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Showing papers on "Missile published in 1986"


Book
01 Jan 1986
TL;DR: In this paper, a conference on tactical missile aerodynamics discusses autopilot-related aerodynamic design considerations, flow visualization methods' role in the study of high angle-of-attack aerodynamics, low aspect ratio wing behavior at high angle of attack, supersonic airbreathing propulsion system inlet design, missile bodies with noncircular cross section and bank-to-turn maneuvering capabilities, asymmetric vortex sheding phenomena from bodies of revolution, and swept shock wave/boundary layer interaction phenomena.
Abstract: The present conference on tactical missile aerodynamics discusses autopilot-related aerodynamic design considerations, flow visualization methods' role in the study of high angle-of-attack aerodynamics, low aspect ratio wing behavior at high angle-of-attack, supersonic airbreathing propulsion system inlet design, missile bodies with noncircular cross section and bank-to-turn maneuvering capabilities, 'waverider' supersonic cruise missile concepts and design methods, asymmetric vortex sheding phenomena from bodies-of-revolution, and swept shock wave/boundary layer interaction phenomena Also discussed are the assessment of aerodynamic drag in tactical missiles, the analysis of supersonic missile aerodynamic heating, the 'equivalent angle-of-attack' concept for engineering analysis, the vortex cloud model for body vortex shedding and tracking, paneling methods with vorticity effects and corrections for nonlinear compressibility, the application of supersonic full potential method to missile bodies, Euler space marching methods for missiles, three-dimensional missile boundary layers, and an analysis of exhaust plumes and their interaction with missile airframes

63 citations



Patent
William R. Yueh1
08 Dec 1986
TL;DR: In this paper, a method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position is presented.
Abstract: A method and apparatus for identifying inertial reference unit (IRU) errors in a guided missile employing a multi-mode guidance system and constructing correction terms to recover the missile true position. Discrepancy parameters are introduced to indicate misalignment between missile and launching platform (or ship) inertial frames where the missile onboard executive computer simultaneously processes the data provided from missile onboard sensors and target relevant data uplinked from the launching platform. The discrepancy parameters are employed to construct correction factors used to reduce the discrepancies. This updated missile configuration is then coupled with the target state estimator outputs to reconstruct smoothed line-of-sight (LOS) angles for terminal homing engagement.

52 citations


Patent
03 Feb 1986
TL;DR: In this paper, a sensor is used to detect the position of a target and for detecting the positions of a missile, and a fire control processor is provided that computes a trajectory for the missile to the target and is connected to the sensor to determine any variations between the actual missile position from a computed trajectory.
Abstract: A missile guidance system including a sensor for detecting the position of a target and for detecting the position of a missile. A fire control processor is provided that computes a trajectory for the missile to the target and is connected to the sensor to determine any variations between the actual missile position from a computed trajectory missile position. A transmitter connected to this guidance computer then provides guidance information to the missile. The guidance information includes the missile position relative to the target and enables a processor on board the missile to recompute a new trajectory to the target. This guidance information is transmitted as a single pulse during a predetermined time interval as a periodic update to the missile.

39 citations


Proceedings ArticleDOI
18 Jun 1986
TL;DR: In this article, the authors developed a methodology for the design of autopilots for bank-to-turn missiles, which accommodates the gyroscopic and coriolis cross-coupling between the pitch and the yaw axes that result due to the high roll rates that can be present.
Abstract: The state-space techniques of modern control theory are used to develop a methodology for the design of autopilots for bank-to-turn missiles. The methodology accommodates the gyroscopic and coriolis cross-coupling between the pitch and the yaw axes that result due to the high roll rates that can be present. The design uses the assumption that the roll rate is constant, but not zero, and results in an autopilot structure in which there are cross-couplings between the pitch and yaw channels that are dependent on the roll rate. The autopilot gains are also scheduled as functions of the dynamic pressure. A reduced-order extended Kalman filter, with fixed gains, is used to estimate the actuator states and the commanded acceleration. The performance of an autopilot designed by this methodology was evaluated in a six-degree of freedom simulation using the dynamics of a typical high-performance tactical missile. Excellent performance was obtained in teres of low miss distance and small side-slip.

32 citations


Patent
02 Sep 1986
TL;DR: A relatively inexpensive, high efficiency, detachable thrust vector mechanism is provided for addressing the current shortcomings in the art in this paper, which is used in conjunction with a nautical or aeronautical vehicle having primary propulsion means and at least one fin movable to provide maneuverability, in response to a conventional control system.
Abstract: A relatively inexpensive, high efficiency, detachable thrust vector mechanism is provided for addressing the current shortcomings in the art In the illustrative embodiment, the invention is used in conjunction with a nautical or aeronautical vehicle having primary propulsion means and at least one fin movable, to provide maneuverability, in response to a conventional control system The invention is a detachable thrust vector mechanism comprising auxiliary propulsion means pivotally attached to the missile through connecting means Contact means are provided for transferring bi-directional motion of the fin to the auxiliary propulsion means The mechanism is operable to provide auxiliary thrust for the missile along a thrust vector determined by the control system The invention is effective to provide missile steerage at low speeds, particularly during initial launch and pitchover The mechanism of the present invention falls away during flight to fully exploit the original optimized aerodynamic or hydrodynamic design of the missile The thrust vector mechanism of the present invention conserves the main motor fuel, reduces the initial missile launch signature and effectively increases its range The invention also provides a low cost, disposable mechanism for converting a missile designed for high speed (air-to-air) launches to one adapted for low speed (surface) launches That is, under the teachings of the present invention, existing missiles may be inexpensively retrofit to provide thrust vector control

29 citations


Patent
19 Dec 1986
TL;DR: In this article, a bus is launched from a launch station remote from a target with the bus missile carrying a plurality of sub-missiles, which are arranged to deploy ahead of the bus and are guided to the target under the control of a guidance beam generated in and transmitted from the bus.
Abstract: A missile system and a method of missile guidance in which a bus missile is launched from a launch station remote from a target with the bus missile carrying a plurality of sub-missiles. The sub-missiles are then launched from the bus missile during flight of the bus missile. The sub-missiles are arranged to deploy ahead of the bus missile and are guided to the target under the control of a guidance beam generated in and transmitted from the bus missile.

26 citations


Journal ArticleDOI
TL;DR: In this article, the authors define ballistic and wound ballistic terms, as well as examples of wound ballistics in application, and use them to determine the extent and type of injury from a missile.
Abstract: Ballistics is the study of the natural laws governing projectile missiles and their predictable performances, and wound ballistics is the study of a missile's effect on living tissue. A knowledge of these topics is essential to determine the extent and type of injury from a missile. The type of missile can often be determined by radiography. The caliber can be measured directly if the bullet is close to the x-ray plate and the x-ray tube is at least six feet from the film. Changing these distances can result in a maximum magnification of the bullet image of 20%, and the exact amount can be calculated using a formula provided. Definitions of ballistic and wound ballistic terms are provided, as are examples of wound ballistics in application.

23 citations


Patent
08 Oct 1986
TL;DR: In this paper, a guidance apparatus for guiding a missile (18) to a target (20) by a beam (16) is disclosed, which includes a device (12) for projecting the beam, the orientation of which controls the flight path of the missile, and a circuit for generating a signal when the missile is in a predetermined spatial relationship (e.g., the center coded portion) with respect to said beam.
Abstract: A guidance apparatus (10) for guiding a missile (18) to a target (20) by a beam (16) is disclosed. The apparatus (10) includes a device (12) for projecting the beam (16), the orientation of which controls the flight path of the missile (18). The missile (18) includes a circuit for generating a signal when the missile (18) is in a predetermined spatial relationship (e.g., the center coded portion) with respect to said beam (16). When such signal is generated, the angular position of the missile with respect to the target is determined. This positioned relationship is then provided to ground based circuitry (56, 58 and 60) which forms a part of apparatus (10) and which adjusts the orientation of the beam (16) to reduce the angular separation of missile and target.

20 citations


Patent
31 Oct 1986
TL;DR: In this article, a system for modifying the demand component to compensate for the lateral acceleration generated by the coupling of the acceleration along its longitudinal axis and the angle between the body of the missile and the sightline is presented.
Abstract: In known guidance systems, the missile is guided by a control loop which includes the missile and a ground-based tracker, the tracker determining the relative positions of the missile and target and hence the lateral acceleration to be applied to the missile. However, these systems do not take account of the lateral acceleration generated by the coupling of the missile acceleration along its longitudinal axis and the angle between the body of the missile and the sightline, as in cases where acceleration is small the effect is insignificant. Described herein is a system for modifying the demand component to effect compensation for the lateral acceleration component imparted to the missile by virtue of its angle of incidence. This is accomplished by modifying the demand component in accordance with a stored predetermined time-varying gain term thereby to effect compensation of the lateral acceleration component imparted to the missile by virtue of the angle of incidence of the missile.

17 citations


Patent
10 Jan 1986
TL;DR: In this paper, a modified toggle lever system is used to accelerate the missile during the propelling stroke, with the lever system being braked by the spring at the end of the stroke.
Abstract: A weapon for propelling missiles, such as arrows, quarrels and the like, which looks like a sub-machine gun and is characterized by a compact missile-propelling assembly which is co-planar with the stock, contrary to the long bow which extends transversely of the stock of a conventional cross-bow. The missile-propelling assembly includes a modified toggle lever system which is spring actuated and is arranged to constantly accelerate the missile during the propelling stroke. The lever system is braked by the spring at the end of the propelling stroke, thereby avoiding any noise.


Journal ArticleDOI
21 Mar 1986-Science
TL;DR: The method for calculating the cost-exchange ratio is illustrated by applying it to a space-based infrared laser system and it should be straightforward to apply it to other proposed systems.
Abstract: Orbiting platforms carrying infrared lasers have been proposed as weapons forming the first tier of a ballistic missile defense system under the President's Strategic Defense Initiative. As each laser platform can destroy a limited number of missiles, one of several methods of countering such a system is to increase the number of offensive missiles. Hence it is important to know whether the cost-exchange ratio, defined as the ratio of the cost to the defense of destroying a missile to the cost to the offense of deploying an additional missile, is greater or less than 1. Although the technology to be used in a ballistic missile defense system is still extremely uncertain, it is useful to examine methods for calculating the cost-exchange ratio. As an example, the cost of an orbiting infrared laser ballistic missile defense system employed against intercontinental ballistic missiles launched simultaneously from a small area is compared to the cost of additional offensive missiles. If one adopts lower limits to the costs for the defense and upper limits to the costs for the offense, the cost-exchange ratio comes out substantially greater than 1. If these estimates are confirmed, such a ballistic missile defense system would be unable to maintain its effectiveness at less cost than it would take to proliferate the ballistic missiles necessary to overcome it and would therefore not satisfy the President's requirements for an effective strategic defense. Although the method is illustrated by applying it to a space-based infrared laser system, it should be straightforward to apply it to other proposed systems.

Patent
Guy Mace1, Andre Anglard1, Andre Insa1
20 Feb 1986
TL;DR: In this article, a bearing shoe connected to a supporting structure by links articulated so as to form a deformable parallelogram was used to determine the position and angular speed of the missile when the thrust of the shoe ceases.
Abstract: A missile launcher comprises a supporting structure a bearing shoe connected to a supporting structure by links articulated so as to form a deformable parallelogram. A fluid pressure cylinder releases a locking system securing the missile on the structure and actuates the links in a direction causing the shoe to push the missile away. The shoe has a sufficient length for determining the distance between the missile and the aircraft at the end of its stroke and also the angular position of the missile. With that arrangement, the position and angular speed of the missile when the thrust of the shoe ceases may be accurately determined.

Patent
24 Feb 1986
TL;DR: In this article, a velocity controller for a ramjet missile, having a supersonic inlet proximate the peripheral skin thereof for admitting air to a combustion zone of a Ramjet engine, is comprised of a variable pitch cover disposed in pivotable engagement within the inlet and an actuator in operative engagement with the cover for adjustably positioning same over an angular range.
Abstract: A velocity controller for a ramjet missile, having a supersonic inlet proximate the peripheral skin thereof for admitting air to a combustion zone of a ramjet engine, is comprised of a variable pitch cover disposed in pivotable engagement within the inlet and an actuator in operative engagement with the cover for adjustably positioning same over an angular range and thereby modulating airflow for the purpose of controlling flight characteristics and, principally, velocity of the missile. A sensing system is provided for detecting a dynamic flight parameter indicative of velocity of the missile and generating an output characteristic thereof for controlling the actuator and, in turn, the pitch of the cover. Methods for improving the flight performance of both solid fuel ramjet missiles and ducted rocket missiles are also disclosed herein.


Patent
06 May 1986
TL;DR: In this article, a beam-rider guidance is provided in which a continuous wave or pulsed laser output is formed into a gaussian cross section or similarly shaped beam and projected to one offset sensor, or to two sensors located on opposite sides and as far from the missile's roll axis as possible.
Abstract: In accordance with this invention, a missile referenced beamrider guidanceink is provided in which a continuous wave or pulsed laser output is formed into a gaussian cross section or similarly shaped beam and projected to one offset sensor, or to two sensors located on opposite sides and as far from the missile's roll axis as possible. The rolling missile motion amplitude modulates the received signal and the amplitude of the modulation is a measure of the missile's distance from beam axis. The phase of the modulation provides the direction to beam center.

01 Aug 1986
TL;DR: In this paper, the authors used wind tunnel tests to predict the aerodynamic characteristics of typical cruciform configurations over a wide range of angles of attack, fin deflection angles, roll angles, and Mach numbers.
Abstract: : A missile-fin data base for a wide range of configurations and flow conditions was obtained. These data were incorporated into an engineering method for predicting the aerodynamic characteristics of typical cruciform configurations over a wide range of angles of attack, fin deflection angles, roll angles, and Mach numbers. This report documents the test programs, describes the new code, MISSILE 3, and presents comparisons of independent experiment and predicted results to verify the code. A user's manual for the code is included. Keywords: Missile aerodynamics; Aerodynamic empirical techniques; Missile aerodynamic loads; Wind tunnel tests; Computer codes.

Patent
14 Aug 1986
TL;DR: In this paper, a tube-launched, optically guided wire-controlled missile is described, where pitch and yaw channels with time variable gains having different transfer functions are provided.
Abstract: Launcher for a tube-launched, optically guided wire controlled missile. Inhe electronic circuitry that forms part of a feedback servomechanism there are provided pitch and yaw channels with time variable gains having different transfer functions. Optionally there are further provided at least two different generators of signals for gravity bias with automatic means for selecting between them in accordance with the physical characteristics of the missile.

01 Jan 1986
TL;DR: In this paper, an evaluation of prospective missile applications for noncircular cross-section bodies, and of recent developments in bank-to-turn missile configuration aerodynamics are discussed, as well as study results obtained for bodies with elliptical and square cross sections and with variable cross sections.
Abstract: An evaluation is made of prospective missile applications for noncircular cross section bodies, and of recent developments in bank-to-turn missile configuration aerodynamics. The discussion encompasses cross-flow analysis techniques, as well as study results obtained for bodies with elliptical and square cross sections and with variable cross sections. Attention is given to both the performance advantages and the stability and control problems of bank-to-turn missile configurations; the aerodynamic data presented for monoplanar configurations extend to those incorporating airbreathing propulsion systems.

Patent
15 Dec 1986
TL;DR: In this paper, a method and apparatus for projecting a laser beam for communication or guidance purposes where transmitted energy goes directly to a receiver area without requiring services of slewing or tracking devices is presented.
Abstract: A method and apparatus for projecting a laser beam for communication or guidance purposes wherein transmitted energy goes directly to a receiver area without requiring services of slewing or tracking devices. The energy is precisely directed from a laser transmitter on a missile toward a receiver at a tracking area. By directing the laser energy from a source on the missile during flight and by performing phase conjugating amplification of this laser energy at a tracking area station, atmospheric distortions are removed from the return energy and beam broadening is limited only to the negligible effects of diffraction broadening of the return energy, with the laser return beam being directed almost exclusively back to the missile.

Journal ArticleDOI
TL;DR: In this article, a tradeoff between radome compensation and wing size for a homing-missile is discussed. But the tradeoff is not specifically related to guidance performance.
Abstract: The aerodynamic configuration of a homing missile is usually based on aerodynamic studies against the spectrum of threats to be engaged The most "aerodynamically efficient" missile is often selected from single fly-out studies not specifically related to guidance This paper delineates a tradeoff related to guidance system performance that can affect the aerodynamic configuration This tradeoff is between radome compensation and wing size It is shown that radome compensation can be used to reduce wing size, and thereby a missile's drag and weight A quantitative example is presented for a representative design

Journal ArticleDOI
TL;DR: In this paper, an analytical model was developed to define the adverse effects that missile exhaust plumes have on radio communications with the missile, based on highly refined computations of the nozzle and plume chemistry and flow fields.
Abstract: An analytical model has been developed to define the adverse effects that missile exhaust plumes have on radio communications with the missile. The computational model, RD3D, describes the three-dimensional propagation of electromagnetic waves through an ionized plume by refraction, the formation of blackout or dead zones, and dual-path contributions by diffraction from the fields outside the dead zone to the missile. The model relies on highly refined computations of the nozzle and plume chemistry and flowfields to establish the electron density distributions in the plume. These distributions are collapsed to a closed-form plume model for use in RD3D, a technique that contributes to computational time savings and increased accuracy. Results show the distortion of an electromagnetic wave as it encounters the plume and the received signal strength at the missile antenna. In order to verify the model and the individual components, comparisons are made to a number of classical refraction and diffraction cases, subscale missile diffraction tests, and full-scale missile development flight data. Results indicate refraction plays only a minor role in the received signal strength, while diffraction around an opaque circular disk may closely approximate the final results for motor propellants having high alkali content.


Proceedings ArticleDOI
18 Jun 1986
TL;DR: In this article, the authors apply optimal control and filtering theory to controller design for a bank-to-turn missile operating under CLOS guidance, based on two identical single-plane compensators.
Abstract: Application of optimal control and filtering theory to controller design for a bank-to-turn missile operating under CLOS guidance is described. One approach is based on two identical single-plane compensators. The second problem formulation involves direct choice of lift force magnitude and orientation. The effect of constraining the roll rate is discussed for both fixed-and variable-wing-angle configurations.

Patent
04 Aug 1986
TL;DR: In this article, an integral cooling system for high temperature missile structures which is essentially a passive cooling system integrated into the missile structure is described, which ejects an evaporative material carried in the missile's outer skin and cools the missile as it flows along the outer surface thereof.
Abstract: An integral cooling system for high temperature missile structures which is essentially a passive cooling system integrated into the missile structure. An evaporative material carried in the missile structure is ejected by vapor pressure through openings in the missile's outer skin and cools the missile as it flows along the outer surface thereof.

01 Jan 1986
TL;DR: In this paper, an account is given of methods for the estimation of a wing-body-tail missile configuration's aerodynamic performance by means of the "component buildup" method, in which the overall aerodynamic loads for an airframe are built up from the assumed characteristics of isolated airframe components and then subjected to additional loads generated by component interference.
Abstract: An account is given of methods for the estimation of a wing-body-tail missile configuration's aerodynamic performance by means of the 'component buildup' method, in which the overall aerodynamic loads for an airframe are built up from the assumed characteristics of isolated airframe components and then subjected to additional loads generated by component interference. Attention is given to the cases of missile airframes in steady flow at arbitrary angles of attack and bank; the unifying thread of the present treatment is slender body theory, together with its nonlinear extensions through the equivalent angle-of-attack concept. The estimation of the forces and moments acting on each of the fins is emphasized, so that control cross-coupling effects as well as longitudinal and lateral directional effects can be determined.

Patent
28 Apr 1986
TL;DR: In this article, a military tank is equipped with an armored box structure in the space nolly occupied by the gun turret and a lid on the box structure is raised to an inclined position suitable for the firing of a missile carried on the lid undersurface.
Abstract: A military tank is equipped with an armored box structure in the space nolly occupied by the gun turret. A lid on the box structure is raisable to an inclined position suitable for the firing of a missile carried on the lid undersurface. As the missile is fired an explosive-charged line attached to the missile rear end is drawn out of the box structure onto the terrain (along the missile line-of-flight). By exploding the line charges it is possible to detonate enemy land mines in the vicinity of the charged line.

Journal ArticleDOI
TL;DR: The drive for increasingly accurate missile guidance systems has long been a principal characteristic of the arms race as discussed by the authors. But negotiated restrictions on accuracy could go a long way toward curbing the threat of nuclear war.
Abstract: The drive for increasingly accurate missile guidance systems has long been a principal characteristic of the arms race. But negotiated restrictions on accuracy could go a long way toward curbing the threat of nuclear war.