Topic
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.
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TL;DR: This paper addresses the problem of computing accurate time-to-go estimates, which is an important issue in implementing various optimal guidance laws developed for missiles of time-varying velocity and includes an error compensation feature which explicitly computes the time- to-go error produced by nonzero initial heading errors.
Abstract: This paper addresses the problem of computing accurate time-to-go estimates, which is an important issue in implementing various optimal guidance laws developed for missiles of time-varying velocity. A recursive time-to-go computation method which updates the time-to-go in a noniterative way is presented. The recursive method includes an error compensation feature which explicitly computes the time-to-go error produced by nonzero initial heading errors. The proposed method is simple and straightforward to implement for any missile velocity profiles. Various numerical examples show that the proposed method works effectively for optimal guidance laws as well as proportional navigation and augmented proportional navigation.
108 citations
TL;DR: In this article, the authors derived air-to-air missile guidance laws using optimal control and differential game theory with final miss distance as the optimization criterion, and two simulation scenarios were used to evaluate the guidance laws: one with missile launch near the inner launch boundary and another near the outer launch boundary.
Abstract: Air-to-air missile guidance laws are derived using optimal control and differential game theory with final miss distance as the optimization criterion. A perfect target airframe/autopilot response is assumed, while both perfect and first-order missile responses are considered. With a first-order missile response the target is always able to force a nonzero final miss distance in the differential game formulation. For all other formulations considered there are states from which the missile can force zero terminal miss. In these cases, an auxiliary performance index (e.g., control energy) can be used to specify unique controls. Two simulation scenarios were used to evaluate the guidance laws: one with missile launch near the inner launch boundary and the other near the outer launch boundary. The differential game guidance laws are less sensitive to errors in estimates of current target acceleration than the optimal control laws. The laws based on a perfect missile response performed better for the outer launch boundary scenario; whereas for the inner launch boundary scenario the laws based on a first-order missile response achieved smaller miss distances.
107 citations
01 Jun 1953
TL;DR: In this article, a tricyclic theory for the free fligbt motion of miseiles is combined with a single theory for a basically symmetrical missile, and the results indicate that the rapidity of passage through the resonance region is a significant factor affecting the nagnitude of the pitch and yaw of the missile.
Abstract: : The theories for the free fligbt motion of miseiles, as generally considered by the aerodynamicist and the ballistician, are combined to yield a single theory for the basically symmetrical missile. The force and moment system contains not only the usual aerodynamic forces and moments but also the effects of slight configurational asymmetries and the effects of rolling velocity. The theory yields the condition for the dynamic stability of both statically stable and statically unstable missiles, and alco predicts that the presence of configurational asynnetries together with rolling velocity may result in resonance instability. Numerical integrations of the differential equations for the pitching and yawing motion are carried cut for three variations in the rolling motion. The results indicate that the rapidity of passage through the resonance region is a significant factor affecting the nagnitude of the pitch and yaw of the missile. rWo models of a simple arrow type missile having control surface deflection are gun launched at supersonic velocity in the Aberdeen Spark Photography Range and the free flight pitching and yawing motion and the transverse displacement are measured. The tricyclic theory is fitted to the experimental data. The results indicate tbat the theory accurately represent. the actual motion of the two models and that the associated static and dynamic aerodyamic derivatives are accurately determined.
103 citations
TL;DR: In this paper, an adaptive nonlinear control design technique is applied to the pitch controller for a missile model, which is aerodynamically controlled, and the model motion is modelled to be nonlinear with unknown parameters and uncertainties.
103 citations
TL;DR: In this paper, a guidance strategy based on the theory of feedback linearization is presented, and simulation results are given comparing miss distance performance of the feedback linearized guidance law to proportional navigation.
Abstract: This paper examines the guidance problem of an acceleration constrained homing missile when the initial missile heading is far from intercept course. A guidance strategy based on the theory of feedback linearization is presented, and simulation results are given comparing miss distance performance of the feedback linearized guidance law to proportional navigation. It is demonstrated that the feedback linearized guidance law is a viable option under these conditions. aT L*A(r) LgLkfh(x) N'
102 citations