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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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Journal ArticleDOI
TL;DR: In this article, improved empirical methods for the prediction of perforation of reinforced concrete barriers by missiles produced by turbine fracture are developed, which result in a more accurate prediction of the occurrence of perorations by missiles typical of those that might be found at nuclear power generating facilities.
Abstract: Improved empirical methods for the prediction of perforation of reinforced concrete barriers by missiles produced by turbine fracture are developed. Data from recent turbine missile tests and existing empirical methods of perforation damage analysis were collected and compared. Selected formulas were chosen for improvement. For each, modifications are proposed which result in a more accurate prediction of the occurrence of perforation of reinforced concrete barriers by missiles typical of those that might be found at nuclear power generating facilities. Also, a method is given to allow perforation analysis of reinforced concrete barriers with a thin steel plate affixed to the back face.

38 citations

Journal ArticleDOI
TL;DR: In this article, the effect of relative deformability of a soft cylindrical missile and a target plate on the ballistic limit of thin ductile plates which are struck at normal obliquity by soft cylinders was investigated.

38 citations

Journal ArticleDOI
TL;DR: Double-engine designs are shown to be more promising than single- engine designs for achieving the desired 750-km range, as well as allowing for increased payload, and the sensitivity of the modeling assumptions on the performance of the optimized designs are explained.
Abstract: Tradeoffs involved in the design of a hydrocarbon-fueled, hypersonic waverider-based missile were explored. The problem of providing acceptable vehicle performance in a volume-constrained package was addressed. The speciŽ c case of amissile constrained to Ž t within a 0:61 £ £ 0:61 £ £ 4:27m navalvertical launch tubewas examined, and a parametric study was performed to determine the probabilistic boundaries of designing a Mach 6 missile to satisfy the desired mission goal of a 750-km cruising range. All missile designs were assumed to reach cruising altitude and velocity through the use of an external rocket booster. The key design elements investigated are fuel volume fraction, engine inlet pressure, the number of scramjet engines, and the effects of changing the engine mixing and burning efŽ ciencies. Missile designs were optimized for steady-state trim conditions at the beginning of cruise using genetic algorithmsoftware. The sensitivities of the modeling assumptionson the performance of the Ž nal optimized designs are explained. The overall contribution of the optimized designs along with the predicted change in performance expected with increased modeling accuracy allows upper performance and range limits to be established. Double-engine designs are shown to be more promising than single-engine designs for achieving the desired 750-km range, as well as allowing for increased payload.

38 citations

Proceedings ArticleDOI
05 Mar 2012
TL;DR: In this paper guidance laws to intercept stationary and constant velocity targets at a desired impact angle, based on sliding mode control theory, are proposed and numerical simulation results are presented to validate the proposed guidance laws for different initial engagement geometries and impact angles.
Abstract: In this paper guidance laws to intercept stationary and constant velocity targets at a desired impact angle, based on sliding mode control theory, are proposed. The desired impact angle, which is defined in terms of a desired line-of-sight (LOS) angle, is achieved in finite time by selecting the missile's lateral acceleration (latax) to enforce non-singular terminal sliding mode on a switching surface designed using this desired LOS angle and based on non-linear engagement dynamics. Numerical simulation results are presented to validate the proposed guidance laws for different initial engagement geometries and impact angles.

38 citations

Proceedings ArticleDOI
08 Jan 2007
TL;DR: In this article, the authors presented an effective and robust numerical approach to the problem of a hypersonic flow over a missile body shielded with aerospike/aerodisc. And they used a pressure-based coupled solver formulation to obtain an accurate fast-coverage solution.
Abstract: Many design concepts of high-speed tactical guided missiles use aerospikes to reduce the drag and heating on the missiles body. The accurate numerical prediction of hypersonic flows over aerospike-protected missile shapes using Computational Fluid Dynamics (CFD) can be a valuable tool in the evaluation of such co ncepts. This study presents an effective and robust numerical approach to the problem of a hypersonic flow over a missile body shielded with aerospike/aerodisc. The problem considers three-dimensional flow around aerospikeprotected missile domes at a free stream Mach number ranging from 4.5 to 6.06 and angles of attack varying from 0 to 16 deg. Steady-state nu merical simulations are carried out using the general purpose CFD code FLUENT, version 6.3. Pressure-based coupled solver formulation is chosen to obtain an accurate fast-co nverging solution. SST ω k turbulence model is employed to simulate turbulence effects. T he near-wall mesh is fine enough to resolve the viscosity-affected near-wall region all the way to the laminar sublayer, and FLUENT’s enhanced wall treatment is applied. Numerical results expressed in terms of pressure coefficient are compared with experimental data, and favorable agreement is found. Effects of aerospike on missile dome surface aeroheating are also presented.

38 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20241
2023270
2022639
2021202
2020352
2019451