220 results about "Missile guidance" patented technology

An accurate and rapid method for characterizing the performance of an APD and setting its operating voltage Vop to an optimal value uses an on-board LED or other pulsed light source to measure APD responses at different operating voltages Vop. An estimated breakdown voltage Vb is determined by comparing the measured responses, and the Vop is adjusted to a new value at a fixed offset from the estimated Vb. The fixed offset is selected according to ambient light conditions, including the presence or absence of light background noise, and whether the sun is partially or fully in the field of view. The method is iterated until convergence, or until a maximum number of iterations is reached. In embodiments, a plurality of APD's having a common Vop can be adjusted, and the Vop is never set below a minimum value VopBW necessary to meet timing requirements for a missile guidance system.

The invention discloses an H-plane waveguide power divider. The H-plane waveguide power divider comprises a coupling cavity, an input port, an isolation port B, an isolation port C, an isolation port A, an output port A and an output port B, wherein the input port, the isolation port B, the isolation port C, the isolation port A, the output port A and the output port B are communicated with the coupling cavity; and the input port is located at a front end face of the coupling cavity, the isolation port A is located at a rear end face of the coupling cavity, the front end face and the rear end face are two mutually-symmetrical opposite faces of the coupling cavity, the isolation port B and the isolation port C are respectively located at the two sides of the input port, and the output port A and the output port B are respectively located at the two sides of the isolation port A. The H-plane waveguide power divider further has the characteristics of simple structure, small volume and low processing difficulty. The H-plane waveguide power divider can be widely applied to the military and civilian fields of antenna arrays, phased-array radar, power synthesis, missile guidance, communications and the like.

A generalized Hough transform is used to acquire and track vehicular targets for missile guidance. This is accomplished by recognizing that most vehicles have silhouettes that may be described as a “rounded rectangle”. The position and shape of such rounded rectangles is described in terms of 5 parameters (xc, yc, a, b, θ) where xc, yc are the center coordinates, a,b are the major and minor axis and Θ is the orientation. The computation of a five dimensional Hough transform on an image including such a target will produce the five parameters that provide the “best fit” rounded rectangle to the target. These parameters are then passed to a missile tracker. This capability can be used to improve track gate handoff from the automatic target recognizer (ATR) to the missile tracker, changing aspect ratios of maneuvering targets, limited lock-on after launch (LOAL), aimpoint designation and fire control system to missile seeker handover.

The invention discloses an attack angle constrained high-speed interception guidance method. The attack angle constrained high-speed interception guidance method comprises the following steps of establishing the relative motion relation between a guided missile and a target with the longitudinal plane where the guided missile and the target are located as an attack plane to obtain an expression ofrelative motion parameters; deducing expressions of the zero effort miss and zero effort speed according to the missile-target relative motion parameters; making the zero effort miss and zero effortspeed as first-layer sliding mode variables according to the hierarchical sliding mode theory and combining a first-layer sliding mode into a second-layer mode; and selecting an exponential reaching law, making the exponential reaching law equal to the second-layer mode about the time derivative and then solving the falling angle constraint missile guidance law of a high-speed flight missile. Through the attack angle constrained high-speed interception guidance method, the missile hits on the target at the preset angle of sight to improve the destroy effect. When the missile intercepts the target at high speed, the missile hits on the target with small zero effort miss. Thus, the attack angle constrained high-speed interception guidance method has good reliability.

The invention discloses a loaded power divider. The loaded power divider comprises a coupling cavity, an input terminal, an output terminal, a coupling terminal and an isolation terminal, wherein the input terminal, the output terminal, the coupling terminal and the isolation terminal are communicated with the coupling cavity; the input terminal and the isolation terminal are located at a front end face of the coupling cavity, the coupling terminal and the output terminal are located at a rear end face of the coupling cavity, the isolation terminal is located at the right side of the input terminal, and the coupling terminal is located at the right side of the output terminal; and columnar bodies are arranged in the coupling cavity, are arranged into at least three rows along the direction of the front-rear axis of the input terminal, are arranged into at least two columns along the direction vertical to the front-rear axis of the input terminal, and are connected with an upper internal wall or lower internal wall of the coupling cavity. The power divider disclosed by the invention has over 59% relative operating bandwidth and has the characteristics of simple structure, small volume and low processing difficulty. The loaded power divider can be widely applied to the military and civilian fields of antenna arrays, phased-array radar, power synthesis, missile guidance, communications and the like.