Showing papers on "Missile published in 1980"

Assessment of Empirical Concrete Impact Formulas

Abstract: Data from 145 recent impact tests of reinforced concrete walls with solid and pipe missiles are used to assess the accuracy of several empirical formulas. For solid missiles, penetration depths greater than six-tenths the missile diameter are predicted by the NDRC formula to within —25%, scabbing is predicted equally well by the NDRC, Bechtel, and Stone and Webster formulas, and perforation is predicted best by the CEA-EDF formula. For pipe missiles, the best overall agreement with data is obtained with the NDRC formulas, using the outside diameter in the penetration equation and the equivalent solid diameter in the equations for scabbing and perforation. The limitations of all of the formulas for impact conditions outside their range of applicability are pointed out. For example, the formulas are inapplicable for highly deformable missiles such as wooden poles and autos and give only approximate results for rotating or irregularly shaped missiles such as fragments from rotating machinery.

Flutter Analysis of Missile Control Surfaces Containing Structural Nonlinearities

Abstract: Missile control surfaces often contain nonlinearities which affect their performance characteristics and flutter boundaries. Analysis techniques accounting for these nonlinearities and an understanding of their potential influence on the flutter mechanism greatly increase the efficiency of the control surface design process. This paper presents such analysis procedures and discusses their application to the investigation of the dynamics of missile control surfaces containing structural freeplay-type nonlinearities. The problem discussed deals with a missile control surface exposed to subsonic flow. Nonlinearities are associated with freeplay in the root support stiffness. Definition of the loads acting on the control surface uses a simplified aerodynamic representation. The basic assumption of this approach is that the lift force is proportional to and in phase with the torsional, or pitch, motion. Both rigid and flexible control surface configurations have been examined with nonlinearities in either one or both of the root pitch or roll degrees-of-freedom.

Perforation of Reinforced Concrete Slabs by Rigid Missiles

Abstract: This paper presents an extension of the penetration theory proposed by the National Defense Research Committee (NDRC). The extension is based on experimental studies, performed over the last few years and covering projectiles with lower impact velocities and larger diameters and weights than originally considered by the NDRC. The missiles are considered to be rigid, that means that no deformation of the missile is taken into account. The paper gives a new expression for the calculation of the perforation thickness for the above mentioned range of missiles and a new formulation of the velocity function is proposed, allowing the estimation of residual velocity after perforation. The new formulation preserves the advantages of the NDRC formula and leaves the basic expression unchanged. The impact time and the reaction force are calculated based on the new velocity function. The results are compared with the experiments.

Aircraft rocket and missile launcher

Abstract: A jettisonable missile launcher pod has support lugs which extend upwardly through a relatively small separate hardback structure to latch into standard release hooks in an aircraft-mounted pylon. The hardback is adjustably attached to the pylon and contains the required high technology electronic gear for the missile system. When the pod is jettisoned, it drops from the release hooks as usual, but the electronic gear remains with the aircraft in the hardback. The hardback is shaped as a thin top section or portion of a conventional launcher pod.

Aerial missile having multiple submissiles with individual control of submissible ejection

Abstract: An aerial missile carrying multiple launching tubes for submissiles in a circular locus about the longitudinal axis of the aerial missile has independent activating means for each said launching tube to pivot the rear discharge end of each launching tube radially outwardly from the aerial missile. Means for ejecting the individual submissile rearwardly from the launching tube are provided. In one embodiment, a single gas generator activates the launching tube and ejects the submissile. Multiple pyrotechnic charges are provided in one embodiment to establish the ejection velocity of the submissile.

Propulsion/control modular booster

Abstract: A modular, apogee-control package is disclosed which can be added to exisg missiles, and which will limit the apogee of the missile trajectory by implementation of thrust vector control (TVC). The package comprises a boost guidance unit, a solid rocket propellant motor, and jet vane TVC.

Missile Aerodynamics - Past, Present, Future

Abstract: Foreword I AM deeply appreciative of the honor of being invited to deliver the Wright Brothers Lectureship in Aeronautics for 1979 in memory of those ingenious aeronautical pioneers who first reduced sustained powered aerial flight to practice. This is the first Wright Brothers lecture devoted to the subject of missiles. While any connection between missile aerodynamics and the Wright Brothers may not be obvious at first glance, there are several important connections. The use of the airplane for the aerial delivery of missiles accounts to a large degree for the extensive current importance of missiles and the engineering and scientific efforts which have gone into the advancement of missile aerodynamics since World War II. Also there is much commonality in the fields of missile aerodynamics and airplane aerodynamics, and each field has benefited from new developments in the other.

Method for guiding missiles

Abstract: In a method for guiding a missile by illuminating the target by means of a laser and tracking the target with a sensor system carried by the missile, the step of illuminating is carried out to illuminate the target by means of the laser for a short period of time, and the step of tracking is carried out with the aid of an electronic optical sensor by causing the sensor to sense the laser light reflected from the target and then locking the sensor onto the target region from which such reflection took place.

Prediction of Aerodynamic Characteristics of Cruciform Missiles to High Angles of Attack Utilizing a Distributed Vortex Wake.

Abstract: : This report describes improved methods for calculating the aerodynamic characteristics of cruciform missiles to high angles of attack. These include a more accurate method of calculating the effects of the vorticity generated by crossflow over the body between the first and second set of fins, an improved fin trailing vortex model, and numerous minor improvements. The improved methods have been incorporated into an existing computer program that computes component forces and moments on a cruciform missile, including effects of arbitrary roll and control deflection.

Passive, recyclable cooling system for missile electronics

Abstract: A cooling system is described which is appropriate to many high performance missiles. The invention comprises heat pipe/thermal diode devices, and a heat storage medium. Heat generated by electronic components of a missile is either conducted to the skin of the missile to be dissipated or is stored internally for later dissipation.

IR radiation-seeker missile jammer

Abstract: Means and method for jamming IR radiation-seeking threat missiles comprising means for generating wavetrains of randomized pulses of radiation of the same wavelengths at which the threat missiles are operating. The apparatus consists generally of radiation-generating means, means for pulse-modulating the radiation-generating means or the radiation itself with a wavetrain of random or pseudo-random pulses, and means for directing the modulated radiation at a target.

Load balancer for multiple loads

Abstract: An apparatus for balancing an asymmetric load of one or more large heavy objects such as missiles and the like including a rotatable horizontally oriented jack screw for moving a block with a lifting eye thereon in a lateral direction. A beam perpendicular to the jack screw holds a fixture to which one or more missiles are attached. Lateral movement of the block in response to rotation of the jack screw serves to balance the load during the hoisting and conveying operation regardless of the number and position of the missiles in the missile holding fixture.

Comparison of simulation and flight-test data for missile systems

Abstract: Simulation models are frequently used to analyze missile performance. These models produce data that must be compared to corresponding flight-test data. This report describes statistical tests usef...

First motion detector

Abstract: An electromagnet sensing device which detects the first axial motion of a ssile relative to its launcher to provide timing information and indicate when the missile first moves axially.

Composite safe and arming mechanism for guided missile

Abstract: An electro-mechanical mechanism is disclosed which controls safety-armingring of an air-launched missile's rocket motor and safety-arming of the warhead. The mechanism has an out-of-line safety pyrotechnic design to maintain the electric firing circuits and explosive train in an open, safe position until a complete sequence of events occurs. Similarly, a second sequence must occur before warhead arming can proceed.

General Purpose Tactical Missile Simulation Program

Abstract: General Purpose Tactical Missile Simulation Program (GPMS) has been developed. This program can be applied to simulating the operation of the tactical missiles pursuing the various targets, such as airplanes, ships and tanks. The GPMS provides with the dynamical models of missile, the dynamical models of target, and many mathematical models of on-board missile subsystems such as sensing systems, control logics and actuator systems. Any missile guidance and control systems can be simulated with selecting and combining the suitable model among many models. Many control elements and operational elements of common use are prepared in function form, so the programming is very easy even if for a complicated control system. This paper describes the construction and functions of GPMS, and shows some examples of simulation.

Aeroload torque simulator

Abstract: OF THE DISCLOSURE The aeroload torque simulator provides torques for either statically or dynamically loading the output shaft of a power servo system such as a missile fin control system. It simulates the aerodynamic torque load developed at the missile fin which varies dynamically in flight.

Missile multiple warhead construction - has distance sensors firing main warhead via time delay after auxiliary warheads

Abstract: The warhead comprises a hollow charge pointing forwards and forming the main warhead, and one or more eccentric auxiliary warheads, typically also hollow charges, on the outside of a central guide sleeve for the hollow charge point of the main warhead One or more distance sensors, which can be cut in and out, fire the auxiliary (7) and main (2) warheads, acting via a time delay on the latter after the former have detonated There is also an impact contact (6), which likewise can be cut in and out, firing the main warhead alone when the sensors are cut out

Airborne frequency-modulation radar and its application to a missile homing head

Abstract: In an airborne frequency-modulation radar designed for the homing head of a guided missile, enhanced resolution both in distance and in velocity is obtained by making use of a solid-state transmitter in conjunction with a frequency-modulating oscillator and by means of a receiver comprising a controlled frequency-shift oscillator.

Missile stowage and launcher system

Abstract: A plurality of missiles stowed within and adapted to be launched from a carrier aircraft, are arranged in cone-shaped clusters, that are in turn nested together to achieve a high density payload. The various clusters are independently rotatable about the conical axes so that individual missiles can be selected at random and moved into a launching position. For this purpose each missile cluster is assembled and secured on an annular support, that in turn is rotatably mounted on an annular bearing structure, wherein each cluster support and associated bearing structure have registerable circumferential gaps congruently disposed with a launching port in an exterior wall of the aircraft. Individual missiles of an inner nested cluster are thus movable, by rotating the associated cluster, into registry with the gaps in adjacent clusters and hence with the launching port and are then transversely and outwardly ejected from the cluster and through the port. The conical clustering of the missiles is used to advantage for high density payload delta-wafer shaped missiles, which are arranged in each cluster so that the longitudinal axes of the missiles lie along the slant of the cone pointing toward the cone apex and the aft ends are disposed in a step-wise circular array around the base of the cone.

Tracking system for monitoring IR self-guided missiles - includes laser producing tracking signal and noise signals to unbalance internal missile guidance system

Abstract: The system includes a laser (1) emitting a beam (2) which passes through a modulator (3) to be reflected by an orientatable mirror (9) towards a missile The beam reflected by the missile is concentrated on a difference measuring detector (12) connected to the control system controlling the rotation of the mirror (9) The modulator (3) creates successive fogging or noise modulations, as well as tracking pulses in the time intervals between the noise modulations USE - Tracking and destruction of missiles

Laser propulsion - 1980

Abstract: An overview of the current government sponsored work in laser propulsion is presented and the NASA program is discussed Attention is given to the overall NASA plan in laser propulsion and the laser rocket engine technology program Some results of an analytical effort at Physical Sciences Inc are presented, as well as results of the NASA/Army Missile Command experimental effort Finally, future plans are briefly summarized

Flight control system for a remote-controlled missile

Abstract: A ground station forming part of a system for controlling the flight of a missile comprises two cascaded computers, the first of these computers generating guidance instructions on the basis of initially available data while the second computer converts these instructions into control signals transmitted to the missile. A receiver aboard the missile translates these control signals into operating commands for missile-borne actuators affecting its course, e.g. motors controlling yaw and pitch through the positioning of aerodynamic surfaces; the responses of the actuators to the operating commands are monitored by negative-feedback loops including error-correcting networks.

Missile guidance mechanism mounting - has fins hinging on sleeves pivoting on bushes fixed to missile body

Abstract: The hinge mounting is for a guidance mechanism, partic. of a missile or flying object, having folding guide fins each on a bracket. These swing out from a rest position inside a chord of the missile outline about a first axis at right angles to this chord into an intermediate position, and from the latter about a second axis into the flight position in a radial plane passing through the lengthwise axis of the missile, being controlled by a sliding member so that they remain permanently in the plane of the chord. Each bracket (2) has a pivot sleeve (31) on which the fin (1) hinges about the first axis (A) in direction P1. The sleeve turns on a bush (28) fixed to the missile body about the second axis (B), and which has a guide slot (29) centred on the second axis, causing the fin to turn on the first axis and the sleeve to turn on the bush.