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Showing papers on "Missile published in 1993"


Book
01 Aug 1993
TL;DR: In this paper, the origins of accidents are discussed, and the limits of safety are discussed in the context of intelligence and warning during the Cuban Missile Crisis and the 1968 Thule Bomber Accident.
Abstract: List of Figures and TablesAcknowledgmentsList of AcronymsIntroduction: Expecting the Unexpected3Ch. 1The Origins of Accidents11Ch. 2Nuclear Weapons Safety during the Cuban Missile Crisis53Ch. 3Intelligence and Warning during the Cuban Missile Crisis117Ch. 4Redundancy and Reliability: The 1968 Thule Bomber Accident156Ch. 5Learning by Trial and Terror204Ch. 6The Limits of Safety250Index281

612 citations


Journal ArticleDOI
TL;DR: In this article, a quasi-LPV (quasilinear parameter varying) state transformation is used to bring a longitudinal autopilot to a quasilevel form via a state transformation.
Abstract: This paper presents a gain-scheduled design for a missile longitudinal autopilot. The gain-scheduled design is novel in that it does not involve linearizations about trim conditions of the missile dynamics. Rather, the missile dynamics are brought to a quasilinear parameter varying (LPV) form via a state transformation. An LPV system is defined as a linear system whose dynamics depend on an exogenous variable whose values are unknown a priori but can be measured upon system operation. In this case, the variable is the angle of attack. This is actually an endogenous variable, hence the expression "quasi-LPV." Once in a quasi-LPV form, a robust controller using H synthesis is designed to achieve angle-of-attack control via fin deflections. The final design is an inner/outerloop structure, with angle-of-attack control being the inner loop and normal acceleration control being the outer loop.

386 citations


Journal ArticleDOI
TL;DR: In this paper, a series of impact tests of small-, intermediate-, and full-scale engine models into reinforced concrete panels was conducted to determine the local damage to a reinforced concrete structure caused by the impact of a deformable aircraft engine.

101 citations


Patent
24 Feb 1993
TL;DR: In this paper, the authors present an active defense system against ballistic missiles. The system includes a fleet consisting of a plurality of flying platforms fitted with interceptor missiles which loiter over hostile territory.
Abstract: An active defense system against ballistic missiles. The system includes a fleet consisting of a plurality of flying platforms fitted with interceptor missiles which loiter over hostile territory. The flying platforms communicate with each other by suitable data links and at least some of them also communicate with a ground station located in friendly territory. The interceptor missiles have electro-optical seeking and tracking capabilities and the data which the missile generates while in captive flight are communicated to a processor of the associated flight platform for autonomous decision whether to launch or not to launch the missile.

65 citations



Patent
27 Aug 1993
TL;DR: In this paper, a weak Hamiltonian finite element method is used for iterative computation of missile guidance acceleration commands for maximizing a missile's terminal velocity while satisfying control authority limits and terminal attitude constraints.
Abstract: A weak Hamiltonian finite element method is used for iterative computation of missile guidance acceleration commands for maximizing a missile's terminal velocity while satisfying control authority limits and terminal attitude constraints. The guidance acceleration commands include commands for controlling the angle of attack (α) and the bank angle (φ) of the missile. The angle of attack (α) and bank angle (φ) are related to a set of virtual control variables selected to avoid convergence problems when the angle of attack is approximately zero. The preferred control variables are β 2 and β 3 such that β 2 =cosφtanα and β 3 =sinφtanα. Iterative convergence is facilitated when control inequality constraint parameters are reached by adjusting iterative solutions between iterations toward satisfaction of the constraints. An approximation to an optimal trajectory is calculated at each guidance cycle during missile flight using data which are revised during each guidance cycle. The revised data include current position data for the target and the current position for the missile. The revised data are taken from the most reliable source currently available, such as on-board target-seeking radar when the target-seeking radar is locked onto the target, uplink data from ground or airborne tracking radar when an uplink is operational, or inertial guidance data. Extracted from the optimal trajectory is an optimal acceleration command for optimally controlling the angle of attack and bank angle of the missile.

47 citations


Journal ArticleDOI
TL;DR: In this article, a three-dimensional pursuit-evasion game between a realistic missile and an aircraft is studied employing point-mass models for both vehicles, and the important role of information in the opponent's acceleration to the game and the effectiveness of the strategy in rotating the line-of-sight vector are shown.
Abstract: A three-dimensio nal pursuit-evasion game between a realistic missile and an aircraft is studied employing point-mass models for both vehicles. Since a direct method to solve this complicated mini-max problem is too time-consuming, the study is conducted by carrying out massive simulations in the parameter space of initial conditions and guidance law parameters. The important role of information in the opponent's acceleration to the game and the effectiveness of the strategy in rotating the line-of-sight vector are shown. It is found that there exist very few cases where the aircraft can avoid the missile, among them typical air-combat maneuvers such as linear acceleration, high-£ barrel roll, split-S, and horizontal-S. Nomenclature flcmax = missile lateral acceleration command limit Ompjdmy = missile acceleration components measured in aircraft pitch and yaw axis, respectively ^p^y^pc^yc = missile-pitch and yaw-axis lateral accelerations and their command signals OpttOyt = aircraft-desir ed pitch and yaw acceleration components, respectively Otp9oty = aircraft acceleration components measured in missile pitch and yaw axis, respectively CD = drag coefficient CDO

44 citations


Journal ArticleDOI
TL;DR: In this article, the influence of a priori uncertainties in launch time and trajectory fly-out profiles, along with sensor angle measurement errors, on the estimation of missile launch location and heading angle is explored.
Abstract: The author explores the influence of a priori uncertainties in launch time and trajectory fly-out profiles, along with sensor angle measurement errors, on the estimation of missile launch location and heading angle. An error model is developed to compute the statistics of the estimation errors using a single pair of angle measurements, one from each of two satellites, or both from the same satellite platform. The measurements and estimation methods are described, followed by a derivation of the estimation errors for the hypothetical case of perfect knowledge of trajectory and launch time. Using the ideal case as a framework, the errors are generalized to include trajectory and launch time uncertainties. The results are discussed with the aid of graphics which were run parametrically to highlight important dependencies and sensitivities. >

41 citations


Patent
24 Aug 1993
TL;DR: In this article, a high-pressure water system which can be generated by a water jet or a body of water explosively created from a water surface is used to change the density of the water medium.
Abstract: A missile defense system generates a change in density in the air path of a missile. The density change is created by a high-pressure water system which can be generated by a water jet or a body of water explosively created from a water surface. When operating against a waterborne missile, the density of the water medium is changed. The change in density creates an effective barrier against an incoming missile.

40 citations


Patent
20 Aug 1993
TL;DR: An electro-mechanical detection system for measuring the point of impact of a missile such as a sports projectile on a target and measuring the velocity and force of impact is described in this paper.
Abstract: An electro-mechanical detection system for measuring the point of impact of a missile such as a sports projectile on a target and for measuring the velocity and force of impact. The detection system is contained in a large plastic envelope, on which a target is displayed and in one embodiment, the detector is a wire or plastic grid that is instrumented to measure changes in stress in the individual grid elements that occur when the missile impacts the target. In another form of this invention, the detector is embedded in an elastomeric mat contained within the plastic envelope with electrical conductors within the mat subject to movement in a magnetic field when the mat compresses in response to the impact of a missile on the target. In either form of the invention, suitable electronic circuitry is used to convert the signals generated at impact to a display.

38 citations



Patent
19 Oct 1993
TL;DR: In this paper, an actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies.
Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Proceedings ArticleDOI
28 Jun 1993

Patent
15 Oct 1993
TL;DR: In this paper, a fast and reliable switch for multi-channel, bi-directional fiber optics data link (FODL) systems is proposed, which can be used in multiple fiber optics guided missile launch systems and fiber optics based surveillance systems with multiple outposts.
Abstract: A fast and reliable switch (50) for multi-channel, bi-directional fiber optics data link (FODL) systems. The FODL channel switching is accomplished through a software command on the subcarrier frequency (SCF) code without using any moving components or wavelength sensitive optical devices. A fiber star coupler (92) and in-line erbium doped fiber amplifiers (94A-94Q) transform the FODL system into an electrically switchable, fiber star network with low optical power loss penalty. The switch can be used in multiple fiber optics guided missile launch systems and fiber optics based surveillance systems with multiple outposts. The switching scheme allows the launcher/controller (60) to perform a time-sharing control on multiple missiles (or outposts) (80-80P) by switching the SCF code sent to the programmable SCF generator of the OE unit in the controller (launcher). The scheme can also easily be extended to operate in a multiple control station mode that uses multiple control station at the launcher/controller (60) to control multiple missiles or outposts (80A-80P).

Proceedings ArticleDOI
11 Jan 1993
TL;DR: In this article, a low-speed wind-tunnel investigation was conducted to examine the aerodynamic characteristics of a one-thirdscale model of a canard-controlled missile at high angles of attack using force and moment measurements.
Abstract: A low-speed wind-tunnel investigation was conducted to examine the aerodynamic characteristics of a one-thirdscale model of a canard-controlled missile at high angles of attack using force and moment measurements. The data were taken at a nominal Mach number of 0.2 for angles of attack up to 50 deg at three different canard deflection settings. The test runs were limited to 0and 45-deg missile roll angles (symmetric configurations) and two sets of tails (aft fins), one with the full area including the roll damping tabs (rollerons) and the other without the rollerons. The data indicate that the rollerons act as an effective fin area at low speeds and high angles of attack, and make the missile more stable. The test data were also used to validate the aerodynamic characteristics of the missile as predicted by the Missile Datcom program. The agreement between the Datcom predictions and the test data is fairly good, with the latter indicating a slightly higher static stability.

Patent
12 Apr 1993
TL;DR: In this paper, a beam rider system and method that utilizes polarization-agile millimeter beams is presented, where information is spatially encoded in the beams by varying the rate of rotation of the linearly polarized vector of the beams.
Abstract: This invention is a beam rider system and method that utilizes polarization-agile millimeter beams. Information is spatially encoded in the beams by varying the rate of rotation of the linearly polarized vector of the beams. In one embodiment, information is encoded on a beam that is nutated around a centerline flight path of a missile. In another embodiment, information is encoded on four parallel beams that form a centerline which is the intended flight path of the missile. Receiver means in the flying missile receive and decode information from the beams and use this decoded information to guide the missile to a target.

Proceedings ArticleDOI
25 May 1993
TL;DR: In this article, a sliding mode control is applied to design autopilot for HAVE DASH II bank-to-turn (BTT) missile systems, which is evaluated using six degree of freedom simulation and shows a significant improvement over the feedback linearization approach.
Abstract: Sliding mode control is applied to design autopilot for HAVE DASH II bank-to-turn-(BTT) missile systems. The design is evaluated using six degree of freedom simulation and shows a significant improvement over the feedback linearization approach.

Patent
15 Jan 1993
TL;DR: In this paper, a convoluted fan structure is provided along the bottom surface of each diagonal segment of a petal-formed aft cover for a missile canister to prevent recirculation of rocket exhaust gases from the plenum into the canister through the formerly open corner areas and augment the closure force to restore the petals to the closed position after completion of a missile launch.
Abstract: A convoluted fan structure is provided along the bottom surface of each diagonal segment of a petal-formed aft cover for a missile canister. As the cover petals open under influence of rocket exhaust impingement on the cover, the fan structures cover the diagonal areas toward the corners of the opening. This prevents recirculation of rocket exhaust gases from the plenum into the canister through the formerly open corner areas and augment the closure force to restore the petals to the closed position after completion of missile launch.

Proceedings ArticleDOI
25 May 1993
TL;DR: In this article, a rapid and robust transfer alignment system for advanced kinetic energy missiles (ADKEMs) is presented, which aligns the salve (missile) inertial measurement unit (IMU) with the master (ground launch vehicle) IMU with high accuracy.
Abstract: The design of a rapid and robust transfer alignment system for advanced kinetic energy missiles (ADKEMs) is presented in this paper. Owing to the high acceleration level and reduced engagement time of the ADKEM, the transfer alignment which aligns the salve (missile) inertial measurement unit (IMU) with the master (ground launch vehicle) IMU must be accomplished in a short time with high accuracy. The scope of transfer alignment system design presented in this paper encompasses the assessment of inertial guidance accuracy, transfer alignment formulation, maneuver scenario design, and sensitivity analysis.

Journal ArticleDOI
W.J. Kerins1
TL;DR: In this article, the effectiveness of off-board RF ECM is analyzed, and specific observations are made about the effectiveness when used to defend friendly aircraft when using such ECM when deployed in RF missile systems.
Abstract: Recent advances in RF missile systems have reduced the effectiveness of conventional on-board electronic countermeasures (ECM) to defend friendly aircraft. To provide the much needed defense, off-board ECM techniques are being developed. The effectiveness of off-board RF ECM is analyzed, and specific observations are made about the effectiveness of such ECM when used to defend friendly aircraft. >

Proceedings ArticleDOI
02 Jun 1993
TL;DR: Sliding mode control is applied to design autopilot for bank-to-turn (BTT) missile systems and shows a significant improvement over the feedback linearization approach.
Abstract: Sliding mode control is applied to design autopilot for bank-to-turn (BTT) missile systems. The design is compared with the feedback linearization approach and shows a significant improvement over the latter.

Journal ArticleDOI
TL;DR: In this article, a generalized guidance law for collision courses is presented, which gives theoretical lateral acceleration commands to guide the missile on a collision course, but it is difficult to realize the true guidance law on most existing tactical missiles.
Abstract: A new generalized guidance law for collision courses is presented. When the missile and target axial accelerations or decelerations are constant, there exists a rectilinear collision course. The guidance law presented, which is called the true guidance law, gives theoretical lateral acceleration commands to guide the missile on a collision course. However, since it is very difficult to realize the true guidance law on most existing tactical missiles, this paper shows a method for simply implementing the guidance law, which is called the simplified guidance law. The small perturbation equation of the true guidance law shows that the definition of an effective navigation constant is the same expression as that in the case of conventional proportional navigation. The performance of the two guidance laws presented is compared with that of proportional navigation using simulation studies of a simple model of a short range air-to-air missile. The simulation results show that the guidance laws presented can intercept the target using far smaller lateral acceleration commands than prepared for proportional navigation. The inner launch envelope shows that the guidance laws presented provide an overall performance improvement over proportional navigation.

Proceedings ArticleDOI
25 May 1993
TL;DR: In this paper, a transfer alignment filter design for the first phase of flight of the advanced kinetic energy missile (ADKEM) is presented, where the estimation of the initial misalignment with transfer alignment technique has to act against various error sources involved in the velocity and/or attitude differences.
Abstract: The first phase of flight of the advanced kinetic energy missile (ADKEM) is inertial guidance whose performance is affected particularly by the navigation accuracy. Owing to the rapid acceleration during the missile launch phase, the effect of misalignment is magnified, significantly contributing to the miss distance. A high precision transfer alignment is thus required to reduce the initial navigation error. The estimation of the initial misalignment with transfer alignment technique has to act against various error sources involved in the velocity and/or attitude differences. On the other hand, due to limitations in complexity and computation, only linear models of first order approximation are used in transfer alignment filter design. Therefore, it is indispensable to evaluate a transfer alignment filter design not only with a linear model-based covariance analysis but also with a nonlinear Monte Carlo simulation. This paper presents in detail such a transfer alignment design and evaluation environment.


ReportDOI
01 Jun 1993
TL;DR: The Missile Datcom as mentioned in this paper is an aerodynamic design tool for preliminary design of a wide variety of missile configuration designs with the capability for the user to easily substitute methods to fit specific applications.
Abstract: : In missile preliminary design it is necessary to quickly and economically estimate the aerodynamics of a wide variety of missile configuration designs. Since the ultimate shape and aerodynamic performance are so dependent upon the subsystems utilized, such as payload size, propulsion system selection and launch mechanism, the designer must be capable of predicting a wide variety of configurations accurately. The fundamental purpose of Missile Datcom is to provide an aerodynamic design tool which has the predictive accuracy suitable for preliminary design, and the capability for the user to easily substitute methods to fit specific applications.

Patent
16 Feb 1993
TL;DR: In this article, an automatic telescoping launch tube (22, 24) and a rest raining system (40, 42) for launching a ballistic missile (20) is described.
Abstract: A missile launching system (18) for launching a missile (20) includes an automatically telescoping launch tube (22, 24) and a rest raining system (40, 42). The telescoping launch tube (22, 24) lengthens the period of guided travel of the missile (20) during launch, to improve its accuracy. The launch tube system has an outer case (24), and an inner launch tube (22) internally dimensioned to receive the missile (20) therein and externally dimensioned to slide within the outer case (24) from a rearward position to a forward position. The restraining system (40, 42) holds the missile (20) and inner launch tube (22) at the proper locations before and during firing, and includes a releasable holdback (40) for the inner launch tube (22) at the rearward position and a releasable holdback for the missile (20) at a preselected position within the inner launch tube (22). The inner launch tube (22) is restrained so that it may not slide past the forward position relative to the outer case (24) at the end of its travel during the launching sequence.

Journal ArticleDOI
01 Jan 1993
TL;DR: In this article, it was shown that at high angles of attack the body leeside flow may become unpredictably asymmetric, even on geometrically symmetric configurations, and their interactions with wing and tail panels can result in possible control problems.
Abstract: A major influence in the aerodynamics of missiles is the significant amount of separated flow encountered for most flight conditions. This flow may be of an ordered nature, forming vortices, or random, such as encountered in wing stall. At high angles of attack the vortices of the body leeside flow may become unpredictably asymmetric, even on geometrically symmetric configurations, and their interactions with wing and tail panels can result in possible control problems. The modelling of such flows both accurately and easily is beyond present capabilities.


Patent
22 Mar 1993
TL;DR: In this paper, a jettisonable adaptor for air-carried missiles is located between an aircraft-mounted launcher and a missile, which can include flight stabilization and retardation functions which are deployable on separation from the launcher.
Abstract: A jettisonable adaptor for air-carried missiles is located between an aircraft-mounted launcher and a missile. The adaptor may include flight stabilization and retardation functions which are deployable on separation from the launcher. Instead of mounting fixing hooks on the missile (which would incur aerodynamic-drag) these are mounted on the adaptor instead. When stabilization has occurred the adaptor is separated from the missile.

Journal ArticleDOI
M.R. Baum1
TL;DR: In this paper, a model was developed to predict the velocity of a single small missile ejected from a vessel containing high pressure gas is driven by the underexpanded gas jet issuing from the breach.
Abstract: A single small missile ejected from a vessel containing high pressure gas is driven by the under-expanded gas jet issuing from the breach. A model is developed to predict the velocity of such a missile and the results are compared with data obtained in a parallel experimental investigation. Using the predicted dependence of missile velocity on the jet source pressure as a basis for correlating the experimental data, upper limit velocities for jet driven missiles are defined.