WO1983003894A1 - Systeme de guidage de projectiles en fin de trajectoire - Google Patents

Systeme de guidage de projectiles en fin de trajectoire Download PDF

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Publication number
WO1983003894A1
WO1983003894A1 PCT/US1983/000585 US8300585W WO8303894A1 WO 1983003894 A1 WO1983003894 A1 WO 1983003894A1 US 8300585 W US8300585 W US 8300585W WO 8303894 A1 WO8303894 A1 WO 8303894A1
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WO
WIPO (PCT)
Prior art keywords
weapon
target
projectile
antenna
missile
Prior art date
Application number
PCT/US1983/000585
Other languages
English (en)
Inventor
David Dillon Lynch, Jr.
William Holden Bell
Original Assignee
Hughes Aircraft Company
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hughes Aircraft Company filed Critical Hughes Aircraft Company
Priority to DE8383901682T priority Critical patent/DE3380528D1/de
Publication of WO1983003894A1 publication Critical patent/WO1983003894A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/305—Details for spin-stabilized missiles

Definitions

  • This invention relates to weapon systems, and more specifically to weapon systems which track maneuvering targets and launch terminally guided projectiles toward targets.
  • One type of weapon system which is intended to destroy enemy ground-based or airborne targets uses as weapons unguided projectiles or missiles against targets with relatively low target acceleration capability.
  • Other systems have been developed which require a means for tracking the target, a means for tracking a projectile or missile initially aimed at the target, and a means for reducing or eliminating the miss vector between the target and the projectile or missile.
  • the means for reducing or eliminating the miss vector provides guidance to the projectile or missile so that the projec ⁇ tile or missile will proceed to either hit the target directly or explode in such close vicinity to the target lethal zone so as to fatally damage the target.
  • Most anti-airborne and anti-ground based target weapon systems provide continuous projectile or missile trajectory correction whereby information is sent to the projectile or missile at some predesignated data rate, so as to alter the course of the projectile or missile, and energy
  • M resources of the projectile are used throughout the course of the flight of the projectile or mis ⁇ ile, or for some relatively lengthy terminal phase of the flight of the projectile, to maneuver the projectile or missile to within the lethal zone at the end of the flight of the projectile or missile.
  • guidance and control systems on board the missile are often actively employed in obtaining information about the target and/or computing corrections to its own flight path. Such guidance and control systems on board the missile greatly increase the cost of designing, manufacturing, testing, and maintaining the missile.
  • the POLCAT concept of weapon delivery employs a gun-launched anti-tank weapon with terminal trajectory correction using a semiactive guidance technique and impulse control.
  • the POLCAT weapon system concept employs a frame-fixed target seeker for guidance and a single-impulse applied at the center of gravity normal to the longitudinal axis of the weapon for trajectory correction.
  • the system operates by firing a missile, in a manner similar to that of a conventional gun system, when a target is engaged.
  • an illuminator in the missile transmits pulsed radiation with a narrow radiation beam throughout the flight, which is required because ground targets, in general, do not have sufficiently intense or discrete signature.
  • Correction of the missile trajectory is initiated when a line-of-sight control angle is determined which indicates an increasing miss of the target.
  • * near misses are controlled close to the target and larger deviations are controlled further from the target, because a threshold angle for trajectory control is a constant value.
  • the missile incorporates a forward-looking receiver that determines the pertinent angles to the target, so as to provide data to alter the trajectory of the missile.
  • the DRAGON missile system is a light-weight system designed to be carried by a foot soldier and fired against tanks or other targets within an approximate range of
  • the system con ⁇ sists of a cylindrical missile, a portable launcher for firing the missile, a sighting means or "tracker” for visually following the missile in flight after launch, and appropriate electronic means for correcting the flight path of the missile during the flight from the launcher to the target.
  • the missile is fired from a tubular launcher after the launcher is aimed at the designated target.
  • the missile is required to be of a
  • OIISS proper aerodynamic configuration and must rotate about its longitudinal axis in flight to maintain flight stability.
  • the rotation, as well as aerodynamic stability of the missile is provided by fins located in the aft area of the periphery of the missile.
  • Guidance of the missile during flight is provided in the following manner. When the missile is launched, the soldier who fired the weapon sights the missile through an optical viewer throughout its flight to the target. The course of the missile is automatically corrected in flight by keeping the view of the missile as near as possible to the cross hairs of the optical viewer through which the soldier sights the missile and computing the deviation of the missile from its course to the target.
  • the system is designed to keep the missile on a direct line-of-sight to the target, rather than having a fixed trajectory from the point of launch to a correction point near the target.
  • the missile is kept on course by discharging (by explosion or detonation) small "thrusters" or jets which are built into the periphery of the missile from front to rear and discharged at an angle to the longitudinal axis of the missile.
  • the timing and direction of application of the thrusters determine the direction of motion of the missile throughout the flight of the missile.
  • the thrust- ers are fired electronically in the following manner.
  • a light source is mounted in the tail of the missile.
  • the beam of light from the light source impinges on an optical detector in the tracker component which senses whether the missile is above, below, to the right, or to the left of the line-of-sight from the tracker to the target.
  • a signal is sent over a wire to the missile to fire one or more of the thrusters at a desig ⁇ nated time and in a designated sequence so as to correct for deviations of the missile from the line-of-sight.
  • the wire over which the signal is transmitted is wound on a spool, which is mounted on the rear of the missile, and the wire feeds out as the missile moves toward the target and maintains the connection between the tracker and the missile throughout the flight of the missile.
  • the cost goal of the weapon round is $2,000-$2,500 and for the tracker of the missile is $8,000-$10,000, according to Aviation Week & Space Technology, "Program Slip Delays Export of Dragons," February 3, 1975.
  • the advantage of the present weapon system invention in relation to prior art ground-based or airborne weapon systems is the ability to provide highly accurate perfor- mance against maneuvering airborne or ground targets with the use of a relatively inexpensive artillery launched round, for example.
  • the need for an expensive weapon and the control thereof through the entire course of flight of the weapon is eliminated.
  • the miss vector between the weapon and the target is deter ⁇ mined as a function of predetermined ballistic-trajectory computations and the position of the target is determined by radar tracking of the target.
  • the miss vector is reduced during the terminal stage of flight of the weapon by sending a single signal to the weapon to fire thrusters located on the periphery of the weapon.
  • the angular orientation of the weapon governs the timing and sequence of the firing of the thrusters so as to force the weapon toward the target.
  • the angular orienta ⁇ tion of the weapon is determined from the transmission of beacon signals from the rear of the weapon via a polarized antenna which is canted by a few degrees with respect to the longitudinal axis of the weapon.
  • a one-time correction signal is sent from a ground-based fire control system causing thrusters located on the periphery of the weapon to rapidly detonate in a particular sequence, so as to force the weapon to destroy the target by exploding within a lethal zone surrounding the target.
  • the timing of the correction signal is based upon an estimated position of the weapon (as computed from bal ⁇ listics), an estimate of the angular orientation of the weapon (as derived from signals transmitted from a canted antenna located at the rear of the weapon), and an estimate of the position of the target at the end of the trajectory of the weapon (as derived from radar tracking).
  • the purposes are accomplished with the unique combination of a fire control system with a radar target tracking system, and a weapon having small thrusters mounted on the periphery thereof and with a small beacon transmitter which is tracked by the ground-based radar system.
  • a terminal maneuver is executed by the weapon by sequentially firing small thrusters located around the periphery at the center of gravity of the weapon. Accordingly, it is a general purpose of the present invention to provide an improved weapon delivery system.
  • Another purpose of the invention is to provide a target weapon system which uses a relatively inexpensive weapon.
  • a further purpose of the invention is to provide weapon system having day-night and zero visibility con ⁇ ditions (including fog, smoke, and haze), all-weather capability.
  • Still another purpose of the invention is to provide an improved anti-airborne or anti-ground target weapon delivery system.
  • FIG. 1 illustrates typical battlefield encounters wherein the weapon system is employed, depicting a tank with a ground-based fire control system (including a radar system), a weapon, and three kinds of airborne targets j ⁇
  • FIG. 2 is a schematic block diagram of the weapon delivery system depicting the elements of the invention
  • FIG. 3 is a diagram which illustrates the air defense weapon delivery concept involved with the invention indi ⁇ cating the flight path of the weapon and the airborne target;
  • FIG. 4 depicts a typical change in flight paths of a target and a weapon * to demonstrate the guidance concept of the weapon system
  • FIG. 5 depicts in further detail the change in flight path of the weapon as a result of thrusters acting * on the weapon ;
  • FIG. 6 depicts the respective antenna fields of the antenna associated with the fire control system and the antenna associated with the weapon
  • FIG. 7 depicts the envelope of the beacon signal sent from the weapon to the ground-based radar system
  • FIG. 8 depicts the modulation of the beacon signal sent from the weapon to the ground-based radar, wherein the antenna on the weapon is canted by a few degrees relative to the longitudinal axis of the weapon;
  • FIG. 9 further illustrates the air defense weapon delivery concept by depicting the weapon, having forces acting thereon by thusters located on the periphery of the weapon, with the antenna located at the rear thereof and the canted orientation of the antenna with respect to the longitudinal axis of the weapon;
  • FIG. 10 is a cross-secti ⁇ nal view of the weapon depicting the manner in whch the thrusters are mounted on the periphery of the weapon.
  • FIG. 1 illustrates fire control system 11 with radar system 15 of the weapon system mounted on tank 10.
  • Tank 10 is located on a typical battlefield.
  • Launcher 12 is a part of tank 10 and is used to launch the weapon associated with the invention.
  • radar system 15 is shown to be tracking, by way of antenna tracking beam 17, various enemy airborne targets.
  • FIG. 1 depicts helicopter 20 as such a target; low flying jet aircraft 21 as such a target; and missile 22 as such a target. Although only airborne targets are shown, the weapon system has the capability of eliminating ground targets with the use of a suitable radar system 15 and weapon 16.
  • FIG. 1 also pictorially illustrates the capability of radar system 15 to track multiple targets. Radar system 15 is shown to be simultaneously tracking the here ⁇ inbefore described targets, viz., helicopter 20, low flying jet aircraft 21, and missile 22. 2. Elements of the Weapon System
  • FIG. 2 is a schematic block diagram of the weapon delivery system of the invention including the weapon, depicting the elements of the invention and the inter- actions thereof, as indicated by data interfaces 51 to 58.
  • FIG. 2 used in conjunction with FIG. 3 describes the weapon system of the present invention.
  • Radar system 15 is a conventional tracking radar used to locate, acquire, and track airborne targets, such as the U.S. Roland II, the APG 63 radar system used on the F-15 military aircraft or the APG 65 radar system used on the F/A-18 military aircraft; an advanced artillary round tracking radar such as the TPQ 36 or TPQ 37 can also be used. Radar system 15 is used to evaluate the range, relative velocity, and angular position of the weapon. It should be noted that any sensor which accurately measures range can be used, such as a laser, as well as a conventional microwave radar.
  • Radar system 15 On data interface 51, the following data is transferred from radar system 15 to fire control computer 14: the position of target 21, in terms of the range and line-of-sight angle from radar system 15 to target 21; the velocity of target 21 relative to radar system 15; the acceleration of target 21 in the direction of the line-of-sight from radar system 15 to target 21; the acceleration of target 21 in the direction normal to the line-of-sight; and the angular rate of the line-of-sight to target 21.
  • Radar system 15 also has a data interface 52 to weapon attitude angle measurement device 13. An appropriate radar system may be used to track maneuvering ground targets, when so required. 2(b) Fire Control Computer
  • Fire control computer 14 calculates significant quantities for fire control system 11 based upon informa ⁇ tion from radar data system 15 and attitude angle measurement device 13.
  • Fire control computer 14 receives data input on data interface 51 from radar system 15 and on data interface 53 from measurement device 13.
  • Fire control computer 14 determines the direction in which launcher 12 should be pointed for weapon 16 to be launched without terminal correction to intercept target 21, assuming that target 21 continues on its trajectory 32 without making a terminal maneuver, and computes the lead angle for launcher ballistics.
  • fire control computer 14 continues to predict the future position of weapon 16 and compare this pre ⁇ dicted position to the predicted target position infor- * mation by using the data obtained from radar system 15.
  • weapon 16 will maneuver upon the receipt of a command signal causing weapon 16 to intercept target 21 to within a lethal zone surounding target 21.
  • the time t c for com ⁇ manding the initiation of the maneuver depends upon the miss vector e, the roll angle of the longitudinal axis of weapon 16 and the roll rate about the longitudinal axis of weapon 16, which are determined by fire control computer 14.
  • a command signal is initiated on data interface 55 from fire control computer 14 to command link 19, whereby the signal is transmitted to weapon 16, as indicated by data interface 56.
  • Measurement device 13 employs a unique use of a conventional scanning tracking system, such as those conventional scanning tracking systems which are used on radar tracking systems. Measurement device 13 has a receiver used to monitor weapon 16 spin attitude. In conjunction therewith, measurement device 13 has a highly polarized antenna which receives a signal sent from antenna 25 located at the rear of weapon 16 (as depicted in FIG. 6) and directed in the vicinity of tank 10. The signal indicates the relative rotational orientation about the longitudinal axis of weapon 16, which is further explained infra with reference to FIGS. 6 and 9. Measur ent device 13 also supplies command link 19 with a local oscillator (LO) reference signal, as indicated by data inteface 54.
  • LO local oscillator
  • Launcher Launcher 12 generally consists of a slaveable gimbaled gun mounted on tank 10. Information to correctly position launcher 12 is provided from fire control com ⁇ puter 14 on data interface 57. The information so provided consists of the commanded angle information to position launcher 12 and any aiding information that is necessaryy to drive launcher 12 at the large angular rates which may be necessary. Weapon 16 is fired in the direction in which launcher 12 is pointing which is so indicated as data interface 58.
  • Command Link Command link 19 transmits the one-time command signal to weapon 16.
  • Command link 19 obtains the information from fire control computer 14 on data interface 55.
  • the information on data interface 55 consists of the one-time command to fire the initial thruster on the periphery of weapon 16 and the time interval for firing the subsequent thrusters.
  • Command link 19 transmits this information on data and interface 56 to weapon 16 in coded form.
  • Weapon 16 is a terminally guided artillery round.
  • Weapon 16 is similar to any other air defense round with the exception that high explosive side thrusters are located on the periphery around the center of gravity and weapon 16 contains a receiver and logic system to detonate the thrusters to impart a single, fixed magnitude lateral velocity upon command from fire control system 11 via command link 19.
  • Weapon 16 is fired from the smooth bore of launcher 12 using a plastic carrier called a sabot. The plastic carrier is separated from weapon 16 immediately after it leaves launcher 12 by wind force.
  • Weapon 16 also has fins located on the periphery of the weapon in order to induce spin, by canting the fins with respect to the longitudinal axis of weapon 16, after it leaves launcher 12, in a conventional design. Spinning weapon 16 provides a more stable ballistic trajectory than a conventional artillery round.
  • Weapon 16 also has a proximity fuse and a blast fragmentation type warhead, which is detonated by the proximity fuse.
  • Explo ⁇ sive thrusters on the periphery of weapon 16 provide the means for the rapid maneuver of weapon 16 at the terminal phase of the flight to eliminate target 21.
  • the maneuver of weapon 16 occurs in response to the command signal from command link 19 when weapon 16 has the correct angular orientation.
  • This command signal could be mechanized by a special modulation added to the tracking radar radiation.
  • the explosive thrusters are detonated in a predetermined sequence as weapon 16 spins so as to impute a fixed lateral velocity (V c ) to weapon 16.
  • Weapon 16 further has a command link receiver and an intervalometer which will fire the initial thruster of weapon 16 on command and the subsequent thrusters at a commanded interval.
  • Weapon 16 has a radio frequency (RF) diplexer in order to permit it to transmit and receive signals simultaneously on different signal frequencies.
  • RF radio frequency
  • FIG. 3 pictorially illustrates in general the weapon delivery concept involved with the invention.
  • Radar system 15 associated with fire control system 14 is shown mounted on tank 10. Radar system 15 is tracking target 21 with antenna tracking beam 17. Target 21 is traversing flight path 32. Target 21' represents target 21 at another location on flight path 32.
  • Weapon 16 has been launched from launcher 12 and is traversing flight path 30.
  • An error vector e is the magnitude of the distance between weapon 16 and target 21 and the relative orienta ⁇ tion of said distance, as indicated by angle 9> , at any instant in time. This distance is determined from the combination of radar measurement of the location of target 21 and ballistic prediction calculations of the location of weapon 16.
  • the vehicle used to carry launcher 12 and radar system 15 is depicted as tank 10.
  • Tank 10 is one of a variety of existing state-of- the-art military tanks. Examples thereof are the M48 tank, the M60 tank, and the Ml Main Battle Tank, which are used by the United States Army.
  • FIG. 3 also depicts the kinematics of weapon 16 for one point on trajectory 30 of weapon 16.
  • VL is the velocity vector of weapon 16 due to accelerations induced by forces acting on weapon 16 as it flies on trajectory 30; such forces include the initial firing velocity from launcher 12, drag on the weapon, wind, and gravity acting on the weapon.
  • O P V c is the correction velocity vector when initiated.
  • Weapon 16 traverses flight path 30 having a rotational rate about its longitudinal axis of between 50 revolutions per second (r.p.s.), and 1000 r.p.s., but typically 100 r.p.s.
  • a beacon signal is transmitted by weapon 16 using antenna 25 located at the rear of weapon 16 (as depicted in FIG. 6) and directed toward radar system 15.
  • Antenna 25 is mounted at the rear of weapon 16 so as to be canted by 2 to 3 degrees with respect to the longitudinal axis of weapon 16.
  • the beacon transmitted signal is used to indicate the relative angular orientation of weapon 16.
  • the beacon signal also could be used to track the projec ⁇ tile to thereby improve the accuracy of the weapon system.
  • the control signal which is sent from fire control system 14 to weapon 16 to properly initiate the rapid firing sequence of the thrusters located on the periphery of weapon 16
  • knowledge of the actual angular orientation of weapon 16 when the firing sequence of the thrusters is initiated is crucial in order for weapon 16 to eliminate target 21.
  • Terminal flight path correction to reduce error vector ⁇ wherein weapon 16 rapidly accel- erates so as to direct the velocity in the direction of target 21, is employed so as to take into account any large maneuvers produced by high accelerations by target 21, which may occcur any time after launching weapon 16 and before sending the control signal from fire control system 11 to weapon 16.
  • the direction of the velocity vector is controlled by synchronizing the command signal with the spin attitude of weapon 16, and t c is so computed.
  • the computation of the t c involves computing the time when the thrusters on the periphery of weapon 16 are to be detonated, which occurs when the lateral correction velocity (V c ) equals the miss distance (M c ), which is the direct linear distance between weapon 16 and target 21.
  • the command time t c is delayed by a vernier amount until weapon 16 is at the proper spin attitude to point the lateral velocity at the proper angle, as determined by fire control computer 14.
  • miss distance M c as derived from error vector ⁇
  • t c which is the optimum time to detonate the thrusters located on weapon 16 is computed to be equal to the computed miss distance (M c ) divided by the correction velocity (V c ) .
  • a time delay is included to account for computational processing.
  • FIG. 3 illustrates the nature of the error vector e at the time t c when the command signal has been received by weapon 16.
  • Error vector ⁇ is shown to have a miss component M c and an angle ⁇ , both measured from a local plane which includes weapon 16.
  • Target aircraft 21 is shown to be executing a high-acceleration, rapid maneuver, producing trajectory 32, just prior to t c .
  • the timing of the sending of the control signal from fire control system 11 to weapon 16 also depends upon the value of the magnitude of error vector ⁇ .
  • Error vector ⁇ is computed at any instant in time while weapon 16 is flying on trajectory 30 from the position coordinates of target 21 and weapon 16.
  • the position of target 21 is estimated from measurements made by radar system 15 which uses radar search, acquisition and tracking techniques well known in radar art to locate and track the position of target 21.
  • the position of weapon 16 is estimated by using ballistics tables and calculations well known in the art, as documented in the U.S. Navy report,
  • OMH A Ballistic Trajectory Algorithm for Digital Airborne Fire Control (A. . Duke, T.H. Brown, K.W. Burke, R.B. Seeley) , NWC Technical Publication 5416, September 1972, based upon the nature of the weapon used; the initial angular orientation of the longitudinal axis of the launch; the initial velocity of the weapon; the air density; and local wind.
  • V T (t) v yT v zT
  • ⁇ w angular rotational (or spin) rate of weapon 16;
  • g constant of gravitational acceleration; t, time.
  • the thrusters located on the periphery of weapon 16 are fired in rapid predetermined sequence so as to decrease the magnitude of error vector ⁇ and intercept or come within a lethal zone of target 21.
  • the firing sequence of the thrusters around the periphery of weapon 16 is performed in a predetermined order, so that the only control variables contributing to the accuracy of the hit are the angular orientation and firing rate of the thrusters of " weapon 16 at the time the control signal is sent from fire control system 11 to weapon 16.
  • the firing sequence of the thrusters is initiated when weapon 16 is within approximately the last second of flight on trajectory 30, and typically when weapon 16 is within the last one-half second of flight.
  • FIG. 4 depicts the alteration in flight path 30 of weapon 16 resulting from the capability of fire control system 11 to track, using radar system 15, a rapid accel ⁇ eration maneuver by target 21 on flight path 32.
  • Fire control system 11 using radar system 15 is thereby capable of predicting the change in the flight path of target 21 to flight path 32 from flight path 32', which would have been the flight path of target 21 had target 21 not pro ⁇ quizd a rapid acceleration maneuver at point 33 on its flight path.
  • fire control system 11 sends a command signal to weapon 16 at time t c so as to detonate the thrusters located at the periphery of weapon 16 in a pre- designated order, causing flight path 30 of weapon 16 to
  • Flight paths 30 and 30' depict the flight path of weapon 15 as predicted from ballistic computations by weapon control system 11.
  • the ballistic computations predict a point of impact 35 of weapon 16 with target 21, assuming no variation in flight path 32' of target 21.
  • the weapon system guidance using the thrusters on the. periphery of weapon 16 permit weapon 16 to rapidly alter its flight path 30 to flight path 34 and thereby, within approximately one second, but typically one-half second, from the receipt of the command signal, come to within a lethal zone indicated by cone 39 of the target 21.
  • FIG. 5 pictorially illustrates how the thrusters located at the periphery of weapon 16 are fired in sequence, thereby exerting forces on weapon 16 so as to alter the flight path of weapon 16 from flight path 30 to flight path 34, at point 31, deviating from flight path 30" which is a predicted flight path based on ballistic computations.
  • Thusters located on the periphery of weapon 16 are shown to be fired at equally-spaced intervals, associated with points 41 to 46 on flight path 34. The duration of the intervals is commanded by the command signal and depends upon the angular orientation and rota ⁇ tional rate of weapon 16, as well as error vector e, when weapon 16 receives the command signal from fire control system 11.
  • FIG. 10 a cross-sectional view of weapon 16, depicts the manner in which thrusters 61 to 68 are mounted on the periphery of weapon 16.
  • typical thruster 66 is shown comprising a frame 72 which encompasses turning charge 73 and an explosive detonator 75; preformed inert assembly 74 is placed adjacent to the thrusters, in effect isolating one thruster from its adjacent thruster.
  • Shell casing 71 of weapon 16 is also shown in FIG. 10.
  • weapon 16 has polarized antenna 25 at the rear of and located in reference to weapon 16 longitudinal axis 60 of weapon 16.
  • the plane of antenna 25 is canted (that is, skewed or tilted) by an angle ⁇ , which is approximately 2 to 3 degrees, with respect to a plane perpendicular to longitudinal axis 60 of weapon 16, wherein orientation line 61 lies in said plane.
  • a signal is transmitted by a relatively low-power (on the order of five milliwatts) transmitter beacon, which is carried by weapon 16, using linearly polarized antenna 25.
  • the signal is sent to angle measurement • device 13.
  • antenna 7 pictorally illustrates the fields of polarization of the antenna associated with angle measurement " device 13 and of antenna 25 associated with weapon 16.
  • the vectors E and H of antenna field of polarization are indicated for the two antenna fields.
  • the field of the antenna associated with angle measurement device 13 is indicated to be vertically polarized.
  • Antenna 25 is indicated to have a spinning field since antenna 25 rotates as weapon 16 rotates in flight. While weapon 16 is in flight, antenna 21 field vectors E and H rotate at the sp ⁇ n rate (typically 100 r.p.s.) of weapon 16 relative to the respective field vectors E and H of antenna 18.
  • the rotation of antenna 25 field vectors E and H relative to the antenna associated with angle measurement device 13 field vectors produces a modulation of the signal sent from weapon 16 to radar system 15.
  • Curve 83 demonstrates that nulls occur twice per spin cycle of weapon 16. Since the spin cycle of weapon 16, while weapon 16 is in flight and rotating (at a typical rate of 100 r.p.s.) is 2 ⁇ , as depicted by waveform 81, the modulation characteristics of signal curve 83 is phase-angle ambiguous insofar as defining the angular orientation of weapon 16, because any particular point on the surface of weapon 16 could be out of phase by ⁇ .
  • FIG. 9 illustrates a typical signal return indicating waveform 85 character ⁇ istics for the E field vector of antenna 25 rotated by 90
  • Waveform 85 indicates that the beacon transmitted signal on weapon 16 has modulation envelope with a wide null and a narrow null, wherein the modulation envelope is produced by the canting of linearly polarized antenna 25 with respect to a plane perpendicular to the longitudinal axis 60 of weapon 16 and having the E field vector of antenna 25 rotated by 90 degrees with respect to antenna weapon orientation line 61. From the modulation envelope of waveform 85, the rotational ambiguity of weapon 16 described supra, can be resolved with use of the wide null and narrow null characteristics. Each time the weapon has gone through a full rotation of 2 ⁇ r, only one narow and one wide signal null is produced.
  • the signal received by radar system 15 from antenna 25 of weapon 16 is modulated by two effects: (1) the polarity modulation caused by the beacon signal E vector spinning with respect to the , stationary receiving antenna's E vector of angle measure ⁇ ment device 13; and (2) the nutating amplitude modulation resulting from weapon 16 rear-facing antenna which is pointed along the ballistic path of weapon 16.
  • SUR E AtT device 13 from weapon 16 would have equally spaced nulls and peaks and it therefore would not be possible to determine the exact angular orientation of weapon 16.
  • the canting of antenna 25 on weapon 16 induces a modula- tion in the CW signal transmitted to measurment device 13, as depicted in FIG. 9 by waveform 85, so that the precise angular orientation of weapon 16 is known.
  • Canting antenna 25 has no impact on the antenna of measurement device 13 until longitudinal axis 60 of weapon 16 is displaced from the line-of-sight of weapon 16 to radar system 15, as gravity changes the position of antenna 25 causing a change in the character of the signal, as depicted in FIG. 9, which will allow the determination of the geometric relationship of the ambiguous signal nulls that occur as weapon 16 rotates.
  • the roll angle orientation and angular roll rate of weapon 16 are determined.
  • the signal transmitted from weapon 16 also can be used to control the relative frequency of the local oscillator (LO) for command link 19. Consequently, data interface 54 command link RF frequency will be offset from this LO reference. It is necessary to determine the roll angle orientation of weapon 16 in order to command the terminal phase maneuver of weapon 16, since the turning capability of weapon 16 occurs in a single plane.
  • LO local oscillator

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Abstract

Un système de commande de guidage de projectiles (11) comprend un système de détection de cibles au radar (15), et un projectile (16) pourvu à sa périphérie de petits dispositifs de poussée (41-46) ainsi que d'un petit émetteur de balise qui est détecté et poursuivi par un dispositif de mesure d'angle basé au sol (13). Une manoeuvre rapide en fin de trajectoire est exécutée par le projectile en un point approprié (31) de la trajectoire du projectile (16) en allumant de manière séquentielle les petits dispositifs de poussée. L'orientation angulaire du projectile (16) est obtenue en inclinant une antenne polarisée (25) disposée à l'arrière du projectile (16), par rapport à l'axe longitudinal (60) du projectile (16) de sorte que le signal transmis du projectile (16) au système au sol (11) de commande de l'allumage est modulé. Le système de commande de l'allumage (11) calcule le temps exact, en fonction de l'orientation angulaire du projectile (16) et de la distance entre le projectile (16) et la cible (20, 21, 22), pour déclencher la manoeuvre en fin de trajectoire du projectile (16), et envoie un signal de commande au projectile (16).
PCT/US1983/000585 1982-04-21 1983-04-21 Systeme de guidage de projectiles en fin de trajectoire WO1983003894A1 (fr)

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US371,636 1982-04-21

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0343131A2 (fr) * 1988-05-17 1989-11-23 Aktiebolaget Bofors Dispositif pour déterminer la position de roulis
DE3608108C1 (de) * 1986-03-12 1990-06-07 Diehl Gmbh & Co Verfahren zur Abwehr von Flugobjekten
US4951901A (en) * 1985-11-22 1990-08-28 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use
FR2660064A1 (fr) * 1990-03-12 1991-09-27 Telefunken Systemtechnik Procede de guidage pour projectiles et dispositifs pour la mise en óoeuvre du procede.
EP0485897A1 (fr) * 1990-11-14 1992-05-20 DIEHL GMBH & CO. Projectile à correction de trajectoire
EP0521839A1 (fr) * 1991-07-02 1993-01-07 Bofors AB Mesure d'angle de roulis
EP0654680A2 (fr) * 1993-11-22 1995-05-24 State Of Israel Ministry Of Defence Rafael Armament Development Authority Amélioration de systèmes de conduite de tir
WO1996025641A2 (fr) * 1995-02-14 1996-08-22 Bofors Ab Procede et dispositif permettant une correction de trajectoire pour poussee radiale pour un projectile ballistique
WO1997016696A1 (fr) * 1995-11-02 1997-05-09 Hollandse Signaalapparaten B.V. Projectile pouvant se fragmenter, systeme d'arme et procede de destruction d'une cible
FR2761767A1 (fr) * 1997-04-03 1998-10-09 Giat Ind Sa Procede de programmation en vol d'un instant de declenchement d'un element de projectile, conduite de tir et fusee mettant en oeuvre un tel procede
WO2002101317A2 (fr) * 2001-02-28 2002-12-19 Raytheon Company Systeme de projectile hypersonique a guidage de precision
WO2003096066A1 (fr) * 2002-05-09 2003-11-20 Raytheon Company Guidage de precision tout temps de projectiles repartis
EP1493987A1 (fr) * 2003-07-04 2005-01-05 MBDA France Missile tournant émettant des impulsions lumineuses
WO2010107611A1 (fr) * 2009-03-17 2010-09-23 Bae Systems Information And Electronic Systems Integration Inc. Procédé de commande pour des projectiles rotatifs

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3141635A (en) * 1953-02-16 1964-07-21 Marion F Davis Missile guidance system
US3374967A (en) * 1949-12-06 1968-03-26 Navy Usa Course-changing gun-launched missile
US3398916A (en) * 1966-07-04 1968-08-27 Armes De Guerre Fab Nat Device for correcting the trajectory of projectiles and the so-equipped projectiles
US3843076A (en) * 1972-01-03 1974-10-22 Trw Projectile trajectory correction system
FR2326676A1 (fr) * 1975-09-30 1977-04-29 Saint Louis Inst Procede et dispositif pour augmenter la portee utile des projectiles tires contre des objectifs ponctuels
DE2650139A1 (de) * 1976-10-30 1978-05-03 Eltro Gmbh Verfahren und vorrichtung zur korrektur der flugbahn eines geschosses
US4097007A (en) * 1974-10-15 1978-06-27 The United States Of America As Represented By The Secretary Of The Army Missile guidance system utilizing polarization
DE2658167A1 (de) * 1976-10-30 1978-07-06 Eltro Gmbh Verfahren und vorrichtung zur korrektur der flugbahn eines geschosses
DE3024842A1 (de) * 1980-07-01 1982-01-28 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Einrichtung zur lenkung eines um seine laengsachse rotierenden flugkoerpers

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3374967A (en) * 1949-12-06 1968-03-26 Navy Usa Course-changing gun-launched missile
US3141635A (en) * 1953-02-16 1964-07-21 Marion F Davis Missile guidance system
US3398916A (en) * 1966-07-04 1968-08-27 Armes De Guerre Fab Nat Device for correcting the trajectory of projectiles and the so-equipped projectiles
US3843076A (en) * 1972-01-03 1974-10-22 Trw Projectile trajectory correction system
US4097007A (en) * 1974-10-15 1978-06-27 The United States Of America As Represented By The Secretary Of The Army Missile guidance system utilizing polarization
FR2326676A1 (fr) * 1975-09-30 1977-04-29 Saint Louis Inst Procede et dispositif pour augmenter la portee utile des projectiles tires contre des objectifs ponctuels
DE2650139A1 (de) * 1976-10-30 1978-05-03 Eltro Gmbh Verfahren und vorrichtung zur korrektur der flugbahn eines geschosses
DE2658167A1 (de) * 1976-10-30 1978-07-06 Eltro Gmbh Verfahren und vorrichtung zur korrektur der flugbahn eines geschosses
DE3024842A1 (de) * 1980-07-01 1982-01-28 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Einrichtung zur lenkung eines um seine laengsachse rotierenden flugkoerpers

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4951901A (en) * 1985-11-22 1990-08-28 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use
DE3608108C1 (de) * 1986-03-12 1990-06-07 Diehl Gmbh & Co Verfahren zur Abwehr von Flugobjekten
FR2642515A1 (fr) * 1986-03-12 1990-08-03 Diehl Gmbh & Co Procede de defense antiaerienne
EP0343131A2 (fr) * 1988-05-17 1989-11-23 Aktiebolaget Bofors Dispositif pour déterminer la position de roulis
EP0343131A3 (fr) * 1988-05-17 1991-07-24 Aktiebolaget Bofors Dispositif pour déterminer la position de roulis
FR2660064A1 (fr) * 1990-03-12 1991-09-27 Telefunken Systemtechnik Procede de guidage pour projectiles et dispositifs pour la mise en óoeuvre du procede.
EP0485897A1 (fr) * 1990-11-14 1992-05-20 DIEHL GMBH & CO. Projectile à correction de trajectoire
EP0521839A1 (fr) * 1991-07-02 1993-01-07 Bofors AB Mesure d'angle de roulis
US5414430A (en) * 1991-07-02 1995-05-09 Bofors Ab Determination of roll angle
EP0654680A2 (fr) * 1993-11-22 1995-05-24 State Of Israel Ministry Of Defence Rafael Armament Development Authority Amélioration de systèmes de conduite de tir
EP0654680A3 (fr) * 1993-11-22 1995-07-26 Israel State Amélioration de systèmes de conduite de tir.
WO1996025641A2 (fr) * 1995-02-14 1996-08-22 Bofors Ab Procede et dispositif permettant une correction de trajectoire pour poussee radiale pour un projectile ballistique
WO1996025641A3 (fr) * 1995-02-14 1996-09-26 Bofors Ab Procede et dispositif permettant une correction de trajectoire pour poussee radiale pour un projectile ballistique
WO1997016696A1 (fr) * 1995-11-02 1997-05-09 Hollandse Signaalapparaten B.V. Projectile pouvant se fragmenter, systeme d'arme et procede de destruction d'une cible
NL1001556C2 (nl) * 1995-11-02 1997-05-13 Hollandse Signaalapparaten Bv Fragmenteerbaar projectiel, wapensysteem en werkwijze.
EP0887613A2 (fr) * 1997-04-03 1998-12-30 Giat Industries Procédé de programmation en vol d'un instant de déclenchement d'un élément de projectile, conduite de tir et fusée mettant en oeuvre un tel procédé
FR2761767A1 (fr) * 1997-04-03 1998-10-09 Giat Ind Sa Procede de programmation en vol d'un instant de declenchement d'un element de projectile, conduite de tir et fusee mettant en oeuvre un tel procede
EP0887613A3 (fr) * 1997-04-03 1999-01-20 Giat Industries Procédé de programmation en vol d'un instant de déclenchement d'un élément de projectile, conduite de tir et fusée mettant en oeuvre un tel procédé
US6216595B1 (en) 1997-04-03 2001-04-17 Giat Industries Process for the in-flight programming of a trigger time for a projectile element
WO2002101317A2 (fr) * 2001-02-28 2002-12-19 Raytheon Company Systeme de projectile hypersonique a guidage de precision
WO2002101317A3 (fr) * 2001-02-28 2003-04-03 Raytheon Co Systeme de projectile hypersonique a guidage de precision
US6614012B2 (en) 2001-02-28 2003-09-02 Raytheon Company Precision-guided hypersonic projectile weapon system
AU2003234414B2 (en) * 2002-05-09 2006-11-02 Raytheon Company All weather precision guidance of distributed projectiles
GB2400512A (en) * 2002-05-09 2004-10-13 Raytheon Co All weather precision guidance of distributed projectiles
GB2400512B (en) * 2002-05-09 2005-08-24 Raytheon Co System for determining line-of-sight angular rate to a target
WO2003096066A1 (fr) * 2002-05-09 2003-11-20 Raytheon Company Guidage de precision tout temps de projectiles repartis
AU2003234414B8 (en) * 2002-05-09 2009-07-30 Raytheon Company All weather precision guidance of distributed projectiles
EP1493987A1 (fr) * 2003-07-04 2005-01-05 MBDA France Missile tournant émettant des impulsions lumineuses
FR2857088A1 (fr) * 2003-07-04 2005-01-07 Mbda France Missile tournant emettant des impulsions lumineuses.
WO2005012824A1 (fr) * 2003-07-04 2005-02-10 Mbda France Missile tournant emettant des impulsions lumineuses
US7410119B2 (en) 2003-07-04 2008-08-12 Mbda France Rotating missile emitting light pulses
WO2010107611A1 (fr) * 2009-03-17 2010-09-23 Bae Systems Information And Electronic Systems Integration Inc. Procédé de commande pour des projectiles rotatifs
US8324542B2 (en) 2009-03-17 2012-12-04 Bae Systems Information And Electronic Systems Integration Inc. Command method for spinning projectiles

Also Published As

Publication number Publication date
CA1242516A (fr) 1988-09-27
EP0105918A1 (fr) 1984-04-25
DE3380528D1 (en) 1989-10-12
AU568300B2 (en) 1987-12-24
AU1519783A (en) 1983-11-21
EP0105918B1 (fr) 1989-09-06

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