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.

Missile autopilot design via functional inversion and time-scaled transformation

Abstract: This paper presents a new approach to acceleration control of STT (Skid-To-Turn) missiles. In the design and stability analysis of our autopilot, we assume perfect roll-stabilization but consider fully all other nonlinearities of the missile dynamics including the coupling effect due to bank angle. Our autopilot controller consists of a partial-linearizing controller and a dynamic compensator. The partial-linearizing controller along with a time scaled transformation can convert the nonlinear missile dynamics to the so-called normalized system which is completely independent of Mach number and almost independent of air density. The dynamic compensator is designed based on this normalized system. This normalized system greatly simplifies the design process of an autopilot controller regardless of flight conditions. Our autopilot controller can provide fast and exact set-point tracking performance but without the slow-varying conditions on angle of attack and side-slip angle required often in the prior works.

Hybrid Switched Gain-Scheduling Control for Missile Autopilot Design

Abstract: This paper presents a new hybrid switched gain-scheduling control method for missile autopilot design via dynamic output feedback. For controller design purpose, the nonlinear missile plant model is first converted to a switched linear fractional transformation system. Then, the new hybrid switched gain-scheduling autopilot is designed, which consists of a switching dynamic output–feedback linear fractional transformation controller and a supervisor enforcing a controller state reset at each switching time instant. The proposed hybrid control scheme is shown to provide a systematic yet simple framework for missile autopilot design. Specifically, the control synthesis conditions that guarantee weighted L2 stability performance are formulated in terms of a finite number of linear matrix inequalities, which can be solved effectively via convex optimization without parameter-space gridding. Furthermore, stringent controlled performance and strong robustness against parameter perturbations are achieved using t...

Game Optimal Guidance Law Synthesis for Short Range Missiles

Abstract: A horizontal pursuit-evasion game of kind in the atmosphere between a coasting pursuer with a final velocity constraint and a maneuvering evader of constant speed is considered. For this model, which is suitable to describe short range missile engagements, the adjoint equations can be integrated analytically. This allows us to determine the optimal strategies of the players on the boundary of the capture set, called the barrier, as a function of the current and final values of the state variables. The main effect of the pursuer's final velocity constraint, an important realistic parameter, neglected in previous studies, is a substantial reduction of the capture zone. However, based on this game solution, a feedback guidance law, suitable for real-time implementation, can be synthesized and compared to other guidance laws. The results show that the corresponding capture set is much larger than the firing envelope of a similar missile guided by proportional navigation with the same final velocity constraint.

Missile detection and neutralization system

Abstract: The present invention is intended to provide a system for determining the precise launch point of ballistic missiles, and may additionally provide the capability of neutralizing said threats. The invention provides a mobile object information means configured to classify electromagnetic frequency activity within satellite and land based commercial and private broadcast and telecommunications spectra in a given geographical area, said means also configured to classify associated area weather normality and anomalies. The system includes a software algorithm configured to extract from said database, a missile launch in a given geographical zone by “tagging” an electromagnetic wave disturbance caused by the high intensity initial fuel burn of said missile launch. Additionally, the system is intended to affect the electrical functioning of a missile guidance system or warhead detonator by transmitting a precisely tuned frequency wave combination from a defensive missile borne frequency generator, or from a network of satellite or land based transmitters.

GPS/INS integration on the Standoff Land Attack Missile (SLAM)

Abstract: The Standoff Land Attack Missile (SLAM) is a worldwide, all-weather, precision-strike weapon system deployed from carrier-based aircraft. In the primary mode of operation, target location and other mission data are generated from intelligence sources available on the aircraft carrier and loaded into the missile prior to aircraft takeoff. After missile launch, the SLAM inertial navigation system (INS) guides the missile along the planned trajectory. Updating the missile INS from the Global Positioning System (GPS) during flight provides precise midcourse navigation and enhances target acquisition by accurate, on-target pointing of the SLAM Maverick seeker. The GPS/INS avionics and software integration used for SLAM are described in detail, along with some of the design tradeoffs that led to the approach. The avionics configuration integrates the Harpoon midcourse guidance unit, which includes a strapdown inertial sensor package and digital processor, with a Rockwell-Collins single-channel, sequential GPS receiver processor unit (RPU), a derivative of the GPS phase-III user equipment. In addition to the GPS receiver elements the RPU contains the navigation processor, which executes the SLAM navigation, Kalman filter algorithms, and other guidance algorithms including seeker pointing. Flight-test results of the SLAM GPS-aided INS are also included. >