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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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ReportDOI
01 Jun 1960
TL;DR: In this paper, the problem of recirculation of hot exhaust gases into the engine compartment at the base of a missile has been investigated, and various tracer techniques were used to visually show the flow pattern at base.
Abstract: : The problem of the recirculation of hot exhaust gases into the engine compartment at the base of a missile has been investigated. Cold flow nozzles were used to simulate the rockets at the base of a missile model, and various tracer techniques were used to visually show the flow pattern at the base. Results are presented for a two-nozzle exploratory model and for various base configurations of the Atlas missile. Similarity parameters for simulating jet exhausts and their application to these investigations are discussed.

23 citations

Journal ArticleDOI
TL;DR: While the numerical simulation is able to capture the experimental trend and results, a comparison of penetration depth and scabbing and perforation limits as per different empirical formulation shows substantial divergence.

23 citations

Proceedings ArticleDOI
01 Aug 1994
TL;DR: In this paper, a new guidance law for a missile with varying velocity is presented, which is useful when implemented on a powerful guidance compulcr on thc ground or on the parent a i r craft.
Abstract: A new guidance law for a missile with varying velocity i s presented. First, the basic guidance equations to compute thc missile acceleration command and time-to-go are derivcd. These equations are available whenever we can predict the intercept point in some way. Taking into account a missile thrust. we obtain the guidance law during boost phase. On the other hand. the guidance law af te r thrust cutoff i s derived by considering an a i r drag. Three forms of guidance laws arc proposed for each phase. One of them, which is called the analytical guidance law, gives the theoretical gujdancc acceleration commands to guide a missile on the collision course. Though this guidance law i s mcaningful from the mathematical viewpoint, the guidance equations are too complicated to perform the computation in real time. Thus, we present the approximate guidance law in order to reduce the computation time. This guidance law i s useful when i t i s implemented on a powerful guidance compulcr on thc ground or on the parent a i r craft. Ncxt, the approximate guidance law i s transformed into the convcnicnt form to realize i t on an existing homing missile. Since the obtained form i s similar to a conventional augmenled proportional navigation. we ca l l i t the modified augmcnted proportional navigation. The guidance laws presenled as well as a conventional proportional navigation and an augmented proportional navigation are applied to a simple model of a short range airto-air miss i lc . Some simulations are performed and then the inner launch envelopes are generated. The simulation results show that the guidance laws presented can intercept the target using fa r smaller acceleration requirement than prepared for the conventional navigations. When the miss i l e velocity varies significantly, the performance of the conventional navigations arc seriously influenced. The inner launch envelopes show that the guidance laws presented provide an overall performance improvement over the conventional navigations. Especially, the modified augmented proportional navigation i s useful and at t ract ive from the real i s t i c viewpoint. * Asso. Professor. NDA. Yokosuka. Japan 239, Member AIAA ** Postgraduate Rcsearcher. NDA. Yokosuka. Japan 239 *** Lecturc. NDA, Yokosuka, Japan 239, Member A I A A = missile axial acceleration vector, a m = 1 a m ] = target la teral acceleration vector, a ,= 1 a, 1 = target la teral acceleration perpendicular to LOS = target axial acceleration vector, a , = 1 a , 1 = zero-l i f t drag coefficient = desired acceleration command vector = acceleration due to gravity = specific impulse = mass of missile = navigation constant = effective navigation constant = position vector of the impact point with respect to the present target position. P = I PI = position vector of the impact point with respect to the present missile position. Q = I Q I = relative distance vector, R = IR I = missile reference area = differential operator = thrust = total f l igh t time = time-to-go or intercept time = I , ,W/T = closing velocity = missile velocity vector, V, = 1 V , 1 = correct missile velocity vector. V,= I V,, I = target velocity vector. V , = 1 V , 1 = missile weight = i n i t i a l missile weight = ba l l i s t i c coefficient = vm v,, = missile flight-path angle = 4 , E = missile flight-path rate vector = P S C ~ d 2 r n = $ , d m = target flight-path angle to LOS = a i r density = LOS angle = LOS rate vector = missile flight-path angle to LOS = the angle between P and LOS Copyrighl c 1994 by the American I n s t i t u t e of Aeronautics and Astronautics. Inc. All r i g h t reserved.

23 citations

Journal ArticleDOI
TL;DR: In this paper, a novel cooperative tracking and interception strategy, which exploits information sharing and missile staggering, is presented, and the key idea underlying the approach is to exploit the superior information collected by the leading missile to improve the interception performance of the trailing missiles.
Abstract: A novel cooperative tracking and interception strategy, which exploits information sharing and missile staggering, is presented. The key idea underlying the approach is to exploit the superior information collected by the leading missile to improve the interception performance of the trailing missiles. For tracking a maneuvering target, the paper derives a nonlinear adaptation of an interacting multiple model filter in cooperative and noncooperative estimation modes. The optimal staggering between the missiles is derived based on a linear model and a deterministic approximation of the stochastic estimation process. An extensive Monte Carlo study, in a nonlinear two-dimensional simulation of a ballistic missile defense scenario, is used to demonstrate the viability of the proposed strategy. It is shown that, for a two-on-one interception engagement, the trailing missile’s estimation performance, in the information-sharing mode, substantially improves, when compared to that of noncooperating missiles. Combi...

23 citations

Patent
08 Jun 1978
TL;DR: In this article, the Model-in-the-Performance Index Technique (MIPI) was used to determine the control law for a missile control system at high angles of attack by crosscoupling roll and steering sensor signals between the steering and roll channels.
Abstract: A missile control system can avoid instability at high angles of attack by cross-coupling roll and steering sensor signals between the steering and roll channels. The control law for the system is derived by use of the Model-in-the-Performance Index Technique which makes the system respond at high angles as it does at low angles with desired response times, bandwidths, and stability.

23 citations


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