Air-to-air missile

About: Air-to-air missile is a research topic. Over the lifetime, 445 publications have been published within this topic receiving 3165 citations. The topic is also known as: AAM & air intercept missile.

Using a Multiple-Model Adaptive Estimator in a Random Evasion Missile/Aircraft Encounter

Abstract: The terminal phase (end game)of an encounter between an air-to-air missileequipped with an activemonopulse radar seeker and an evading e ghter aircraft, possibly employing electronic countermeasures in the form of electronic jinking, is addressed. The missile uses a guidance law derived from linear differential game theory, which is implemented by using a multiple-model adaptiveestimator (MMAE). TheMMAE identie es theevasion strategy of theaircraft, which consists of thecombination of evasion maneuverand electronic jinking. An extensivenumerical study is used to demonstrate the viability of the concept. In comparison with a previously proposed mixed strategy guidance methodology, the new MMAE-based approach leads to a substantial improvement in the guaranteed single-shot kill probability for the missile. ODERN air-to-air missiles, designed to intercept highly maneuverable aircraft equipped with electronic countermeasures (ECM), have to operate in a highly uncertain environment. This paper is concerned with the terminal phase (end game) of an encounter between a missile equipped with an active monopulse radar seeker and an evading e ghter aircraft having the option to use ECM. The terminal homing phase of the interception starts when the active seeker of the missile locks on its target, generating also a warning signal (including some threat identie cation ) in the aircraft. This warning is the only information the pilot has. At the moment when the warning is received, the pilot starts to execute a sequence ofperiodicalevasivemaneuvers.Simultaneously,toenhanceitssur

Near-optimal three-dimensional air-to-air missile guidance against maneuvering target

Abstract: Closed-loop guidance of a medium-range air-to-air missile (AAM) against a maneuvering target is synthesized using a three-phase, near-optimal guidance scheme. A large period of the closed-loop guidance is performed using neighboring optimal control techniques about open-loop optimal solutions obtained by solving the associated minimum time to intercept trajectories. The first phase is the boost phase guidance where the normal acceleration limit may be active due to high lofting of the boost-sustain-coast AAM. The guidance in this phase accommodates only errors in the missile's state variables, the target maneuvering being neglected. The boost phase guidance involves guidance in the presence of active control constraints. The second phase is the midcourse guidance where both state perturbations and target maneuvers are considered. Comparisons are made between guidance with gain indexing performed with clock time and with performance index to go. Models of aggressive target and run-away targets were used and the guidance scheme performance is excellent. Three methods of optimal gain evaluation are also discussed. Performance augmentation is obtained by using a center of attainability as a pseudotarget that fairs into the actual target as time to go becomes zero. The final phase is the terminal guidance, which employs proportional navigation and its variants.

Missile guidance system utilizing polarization

Abstract: A missile guidance system in which a projectile or missile is fired toward predetermined target with the missile being tracked on its flight toward the target by radar, processing the radar information in a computer apparatus and finally computing a new trajectory from the missile to the target and transmitting correction signals to a correction device on the missile including thrusters on the missile to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time Thisenables the missile to only contain radar reflecting means, and correction detection and control means on the missile rather than having gyro and other type devices on board the missile which take up a considerable amount of space and weight

Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results

Abstract: An experimental investigation was conducted on a model of a wing control version of the Sparrow III type missile to determine the static aerodynamic characteristics over an angle of attack range from 0 deg to 40 deg for Mach numbers from 1.50 to 4.60.

Missile carrier airplane

Abstract: An air launched cruise missile carrier airplane having a floor mounted track system for moving missile racks into a launch position adjacent to a side opening in the fuselage and ejecting missiles therethrough, then moving the empty missile racks from the launch location and repositioning a full rack of missiles thereat. A continuous missile launching sequence is provided by the floor track system which guides the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement.