Showing papers on "Air-to-air missile published in 1994"

Missile guidance algorithm against high-g barrel roll maneuvers

Abstract: The features of high-# barrel rolls for an aircraft and the countermeasures for a proportional navigation guidance missile against this maneuver are studied First, the features of the barrell roll maneuver, and the effects of the parameters on the miss distance are discussed The simulation results show that a high-£ barrel roll maneuver generally produces a larger miss distance than a split-S (a sustained maximum g turn) and the miss distance does not critically depend on the maneuver initiation time, if the aircraft has a certain length of "time-to-go" and maneuvers with an appropriate roll rate Second, the inference is made that the provision of a phase lead in the pitch-yaw plane in the missile guidance loop and adoption of the augmented proportional navigation guidance may be effective It is also proven that a large phase shift (but less than ir/2) results in a smaller miss distance and that the combination of the phase lead and the augmented proportional navigation produces better results

The Analysis of a Generic Air-to-Air Missile Simulation Model

Abstract: A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft9s position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile9s probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

Aircraft infrared guided defense missile system

Abstract: A defense missile system for an aircraft to provide protection against hostile attack on the aircraft, the system including an aerodynamically shaped launch housing structured for external mounting on the aircraft, and a missile assembly fitted within an interior launch chamber of the launch housing. The missile assembly includes at least one, and preferably several infrared guided missiles each contained within an elongate tube and having a propulsion engine at one end and a seeker head at the opposite end. A missile support structure holds each of the missiles within the launch chamber such that the missile seeker heads are at least partially exposed through an open aft end of the launch housing. A cylinder containing pressurized coolant gas is supported within the launch chamber and is interconnected to each of the missiles for providing coolant gas to the respective seeker heads. A missile fire activation system interconnects with a fire control located in the aircraft's cockpit which is electronically interconnected to each of the missiles to facilitate sequential release of the coolant gas and electrical power to each seeker head and subsequent firing of the missile, so as to effectively launch the missile in an aft direction relative to the aircraft. A drag inducing stage is provided for use with higher speed aircraft, such as fighter jets, including a tube fitted with a ballute which inflates when the tube is ejected from the launch chamber, effectively decelerating the forward speed of the tube so that the missile can be fired into the air stream with a positive aerodynamic stability in the rearward direction relative to the aircraft.