Showing papers on "Missile published in 1970"

A Review of the Literature on the Missile-Allocation Problem

Abstract: This paper reviews the missile-allocation-problem literature. The problem considered is: given an existing weapon force and a set of targets, what is the optimal allocation of weapons to targets? References are organized by type, characterized by submodel, discussed, and annotated. It is proposed that this review methodology by applied to other appropriate areas.

Vascular injuries. An experimental study of high and low velocity missile wounds.

Abstract: In order to design procedures for adequate repair of vascular injury, we have conducted a study of arterial trauma caused by high velocity missiles. This report is concerned with the mechanism of arterial injury in ballistic wounds. The femoral arteries of anesthetized dogs were injured with missiles accurately calibrated at velocities of 1,000, 2,000, and 3,000 feet per second. The technique included angiograms of vessels at the moment of impact. High speed photographs demonstrated the sequential course of mechanical disruption with low and high velocity missiles. We have shown that the high velocity missile neatly shears the blood vessel wall at moment of impact. However, additional damage to the arterial wall, both gross and microscopic, is caused within 5μ to 10μ sec by the formation of the temporary cavity.

Distance ranging system

Abstract: A missile is traveling from its launch point towards an intended target. A signal source, located near the launch point, radiates a train of pulses towards said missile and towards said target. Each radiated pulse is received by the missile as a pair of pulses, one received directly from the signal source and the other received after being reflected from the target. Computing means on the missile determines the difference in arrival times of the two pulses of each pair of pulses, and then, from successive ones of such determinations, computes the distance between missile and target, missile velocity and acceleration, and finally the expected arrival time of the missile at the target; said computations being updated with the reception of each succeeding pair of pulses.

Missile impacts as sources of seismic energy on the moon

Abstract: Seismic signals recorded from impacts of missiles at the White Sands Missile Range are radically different from the signal recorded from the Apollo 12 lunar module impact. This implies that lunar structure to depths of at least 10 to 20 kilometers is quite different from the typical structure of the earth's crust. Results obtained from this study can be used to predict seismic wave amplitudes from future man-made lunar impacts. Seismic energy and crater dimensions from impacts are compared with measurements from chemical explosions.

Weapon training systems

Abstract: A weapons-effect simulating system especially suitable for use with missile-launching weapons such as bazookas. The system includes sighting means for aiming the launcher at a target and a source of electromagnetic radiation having its orientation or direction changed with respect to the sighting means by generated signals applied to a control system coupling the sighting means and the source. Subsystem apparatus for generating the control signals include aerodynamic and kinematic simulation circuits; the output of the aerodynamic circuit representing the dynamic response of the simulated missile to, for example, changes in sidewise acceleration, and the output of the kinematic circuit representing, for example, random flight disturbances and crosswinds.

Temporary cavity effects in blood vessel injury by high velocity missiles.

Abstract: : Historically, the effect of the temporary cavity upon arteries has been controversial. Angiographic and photographic documentation is presented of low velocity and high velocity injuries to arteries. The low velocity missile pushes the blood vessel ahead stretching it slightly before penetration and can be pushed aside with little or no formation of the temporary cavity. The high velocity missile neatly cuts the arterial wall at impact but then the explosive effect of the temporary cavity crushes the ends of the artery against its walls. Severity of arterial damage is proportional to the velocity of the wounding missile. The energy transferred from the high velocity missile forms the temporary cavity. Varied tissue destruction by identical missiles at equal velocity can be explained by the shape of the missile, its motion in flight, and most important the angle to the tissue at moment of impact. Knowledge of the ballistic behavior of high velocity missiles in causing arterial damage is necessary for the proper evaluation, and management of missile wounds.

Quasi-optimum proportional navigation

Abstract: The problem of deriving feedback guidance laws for interceptor type aerodynamically controlled missiles which seek to engage moving targets is considered. These missiles contain target trackers which provide angular information about the relative interceptor-to-target geometry. The performance criterion for this problem is quadratic, but the system equations are nonlinear. Suitable guidance mechanizations are obtained by applying the technique of quasi-optimum control. The efficiency of the resulting guidance system, relative to a linear optimum guidance system and a proportional navigation system, is demonstrated by simulations of attack situations in which the interceptor missile launch conditions depart from the nominal attack geometry.

Range gated retroreflective missile guidance system

Abstract: An optical tracking link in an automatic command to line-of-sight missile idance system improves the system efficiency and employs a reuseable light source. In tracking a missile during trajectory toward a target, short pulses of collimated light are transmitted from the launch site toward the missle. These light pulses are received by a missile optical receiver for guidance of the missile and are simultaneously reflected by a retrodirective prism on the missile. The reflected energy follows a path parallel to the incident wave and is thus directed back to the launch site. A missile tracker at the launch site responds to the reflective energy, measuring any deviation of the missile from a line-of-sight axis maintained between the launch site and a target. Guidance commands are transmitted toward the missile for maintaining the missile on the line-of-sight trajectory and containing correctional signals in response to any missile deviation. During intervals between return reflections, the missile tracker can be gated off. This greatly reduces background and jamming source reflections and signals, received by the tracker providing effective counter measures hardening of the system.

Stowable air scoop

Abstract: A foldable ram air scoop for gathering and channeling external air into a secondary thrust chamber, or afterburner, of an airaugmented thrust propelled missile is provided. The scoop is deployable prior to launch, being foldable against the missile body while stowed within a volume restricted storage magazine. The present air scoop essentially comprises a two-stage folding mechanism which compactly holds the scoop body against the missile, controllably deploys the scoop to a desired configuration, and positively locks the scoop in the proper position.

Method and apparatus for suppression of antiaircraft fire

Abstract: An aerial weapon is provided for the suppression of antiaircraft artillery fire against an air attack. This concept has been called various names in the past, notably AFIRM standing for Anti-Flak InfraRed Missile. A first rocket delivers the missile which descends on a parachute until the heat of an antiaircraft gun is sensed. A second rocket propels the missile to target under control of heat sensing guidance and control unit.

System for determining the orientation of an object by employing plane-polarized light

Abstract: A system for ascertaining the positional characteristics of a moving object from a given viewing point. In one embodiment, the invention is employed to determine the attitude of a missile subsequent to its being launched from an aircraft. A plurality of specially oriented light-polarizing reflectors are attached to the missile surface, and observed by a viewing camera on the aircraft. A source of plane-polarized light on the aircraft illuminates the reflectors on the missile. The attitude of the latter with respect to this source determines the amount of illumination picked up by the camera from each reflector. Such data is then coordinated to yield the positional information desired. In another embodiment, the invention time-correlates a plurality of viewing cameras by causing a time-coded reflection of light to be visible on the missile regardless of view angle.

A method for predicting the static aerodynamic characteristics of typical missile configurations for angles of attack to 180 degrees

Abstract: : A method for predicting the static, longitudinal aerodynamic characteristics of typical missile configurations at zero roll angle (i.e., in a plus configuration) has been developed and programmed for use on the IBM 7090 digital computer. It can be applied throughout the subsonic, transonic, and supersonic speed regimes to slender bodies of revolution or to nose-cylinder body combinations with low aspect-ratio lifting surfaces. The aerodynamic characteristics can be computed for missile configurations operating at angles of attack up to 180 degrees. The effect of control surface deflections for all modes of aerodynamic control are taken into account by this method. The method is based on well-known linear, nonlinear crossflow and slender body theories with empirical modifications to provide the high angle of attack capability. Comparisons of the theory with experimental data are presented to demonstrate the accuracy of the method.

Missile launch control system

Abstract: A control system for launching missiles from aircraft wherein said missiles are automatically prepared and fired in either an individual or ripple fire sequence, particularly embodying logical mechanisms for arming and firing said missiles in predetermined sequence, including the arming and firing of said missiles in an alternate sequence when individual missiles are missing from their firing positions.

The Missile Gap Controversy

Abstract: The disputes surrounding the formation of military policy are not famous for their clarity, yet, even so, the controversy over the missile gap stands out as a muddled issue. The controversy arose in the late 1950S as a result of intelligence estimates that between 1960 and 1964 the Soviet Union might have more intercontinental ballistic missiles (ICBMs) operational than would the United States. Assuming the existence of a missile gap, opponents of the Eisenhower administration argued the existence of a deterrence gap, that Soviet supremacy in ICBMs was so great that the American strategic forces could be eliminated in a single massive attack. Administration spokesmen generally conceded the missile gap but denied a deterrence gap on the grounds that the American strategic forces were too numerous and varied to be eliminated by a single attack and that the leaders of the Soviet Union were aware of this fact. We now know that the administration's contention that a missile gap did not necessarily imply a deterrence gap was never tested, since the missile gap itself never developed. Therefore it

Proportional Navigation on Nonstationary Targets

Abstract: In a missile flying a proportional navigation course, the missile heading rate is made proportional to the indicated line of sight rate. While for stationary targets the resulting differential equations of motion can be readily integrated, this is no longer the case for moving targets. To obtain closed-form expressions convenient for the evaluation of trajectory parameters, the assumption is made in this paper that for moving targets, the angular rate of the closing velocity vector is made proportional to the line of sight rather than the actual heading rate.

Method and apparatus for stabilizing the trajectory of a reaction-propelled missile

Abstract: In a method and apparatus for stabilizing the trajectory of a reaction-propelled missile, tensile forces are exerted at the stern of the missle through a single tensile member connected to the stern, the tensile forces, at angles of incidence of the missile differing from zero, producing moments which rotate the missile back about its center of gravity. The single tensile member, at its connection with the missile, is wound on a coil at the stern of the missile, and this coil has an axis of rotation coinciding with the longitudinal axis of the missile. The single tensile member may be the cable for transmitting guiding signals to the missile, although the tensile member may be independent of this cable.

Cavity antenna mounted on a missile

Abstract: An antenna for use on a missile wherein a cylindrical conductor is concentrically positioned about a metallic surface portion of the missile so as to define a cavity of one-quarter wavelength between one end of the cylindrical conductor, which is connected with the missile surface, and a plurality of connecting positions of energy transfer means The energy transfer means is connected about the periphery of the cylindrical conductor at intervals substantially equal to a single wavelength of a signal so that the cylindrical conductor and the missile surface adjacent an opposite end of the cylindrical conductor form the elements of an asymmetric dipole of high impedance

Apparatus for guiding a missile

Abstract: A device for correcting the flight path of an air to surface missile and ding said missile to a target. A first map of a strip of ground which is transverse to the direction of flight is provided on a rotatable drum along with a second map of a strip of ground which is parallel with the direction of flight. A live image of the ground over which said missile is traveling is projected first through the first map to provide a position fix of the missile in range and azimuth relative to a target and after a correction has been made to the flight path of the missile, the live image of the ground is projected through the second map to provide guidance correction to direct the missile to the target.

Guided missile trajectory alignment method

Abstract: Method aligning a guided missile with its velocity vector at the beginning of post exoatmospheric flight. This missile velocity vector data is established during preexoatmospheric flight. At re-entry, the outputs of normal and axial accelerometers and the missile velocity vector data are used to determine the difference angle existing between the missile''s major longitudinal axis and the missile velocity vector. When the difference angle is less than 0.5* pitch and yaw integration functions are initiated. The integration functions are based upon a value of roll attitude that makes the pitch angle equal to 0 and the yaw angle equal to the difference angle. System roll attitude data is then used to transform the reference to a frame in which the local horizontal frame is known.

Archery bow with projectile

Abstract: A bow and missile device, the bow having a central opening integrally therein, so that a missile when impelled by the bowstring passes through the central opening. The missile is of spherical or other solid configuration, and has a pair of wings affixed to a slit in the missile so that the wings may be folded around the bow string and be grasped by the user to facilitate propelling the missile by means of the bowstring, through the central opening in the bow.

Self-propelled, vaned missile

Abstract: A self-propelled vaned missile, designed to be fired by means of a launching tube and wherein the vane system comprises at least three fins articulated onto pins disposed at the rear of the missile, the pins being perpendicular to the axis of the missile. It is new in that the fins of the said vane system are double fins, each having blades which are joined at their hinged end by a bridge and equipped with spacing springs. These springs exert on the fins a force greater than the resistance which the air exerts on them in the course of the missile''s advance, and cause the open out of the said rear fins towards the front as soon as the missile has left the launching tube.

Missile guidance systems

Abstract: A sighting and tracking apparatus for a missile guidance system, of the kind which employs an optical tracker for tracking and controlling the flight of a missile, the tracker providing output signals which are transmitted to the missile to control the missile to a demanded flight path. The apparatus includes an adjustable electrical model of the flight path demanded by the tracker, and a computer to which the tracker output signals are continuously fed, the computer being programmed to adjust the model continuously during missile flight in such a way as to cause the model to conform to the demanded flight path at each instant of flight. The model produces continuous control signals dependent on its adjustment, and in the event that control of the missile by the tracker is lost during flight, adjustment of the model by the computer is immediately stopped and the control signals from the model in its existing state of adjustment are employed to direct the continued flight of the missile.

Ballistic-missile defense radars

Abstract: Ballistic-missile defense has been continuously researched in the United States for the past 14 years. The Safeguard system itself is an outgrowth of both the Nike?Zeus system and later ballistic-missile components developed by various government agencies. The classic result of this early work was clear?an ICBM could be intercepted by another missile. Hence, the real controversy concerning the workability of such systems centered around an entirely different problem?the ``high-traffic environment''?or how to make tens to hundreds of near-simultaneous intercepts while tracking thousands of targets. This article describes the radars that have led to a solution of this problem, and how such radars operate within the framework of the world's most sophisticated defense system.

Method and system of surveillance processing

Abstract: Surveillance of missile tracks is obtained by a satellite having a series of sensors that activate an image storage tube which is periodically slit scanned. The scan data is processed to determine when the length of the series of images is sufficient to represent a missile track and the information is transmitted to a ground control station and a ground user station. By transmitting signals the control station controls the threshold levels, blanking, and the data processing program. The user station combines the data from the satellite and the ground station to determine the location of the missile and predict its trajectory.

Single jet pneumatic pulse duration modulation gyro

Abstract: A two axis all pneumatic displacement gyroscope that detects a change of position in pitch and jaw of a missile. The spin axis of the gyro rotor is directed along the longitudinal axis of the missile. The rotor utilizes a hydrostatic air bearing and the gyro pickoff responds to the exhaust from the air bearing. A single air jet provides the rotor exhaust for the pickoff collectors. To provide the air bearing, a gas is introduced into a plenum chamber within the stator about which the rotor spins. The gas is uniformly passed through output passages of the plenum chamber, exiting at the spherical surface of the stator. The inner spherical surface of the rotor is supported by the exhausting gas. In exhausting from the air bearing, the gas passes through a single passage in the rotor that terminates on the surface of the rotor. The single output gas stream periodically impinges on pickoff devices arranged around the circumference of the rotor. The relative position of the pickoffs, with respect to the rotating output jet, controls the period that the gas is accepted by the pickoff. When the rotor and stator are changed in reference to each other, as when a missile changes position or direction, the air jet makes a varying path as it passes across the pickoffs. With variations in pitch and jaw, the period that gas impinges on the pickoffs is also varied, thus providing an output signal in response to the direction of change in trajectory.

Game apparatus including target, projectile, and playing court

Abstract: A game apparatus comprising a court upon which the game is played, a goal and a missile. A player stands behind a boundary line on the court which is spaced from the goal and throws the missile at the goal. The missile comprises a head and a tail which are connected together in a manner to allow universal movement therebetween. In throwing the missile, the player grips the tail and throws the missile in an underhanded throwing motion. The missile can be thrown to follow trajectories ranging from a trajectory in which the head leads the tail throughout its path to the goal to a trajectory in which the head and tail tumble one over the other. A score is kept depending upon the final resting place of the missile, i.e., the missile within the goal, the head within the goal and the tail without the goal, the tail within the goal and the head without the goal, the missile without the goal.

Missile proportional navigation system using fixed seeker

Abstract: The outputs of a fixed array detector are employed as inputs to a homing missile steering system using proportional navigation. The seeker outputs are in the form of quantized signals, and are summed with gyro-derived attitude signals to produce missile control signals.

Gravity projected ball game with manually maneuverable target opening

Abstract: A game device of the type including a chute-like element for launching a ball-like missile into a path of flight and a selectively closable aperture for receiving a ball-like missile, characterized by the provision of a masking means at the upper or depositing end of the chute-like element and the provision of missiles of different color, whereby a player manipulating the closable aperture may request the launching of the missile of a certain color and will be unable to determine such color until shortly before, or at the time that the missile is launched out of the end of the chute.