Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Hierarchical closed-loop flow control system for aircraft, missiles and munitions

Abstract: The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

Russian nuclear and missile exports to Iran

Abstract: (1999). Russian nuclear and missile exports to Iran. The Nonproliferation Review: Vol. 6, No. 2, pp. 134-143.

Fragmentable warhead of modular construction

Abstract: An improved fragmentable warhead of modular construction for a missile andhe like, that is generally made up of an intermediate warhead missile section and an explosive cartridge. The cartridge is selectively removable from the missile section thereby permitting the missile to be without an explosive charge until the missile is ready for tactical use. Moreover, the cartridge is of composite construction such that the outer shell of the cartridge is advantageously composed of an admixture of a suitable resin and a graphite material. By reason of this admixture the shell is not only of thin wall construction and of sufficient strength for handling the cartridge during storage and assembly, but also has sufficient electric characteristics so that the cartridge will not have electrostatic buildup that would detonate its explosive during handling and storage of the cartridge prior to assembly to a missile section. Moreover, the interior annular surface of the missile section is preferably provided with an appropriate grooved grid pattern for assisting in the formation of fragments of predetermined size when the cartridge is detonated. Furthermore, it has been found that the outer shell of the cartridge in being of thin wall construction does not adversely affect the detonation wave front of the explosive but in fact results in the fragments having a greater velocity than heretofore possible for impacting a target.

Optimal Stochastic Guidance Laws for Tactical Missiles

Abstract: : Guidance laws are developed for tactical missiles which take into account the following important dynamic and random effects: random target motion, homing sensor measurement noise, bounded control level, bounded acceleration level, and missile autopilot dynamics. Several different guidance laws are derived using optimal stochastic control theory and evaluated by computer simulation. An important conclusion of this work is that when intercept accuracy is appreciably limited by missile maneuvering capability, a control policy obtained by taking control saturation into account can yeild significantly better performance than control policies derived assuming that control levels are unconstrained.

Partial integrated missile guidance and control with state observer

Abstract: This paper conducts a partial integrated guidance and control design for missile interception. With only the output available for feedback, a novel state observer is firstly proposed in the presence of unknown disturbances. The proposed observer reconstructs full system states in finite time. Interestingly, observer parameter is updated by an adaptive law. Then, a terminal sliding mode controller based on the proposed observer ensures the system states converge to zero in finite time, which is proved by the Lyapunov stability theory. The obtained result is applied to partial integrated guidance and control design of missile and hit-to-kill interception is achieved. Finally, a simulation example is presented, and a comparison to standard sliding mode observer is discussed to illustrate effectiveness of the proposed method.