A facility was constructed for the study of waterentry, water-exit, and underwater trajectory behavior of small momentum-propelled missiles for varied trajectory launching angles, missile accelerations and velocities, wave fields and condi tions of cavitation. A unique feature is the electromagnetic missile propulsion system. The facility is made principally of non-magnetic and electrically non...

This paper examines the proposed integrated backstepping design of missile guidance and control to the engagement of manoeuvring targets. To control engagement geometry, impact-anglecontrol guidance (IAGC) is analysed in two dimensional geometry. The integrated backstepping design with disturbance observer is then developed and interpreted in view of stability and robustness. The performance of...

Boost-phase ballistic missile defense is alluring because rocket boosters are easy to detect and track, they are relatively vulnerable due to the large axial loads on a missile under powered flight, the entire payload (single or multiple warheads and midcourse penetration aids) may be destroyed in a single shot, and countermeasures to defeat boostphase defense are more difficult to devise than ...

In order to measure the velocity of a missile, several models have been discussed in this paper. It deals with the tracking and following of single/multiple missile in a sequence of frames and the velocity of the missile is determined. Algorithms have been developed for improving the image quality, segmentation, background subtraction, feature extraction and determining the velocity. Segmentati...

At present, there is no publicly published research on the unsteady interference effect in start-up process of lateral jet control spinning missile. The variation aerodynamic characteristics during missile still unclear. Therefore, numerical method based three-dimensional compressible Navier–Stokes equations and sliding mesh used to study starting jet. Based verification simulation this paper, ...

To ensure that the missile is safely separated from internal weapons bay, jet used to control process of separation, which mounted on front edge bay. The length-to-depth ratio bay was L/D=8, diameter d1 =0.178 m, d2 =0.05 m . FLUENT software combined with our group-developed code under platform a user-defined function (UDF) solve flow field and six-degrees-of-freedom (6DOF) missile. detached ed...

This paper introduces a receding horizon control scheme for obtaining near-optimal controls in a feedback form for an aircraft trying to avoid a closing air-to-air missile. The vehicles are modeled as point masses. Rotation kinematics of the aircraft are taken into account by limiting the pitch and roll rates as well as the angular accelerations of the angle of attack and the bank angle. The mi...

In this paper, a new guidance method for surface to surface ballistic missiles without mandatory engine cut-off will be presented. The complexity of solid fuel engine cut-off demands a comprehensive method for guiding these missiles. In the method presented in this paper, a certain guidance law is applied such that by transmitting appropriate commands to the control system, by changing the miss...

Most publications discussing missile interception systems assume a zero computer response time. This paper studies the impact of computer response time on single-missile single-target and multiplemissile multiple-target systems. Simulation results for the final miss distance as the computer response time increases are presented. A simple online cooperative adjustment model for multiple-missile ...