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 using quasi-LPV polynomial eigenstructure assignment

Abstract: This paper presents the design of a missile autopilot over its flight envelop using quasi-linear parameter-varying polynomial eigenstructure assignment (PEA). The paper describes the extension of PEA to parameter-varying systems using a nonlinear missile model developed by Horton as an example. The autopilot is designed for a single-plane lateral acceleration control and a 5 degree of freedom (DOF) autopilot is also designed. Both lateral acceleration and augmented lateral acceleration outputs are considered. The lateral acceleration autopilot has nonminimum phase characteristics, and it is shown that the quasi-linear parameter-varying PEA approach can handle nonminimum phase systems unlike classic dynamic inversion techniques. Simulation results are presented over fast variations in Mach number and show that the design is robust.

Fiber optic track/reaim system

Abstract: In a missile tracking and guidance system, a fiber optic link is maintained between a missile and the launcher. Tracking after launch is via a video link between the missile seeker and a video imager at the launcher. Guidance signals are derived from the video signal input to the imager and transmitted back to the missile. Additionally, rate sensors and an interrupt or reaim circuit within the launcher allows an operator to reacquire the target for refining the missile seeker look axis toward a target during flight. After the target aimpoint is refined the operator can then release the interrupt circuit, allowing the system to continue tracking from the video input, with a newly established seeker heading established during the aimpoint refinement.

A Preliminary Method for Calculating the Aerodynamic Characteristics of Cruciform Missiles to High Angles of Attack Including Effects of Roll Angle and Control Deflections

Abstract: : A method is presented together with a computer program for calculating the forces and moments on the components of a cruciform missile: nose, canard section, afterbody, and tail section. The program utilizes a skeleton data base for the fin normal forces and center-of-pressure positions. These quantities were derived from a set of fins of varying aspect ratio and taper ratio tested on a body having a diameter equal to half the tail span. The data base, covering a range 0.8 < or = M at infinity < or = 3.0, is extended to arbitrary cruciform body-tail configurations or body-wing-tail configurations using analytical and empirical methods. Pitch, yaw, and roll control are included in the method as well as the effects of missile roll angle. Comparisons are made between the predictions of the computer program and experiment for fin forces and configuration forces and moments for body0tail and wing-body-tail combinations up to angles of attack of 45 deg. On the whole acceptable agreement between prediction and experiment is obtained.

System, device and method of protecting aircrafts against incoming missiles and threats

Abstract: The present invention includes a system for protecting an aircraft against one or more incoming threats. The system includes one or more electro-optic sensors to scan an area around the aircraft for one or more possible incoming threats, and to generate an indication signal once an incoming threat is detected; an integrated unit combining a Missile Approach Confirmation Sensor (MACS) with Directed Infra-Red Counter Measure (DIRCM), to verify the incoming threat and to activate a countermeasure against the verified incoming threat; and a processor to receive data from said one or more electro-optic sensors and the integrated MACS-DIRCM unit, and to select a countermeasure technique for deployment against the incoming threat.