Showing papers on "Missile published in 1968"

Infrared detection of fatigue cracks and other near-surface defects.

Abstract: This paper describes a noncontacting, nondestructive inspection system that can rapidly locate, in real time, the position and extent of fatigue cracks in aircraft and missile structures. The automated ir system described was developed for the USAF for use in their Sonic Test Facility at Wright-Patterson AFB. This facility is capable of subjecting large aircraft or missile structures to the intense sound fields experienced in actual flight or launch. In addition to presenting the basic concepts of the method, this paper (1) describes briefly the design of the system that was developed for the USAF, (2) discusses test results, and (3) presents conclusions and indicates future applications of the technique.

Rolling dual mode missile

Abstract: In a rolling missile a seeker system which is responsive to two forms of energy emanating from a target. The system has the capability to switch between guidance modes during its path towards its intended target.

Optimal biased proportional navigation

Abstract: Proportional navigation has frequently been used for the guidance of interceptor missiles. When such missiles are operated outside the atmosphere, since a velocity change can be accomplished only by the expenditure of propellant, it is important that any path correction be achieved efficiently. In this correspondence, it is shown that the addition of an appropriate bias term to a proportional navigation guidance equation allows an interceptor missile to attain an efficiency which can be made to approach that of an optimum system.

Missile guidance system using an injection laser active missile seeker

Abstract: A missile guidance system utilizing an integrated active missile infrared eker including an injection laser transmitter, a semiconductor detector and a conical scanning acquisition and guidance system.

Optical range resolution system

Abstract: Disclosed is improved sensor apparatus for guidance systems, and the sensor apparatus includes means for receiving light reflected from a target and for processing this light to provide steering signals to the missile guidance and control mechanism; more specifically, the sensor apparatus includes means for receiving a single pulse of light reflected from the target and for forming a two-dimensional image therefrom, quantizing the data from the image, and re-forming the quantized data into a straight-line image from which a time-dependent signal is generated to be input to the missile control mechanism.

Data conversion and control system

Abstract: A data conversion and control system comprising an input and an output section, which function to establish compatibility between an inherently analog missile fire control system or the like and a general purpose digital computer and thereby form a closedloop, digital type fire control system. More specifically, means are provided at the input to the digital computer for converting all of the input data signals from the fire control system, regardless of their form, into a digital format acceptable by the computer and, moreover, such conversion operations are performed accurately, in reduced data conversion time. Also, means are provided at the input to the computer for making, where necessary, determinations of the algebraic sign of the input analog data signals and of the angle of input synchro data signals, for later use in the digital computer. At the output of the computer, means are provided to accept the digital outputs therefrom and convert them, where appropriate, into the various types of control signals normally associated with the missile fire control system. The present invention also provides for connecting the computer in a novel end-around test mode for the purpose of checking that both the input and output sections of the proposed data conversion and control system are operating properly. The proposed data conversion and control system of the present invention is particularly adapted for use with the fire control system for the Talos missile and provides a more accurate control of the doppler frequency guidance control signal communicated, by the fire control system, to the missile, in such a manner that there is a quicker acquisition of the target, by the missile.

Electronic countermeasure system

Abstract: A countermeasure method and apparatus for use by two mutually cooperating aircraft against a radar-homing anti-aircraft missile, and including the steps of transferring doppler shifted radar signals received at a respective one to the other of the two mutually cooperating aircraft, and retransmitting the transferred radar signals toward the homing missile, thus simulating a target having the doppler characteristics of each of the two aircraft and further having a centroid located between the two aircraft.

Missile command system

Abstract: A command-type guided missile system wherein a gunner launches a missile and guides it during flight solely by maintaining the cross hairs of his sight reticle trained on the target. A source on the missile emits, rearwardly to the command station, modulated (coded) infrared (IR) light. Visible light from the target and IR light from the source are received at the command station through a common optical system. A beam splitter then sends the visible light to the gunner''s sight and sends the IR light through a nutator to a quadrant-type IR detector, which is coupled to the gunner''s sight so that the axis of symmetry thereof is always aligned on target. Error signals from the detector indicate the direction of deviation of the image of the source from the axis of the detector and hence the direction of deviation of the missile from the gunner''s line of sight to the target. A transmitter, responsive to the error signals, sends modulated IR control signals to the missile to correct its flight path.

Pulse phase modulated servoactuator

Abstract: Pulse phase modulated servoactuator for use as in flight control of missiles and the like characterized in that the servoactuators which turn the respective missile fins to control the pitch and the yaw of the missile are under the control of valves which are operated in or out of phase with a main control valve.

Body motion decoupler

Abstract: 1,206,745. Radio navigation. GENERAL DYNAMICS. 17 Feb., 1969 [15 March, 1968], No. 8559/69. Heading H4D. A body motion decoupler is described which is an integral part of a proportional navigation guidance system for a vehicle such as an aerial missile 14, Fig. 1. Energy from a radar 10 is reflected from a target 12 to receptor means 16 which are rigidly affixed to the missile 14. In a first embodiment, for a rolling missile, a pair of receptors 20, 22, Fig. 2, such as circularly polarized slip-cast fused silica polyrods, are mounted on the missile body 18 and their outputs are fed directly to respective microwave mixers 24, 26. Separate phase shifters 28, 30 fed by an oscillator 32 and by a phase shift driver 34 are respectively coupled with the mixers 24, 26, which feed into a summer 48. Mounted within the missile body is spinning magnetized free gyroscope 36 around which is provided a position sensing coil 38. The e.m.f. generated in the coil 38 is fed through a gain and phase adjuster 40, a modulator 42, and a filter 44 to the phase shift driver 34. A precession coil 46 is also provided around the gyroscope 36. Output from the summer 48 is fed through an amplitude detector 50, a filter 52, a modulator 54, a phase and gain adjuster 56, and an amplifier 58 to the precession coil 46. Output from the phase and gain adjuster 56 is also fed to the missile control system (not shown). A Hall-effect generator 60 fed by a direct current and by the gyroscope magnetic flux is coupled to both the modulator 42 and the modulator 54 to vary their outputs in accordance with the strength of the flux. In operation, the target angle data #-# (Fig. 1) is derived from the phase difference of the target signals at the receptors 20, 22. The e.m.f. induced in the coil 38 by the spinning magnetized gyroscope 36 is indicative of the position of the gyroscope relative to the missile body 18 and also of any missile body motion # which occurs. It is fed into the circuitry of Fig. 2 and is utilized, together with the receptor outputs, to precess the magnetized gyroscope 36 by inducing a field in the precession coil 46. By properly providing near-unity gain between the coil 38 and the phase shifters 28, 30, any body motion sensed by the fixed body receptors 20, 22 can be cancelled by the body motion sensed by the coil 38 from the magnetized gyroscope 36. The error output from the phase and gain adjuster 56 will therefore be proportional only to the missile to target line of sight rate of change #. In a second embodiment (Fig. 3, not shown), for a non-rolling missile, four fixed receptors are mounted at 90 degree intervals around the periphery of the missile body, and are grouped into two pairs of diametrically opposed receptors. Each pair of receptors is associated with a pair of microwave mixers, a pair of phase shifters, an oscillator, and a phase shift driver. The output of the gyroscope position sensing coil is fed to a gain and phase adjuster, and is then split into two channels, one for each phase shift driver. The outputs of the four microwave mixers are fed to a summer, which is followed by circuitry as in the first embodiment for deriving an error output and a precession coil signal.

An Experimental Investigation of the Interference Effects Due to a Lateral Jet Issuing from a Body of Revolution Over the Mach Number Range of 0.8 to 4.5

Abstract: : A research study currently being conducted by the U S Army Missile Command is aimed at developing a technique for predicting the aerodynamic characteristics of missiles that use lateral or transverse jets as the control system As a part of this study, an experimental test program was conducted with the use of a body of revolution with a lateral jet located at several body locations over the Mach number range from 08 to 45 The jet pressure ratio was varied between 0 and 100 in increments of 20, and both slots and circular nozzles were tested The data are presented in plots and tabular form In addition, short descriptions of two other approaches are also presented These approaches are compared with the experimental data and show agreement with 10 to 16 percent

Auxiliary rocket apparatus for installation on a missile to impart a roll moment thereto

Abstract: An auxiliary rocket system for imparting a roll to a missile employing a unitary dual nozzled rocket motor. The dual nozzled rocket motor comprises a rocket tube containing a propellant grain of the type having internal burning surfaces, such as a central bore or the like, by which the propellant gases are communicated directly to both ends of the tube. Canted nozzles are affixed over the ends of the tube. The unitary dual nozzled rocket motor is mounted in a diametric disposition athwart the cylindrical body of the missile, with the canted nozzles directed in the same circumferential direction about the missile body.

Adaptive missile control system incorporating a supervisory loop

Abstract: An adaptive missile control system having a supervisory loop operative during high speed and low altitude of the missile in which high dynamic pressures are effective on the control surfaces requiring small deflection actuation of the control surfaces which supervisory loop is inoperative during low speed and high altitudes of the missile to provide adaptive control to the control surfaces for equally effective missile guidance control in accordance with the speed of the missile and the density of the air through which it travels.

Closed breech launch tube and valve means therefore

Abstract: A closed breech launch tube for elongate rocket powered missiles including a source of high-pressure air or gas and a rocket blast actuated valve to suddenly release a large quantity of such air or gas into the space behind the missile to assist its expulsion from the launch tube.

Method of and system for training in firing guided missiles from a mobile platform

Abstract: In a method of and device for training in firing guided missiles from a mobile platform, both a device for generating a spot simulating a trace of the missile, and the eyepiece of an aiming device, are made unitary with said platform, an image of the real landscape is gyroscopically stabilized in relation to the platform, and an image of the spot simulating a trace of the missile is superimposed on the landscape image by introducing the spot image into the eyepiece of the aiming device.

Missile Wounds Since the Second World War

Abstract: MAY I express my deep appreciation and that of my colleagues in the Royal Army Medical Corps for the honour the Committee of Management has done to us in inviting me to give this address on the 25th anniversary of the loss of Alex Simpson-Smith (Fig. 1), talented surgeon, war-time Lieutenant-Colonel, Royal Army Medical Corps and wartime colleague. His loss was part of the heavy price our country paid to buy the peace it has since worked so hard to maintain in this troubled world.

Head-coupled missile-aiming device

Abstract: A device having multiple sensors which provide a voltage, responsive to the movement of the head of an aircraft pilot, proportional to an angle from the axis of the aircraft to align the tracking unit of a missile with a target to permit firing of the missile when the aircraft cannot be aligned with the target.

Missile launching apparatus

Abstract: A rocket powered missile and cooperating launching tube from which the missile can be catapulted at high initial velocity. The missile includes a hollow fuselage section which is telescopingly fitted over a launching tube open at its forward end and closed at its rearward end. Stabilizing fins and rocket motors are provided on the fuselage section, and a gas generator is provided toward the forward end of the section to supply sufficient gas pressure within the launching tube to launch the missile. Prior to launching, the missile is held on the launching tube by shear pins. Ignition of the gas generator pressurizes the launching tube so that the resultant force on the shear pins exceeds their shear strength, whereupon the missile is launched, and the rocket motors are ignited to propel the missile in its flight.

Flueric arming device

Abstract: A device for arming an explosive missile. Fluid pressure for operation of the device is provided by ram air, which drives a flueric oscillator. A count of the output cycles of the oscillator determines the distance through the air that the missile has travelled. When the count reaches a predetermined point, unless other conditions inhibit arming, a detonator is armed.

Optimal Terminal Guidance of an Air-to-Surface Missile

Abstract: An optimal guidance law for the linearized equations of an air-to-surf ace missile is constructed. This guidance law is based on information supplied from an inertial platform and a noisy TV tracker. The mean square miss distances of missiles respectively using the optimal guidance law, pursuit guidance, or proportional guidance are compared. This comparison is made for typical initial position and velocity errors, and a variety of system parameter variations, and nominal terminal trajectories. The mean-square miss distance in each case was obtained from a computer solution of the matrix Riccati equation for the covariance matrix of the state vector of the linearized missile equations. I. Introduction T HE aim of this paper is to study the practicality of using linear stochastic optimum control theory to design a guidance system for the terminal guidance of an air-to-surface missile (ASM). The design of the best possible guidance system for a missile is an intriguing objective. The design of an exactly optimum guidance system for a missile governed by nonlinear equations with random system and sensor errors is beyond the scope of presently existing theory. However approximation of the nonlinear missile equations by linearized equations and the design of an optimal guidance system for the linearized missile equations offers a possibility for improved performance. In this paper the details of constructing such a guidance system for the terminal guidance of an air-to-surface missile are carried out. The air-to-surface missile is assumed to be equipped with both an inertial platform and a television (TV) tracking system. Random system errors due to winds and random sensor errors in the tracker are assumed to be present. A blind zone near the target in which the tracker cannot see the target due to the target filling the entire TV screen is considered. The performance of the linearized optimal guidance system, pursuit guidance, and proportional guidance are compared by computing for each system the mean square position deviation perpendicular to a given nominal trajectory at the time this trajectory hits the target.

Self monitoring strike system

Abstract: A missile includes a detachable data collection and return element (CRE) which separates from the missile at an appropriate point in its trajectory at, for example, the apogee, continues to collect data with respect to the environment and the missile itself (including confirmation of its own burst and also bursts of other missiles in its salvo). Such CRE unit either relays instantly or stores and relays back upon command when its trajectory brings it within range of an intelligence collecting or command station which may be located at a great or safe distance from the scene of destruction. When the missile trajectory is ballistic (for example in a typical ICBM or IRBM case) then the CRE unit carries a propulsion module capable of providing enough additional boost to place it in an orbit or longer trajectory such that it will be brought back into suitable position for retransmission of collected data. In the case when the missile trajectory is orbital the CRE unit needs no propulsion and in such case continues on in its initial orbit after the warhead is deboosted to the target. In some cases the CRE unit may be used as a moving reference point from which signals are transmitted to the warhead for accurate control of a flight path to the target.