Showing papers on "Missile published in 1990"

Tactical and strategic missile guidance

Abstract: Numerical Techniques Fundamentals of Tactical Missile Guidance Method of Adjoints and the Homing Loop Noise Analysis Convariance Analysis and the Homing Loop Proportional Navigation and Miss Distance Digital Fading Memory Noise Filters in the Homing Loop Advanced Guidance Laws Kalman Filters and the Homing Loop Other Forms of Tactical Guidance Tactical Zones Strategic Considerations Boosters Lambert Guidance Strategic Intercepts Miscellaneous Topics Ballistic Target Properties Extended Kalman Filtering and Ballistic Coefficient Estimation Ballistic Target Challenges Multiple Targets Weaving Targets Representing Missile Airframe with Transfer Functions Introduction to Flight Control Design Three-Loop Autopilot. Appendices: Tactical and Strategic Missile Guidance Software Converting Programmes to C Converting Programmes to MATLAB Units.

Inventing Accuracy: A Historical Sociology of Nuclear Missile Guidance

Abstract: Winner of the 1993 Ludwik Fleck Prize presented by the Society for Social Studies of Science (4S).Among books on the arms race, Donald MacKenzie's stands out for its welcome demystification of the "black box" of nuclear weapons technology. MacKenzie follows one line of technology - strategic ballistic missile guidance - through a succession of weapons systems to reveal the ordinary workings of a world that is neither awesome nor unstoppable. He uncovers the parameters, the pressures, and the politics that make up the complex social construction of an equally complex technology.MacKenzie argues that it is wrong to assume that missile accuracy (or any other technological artifact) is a natural or inevitable consequence of technological change. By fostering an understanding of how the idea of accuracy was constructed and by uncovering the comprehensible and often mundane processes that have given rise to a frightening nuclear arsenal, he shows that there can be useful and informed intervention in the social processes of weapons construction. He also shows in what sense it is possible, contrary to the common wisdom, to "uninvent" technologies.Examining the technological politics of the transition from bomber to ballistic missile, MacKenzie describes the processes that transformed both air force and navy ballistic missiles from moderately accurate countercity weapons to highly accurate counterforce ones. He concludes that neither the United States nor the Soviet Union has ever accepted the idea of deterrence as the public understands it."Inventing Accuracy" is based on 140 interviews with guidance and navigation technologists, navy and air force military officers, and defense officials Robert McNamara, James Schlesinger, McGeorge Bundy, and John Foster. It brings to light the confluence of forces, both physical and social, that gave rise to a selfcontained system of missile navigation, and it discusses the major U.S. groups involved in the early development of inertial guidance and navigation.Donald MacKenzie has published a number of influential articles on statistics, eugenics, and missile technologies. He is Reader in Sociology at the University of Edinburgh.

Cardiac missiles. A review of the literature and personal experience.

Abstract: The management of retained missiles in the heart is still controversial. In an attempt to define the issue more clearly, the reported cases in the English literature from 1940 to 1988 (group 1) and our experience from 1968 to 1988 (group 2) were reviewed. In group 1 there were 222 missiles retained in the hearts of 201 patients. The retained missiles were 45 bullets in 45 patients, 109 shrapnel in 99 patients, 18 pellets in 7 patients, and 50 unidentified missiles in 50 patients. Thirteen of the missiles were completely embedded intramyocardial missiles, 122 were partially intramyocardial, 47 were free in a cardiac chamber, and 40 were intrapericardial. One hundred four of the missiles were removed and 118 were left in place. In group 2 there were 24 missiles, 18 bullets, 1 bullet fragment, and 5 pellets retained in the hearts of 24 patients. Ten missiles were removed, no attempt was made in 13 patients, and an unsuccessful attempt was made to remove one other. From group 1 patients, 6 died, 2 with intracavitary missiles, 3 patients with partially intramyocardial, and 1 patient with an intrapericardial missile, all of whom had either unsuccessful or no attempt to remove the missile. Twenty-seven patients had symptoms, all of whom, except two, had either unsuccessful or no attempt to remove the missile. All group 2 patients did well and had been free of symptoms related to the missiles. This review suggests that the management of missiles in the heart should be individualized according to the patient's clinical course, the site, shape, and size of the missile, and that in selected patients missiles in the heart are tolerated well.

The alignment of ship launched missile IN systems

Abstract: The author outlines the requirements for on-board inertial navigation systems in the next generation of tactical missiles. The significance of alignment accuracy in the performance of such missile systems is discussed, drawing attention to the physical processes which introduce alignment error in a ship launched missile. Two different techniques which may be used to alleviate the problems of alignment inaccuracy are discussed. The first method involves the use of shipboard inertial measurements to carry out an alignment prior to launch. Such methods are strongly dependent on ship motion. The second method involves tracking the missile with the ship's radar and the use of the radar measurements to aid the missile navigation system during flight. The author outlines the integration of the different measurements, the algorithms needed to implement each scheme and concludes with a comparison of the relative merits of shipboard and in-flight alignment.

Optimal guidance for acceleration constrained missile and maneuvering target

Abstract: Explicit formulas of optimal guidance laws for an acceleration-constrained, arbitrary-order missile and maneuvering target are derived. These formulas are given in terms of the transfer function and acceleration constraint of the missile and the transfer function/shaping filter of the target. Optimal full-state feedback guidance law is synthesized against a target performing a barrel roll maneuver, and compared with the performance of proportional navigation (PN) for minimum and nonminimum phase missile. Simulation of a third-order missile shows the relative gain from using the full-order guidance law. >

Multi-mode missile seeker system

Abstract: A broad band multimode seeker system for a missile includes a wide band phased array transmitter/receiver unit incorporating a wafer scale phased array device with a bandwidth of about 2 GHz to 35 GHz. A multimode intermediate frequency unit selectively generates radar and jamming waveforms and measures parameters of reflected radar and external emissions of RF energy. A guidance processor manages the front end assets for selective active or semiactive radar searching and tracking, and simultaneous searching for, tracking of, homing on, and applying a selection of electronic countermeasures to, multiple defensive radars. Confirmation of an assigned target is made through correlation of received RF signals with libraries of expected defensive system parameters and high resolution target profiles and preloaded target geographical coordinates.

Robust autopilot design using μ-synthesis

Abstract: This paper examines the applicability of H∞ and μ-synthesis control to the design of automatic flight control systems for highly maneuverable, tail-controlled missiles. The impact on performance, of the degree of conservatism inherent to each approach, is examined. It is shown that μ-synthesis provides a superior framework for the design of missile autopilots which exhibit robust performance.

Gamma-ray measurements of a soviet cruise-missile warhead.

Abstract: A portable germanium detector was used to detect gamma-ray emissions from a nuclear warhead aboard the Soviet cruiser Slava. Measurements taken on the missile launch tube indicated the presence of uranium-235 and plutonium-239-the essential ingredients of nuclear weapons. With the use of this equipment, these isotopes probably could have been identified at a distance of 4 meters from the warhead. Such inspections do not reveal detailed information about the design of the warhead.

Game using radio-controlled vehicles

Abstract: The invention relates to a game using remotely-controlled miniature vehicles. One player drives an invading vehicle which shoots a ping-pong ball at a target which is defended by a second player. The defender fires balls at the vehicle and, if he strikes the vehicle, the vehicle incurs a penalty of temporary disablement. In addition, the vehicle can be required to periodically tag bases which the defender strews on the playing field; failing to do inflicts a penalty. Further, the invader can fire two types of missiles, and the defender must protect two goals. Firing the first missile can act as a feint by which the defender is distracted from defending one of the goals.

Imaging target sight

Abstract: An optical missile sight that provides a gunner with the ability to view along a missile line of sight in order to sight a potential target prior to missile launch. The sight comprises an imaging telescope, an optical coupling arrangement that comprises (1) a flexible fiber optic bundle disposed in obedient sheathing, or (2) a reflective optics arrangement and a fiber optic bundle, and an objective lens employed for viewing. In the case of the flexible fiber optic bundle, the telescope is disposed along the centerline of the missile, and the optical components of the optical coupling arrangement are disposed in a flexible housing that extends from inside the missile to the outside of the launch tube. In one embodiment the fiber optic bundle is sheared during launch, while in another embodiment, the fiber bundle is separated at the missile/launch tube interface prior to launch. In the case of the reflective optics arrangement, the optical components of the telescope are disposed inside the missile and the optical coupling arrangement components are disposed both inside and outside of the missile, and a fiber optics bundle is employed to transmit the image scene to the gunner outside the launch tube.

Apparatus and method for multiple target engagement

Abstract: Apparatus (10) for simultaneously engaging a multiplicity of selected targets (V1-V7) to launch one or more missiles (T) at each target and acquire, track, and guide each missile to its respective target. A field of view (FOV) is scanned to detect one or more targets therewithin. A target selection system (34) is used to designate various of the targets at which to launch missiles. A plurality of missiles are then launched, and directed to each selected target. A plurality of sensors (58) detect radiation from each missile as it travels toward its respective target. An acquisition and tracking system (74) is used to track each missile and its target. The system includes a processor (80) for determining the position of each missile relative to its respective target, and a control module (82) responsive to the processor for generating and transmitting guidance signals to each missile to guide it to its target.

GPS/INS integration on the Standoff Land Attack Missile (SLAM)

Abstract: The Standoff Land Attack Missile (SLAM) is a worldwide, all-weather, precision-strike weapon system deployed from carrier-based aircraft. In the primary mode of operation, target location and other mission data are generated from intelligence sources available on the aircraft carrier and loaded into the missile prior to aircraft takeoff. After missile launch, the SLAM inertial navigation system (INS) guides the missile along the planned trajectory. Updating the missile INS from the Global Positioning System (GPS) during flight provides precise midcourse navigation and enhances target acquisition by accurate, on-target pointing of the SLAM Maverick seeker. The GPS/INS avionics and software integration used for SLAM are described in detail, along with some of the design tradeoffs that led to the approach. The avionics configuration integrates the Harpoon midcourse guidance unit, which includes a strapdown inertial sensor package and digital processor, with a Rockwell-Collins single-channel, sequential GPS receiver processor unit (RPU), a derivative of the GPS phase-III user equipment. In addition to the GPS receiver elements the RPU contains the navigation processor, which executes the SLAM navigation, Kalman filter algorithms, and other guidance algorithms including seeker pointing. Flight-test results of the SLAM GPS-aided INS are also included. >

Third World Ballistic missiles

Abstract: Ballistic missiles and other means of long-range destruction, traditionally limited to a handful of industrialized nations, are fast becoming a fixture in many regional conflicts. The Third World military buildup is perhaps even more worrisome than its First World prototype, for it is far more likely to find expression in war. There are several reasons why this should be so. In the past decade the number of countries in the missile club has more than doubled, to 18. Many of the new members have been at war or are embroiled in disputes. Unlike the major powers, these countries have not had time enough to perfect systems of command and control over their new strategic forces. They have had little time to learn to manage the complexities of military brinksmanship. Finally, because many regional conflicts overlap, an escalation in the arms race tends to convey itself from one area of tension to another. For many years the big industrialized countries ignored the proliferation of ballistic missiles and sought political advantage by arming their clients. In doing so, they presumed that the bipolar alignment of power would restrain regional conflicts. The preoccupation with East-West issues overshadowed problems in the Third World. Smallermore » industrialized powers sold missiles to generate revenues to support their own military industries. Meanwhile the developing countries eagerly acquired missiles for the same reasons that had motivated their predecessors: to deter attack, intimidate enemies, build a technological base and win prestige.« less

Applying mu -synthesis to missile autopilot design

Abstract: mu -synthesis combines the structured singular value and H/sub infinity / control to design compensators for plants with structured uncertainty. The application of mu -synthesis to the design of a flight control system for a highly maneuverable tail controlled missile is discussed. Performance goals are given in the time and frequency domains and include time constant, overshoot, stability margins, and high-frequency attenuation. The resulting control law desensitizes the system's performance to structured variations in the missile's aerodynamic properties and provides some robustness, in both a single-loop and a multiloop sense, to variations and/or perturbations not included in the uncertainty model. >

Missile tracking, guidance and control apparatus

Abstract: Apparatus (10) for acquiring and tracking a missile (M), and guiding it to a target (T). Beacons (18, 19) are carried on the missile to provide an indication of its location in a field of view. One beacon (18) is a xenon beacon which emits energy in a short wave-length portion of the light spectrum. The other beacon (19) is a thermal source which emits infrared radiation in a longer wave-length portion of the spectrum. A sight unit (20) includes both a xenon beacon detector and a forward looking infrared receiver (FLIR). The FLIR provides two independent channels (A, B) of video. An electrical signal developed within the sight unit is separately processed on both of the channels. One channel is used to develop a video display for an operator for target acquisition and tracking. The other channel is used for missile tracking and clutter and countermeasure (CM) rejection. A tracking unit (40) processes the signal to determine missile location relative to the target; and, if corrections to the missile freight path are necessary, a missile control unit (56) transmits them to the missile over wires (W). If two or more objects (M, D1, D2) are located in the field of view, a module (88) of the tracking unit undertakes a "segmentation" process to differentiate and characterize the objects to determine which object is the missile and which is not.

An angle-only tracking filter for a maneuvering target

Abstract: A nine-state extended Kalman filter for tracking a maneuvering target with angle measurements only, by an interceptor missile executing a low-frequency spiral maneuver with moderate acceleration, is described. The filter coordinate system is that of the seeker at the last measurement. The state variables are: the two boresight errors; the two line-of-sight angular rates; 1 /range; (range-rate)/range; and the three components (along the three principal axes of the seeker) of target absolute acceleration divided by range. The choice of axis system, state variables, missile dither maneuver and accuracy of measurements are important. In a simulation with noise, the estimated variables were reasonably accurate near intercept and led to a low miss distance. Improvements in analysis and design are possible.

Method and apparatus for a reprogrammable program missile memory

Abstract: A method and apparatus are disclosed for a reprogrammable program missile memory module 26 which is placed within a missile 14 in substantially the same manner as the currently used programmable read only memory. The reprogrammable program memory module 26 provides for remote writing of tactical program data thereto while allowing the missile 14 to remain in a substantially operational state.

Electrically-initiated time-delay gas generator cartridge for missiles

Abstract: A time delay gas generator for missiles, characterized by very long shelf life and accurately-determined time delay. Time delay powder (42, 43, 44) is layered at high pressure, and causes heating of a metal disc (51) at the end of a time delay interval that is accurately known. Such heating ignites an output charge (51) to generate gas, the gas breaking a closure (52) and performing a function in the missile.

Lateral Oscillations of Sting-Mounted Models at High Alpha

Abstract: It is shown that in a static test of a model of a high-performance aircraft or missile, lateral oscillations can occur, resulting in static, time-average measurements of the asymmetric loads that are close to zero. In contrast, the loads needed for analysis of full-scale aircraft or missile maneuvers are the instantaneous asymmetric loads, which because of the coupling between vehicle motion and flow separation will approach their maximum magnitude. Results applicable to full-scale free flight could be obtained by use of an apparatus such as the rotary rig, which permits coning and/or spinning motions of the model, provided that the measurements are corrected for support and wall interference effects. Until such capability is in hand, the best approach appears to be to use the asymmetric load extremes, e.g., such as determined in a static test where the model has been rolled through the full 360-deg range.

Ring laser gyro applications for tactical missiles: the Army TACMS solution

Abstract: The Honeywell H700-3A ring laser gyro missile guidance set (AN/DJW-51) provides navigation, guidance, autopilot, weapons dispensing, and communications functions for the US Army TACMS missile in a low-initial-cost and low-life-cycle-cost package. It is primarily the use of low-cost inertial sensors which make the use of a ring laser gyro navigation system feasible in the tactical missile market. The H700-3A ring laser gyro missile guidance set has proven to be a low-cost, high-accuracy guidance and navigation system for the deep-strike Army missile weapons system. This has been borne out by a highly successful test program of 26 missile flights. The components of the missile guidance set are described in detail. >

Missile homing device

Abstract: The disclosed device can be used to determine coordinates expressing the angular deviation between the direction in which a missile is located and a line of sight in which a target is located. The device comprises means to project and shift an image on a linear senor, in such a way that the field of acquisition of the homing device has a section, by a plane perpendicular to the line of sight, that is ring-shaped having a diameter corresponding to a wide field aperture at the moment when the missile is launched, so that the missile is definitely intercepted in the field of acquisition, and then having a diameter that is variable as a function of time in such a way that the ring follows the missile as and when it approaches the line of sight through the action of a remote control system or a directive beam system. Finally, the section of the field is reduced to a simple disk, corresponding to a field having a very small angular aperture, giving a better range than standard homing devices and giving a low probability of false alarms arising out of the presence of the sun or of decoys. The device can be applied to weapons systems.

Hand held video game with simulated air battle

Abstract: A novel hand held electronic LCD video game simulating an air battle at sea. Approach of enemy aircraft and aircraft carriers is simulated by sequential display of multiple images. The player manipulates missile sights between nine positions to aim and then fire missiles to destroy the approaching enemy aircraft and carriers. In addition, enemy missile attack is simulated by sequential display of missile images and the player must aim his sights and destroy the missiles before they destroy his aircraft. Five stages of play are provided with increasing speed of play for each subsequent stage. An energy gauge which decreases for each missed enemy aircraft or aircraft carrier limits the number of misses permitted to the player.

Analysis of selected data from the triservice missile data base

Abstract: An extremely large, systematic, axisymmetric-body/tail-fin data base has been gathered through tests of an innovative missile model design which is described herein. These data were originally obtained for incorporation into a missile aerodynamics code based on engineering methods (Program MISSILE3), but these data are also valuable as diagnostic test cases for developing computational methods because of the individual-fin data included in the data base. Detailed analyses of four sample cases from these data are presented to illustrate interesting individual-fin force and moment trends. These samples quantitatively show how bow shock, fin orientation, fin deflection, and body vortices can produce strong, unusual, and computationally challenging effects on individual fin loads. Flow-visualization photographs are examined to provide physical insight into the cause of these effects.

Covert millimeter wave beam projector

Abstract: Van Atta array is used to receive a millimeter wave beam from a beam transmitter located in a missile in flight and retransmit the beam back to its source along its original optical path after the beam is phase conjugated and modulated at a tracking station by imparting to it missile guidance information. The missile extracts guidance information from the retransmitted beam and guides its trajectory closer to the course leading to the target.

System for sensing the approach of a moving missile to a target

Abstract: A system for determining the trajectory of a missile (54) and the minimum miss distance with respect to a target aircraft (10), comprises two transmitters (12, 14) on the aircraft each cooperating with four receivers (16, 18, 20, 22) on the aircraft. Each transmitter radiates a succession of pulses each having a very short duration of the order of 2 nanoseconds and each having a shape approximating to a single sine wave. The transmitted pulses are reflected from the missile (54) and received by the receivers each of which is accurately time gated so that the received signal is sampled at a predetermined time delay after the radiation of each transmit pulse. A time delay corresponds to a particular missile range, and by gating at different delays the sampled signals indicate when the missile enters or leaves a plurality of range envelopes surrounding the target. Processing of the sampled signals enables the missile trajectory and minimum miss distance to be computed.

Energy management for multiple-pulse missiles

Abstract: This paper examines maximum final speed and minimum flight-time trajectories of missiles that have two- or three-pulse rockets for both horizontal and vertical plane flight. The optimal rocket-propellant loadouts and pulse ignition times are determined using parameter optimization coupled with explicit solution of the trajecto- ries. The results indicate that the three-pulse configuration is superior for both problems in horizontal flight and that it matches the performance of an ideal boost-sustain motor. For vertical plane flight, the twb:0ulse motor is superior to a boost-only motor. The three-pulse motor does not produce a significant practical improvement in performance for vertical plane flight beyond that of the two-pulse motor. HE development of practical designs for pulsed solid rocket motors has opened new avenues for the control of missile trajectories. To effectively utilize this new technology, techniques must be developed to optimize the trajectories and pulse motor designs. The present paper seeks to create a method to rapidly optimize pulse rocket-motor designs and trajectories and to determine the applicability of pulse motors to a spectrum of missile missions with an emphasis on the surface-to-air missile. The seminal works in the field of rocket-thrust and rocket - motor design optimization used the calculus of variations to demonstrate that the continuously throttleable ideal boost- sustain motor maximized missile performance.1'2 The require- ment of the use of fixed nozzle designs in actual rocket-motor designs prevented these theoretical performance limits from being achieved. The practical boost-sustain motor suffers a specific impulse degradation in both the boost and sustain portions of the thrust history with the greatest losses in the low-burn-rate sustain phase. The pulse rocket motor allows the use of nearly constant mass flow rate during operation, which gives a 5-1% advantage in overall specific impulse over the practical boost-sustain motor. Through proper design of the motor and control algorithms, the pulsed rocket motor is able to approach the theoretical limits set for the ideal boost- sustain motor. Thus, the pulse motor should offer perfor- mance improvement over the practical boost-sustain motpr. The complete solution to the optimal pulse motor problem involves simultaneous optimization of the motor parameters, ignition times, and trajectory shaping. Two broad approaches are available for solution of this problem. The first is the optimal control methodology, which yields a two-point boundary value problem. The resulting problem can be solved numerically using an open-loop solution for both the motor design and the missile guidance. Another method to solve the optimal control problem is to approximate the system by a reduced-order model and to find the corresponding closed- loop analytical guidance and ignition law. While yielding an implementable algorithm, this method involves approxima- tions which may not be appropriate. In addition, the reduced- order analytical solutions do not address the selection of the pulse motor design parameters.

Launching device for surface to air guided missile

Abstract: PURPOSE:To permit the quick turning of a guided missile against a short- distance low-altitude target by supplementing the shortage of a turning torque generated by aerodynamic steering by a method wherein a plurality of jot injection nozzles is provided at the tip end of a launching tube while the injecting amount of high-pressure gas is controlled by a launching control device through solenoid valves. CONSTITUTION:Either one of solenoid valves 6 is opened at a timing when the rear end of a launched guided missile 8 passes the tip end part of a launching tube 2, gas, compressed in a high pressure and stored in a pressure accumulator 4, is released through a pipeline 5 and is injected out of a jet injection nozzle 3 corresponding to the solenoid valve G whereby the gas is collided against the rear end of the guided missile to provide the same with a turbing force. The turning direction of the guided missile is determined by a condition that which one among 4 sets of the solenoid valves 6 arranged at the tip end part of the launching tube is opened while the turning amount of the missile is determined by the opening degree of the solenoid valve. The control of the turning direction and the turning amount is effected by a launching controller 7.

Mobile missile launcher and guidance system - is capable of being transported by modified cross country vehicle for speedy deployment

Abstract: The modular constructed launcher assembly (11) and guidance control cabin (12) are mounted onto a steel section frame (13) which is attached to the chassis of a cross country vehicle (10) by self-centering bolts. The complete launcher assembly (11) which consists of four containers (11a), each having four missile launch tubes (11b), can be elevated as a single unit to its operational position by a hydraulic ram unit. The air-conditioned guidance control cabin (12) is fitted with the necessary guidance, monitoring and comminication equipment requred to control a missile engagement sequence and fulfil the fole of an independent or integrated defence system. USE/ADVANTAGE - Mobile missile system which can be quickly mounted on a relatively inexpensive carrier vehicle. High degree of mobility gives weapon system broad operational spectrum.