Showing papers on "Air-to-air missile published in 1979"

Trajectory shaping of anti-armor missiles via tri-mode guidance

Abstract: In a missile system, a simple way to guide a missile in a predetermined tectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.

A comparison of air - to- air missile guidance laws based on optimal control and differential game theory

Abstract: In contrast, the differential game approach Air-to-air missile guidance laws are derived makes no assumption on future target maneuvers, using optimal control and differential game theory but instead takes into consideration the target's with final miss distance as the optimization cri- maneuver capabilities. The guidance law then terion. A perfect target airframe /autopilot re - guides the missile so as to minimize the potential sponse is assumed, while both perfect and first effects of the target's intelligent use of hie maorder missile responses are considered. With a neuver capabilities. first order missile response the target is always able to force a non zero final miss distance in the differential game formulation. For all other formulaticjns considered there are states from which the missile can force zero terminal miss. In these cases, an auxiliary performance index (e. g., control energy) can be used to specify unique controls. Two simulation scenarios were used to evaluate the guidance laws: one with missile launch near the inner launch boundary and the other near the outer launch boundary. The differential game guidance laws are less sensitive to errors i,: rstimates of current target acceleration than the optimal control laws. The laws based on a perfect missile response performed better for the outer launch boundary scenario, whereas for the inner launch boundary scenario the laws based on a first order missile response achieved srnaller miss distances. The purpose of this paper

A new tracker for air-to-air missile targets

Abstract: An extended Kalman filter is developed to aid the tracking of an air-to-air missile from a maneuvering target aircraft. The filter exploits knowledge of the dominant aerodynamically induced lift and drag forces of a nonthrusting missile employing proportional navigation guidance, and it also accounts for the dynamic lag and bandwidth effects of the missile seeker, guidance, and control systems. Incorporating the refined missile acceleration model enhances the filter's tracking estimate precision and provides meaningful threat predictive capabilities. Identifiability of parameters within the acceleration model is established, an adaptive filter is developed, and its performance capabilities portrayed through realistic Monte Carlo simulations.

Boost assisted missile launcher

Abstract: An apparatus for launching missiles from aircraft or other launching platms without use of missile fuel is provided through hydraulic means. A hydraulic actuating system provides a high pressure piston stroke over a short distance which permits missiles to be accelerated up to launch speeds prior to initiation of the missile motor. In addition to the use of the hydraulic actuator system, the missile is mounted without external mountings on the missile which affect the aerodynamic performance.

Aerodynamic characteristics of missile configurations based on Soviet design concepts

Abstract: The aerodynamic characteristics of several missile concepts are examined. The configurations, which are based on some typical Soviet design concepts, include fixed-wing missiles with either forward- or aft-tail controls, and wing-control missiles with fixed aft stabilizing surfaces. The conceptual missions include air-to-air, surface-to-air, air-to-surface, and surface-to-surface. Analytical and experimental results indicate that through the proper shaping and location of components, and through the exploitation of local flow fields, the concepts provide generally good stability characteristics, high control effectiveness, and low control hinge moments. In addition, in the case of some cruise-type missions, there are indications of the application of area ruling as a means of improving the aerodynamic efficiency. In general, a point-design philosophy is indicated whereby a particular configuration is developed for performing a particular mission.

Guidance System Application to Missile‐X Basing Alternatives

Abstract: The Missile-X concept is based on the achievement of post-attack survivability. This is accomplished by preservation of missile location uncertainty through continuous or random missile/launcher movement which obscures observation by hostile forces. Three basing concepts have been developed to accommodate this periodic movement: (1) shuffling missile/launcher and missile/launcher simulators among a number of vertical shelters; (2) random movement of missile/launcher along a covered trench to presurveyed launch sites (Ground Mobile); (3) moving missiles via aircraft to random remote bases with the capability of air launch (Air Mobile). The first two modes are land launch, the missile guidance being achieved through use of a self-contained inertial guidance system. The Air Mobile guidance is accomplished with the same inertial system, however, augmentation is needed to obtain an acceptable accuracy. The guidance problem in the Air Mobile case is the determination of initial conditions at launch—estimation of position, velocity and alignment to tens of meters, several centimeters per second, and a few arc seconds, respectively, after up to 6 hours of cruise. The problem is made difficult by the uncertainty of the local gravity field. Several schemes have been investigated as a means to solve this problem; the basic Missile-X inertial guidance aided by: (1) doppler/altimeter radars with and without improved gravity data during cruise; (2) radio ground beacons during cruise; and (3) radio ground beacons during the missile boost phase. The use of Star Trackers is also considered. Results show that a combination of all these (except the Star Tracker) would provide a reliable system with a reasonable missile accuracy from an ensemble point of view. The study describes a specific configuration for such a system—for both land launch and air launch.

Advanced missile technology. A review of technology improvement areas for cruise missiles. [including missile design, missile configurations, and aerodynamic characteristics

Abstract: Technology assessments in the areas of aerodynamics, propulsion, and structures and materials for cruise missile systems are discussed. The cruise missiles considered cover the full speed, altitude, and target range. The penetrativity, range, and maneuverability of the cruise missiles are examined and evaluated for performance improvements.

Optimal propuslsion/guidance analysis of ramjet powered air-to-air missiles

Abstract: This paper presents an optimal component integration and effectiveness analysis of ramjet powered air-to-air missiles. The approach is based on the simultaneous optimization of the propulsion and guidance, where classically these have been treated separately. To accomplish this, an optimal control approach is required that can determine the optimal propulsion/guidance control algorithm which is in feedback form for the nonlinear ramjet problem, and which can be mechanized on board the missile. Optimal control solutions using singular perturbation techniques (SPT) are derived for ramjet controlled missies which incorporate optimal aerodynamic control of turn rate and optimal thrust magnitude control of velocity. Maximum lift coefficient, maximum load factor, minimum and maximum velocity and thrust, and instrumentation related constraints are enforced. The control solutions are nonlinear and in a feedback form suitable for on-board implementation. Simulation studies have been conducted to measure total system performance when alternative mission/ propulsion/guidance related parameters are varied. Results are presented which both demonstrate the impact on trajectory shaping and the improvement in engagement performance which may be achieved over conventional (maximum thrust and conventional proportional navigation guidance) flight trajectories through use of optimal control techniques. As a consequence of the analytical techniques developed in this paper, a powerful new design evaluation tool is available to the designer of ramjet propelled vehicles.