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.

Trajectory and launch point estimation for ballistic missiles from boost phase LOS measurements

Abstract: This paper addresses the problem of estimating the trajectory and the launch point of a tactical ballistic missile using line of sight (LOS) measurements from one or more passive sensors (typically satellite-borne), The major difficulties of this problem include the ill-conditioning of the estimation problem due to poor observability of the target motion via LOS measurements, the estimation of the unknown launch time, and the incorporation of inaccurate target thrust profiles to model the target dynamics during the boost phase. We present a maximum likelihood (ML) estimator based on the Levenberg-Marquardt algorithm that provides both the target state estimate and the associated error covariance, taking into consideration the complications mentioned above. One important consideration in the defense against tactical ballistic missiles (TBM) is the determination of the target position and error covariance at the acquisition range of a surveillance radar located in the vicinity of the impact point. We present a systematic procedure to propagate the target state and covariance to a nominal time, when it is within the detection range of a surveillance radar to obtain a cueing region. We also provide an estimate and the error covariance of the (two dimensional) launch position, which can be used to search for the missile launch site. Monte Carlo simulation studies on typical single and multiple sensor scenarios indicate that the proposed algorithms are accurate in terms of the estimates and that the estimator calculated covariances are consistent with the errors.

Engineering, intermediate, and high level aerodynamic prediction methods and applications

Abstract: This paper presents summarized descriptions and applications of engineering, intermediate, and high level missile aerodynamics prediction methods developed and/or used by NEAR. The engineering level method is represented by the M3HAX experimental data based code, the intermediate level method includes the analytical panel-method based SUPDL/SUBDL and modified linear theory VTXCHN codes, and the high level methods include the NEARZEUS space marching Euler flow solver. All of the methods contain models to account for fin and body vorticity effects in the aerodynamic loads. The engineering and intermediate level methods are applied to the prediction of high angle of attack pitch plane and lateral aerodynamic characteristics of missiles at arbitrary roll angle and aerodynamic loads acting on conventional and chined body shapes, and to assess effects of fin-body gap on fin loads. The intermediate level methods are also employed in the design of nonconvention al fin planforms for minimum hinge moment The Euler flow solver is applied to the prediction of rolling moments acting on a canard configuration. Comparisons with experimental data are presented It is concluded that the missile aerodynamicist and/or designer should be aware of the availability and utility of the various levels of missile aerodynamics prediction methodology.

Variable-geometry inlet

Abstract: A two-dimensional inlet for a high speed ram jet missile includes in combination an educated slot and a single ramp for varying the geometry of the inlet.

Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results

Abstract: An experimental investigation was conducted on a model of a wing control version of the Sparrow III type missile to determine the static aerodynamic characteristics over an angle of attack range from 0 deg to 40 deg for Mach numbers from 1.50 to 4.60.