LN200 inertial measurement unit were used to
investigate the influence of noise on the resulting accuracy. It was shown that
with the proposed guidance method, the dispersion could be reduced by more than
250 times and the projectile impact angle might be increased when compared to an
unguided projectile.

제 1편 : SIMULINK 기본편

1.1 SIMULINK의 시작 1
블록의 연결 5
블록 파라미터의 설정 7
시뮬레이션 파라미터 (Configuration Parameters)의 설정 8
시뮬레이션의 수행 9
블록 파라미터의 표시 9
복수 데이터의 표시 11
2.2 동적 시뮬레이션 13
이차 미분방정식 17
선형 상태변수 모델 23
DC 모터의 시뮬레이션 24
함수 블록의 사용 29
차분방정식(difference equation)의 모델링 34
Subsystem(부시스템)의 구성 37

제 2편 : 연구논문

1. Introduction 41
2. Materials and Methods 43
3. Results 50
4. Conclusions 62
5. References 65