Showing papers on "Missile published in 2001"

Tactical Missile Design

Abstract: Introduction / Key Drivers in the Design Process Aerodynamic Considerations in Tactical Missile Design Propulsion Considerations in Tactical Missile Design Weight Considerations in Tactical Missile Design Flight Performance Considerations in Tactical Missile Design Measures of Merit and Launch Platform Integration Sizing Examples Development Process Summary and Lessons Learned References List of Acronyms/Symbols Conversion Factors Index

A procedure for analyzing the flight of missiles from explosions of cylindrical vessels

Abstract: The fragmentation of storage tanks or other equipment of the process industry, for example caused by boiling liquid expanding explosions (BLEVEs), and the consequent missile generation is a problem in industrial safety whose importance is underlined by accidents such as that of Mexico City. It is inscribed in what is called the “Domino Effect”. A method is presented to calculate the trajectories of missiles from horizontally mounted cylindrical vessels using analytical solutions of the equations of motion. The principal input parameters of these equations, e.g. drag and initial fragment energy, are stochastic or uncertain. Hence, they are represented by statistical distributions, whose parameters are determined as far as possible from experimental results or findings from past accidents. If no such evidence is available, reasonable assumptions, e.g. constant probability density function, are made. The Monte Carlo method is used to propagate the effect of the stochastic and uncertain input parameters through the calculation. Numerical results thus obtained are compared with evidence from accidents.

The lessons and non-lessons of the air and missile campaign in Kosovo

Abstract: The Lessons and Non-Lessons of the NATO Air and Missile Campaign in Kosovo The Historical Background: The Course and Character of the NATO Campaign The Grand Strategic Aspects of Kosovo: The "Whys" and "Hows" of the War and the Implications for Strategy and Force Planning The Strategic Impact and Military Effectiveness of the Air and Missile Campaign The Problems of "Perfect" and "Bloodless" War NATO Reporting on the Effectiveness of the Air and Missile Campaign Strategic Bombing The Air and Missile War and Serbian Air and Land Force Targets The "Ground Option": The Possible Impact of NATO Planning for an Invasion The "Ground Option": The Role of the KLA Detailed Lessons and Issues of the Air and Missile Campaign Beyond Air and Missile Power: The Ground Phase of Kosovo, Nation-Building, and Continuing Instability in the Balkans

Geometric analysis of flight control command for tactical missile guidance

Abstract: In this paper, unlike other developments in missile guidance which rely on solving a system of coupled nonlinear differential equations, an innovative approach is presented for studying tactical missile guidance. The moving orthogonal coordinate system of classical geometric curve theory is similar to the stability axis system used in atmospheric flight mechanics. Based on this similarity, the Frenet-Serret formula of classical geometric curve theory together with the concept of a pseudo-missile pointing velocity vector are used to analyze and design a missile guidance law. The capture capability of this guidance law is qualitatively studied by comparing the rotations of the velocity vectors of missile and target relative to the line of sight vector. Sufficient initial conditions for capture are found by following sequences of engagement geometry with different initial conditions.

Autopilot Design for a Missile with Reaction-Jet Using Coefficient Diagram Method

Abstract: Advanced guidance missiles employ blended control of aero-fin and reaction-jet to improve the guidance performance against highly maneuverable targets. The blended control requires multiple inputs and multiple outputs (MIMO) control system design, the design process is much complex than that of conventional aero-fin autopilot. This paper describes a autopilot design for a missile with aero-fin and reaction-jet using the Coefficient Diagram Method (CDM). Performance and stability trade-off study using the CDM is summarized. It is shown that MIMO autopilot design problem can be decomposed into feedback and feedforward controller design problems. A reasonable form of the controller is suggested using the coefficient diagram. A feedback controller is designed using the algebraical approach. The form of the controller has the same form as the conventional design. A wash-out type feedforward controller achieving the minimum fuel consumption is designed using the same manner. It is shown that the feedforward controller can be designed independently of the feedback controller. Improved response and robustness against the reaction-jet force saturation of the designed control system is proven by the simulation.

Nonlinear, Hybrid Bank-to-Turn/Skid-to-Turn Missile Autopilot Design

Abstract: Nomenclature A full-envelope, hybrid bank-to-turn (BTT)/ skid-to-turn (STT) autopilot design for an air-breathing air-to-air missile is carried out using the state-dependent Riccati equation (SDRE) technique of nonlinear control. Hybrid BTT/STT autopilot command logic is used to convert the guidance law's commanded acceleration to angle of attack, side-slip, and bank angle reference commands for the autopilot. In the midcourse and terminal phases of flight, BTT control is employed to prevent engine flameout. In the endgame, STT control is employed to increase response time. As the missile approaches the endgame phase and passes a preset time-to-go threshold, STT commands are ramped into the BTT commands over a preselected time interval to attenuate transient responses. During this interval, the missile is flying hybrid BTT/STT. An SDRE nonlinear outer-loop controller converts the angle-of-attack, sideslip, and bank angle commands to body rates commands for the inner loop. An inner-loop SDRE nonlinear controller converts the body rate commands to fin commands. Hard bounds on the fin deflections are embedded within the inner-loop controller dynamics ensuring that the autopilot only commands deflections that are achievable. The nonlinear design is evaluated using a detailed six-degrees-of-freedom simulation.

Three-Axes Missile Autopilot Design: From Linear to Nonlinear Control Strategies

Abstract: A three-axes skid-to-turn missile autopilot design is presented. The modeling is that of a missile developed by AerospatialeMatraMissiles.Variouscontrollawshavebeencomparedinordertoestimatetheirpotentialandtheir applicability: classical linear time-invariant control and static and dynamic approximate input-output linearizing feedbacks. The robustness is studied, and the best results, in terms of stability, performance, and robustness, are shown to be obtained by using a special type of nonlinear dynamic control. The simulation results are explained using a table of comparison.

Probabilistic map building for aircraft-tracking radars

Abstract: We develop a formalism to assess the risk of missions that consist of flying an aircraft over a region infested by enemy radars and co-located surface-to-air missile launchers. This is accomplished by building several probabilistic maps that will allow one to compute the probability of success for the missions.

New parametric affine modeling and control for skid-to-turn missiles

Abstract: This paper presents a new practical autopilot design approach to acceleration control for tail-controlled skid-to-turn (STT) missiles. The approach is novel in that the proposed parametric affine missile model adopts acceleration as the controlled output and considers the couplings between the forces as well as the moments and control fin deflections. The aerodynamic coefficients in the proposed model are expressed in a closed form with parameters that can be fitted over the whole operating range. The parameters are fitted from aerodynamic coefficient lookup tables by the proposed function approximation technique, which is based on the combination of local parametric models through curve fitting using the corresponding influence functions. In addition, a feedback linearizing controller is designed by using the proposed parametric affine missile model. Stability analysis for the overall closed-loop system is provided, considering the uncertainties arising from approximation errors. The validity of the proposed modeling and control approach is demonstrated through simulations for an STT missile.

Nonlinear autopilot for high maneuverability of bank-to-turn missiles

Abstract: This paper presents a novel approach to autopilot design for highly maneuvering bank-to-turn (BTT) missiles. In the design and performance analysis of the proposed nonlinear autopilot, all nonlinearities of missile dynamics including the coupling between roll, yaw, and pitch channels as well as the asymmetric structure of missile body are taken into full account. It is shown that through a kind of feedback linearization technique along with a singular perturbation-like technique, the input/output (I/O) dynamic characteristics of pitch, yaw, and roll channels are made linear, decoupled, and independent of flight conditions such as air density and missile velocity. In particular, the proposed autopilot controllers can provide excellent set-point tracking performance for roll and pitch channels while keeping the side-slip angle negligible. The generality and practicality of our approach are demonstrated through mathematical analysis and various simulation results using an ILAAT missile.

Directional control of missiles

Abstract: Missile (10) includes one or more of barrel assemblies (11) which are displaced from the centre of gravity of missile (10). Each barrel assembly (11) includes a plurality of projectiles axially disposed within the barrel, and each projectiles is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies (11) is capable of selectively firing the projectiles from selected barrels whereby missile (10) is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected onto a new course or trajectory. This enables missile (10) to be steered to intercept its target even if the target is undertaking evasive manoeuvre. Each barrel assembly (11) can include up to twelve projectiles.

Mobile ballistic missile detection and defense system

Abstract: The present invention is directed towards a mobile ballistic missile detection and defense system. The system of the present invention comprises a ship based antiballistic missile (“ABM”), a missile launch detection system, a missile tracking system, and a ship based signal processing system capable of receiving said tracking signal, calculating an intercept trajectory for an antiballistic missile to intercept a missile, and further capable of outputting an intercept trajectory program to an antiballistic missile. The ABM system of the present invention is capable of deployment in the vicinity of rogue nations which may pose a ballistic missile threat to the United States.

Critical Design Issues for Airbreathing Hypersonic Waverider Missiles

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.

Using a Multiple-Model Adaptive Estimator in a Random Evasion Missile/Aircraft Encounter

Abstract: The terminal phase (end game)of an encounter between an air-to-air missileequipped with an activemonopulse radar seeker and an evading e ghter aircraft, possibly employing electronic countermeasures in the form of electronic jinking, is addressed. The missile uses a guidance law derived from linear differential game theory, which is implemented by using a multiple-model adaptiveestimator (MMAE). TheMMAE identie es theevasion strategy of theaircraft, which consists of thecombination of evasion maneuverand electronic jinking. An extensivenumerical study is used to demonstrate the viability of the concept. In comparison with a previously proposed mixed strategy guidance methodology, the new MMAE-based approach leads to a substantial improvement in the guaranteed single-shot kill probability for the missile. ODERN air-to-air missiles, designed to intercept highly maneuverable aircraft equipped with electronic countermeasures (ECM), have to operate in a highly uncertain environment. This paper is concerned with the terminal phase (end game) of an encounter between a missile equipped with an active monopulse radar seeker and an evading e ghter aircraft having the option to use ECM. The terminal homing phase of the interception starts when the active seeker of the missile locks on its target, generating also a warning signal (including some threat identie cation ) in the aircraft. This warning is the only information the pilot has. At the moment when the warning is received, the pilot starts to execute a sequence ofperiodicalevasivemaneuvers.Simultaneously,toenhanceitssur

Robust Autopilot for a Quasi-Linear Parameter-Varying Missile Model

Abstract: A sideslip velocity autopilot is designed for a model of a tactical missile, and robust stability of the closed-loop system is investigated. The tail-controlled missile in the cruciform e n cone guration is modeled as a second-order quasi-linear parameter-varying system. This nonlinear model is obtained from the Taylor linearized model of the horizontal motion by including explicit dependence of the aerodynamic derivatives on a state (sideslip velocity ) and external parameters (longitudinal velocity and roll angle ). The autopilot design is based on input ‐output pseudolinearization, which is the restriction of input ‐output feedback linearization to the set of equilibria of the nonlinear model. The design makes Taylor linearization of the closed-loop system independent of the choice of equilibria. Thus, iftheoperating points are in thevicinity of the equilibria, then only onelinear model will describe closed-loop dynamics, regardless of the rate of change of the operating points. Simulations for constant lateral acceleration demands show good tracking with fast response time. Parametric and H1 stability margins for uncertainty in the controller parameters and aerodynamic derivatives are analysed using Kharitonov’ s approach. The analysis shows that the design is fairly robust with respect to both kinds of uncertainty.

Radar device for object self-protection

Abstract: With a view to radar guiding of a busting shell (16) launcher (15) to defend an object (11) against an incoming missile (12), existing elements allow to provide for low cost and interference free operation radar guiding, thanks to the absence of interface between the object (11) and the shooting container (15), when a planar antenna (20) is arranged on the launcher (15) base (11), fixed to the object in order to have surveillance of space and target detection. Said antenna transmits information regarding the target assigned to a tracking radar (19) integrated into the launcher (15), in order to guide the launcher (15) immediately and consequently towards the approach of the missile (12) against which defense is to be provided.

Integral data acquisition capacity

Abstract: Provided is a modified configuration that permits operation of instrumentation onboard platforms that may experience severe environmental conditions. The instrumentation permits autonomous acquisition of performance data. Acquired data may be recorded for later playback as well as provided to the platform's operator in real time in multiple formats, such as warning lights, digital displays, video, or audio. An application would be for sensor systems used on an automobile to record performance data, providing a warning when routine maintenance is due or a catastrophic failure is imminent. A specific application uses a flight-certified missile launcher pod on an F/A-18 aircraft, as incorporated in the aircraft's wingtip and modified to hold instrumentation conforming, at least in part, to the launcher pod's internal dimensions. This arrangement enables autonomous onboard display and recording of data from the captive carry testing of an AIM-9X missile and follow-on designs that may be based on the AIM-9X.

Three‐dimensional nonlinear H∞ guidance law

Abstract: This paper proposes a novel three-dimensional missile guidance law design based on nonlinear H∞ control. The complete nonlinear kinematics of pursuit–evasion motion is considered in the three-dimensional spherical co-ordinates system; neither linearization nor small angle assumption is made here. The nonlinear H∞ guidance law is expressed in a simple form by solving the associated Hamilton–Jacobi partial differential inequality analytically. Unlike adaptive guidance laws, the implement of the proposed robust H∞ guidance law does not require the information of target acceleration, while ensuring acceptable interceptive performance for arbitrary target with finite acceleration. The resulting pursuit–evasion trajectories for both the H∞-guided missile and the worst-case target are determined in closed form, and the performance robustness against variations in target acceleration, in engagement condition, and in control loop gain, is verified by numerical simulations. Copyright © 2001 John Wiley & Sons, Ltd.

Physics of Direct Hit and Near Miss Warhead Technology

Abstract: This title discusses direct hit technology in conjunction with a class of warheads coined "near miss or direct hit warhead technology". These warheads utilize most of their entire volume and mass as damage mechanisms generating 10 to 30 times more mass deployed in the target's direction when compared to today's warheads. Most missiles and kill vehicles of today are direct hit only and do not contain a warhead mechanism. This new book discusses the challenges of designing small lethality enhancement technologies that can be implemented on a direct hit kill vehicle. What makes anti-ballistic missile warhead design so difficult is that a designer must be able to design a warhead against many different tactical ballistic missile payloads. These payloads can vary from chemical submunitions to unitary high explosive to nuclear. Warhead designers of tomorrow must have an understanding of the kill requirement and vulnerabilities of ballistic missile payloads before an optimum direct hit missile or warhead is designed.

System and method for disabling time critical targets

Abstract: The present invention is a method and system for disabling time critical and moving targets and an air deployed guided missile launcher. A system for disabling a time critical target at a site within a geographical area in accordance with the invention includes a plurality of spaced apart mostly buried missile launchers located within or adjacent to the geographical area with each spaced apart mostly buried mobile missile launcher containing a guided missile, any site within the geographical area being located at a distance from at least one spaced apart missile launcher not more than a maximum distance of travel of a guided missile launched from at least one of the spaced apart missile launchers to the site, the time of travel of a missile from the missile launcher to the site requiring less time than a maximum time required to enable the time critical target at the site.

Hit To Kill: The New Battle Over Shielding America From Missile Attack

Abstract: The definitive account of the biggest national security issue of our time: the precipitous and politically charged revival of national missile defense The new Bush administration has wasted no time in making national missile defense the centerpiece of its national security policy and is expected to move forward with testing and eventual deployment of a system to destroy incoming missiles in flight-even though the Russians, the Chinese, and our own European allies have expressed alarm at such action The system's defenders say that we must press forward if America is to be secure against nuclear, biological, and chemical threats in the decades to come There's only one problem: No one has ever shown that such a system would actually work In Hit to Kill, Bradley Graham, a longtime military and foreign affairs correspondent for The Washington Post, tells the behind-the-scenes story of how national missile defense-once considered a discredited relic of the Cold War-was revived during the 1990s to address an emerging Third World missile threat Graham recounts the political battles surrounding national missile defense during the Clinton administration and the technological trials and tribulations of the major defense firms involved in the project He reports on the experts who have mobilized in the last year to question the system's unworkability and examines the scientific evidence for and against it Over the past half century, no proposed weapons system has drawn more argument or more dollars than national missile defense, and Graham explores the reasons for the enduring debate and the costs to the nation of having failed to resolve it

Design of a Guided Missile Interceptor Using a Genetic Algorithm

Abstract: An apportioned pareto genetic algorithm was used to manipulate a solid rocket design code, an aerodynamic designcode,andathree-loopautopilottoproduceguidedmissileinterceptordesignscapableofaccuratelyengaging a high-speed/high-altitude target. Dee nition of the optimization problem required 29 design variables, and 4 primary goals were established to assess the performance of the interceptor designs. Design goals included the following: minimize miss distance, minimize intercept time, minimize takeoff weight, and minimize maximum g loading. In 50 generations, the genetic algorithm was able to develop 2 basic types of external aerodynamic designs that performed nearlythe same, with miss distances less than 1.0ft. The solid rocket motors that propelled these external shapes shared common characteristics such as a large initial burning area and a large combustion chambervolume. Thegeneticalgorithmdid not prefermaximizing theamount offuel within therocket motorcase (high fuel volume ratio). A higher fuel volume ratiotypicallymeans higher launch weight, but does not necessarily guarantee faster intercepts given enite thermal limits. Examination of the intercept trajectories themselves shows that standard proportional navigation guidance works adequately, but could probably be improved by thrust compensation,especiallyduringthelaunchtransient.Thethree-loopautopilotperformswellevenforhigh-altitude engagements, and the analytic gain determination makes the autopilot straightforward to implement.

Fin-stabilized guidable missile

Abstract: The present invention relates to a fin-stabilized missile (1) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins (3, 32) arranged at its rear end, and control elements (6, 7) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1). According to the invention, said bearing (14, 36) is arranged near the dividing plane between the missile (1) and the body part (4, 31) and has a short length in the longitudinal direction of the missile, this having been made possible by the fact that it has been given a large diameter compared with its length and it has been designed with special load-bearing contact surfaces (20, 21, 27, 28) which limit the stresses during ramming and firing and during the flight of the missile (1) through the air. The freely rotatable body part (4, 31) for the fins (32) can then in turn be axially displaced from a launch position located inside the missile to a flight position where the fins (32) are pushed out behind the rear plane of the missile, where they can rotate freely.

Precision conformal optics technology program

Abstract: Conformal optics are defined as optics that deviate from conventional form to best satisfy the contour and shape needs of system platforms. Precision Conformal Optics Technology (PCOT), a comprehensive 48 month program funded by the Defense Advanced Research Program Agency (DARPA) and the U. S. Army Missile Research, Development, and Engineering Center (MRDEC), assessed the potential benefits achieved by use of conformal optics on a variety of U.S. weapon systems. Also addressed were all barriers impeding conformal optics use. The PCOT program was executed by a consortium of organizations ranging from major U.S. defense prime contractors, to small businesses, and academia. The diversity of organizations encouraged synergy across a broad array of skills and perspectives. Smooth team interaction was made possible by the 845 contractual structure of the program. Benefits identified by the PCOT consortium included major reductions in aerodynamic drag (by as much as 50%), reduced time-to-targets (by as much as 60%), and reduced weapon signatures. Impediments addressed included inadequacies in optical design tools, optical manufacturing methods and equipment, optical testing, and system integration. The PCOT program was successfully completed with a demonstration of a highly contoured missile dome, which reduced overall missile drag by 25%, and led to a predicted twofold increase in missile range.