In this paper the Monte-Carlo method was used to investigate the sounding rocket dispersion. It was assumed that the rocket is equipped with a control unit composed of 32 solid propellant lateral thrusters. The 6 degree-of-freedom model was developed and implemented in the MATLAB/Simulink environment. Several factors affecting the projectile dispersion were taken into account, including uncertainties in rocket’s inertial and aerodynamic parameters, magnitude and direction of wind velocity as well as uncertainties in initial conditions. In addition, the influence of the malfunction of the rocket fins and the time of flight of its occurrence on the mean impact point was investigated.
Analysis of Sounding Rocket Dispersion Using Monte-Carlo Simulation
Lect. Notes in Networks, Syst.
Conference on Automation ; 2023 ; Warsaw, Poland March 07, 2023 - March 09, 2023
Automation 2023: Key Challenges in Automation, Robotics and Measurement Techniques ; Kapitel : 4 ; 39-50
2023-02-05
12 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
NTIS | 1998
|NTRS | 1998
|Sounding Rocket Dispersion Reduction by Second Stage Pointing Control
Online Contents | 2012
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