Showing papers on "Missile published in 1978"

On validating simulation models of missile systems

Abstract: Simulation of missile systems is mainly used to pre dict missile flight and terminal miss distance and to study flight safety. Computer simulations of mis sile systems produce results that otherwise could only be obtained by actual tests and missile flights. The increasing cost of firings limits their number and hence reduces the amount of available flight-test data. Theil's inequality coefficients (TIC) and their geometric representations are the basis for a procedure which provides insight into the validity of a simulation and reduces the dependence of validation on flight-test data.

Missile launcher for aircraft

Abstract: A launching mechanism for missiles from aircraft is defined which eliminates the need for changing the missiles from a transport position to a launch position and which employs the force of gravity as the motive force for launching. Missiles are suspended from carriage assemblies which incorporate an ejector mechanism, power sources, power actuators and trigger/safety devices. Each carriage/missile unit is installed in a transport module which can be configured to contain an array of missiles. One or more transport modules are installed in the aircraft cargo compartment aligned with each other and an acceleration module, all such modules being secured to the compartment floor and to each other. The acceleration module is the aftmost unit of the launcher system, serving as a transition unit for each missile from the transport modules to the release position and as an acceleration unit for each missile just before it leaves the aircraft.

Submunition dispenser system

Abstract: A system for dispensing a large number of submunitions from a missile or aircraft in uniform selected pattern. Small, cylindrical submunitions are carried in ejection tubes in a generally cylindrical housing. Sets of tubes are arranged in parallel planar arrangement approximately perpendicular to the housing longitudinal axis, with different sets at different angles to vertical. Timing means cause the submunitions to be ejected at selected times, and drag means on the individual submunitions are actuated at selected times so that the submunitions strike the ground along lines perpendicular to the line of housing mount. This system is especially useful with low-flying cruise missiles in attacking airfields, since a plurality of cuts across the airfield can be inflicted as the missile traverses the length of the field.

Local Effects of Tornado-Generated Missiles

Abstract: Nuclear power plant facilities and many other structures need protection against missiles generated by tornadoes and explosions. Empirical formulas are presented to determine the local effects on concrete barriers. Calculated depth of penetration, and thickness to prevent perforation and scabbing have been compared with all available results for full-scale simulated tornado-missile tests. The comparisons are excellent. The tests included missiles of various sizes, shapes, materials and impact velocities. The target properties also varied significantly. The new formulas can predict the local effects of missile impacts better than any other existing set of formulas.

Missile carrier airplane

Abstract: An air launched cruise missile carrier airplane having a floor mounted track system for moving missile racks into a launch position adjacent to a side opening in the fuselage and ejecting missiles therethrough, then moving the empty missile racks from the launch location and repositioning a full rack of missiles thereat. A continuous missile launching sequence is provided by the floor track system which guides the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement.

Anti-ship torpedo defense missile

Abstract: A ship anti-torpedo defense system includes a detecting device for detecting and locating an incoming threat, such as a torpedo, and an interrelated missile launching and control system for firing at least one warhead carrying missile into the path of the oncoming threat, the missile having an active acoustic fuze system including a highly directional sensing system for continuously monitoring the position and proximity of the incoming threat and for detonating the warhead at the optimum proximity of the incoming threat with the missile. The missile floats at a predetermined depth determined by the predetermined depth of the torpedo to be intercepted.

Target and missile angle tracking method and system for guiding missiles on to targets

Abstract: The invention relates to missile guidance and provides a method and system for guiding one or more missiles on to one or more targets. Aim on the targets and missiles is taken by means of two electro-optical pick-ups having a switchable field of view and supported on a stabilized and orientable platform. The pick-ups provide images displayed on screens and the corresponding video signals are processed by deviation measuring circuits which form tracking windows around the image of the targets and the missiles and determine their coordinates, the latter being addressed to a computing unit which generates guidance and steering commands transmitted to the missiles. Application to the automatic guidance of missiles fired as a salvo from an anti-tank helicopter.

High angle-of-attack missile control system for aerodynamically controlled missiles

Abstract: A missile control system can avoid instability at high angles of attack by cross-coupling roll and steering sensor signals between the steering and roll channels. The control law for the system is derived by use of the Model-in-the-Performance Index Technique which makes the system respond at high angles as it does at low angles with desired response times, bandwidths, and stability.

Steering arrangement for projectiles of the missile kind, and projectiles fitted with this arrangement

Abstract: A steering arrangement for missile type projectiles. A source of steering propulsion which is accommodated in the vicinity of the center of gravity of the missile comprises two gas generators which are positioned symmetrically on either side of the center of gravity a system being provided to switch or divert the gases to the exterior of the missile in at least two directions which are transverse to the projectile and to its axis. The arrangement according to the invention considerably improves the reliability and effectiveness with which the projectile is steered.

Automatically disintegrating missile

Abstract: There is disclosed a missile which automatically disintegrates after a predetermined flight time. The missile is made up of several parts which are positively secured together by a locking means which is released at a predetermined time after the firing of the missile by the action of the air through which the missile passes during its flight. The invention may by used to advantage in both practice missiles and service missiles.

Missile detecting and tracking unit

Abstract: A system for detecting, tracking and guiding a missile to a target is disclosed. The missile has a beacon which emits infrared signals. A night sight, which has a reticled infrared receiver for sighting a target, detects the infrared signals of the missile relative to the center of the reticle and converts the infrared signals to electrical signals representative of the impinging infrared energy. The IR receiver output is connected to a computerized beacon tracking unit. The tracking unit determines when beacon signals are detected by the receiver, tracks and guides the missile to its destination by computing missile position pitch and yaw guidance signals to align the missile with the target.

Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot

Abstract: A missile system in which a missile is guided in a predetermined trajectoryrom launch or shortly thereafter in yaw by proportional navigation and in pitch first by a pitch programmer until said missile reaches a predetermined angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a time optimal controller to direct the missile at a predetermined angle toward a target and finally by proportional navigation in pitch of the missile to the target.

Dynamic Derivatives for Missile Configurations to Mach Number Three

Abstract: AN extension of aerodynamic prediction methodology1 for tactical weapons to compute dynamic derivatives, including Magnus, pitch damping, and roll damping moments, is discussed. The methodology is applicable to general wing-body-tail configurations for Mach numbers to about 3 and small angles of attack. Predictions agree with experiment to about ±25%. The CDC 6600 computer program calculates the static and dynamic derivatives in less than a minute per case (one configuration, one Mach number, one angle of attack). The computer program and methodology are available to government facilities and their contractors through Refs. 2 and 3. Content This synoptic discusses the application of a general design methodology for tactical weapons. These weapons include guided missiles and projectiles and unguided ordnance such as free-fall bombs, unguided rockets, and spin-stabilized projectiles. Typical geometries may consist of general shaped bodies with up to two sets of lifting surfaces. The body may be pointed, spherically blunted, or truncated. It may have up to two slope discontinuities along the nose followed by a cylindrical afterbody with a boattail or flare at the aft end. The wings may have biconvex or double wedge planforms (or modifications thereof) and the wings may have sharp or blunt leading and trailing edges. The planform may be swept and the wing thickness to chord ratio may vary along the span. Previously, operational requirements for these weapons dictated Mach numbers 0 to 3 and angles of attack up to about 20 deg with only secondary interest outside these regions. Future requirements indicate higher Mach numbers and angle of attack as well as nonaxisymmetr ic body geometries. This synoptic deals only with the lower spectrum of the operational requirements. The overall approach to developing a general tactical weapon design code has been threefold: a) utilize existing state-of-the-art approximate analytic schemes where possible; b) modify these approximate schemes or develop new methods if feasible; and e) utilize existing empirical or develop new empirical techniques as a last resort. This overall approach was dictated by a tradeoff between accuracy and minimum computational time and cost. It was felt an allempirical methodology such as that of Ref. 4 would not be accurate enough whereas an exact numerical procedure would be too costly, both in development and computer execution time for most design applications.

Light emitting diode beacons for command guidance missile track links

Abstract: An improved automatic missile tracking and guidance system wherein a laund missile is guided along a line-of-sight maintained by the operator with the target. The position of an infrared source disposed on the missile is detected and guidance signals generated in accordance therewith to control the flight of the missile along the line-of-sight. The infrared source or beacon disposed on the missile comprises an array of semiconductor light emitting diodes. The solid state characteristics of the light emitting diodes provide heretofore unobtainable reliability over existing beacons. The beacon may be used to produce a modulated, high frequency, rectangular waveform, incoherent emission offering performance improvements including virtual immunity to optical countermeasures.

Broadband interferometer and direction finding missile guidance system

Abstract: A wide bandwidth interferometer which may be employed in a guidance systemor a rolling missile delays the radar signals detected by one of the antennas by a fixed amount and the signals detected by the other antenna by a variable amount prior to their multiplication in a device which first advances the phase of one of the signals by 90°. The product signal, which is proportional to the sine of the angle between the rolling axis and the line-of-sight to the target, is integrated in a limited-integrator whose output is summed with a pick-off signal from an onboard gyroscope. The sum signal determines the amount of the variable delay, while the output of the integrator controls the gyroscope to align it with the radar signal direction and the missile steering apparatus to home it on target.

Missile director with beam axis shift capability

Abstract: A line of sight guidance system in which the radiated output of a pulsed laser is spatially modulated to produce a beam radiated from an optical projector along a first axis, including a missile or projectile carrying a beam receiver and signal decoder which receives and decodes information in the beam to enable the missile to seek beam center, is provided with apparatus for generating a lead angle axis reference for the missile. The basic technique comprises FM modulating the rotational rate of an orbitally driven projected beam chopping spoked reticle. The FM modulation amplitude is chosen to equal the magnitude of the desired angular change of the projected spatially coded axis, while the FM modulation phase is made to equal the direction in which the projected spatially coded axis is shifted. The receiver at the missile interprets the image of the recticle pattern as if the receiver where displaced from the unmodualted first axis position in a direction from beam center as indicated by the modulation phase. Since the missile is controlled to the beam axis center, it follows the coded axis shift.

Technology Creep and the Arms Race: ICBM Problem a Sleeper.

Abstract: In three articles, Science will discuss how the creep of technology affects the arms race The first two articles will deal with the most important current example: first, how ICBM modernization is giving both sides a destabilizing, first-strike capability, and second, how arms control seems to be dealing inadequately with this pressing problem The third article will describe other cases of incremental technical improvements affecting arms control, such as antisatellite research and ballistic missile defense research, which are bringing both sides closer to the antiballistic missile capability they forswore in a 1972 treaty

Angular Motion of Spinning Almost-Symmetric Missiles

Abstract: : An almost symmetric missile is a missile whose zero-spin pitch and yaw frequencies are 'nearly' equal. The angular motion of a spinning almost symmetric missile can be described by five rotating modal vectors. Two of these vectors vanish when the frequencies are equal. Good approximations for modal frequencies and amplitudes are derived for the special cases of near zero spin and spins near pitch or yaw resonance as well as for spins away from these special regions.

Ground-ground anti-tank missile - has target sensor to initiate orientation swivelling about centre of gravity using transverse acting powder charges

Abstract: The ground-ground missile has an electromechanical sensor to detect the target and trigger the homing sequence when above it. The missile can include a series of powder charges producing a transverse manoeuvring action, these charges being fired by the sensor to turn the missile about its centre of gravity so that it points down onto the target. The sensor can also be used to arm the head of the missile. The sensor can include a high density body with a cap to which a contact wire is attached. The sensor is located in a barrel in the missile, and is pref. of the impact type.

Electro-mechanical guidance actuator for a missile

Abstract: In flight guidance of a missile is provided by a plurality of orthogonallyisposed wing panels which can be rotated by a self-centering biased torque producing lever-ball joint assembly. A plurality of solenoids, operatively positioned proximate to a rotary cam member, are individually selectively activated to engage the rotary cam member which inclines the torque producing lever-ball joint assembly and rotates the wing panels in a desired direction.

Stowable nozzle plug and method for air breathing missile

Abstract: A missile with an air breathing gas turbine propulsion engine configured with a translating exhaust plug nozzle to minimize longitudinal length of the engine section.

Safe-arm device for directed warhead

Abstract: A safety and arming device for a directed missile warhead using a rotor hng a plurality of explosive paths therethrough. A central shaft guides axial and rotary movement of said rotor. Missile launch is sensed and unlatches the rotor. Missile launch acceleration causes the rotor to move axially. Receipt of a second signal causes the rotor to rotate, thereby arming the device by aligning the explosive paths and the detonators. Circuit breakers may also be included on the housing and rotor to produce a continuous electrical path for the firing circuits only when the device is armed.

Multiple headed missile system - moves initial- and after-action bodies apart axially before detonation

Abstract: The multiple-headed missile has an explosive initial-action body, particularly a hollow charge, a compression charge or a solid shot. Members (8) are provided to move the bodies (3,4) apart in the axial direction before the first is detonated, typically in the form of a cartridge, or a rocket motor on the first one. The design affords a simple system for protecting the after-action body from the effects of the explosion of the initial-action body.

Rocket missile extending stabilising fins - have sections extended progressively by springs and releasing charges

Abstract: The rocket propelled missile has stabilising fins extended in starting phase step by step. These fins are extended to match the stabilising requirements on launching. The fins are extended according to a specific programme. The fins are held so that they or their actuators do not project beyond the missile circumference. The stabilising fin sections (1, 2, 3) are extended in stages until the whole articulated fin is extended. Each fin section pivoting axis is parallel to missile longitudinal axis. These axes are spring (17) loaded. A folded fin section is released by pyrotechnical delay element which initiates releasing charge of locking bars (25).

Method for increasing the hit probability of jammed missiles and device for carrying out the method

Abstract: A method and device is disclosed for increasing the hit probability of guided missiles exposed to jamming by double or multiple targets. In particular, the missiles are guided by the proportional navigation principle and have a follow-up target-seeking head. With the addition of a plurality of tracking filters, means for performing data analysis and means for performing data control to a conventional missile guidance system, signals from the target-seeking head or the missile may be analyzed to provide recognition of double or multiple target situations. Once recognition of the double or multiple target situation is made, the flow of data for controlling the guidance and target-seeking head follow is corrected to keep the missile permanently on the target.