The Electronic Warfare Division, of the Avionics Laboratory at the Wright Research and Development Center (WRDC), WPAFB, has two in-house facilities which are used in the evaluation of conceptual infrared (IR) and electro-optical (EO) countermeasure techniques. The ftrst facility, called the Dynamic Infrared Missile Evaluator (DIME), is a 6-degree of freedom hardware-in-the-loop infrared (IR) m...

– A flight path rate demand modified two-loop lateral missile autopilot design methodology for a class of rear controlled guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) and PI controller is proposed. The open loop undamped model of two-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase feature...

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The U.S. Navy is currently developing its next-generation cruise missile, the Tactical Tomahawk, which improves upon current versions by its ability to be retargetedin flight against emergent time-critical targets. In this study, we developed an advanced operator interfaceprototype for monitoring, controlling and retargeting the Tactical Tomahawk missile and empirically tested the effect of mis...

The analysis of missile telemetry data from live or simulated firings has traditionally been a time consuming and complex task. Missile telemetry data can consist of over a thousand channels, and data files can be hundreds of megabytes. Hundreds of runs can be performed in a single day of testing, resulting in an information overload for the analyst. The Generic Telemetry Viewer (GTV) and White...

The application of a new nonlinear robust control strategy to the design of missile autopilots is presented. The control approach described and demonstrated here is based upon the numerical solution of the Hamilton-Jacobi-Isaacs equation by Successive Galerkin Approximation. Using this approach, feedback controllers are computed by an iterative application of a numerical Galerkin-type PDE solve...

A new missile midcourse guidance algorithm is proposed in this paper. It is a combination of sampling based path planning, Dubins’ curves and classical guidance laws. Moreover, a realistic interceptor missile model is used. It allows to anticipate the future changes of flight conditions along the trajectory, especially the loss of maneuverability at high altitude. Simulation results are present...

A second investigation into sympathetic detonation of ammonium nitrate (AN) and ammonium nitrate-fuel oil (ANFO) was conducted to define the scaling law for safe separation from detonating ANFO. Both missileand non-missile-producing ANFO donors weighing up to 5,400 pounds were employed with equal sizedacceptors. The usual cube root scaling law was not confirmed; exponents for the relationship S...

High-level networking model and technology suitable for effective management of large distributed dynamic air and missile defense systems will be described which can cope with different kinds of unpredictable and asymmetric situations including massive air and missile attacks. Using this Spatial Grasp Technology (SGT), intelligent distributed command and control infrastructures, as demonstrated...

– A flight path rate demand modified three-loop lateral missile autopilot design methodology for a class of guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) and Linear Quadratic Regulator (LQR), is proposed. The open loop undamped model of three-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase...