Sensitivity Analysis and Flight Tests Results for a Vertical Cold Launch Missile System

Abstract

In vertical cold launch the missile starts without the function of the main engine. Over the launcher, the attitude of the missile is controlled by a set of lateral thrusters. However, a quick turn might be disturbed by various uncertainties. This study discusses the problem of the influences of disturbances and the repeatability of lateral thrusters’ ignition on the pitch maneuver quality. The generic 152.4 mm projectile equipped in small, solid propellant lateral thrusters was used as a test platform. A six degree of freedom mathematical model was developed to execute the Monte-Carlo simulations of the launch phase and to prepare the flight test campaign. The parametric analysis was performed to investigate the influence of system uncertainties on quick turn repeatability. A series of ground laboratory trials was accomplished. Thirteen flight tests were completed on the missile test range. The flight parameters were measured using an onboard inertial measurement unit and a ground vision system. It was experimentally proved that the cold vertical launch maneuver could be realized properly with at least two lateral motors. It was found that the initial roll rate of the projectile and the lateral thrusters ‘igniters’ uncertainties could affect the pitch angle achieved and must be minimized to reduce the projectile dispersion.

Attitude Autopilot Design Based on Fuzzy Linear Active Disturbance Rejection Control

“…Selecting the appropriate observer gain can assist in the real-time tracking of various variables in (4). We can write (6) as a state space model:…”

“…However, missiles face interference from various uncertainties during the attitude control process. If the anti-interference performance is not good, it will seriously affect the missile's command tracking accuracy [1][2][3][4][5][6]. Therefore, the designed controller must ensure the performance and stability robustness of the system under strong uncertainty.…”

Path-Following Control for Thrust-Vectored Hypersonic Aircraft

“…Meanwhile, Glebocki and Jacewicz [30] investigated the use of gasodynamic control together with a modified guidance scheme for rocket artillery projectiles. Finally, Glebocki and Jacewicz [31,32] analyzed the use of small lateral thrusters to realize the cold vertical launch of the projectile. From a practical point of view, several military projectiles, such as AIM-X9 [33,34] and MICA [35], use TVC to increase agility.…”

Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile

“…In [15] the effects of launch condition variability, atmospheric factors, and IMU errors on the guidance accuracy were investigated. The influence of missile initial conditions' uncertainties and IMU errors on the impact point dispersion using lateral thrusters for control were investigated in [16] and the influence of uncertainties in rocket parameters on the performance of a cold launch were analyzed in [17]. IMU errors and noise impact on the guidance were also investigated in [18,19].…”