12/29/2022 0 Comments Atlauncher divergence![]() On the other hand, if the roll channel stabilization is not present, the initial roll rate should be minimized to eliminate the undesired rotation effects. A set of nozzles mounted tangentially to the fuselage might be used to generate the control rolling moment (like in CAMM missile), but this makes the whole system more complicated and expensive. To successfully perform the rapid turn maneuver and achieve the commanded flight direction, the projectile could be controlled in the roll channel before the lateral thrusters fire. First, in the ascending phase of flight, the projectile could freely rotate around the longitudinal axis. As a result, projectile dispersion might occur. Several factors, such as manufacturing errors, main motor thrust misalignment, and igniter time delays could influence the projectile’s attitude after the completion of the cold vertical launch maneuver. Repeatability is one of the most important features of the missile launching process. Harriss in presented the design of a roll-decoupled thruster pack mounted on a bearing which allows one to realize the rapid turn maneuver when the projectile is not stabilized in the roll channel. presented skid-to-turn with initial roll realized by thrust vector and aero control. in presented the cold vertical launch concept with thrusters located at projectile tail. presented wind tunnel investigations of the generic missile and Monte-Carlo simulations of the launch phase. Numerical simulations of the initial phase of flight were performed by Glebocki et al. As a result, Taur has proposed a program that could realize the pitch attitude in the shortest possible time. ![]() has evaluated the theoretical analysis of the optimal open-loop trajectories which could occur in a soft vertical launch. ![]() Only a few works on this subject can be mentioned. In the literature, the agile turn maneuver realized in the launch phase with lateral thrusters is poorly described. 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. It was experimentally proved that the cold vertical launch maneuver could be realized properly with at least two lateral motors. The flight parameters were measured using an onboard inertial measurement unit and a ground vision system. Thirteen flight tests were completed on the missile test range. ![]() #Atlauncher divergence seriesA series of ground laboratory trials was accomplished. The parametric analysis was performed to investigate the influence of system uncertainties on quick turn repeatability. 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 generic 152.4 mm projectile equipped in small, solid propellant lateral thrusters was used as a test platform. This study discusses the problem of the influences of disturbances and the repeatability of lateral thrusters’ ignition on the pitch maneuver quality. However, a quick turn might be disturbed by various uncertainties. Over the launcher, the attitude of the missile is controlled by a set of lateral thrusters. In vertical cold launch the missile starts without the function of the main engine. ![]()
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