Showing papers on "Missile published in 1977"

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

A Preliminary Method for Calculating the Aerodynamic Characteristics of Cruciform Missiles to High Angles of Attack Including Effects of Roll Angle and Control Deflections

Abstract: : A method is presented together with a computer program for calculating the forces and moments on the components of a cruciform missile: nose, canard section, afterbody, and tail section. The program utilizes a skeleton data base for the fin normal forces and center-of-pressure positions. These quantities were derived from a set of fins of varying aspect ratio and taper ratio tested on a body having a diameter equal to half the tail span. The data base, covering a range 0.8 < or = M at infinity < or = 3.0, is extended to arbitrary cruciform body-tail configurations or body-wing-tail configurations using analytical and empirical methods. Pitch, yaw, and roll control are included in the method as well as the effects of missile roll angle. Comparisons are made between the predictions of the computer program and experiment for fin forces and configuration forces and moments for body0tail and wing-body-tail combinations up to angles of attack of 45 deg. On the whole acceptable agreement between prediction and experiment is obtained.

Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results

Abstract: An experimental investigation was conducted on a model of a wing control version of the Sparrow III type missile to determine the static aerodynamic characteristics over an angle of attack range from 0 deg to 40 deg for Mach numbers from 1.50 to 4.60.

Experimental Missile Pitch- and Moll-Damping Characteristics at Large

Abstract: Pitch- and roll-damping test mechanisms were developed for obtaining stability characteristics of high fineness ratio missiles at angles of attack up to 90 deg. Wind-tunnel tests were conducted on two missile configurations at Mach numbers 0.22 through 2.5. Mechanism evaluation tests showed that strut interference was not appreciable. The pitch-damping derivatives were found to be highly nonlinear functions of angle of attack, and the roll-damping and Magnus characteristics were very nonlinear with spin rate'at high angles of attack and low Mach numbers. Large and erratic variations in side force and yawing moment with angle of attack and high autorotation characteristics also were found at the low Mach numbers.

Extended range, light weight laser target designator

Abstract: Pulse integration is utilized on board an optically guided missile or other ordinance device used as a part of a target designation system for extending the lock-on range of the missile by approximately 18%, when a double pulse laser is utilized to illuminate and designate the target. Pulse integration is accomplished with a recirculating delay unit which superimposes the first pulse on the second pulse, such that while the pulses add coherently, noise does not add in phase. The pulse integration technique therefore enhances the signal-to-noise ratio when the missile is at the outer limits of its operating range. When the missile is sufficiently close to the target, doublet decoding is actuated to offer countermeasure resistance. At this point, pulse integration may proceed in lieu of doublet decoding or may be dispensed with in view of the increased signal-to-noise ratio due to the close range of the missile to the target.

History of Inertial Navigation

Abstract: the guidance system used by the Germans in 1942 in the V–2 missile can be considered to be the first use of inertial navigation. It is true that Foucault defined the gyroscope in 1852 and that Schuler developed the gyrocompass in 1908, but the former device was only a measuring instrument and the latter, although of inertial quality, was only a partial inertial system. The Sperry flight instruments of the late 1920's and early 1930's were attitude–indicating not velocity or position-indicating devices. Earnest development of inertial navigation systems began in the United States in the late 1940's and early 1950's by the M.I.T. Instrumentation Laboratory, Northrop and Autonetics under Air Force sponsorship. This work led to the inertial guidance systems for ballistic missiles—both land and ship launched. The 1960's brought the Space Age and the advance of inertial guidance in Apollo. During this time inertial guidance systems also found their way into military and then commercial airplanes. Behind the system development was the simultaneous and necessary development of theory, analysis, components, subsystems and testing. The author, whose professional career has been simultaneous with the growth of inertial navigation, draws on his personal experiences in the field of direct association with many of the people and events involved.

Guidance systems for mobile craft

Abstract: A missile is guided onto a target by means of a laser beam, so that the missile can determine and correct its displacement from the boresight of the laser beam. This leads to greater accuracy of guidance, and avoids the need for very narrow beams which could be lost by the missile.

Large Angle-of-Attack Missile Control Concepts for Aerodynamically Controlled Missiles

Abstract: A coupled or cross-axis autopilot control concept is presented which can provide a significant increase in the usable range of angle of attack for aerodynamically controlled tactical missiles without an attendent increase in either steering response time or roll channel bandwidth. The unique feature of the coupled control system design is that adequate airframe stability can be maintained in the presence of aerodynamic cross-coupling at large angles of attack without either physically rolling the airframe to a preferred orientation with respect to the airstream or increasing the bandwidth of the roll system. Stability is maintained by intentionally cross-coupling sensor signals among the control channels (i.e., roll sensor signals into steering control, and vice versa) at large angles of attack. In effect, the intentional cross-channel coupling partially cancels the destabilizing effect of the interchannel aerodynamic coupling.

Weapons system simulator and method including ranging system

Abstract: A weapons simulator for training an operator in the use of a weapons system, particularly a guided missile system of the type employing operator positionable optics. The operator centers a target, having two optically detectable markers, within a predetermined field of view which is viewed through the optics. A television camera in optical communication with the optics scans the field of view and generates a first video signal representing an image including the target and the markers. The markers are detected in the video signal to generate a target signal representing the position of the target in the scanning pattern of the camera and a range signal representing the range between the simulator and the target. The operator initiates simulated flight of a missile, and an electronically generated missile signal simulates the flight of a missile. The missile signal is automatically varied in value in accordance with a guidance signal and time from initiation of flight to thereby represent the size and location of the missile within the field of view. A cathode ray tube in optical communication with the optics projects an image of the simulated missile onto the image presented to the operator, and a kill signal related to the proximity of the target is generated in response to the target, range and missile signals. Provision is made for simulating all of the sounds made by the real system, and for displaying the missile flight and other data on a TV monitor.

Carrier missile for ejectable bodies

Abstract: A subcaliber missile to be launched from a barrel, in order to serve as a carrier for satellite missiles of other ejectable bodies, has an envelope divided into two half-shells of tapering configuration which are articulated to the missile bottom and are held together by a missile head and by internal partitions separating the ejectable bodies from one another. When the missile is in flight, the ejection of the head by the detonation of a charge exerts a backward reaction force upon the envelope, causing its load to move forward therein whereby the partitions are disengaged from the two half-shells and allow them to flip apart. The half-shells are provided with slots for a recessed tail-wing assembly and with back fins which, like the missile bottom, conform to the caliber of the barrel.

Wedge clamp for missile launcher

Abstract: An adjustable clamp for a missile launcher system having a pair of semi-resilient wedge members which fit between the missile hanger lugs and launcher rail and are drawn into the gap by means of a pair of plate members and a pair of bolts. The Teflon wedges fill the gap between the missile hanger lugs and the launcher rail and reduce vibration during captive flight and protect the rails against damage.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval Vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed. The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets. Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile.

Device for a missile

Abstract: The present invention relates to a missile launching assembly, and in particular to an apparatus for automatically separating a front cover of a missile launching tube with a reverberating shock wave created by missile propellants striking a rear cover of the tube, thereby avoiding direct contact between the front cover and the missile.

Method for guiding the final phase of ballistic missiles

Abstract: A method for guiding the final phase of a ballistic missile wherein the target and the missile are continuously tracked to determine their positions with respect to the missile firing platform; the actual coordinates of the missile position, which are continuously being furnished by the tracking system, are constantly compared with nominal coordinates determined by a fire control computer and the deviation is computed therefrom; a correction signal, as to magnitude and direction of the path of the missile is generated from the deviation and is transmitted to the missile as a wireless, coded signal; and this correction signal, together with measurements for the dynamic flight characteristics are translated in the missile into a triggering pulse to actuate a path correction for the missile.

Component aerodynamic characteristics of banked cruciform missiles with arbitrary control deflections

Abstract: A comprehensive computer code has been developed for the prediction of the static aerodynamic characteristics of cruciform wing-body combinations with one or two sets of fins. The code may be used for subsonic, transonic, and supersonic speeds. Arbitrary bank angles and control deflections are allowed. The present version of the code may be used for angles of attack up to 20 deg. The code computes the forces and moments acting on each component of the missile including the effects of vortices shed by the body and fins. Comparisons between experiment and theory indicate good agreement for longitudinal characteristics and fair to good agreement for lateral characteristics.

Trajectory adaptive safety-arming device

Abstract: A safety-arming device for use in a highly maneuverable missile is disclo which takes into account lateral acceleration of the missile and selects the proper point in the trajectory after which arming of the missile warhead may safely proceed. The safety-arming device uses a series of electrical, mechanical, and electromechanical interlocks to insure that premature arming of the missile warhead does not occur.

Warhead and anti-tank missile construction

Abstract: A warhead for an anti-tank projectile or a rocket propelled missile inclu a warhead body with a casing having a plurality of concave shaped-charge type liners arranged around the periphery and surrounding the interior explosive charge and in a plurality of planes extending along the axis of the warhead The explosive charge forms a portion of the body of a rocket propelled missile which includes a nose having a telescopic rod which is extendable from the tip and which is actuated upon impact at the target zone to initiate explosion of the explosive charge when at least one of the charge liners is at a height which corresponds to the maximum height of the target, for example, a tank The missile body carries a plurality of flaps which may be moved outwardly or a parachute which may be ejected, such as by suitable operating mechanism, or by the withdrawal of a covering such as at the head of the missile to provide a braking effect on the missile to cause the axis of the projectile to adjust to a direction substantially perpendicular to the tangent of its trajectory and to cause the forward speed to become considerably reduced The missile also advantageously includes means for restabilizing the missile after it has been adjusted to a substantially vertical drop by control devices such as tail fins or a parachute which is ejected from the nose of the missile and which effects the reversal thereof to a position in which the tail extends downwardly

Missile for discharge towards a target

Abstract: A missile for discharge towards a target, comprises a power source, an explosive charge, a release unit, and a sensor means adapted to influence the release unit in response to certain conditions appearing during the flight of the missile towards the target. The missile further comprises a plurality of explosive elements which have their own power source, explosive charge, detonator unit and sensor means, and which under the influence of the release unit are separated from the missile and independently thereof approach the target for under certain conditions sensed by the sensor means to detonate individually at a desired distance from the target. The power source of each explosive element is a chargeable condensor battery which during the flight of the missile is connected to and charged by the power source of the missile. The power source of the missile comprises a rotating generator mounted in the front part of the missile and driven by ram-air during the flight thereof.

Shipboard point defense system and elements therefor

Abstract: A combined defense and navigational system on a naval vessel is disclosed The disclosed system includes a track-while-scan pulse radar which is controlled to provide either navigational information or tracking information on selected targets Additionally, the disclosed system includes a plurality of guided missiles, each of which may be vertically launched and directed toward intercept of a selected target either by commands from the track-while-scan radar or from an active guidance system in each such missile The invention herein described was made in the course of or under a contract or subcontract thereunder, with the Department of Defense

Missile roll position processor

Abstract: A weapon system using a line of sight guidance system is provided with a missile containing two symmetrically located optical receivers. Information contained in a beam into which a missile is launched is used by the two receivers and associated processor means to derive roll position for the missile. Because the roll signal is derived electronically, mechanical means for determining roll position of the missile in the form of a conventional roll gyro, for example, may be eliminated. Elimination of the mechanical roll gyro from the missile permits much higher launch accelerations than are realistically feasible with missile control systems employing mechanically derived roll data. A processor located in the missile receives its signals from the pair of optical receivers. The processor uses the data from the first receiver to derive the position error of the missile relative to beam center. The data of the second receiver is used by the processor, along with a phase angle reference from the first receiver signal to develop a signal representation of the missile roll angle. The signal representation is further processed, when used with missile control systems requiring the roll reference signal in the form of a linear voltage with missile roll angle, to develop a missile roll angle reference in the form of two ramp voltages, each representing 360° of missile roll angle and being separated in phase by 180°.

Active optical tracking system

Abstract: An active optical tracking system for air-to-air type missiles of relatively small dimensions having a pulsed laser transmitter operating through a gimbaled mirror system and a reflection receiving system connected to the guidance and control unit of the missile to direct it to a target.

A simple method for predicting rocket exhaust smoke visibility

Abstract: Ambient light scattered from metal oxide particles in composite-propellant rocket exhausts makes the missile trail visible at long ranges. In the selection of propellant aluminum concentration, it is important to be able to predict the distance from which the exhaust no longer is visible. In this paper, a simple methodology, amenable to hand calculation, is presented for this purpose. The user need supply only the propellant aluminum concentration, missile velocity and altitude, and the rocket motor thrust level. The methodology predicts smoke trail dimensions, particle concentration as a function of location in the trail, sunlight and skylight scattering, background obscuration, and the range at which the trail may be detected visually for any atmospheric attenuation level. The entire calculation can be carried out with a scientific pocket calculator.

Missile Warhead Modeling: Computations and Experiments

Abstract: : A computational warhead modeling capability has been developed which models the effects of warhead length to diameter ratio, end confinement variation, explosive material and initiation posture, and internal cavity shape and material. These effects are modeled with a time-dependent, two-dimensional, Lagrangian finite - difference computer code, integrally modified to include fragment separation (or fragmentation for continuous warheads) and subsequent explosive gas leakage between fragments. Experimental results of a variety of modeled missile warheads (discrete-fragment warheads) are presented and compared with the computational results. In the experiments the fragment speed and angle distributions with respect to their original position on the warhead are determined through time-sequential, orthogonal flash radiography of the warhead fragment spray in flight, and soft recovery of the fragments after launch.

Support and retention mechanism for missiles in launchers

Abstract: The proposed support and retention mechanism makes it feasible to hot launch missiles or anti-missile missiles especially from aircraft using constant section, open ended, vertical or nearly vertical launch tubes to significantly increase missile range or payload without increasing the missile weight. This bazooka method of launching, results in much lighter launch tubes and support structure and no appreciable reaction on the aircraft. The hot launch feature permits a simplification of the method of storing such missiles as the Polaris, Poseidon and Trident in missile launch submarines. At the same time the jettison feature permits missiles to be stored and released from a vertical position which can increase the load passing through a smaller bomb bay and result in decreased aircraft weight.

Antimissile system for armoured vehicles - has electrically ignited explosive charges to destroy or deflect approaching missile by gas press. and mine effect

Abstract: The antiaircraft armament system is used armoured fighting vehicles. This arrangement makes it possible to fight all nonguided missiles as well as all those guided by wire, ultrasonics, wireless, infrared or by other control means. Electrically ignited explosive charges are accommodated either directly on the armoured fighting vehicle or on overhanging arms. The approaching missile is either destroyed or deflected in the region of the ignited explosive charges by the gas pressure and mine effect. These explosive charges can be initiated either by the armoured vehicles 2 or by electronic missile tracking devices.

The future of land-based missile forces

Abstract: (1977). The future of land‐based missile forces. The Adelphi Papers: Vol. 17, The Future of Land‐Based Missile Forces, pp. 1-2.