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WO1992018823A1 - Dispositif de pointage vers une cible mobile et de guidage d'un canon anti-aerien sur ladite cible - Google Patents

Dispositif de pointage vers une cible mobile et de guidage d'un canon anti-aerien sur ladite cible Download PDF

Info

Publication number
WO1992018823A1
WO1992018823A1 PCT/SE1992/000226 SE9200226W WO9218823A1 WO 1992018823 A1 WO1992018823 A1 WO 1992018823A1 SE 9200226 W SE9200226 W SE 9200226W WO 9218823 A1 WO9218823 A1 WO 9218823A1
Authority
WO
WIPO (PCT)
Prior art keywords
barrel
aiming
elevation
azimuth
target
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/SE1992/000226
Other languages
English (en)
Inventor
Hans-Arne Nilsson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Saab Instruments AB
Original Assignee
Saab Instruments AB
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 Saab Instruments AB filed Critical Saab Instruments AB
Priority to DE69200849T priority Critical patent/DE69200849T2/de
Priority to EP92909132A priority patent/EP0580701B1/fr
Publication of WO1992018823A1 publication Critical patent/WO1992018823A1/fr
Priority to FI934557A priority patent/FI107295B/fi
Anticipated expiration legal-status Critical
Priority to NO933737A priority patent/NO306579B1/no
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/06—Aiming or laying means with rangefinder
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G5/00—Elevating or traversing control systems for guns
    • F41G5/08—Ground-based tracking-systems for aerial targets

Definitions

  • the present invention relates to a device for aiming at a mobile target and to directing an anti-aircraft gun or similar with the same, the barrel direction of the anti-aircraft gun being adjus ⁇ table in azimuth and elevation by means of servomotors with an aiming unit incorporating a sight for optical aiming at the tar ⁇ get along an aiming line, preferably field glasses, a device for ranging to the target, preferably a type of laser, the aiming unit being held by a support and being swivelling by manual ac ⁇ tion in azimuth and in elevation, the support being fixed to said barrel, where the aiming unit also comprises means for measuring the angle in azimuth and in elevation between the aiming line and the barrel direction, and the device comprising means for measu ⁇ ring directly or indirectly the angular velocity of the aiming line in azimuth and in elevation, said means being arranged to send signals in accordance with their corresponding measured values to a calculating device being adapted to calculate accor ⁇ ding to said received
  • Such devices are already known by several designs. Common to them is that they are using advanced techniques with a high level of costs.
  • the ranging of the target is usually performed by a radar or a laser range meter with a high frequency measuring in combi ⁇ nation with a television camera with an automatic target tracking device.
  • the present invention has as an object to propose a device of the kind mentioned above, which device allows for shorter reaction periods between a target observation and its fighting, high hit ⁇ ting probability when used repeatedly, a passive target tracking function, easy manipulating, training and service and which devi ⁇ ce has a low cost profile for capital, service and operation.
  • a device of the kind mentioned above is characterized in the first place of being adapted to operate in three phases, where
  • said servomotor at a first initialisation of the aiming unit and the calculating unit are adapted to be acti ⁇ vated, so that the angular velocity of the barrel in ' azimuth ⁇ A and in elevation 6._, has a defined correlation to the angular deflection in azimuth and elevation of the aiming line from a neutral position, achieved by manual action in following the tar ⁇ get with the aiming line and during a second initialisation of the aiming unit and the calculating unit a series of range measu ⁇ res are taken intermittently, the calculation unit registering corresponding values of the aiming line azimuth angle " ⁇ and elevation angle with in space fixated reference values as well as range and measuring time, the calculating unit calcula ⁇ ting on basis of said corresponding values a first preliminary target path and target speed and precalculating preliminary directions, i.e. angles in azimuth ⁇ - and in elevation ⁇ and angular velocities in azimuth C ⁇ , and in elevation of the barrel for a
  • phase III is comprising that at a third initialisation of the aiming unit and the calculating unit the range measuring is stopped and said servomotors are activated to direct the barrel direction with said angles and 0 and simultaneously provide the barrel direction with angular velocities O and Co _ corresponding to the angles precalculated during phase I, and the angular veloci ⁇ ties corresponding to said calculated target path and target speed; Phase III
  • a series of range measures are performed intermittently, the calculating unit registrering correlated values of the aiming line azimuth angle and elevation angle 0 as well as of the range, the calculating unit basing on these correlated values calculating a definite target speed and thereby correct barrel directions and angular velocities in azimuth and in elevation for a fired projectile to hit the target, whereafter the calculating unit is activating the servomotors to adjust these angles and angular velocities.
  • phase II mea ⁇ sured data are collected during phase I during a relatively short first time period.
  • the coarse target aiming phase the barrel directing is performed to a preliminary offset and lead.
  • no dectecing af measure points is performed.
  • the fine measuring and fine direc ⁇ ting phase further measure data are collected.
  • the calculating unit can calcu ⁇ late a relevant medium speed of the target.
  • the barrel is finely directed according to the last measured data and the firing of the projectile can be performed.
  • the range measuring can be performed by a laser which only has to create a restricted number of laser pulses for an exact target ranging, and thus enabling the use of a laser without any special cooling and with a resulting high reliability and low service costs with the function simultaneously being almost passive.
  • rate gyros are incorporated for measuring the barrel angular velocities in azimuth - ⁇ and in elevation .
  • the output signals from these are integrated to corresponding angles.
  • the angles between the sight line and the barrel direction are measured in azimuth ⁇ " ⁇ and in elevation ⁇ , whereby the calculating unit is correlating the range measure values with the corresponding angle positions for the sight line to the target in a system with in space fixated references.
  • the rate gyros are in fact in space fixated references for all measure values being the basis for the directing of the barrel.
  • rate gyros are in fact in space fixated references for all measure values being the basis for the directing of the barrel.
  • the adaption of in space fixated references enables a sustained sta ⁇ bility in repeated use, such as repeated firing.
  • the subsidence of an anti-aircraft gun relatively to the ground is not inflic ⁇ ting on the hitting result. Any play and roughness due to wear and similar in the anti-aircraft gun machinery is eliminated by the rate gyros directly measuring the barrel velocities.
  • the device according to the invention is adapted to direct the barrel angles during said phase II with the servomotors being activated in azimuth ' ⁇ and in elevation & with an accelerated movement.
  • the operator is risking to drop the target out of sight.
  • said acceleration is in a sui ⁇ table embodiment of the device according to the invention re ⁇ stricted correspondig to the difference between the angles of the barrel direction and the sight line in azimuth ⁇ ⁇ and in eleva ⁇ tion ⁇ @ •
  • the servomotors should direct it in azimuth and in elevation with feedback, i.e. in closed control loops.
  • the device according to the invention can also be achieved in many apparative ways within the scope of the appending claims.
  • the unit can be swivelled rela ⁇ tively to the onto the support fixed barrel in azimuth and in elevation by means of two handles to be gripped by the right and left hand respectively, the three phases I-III are initiated by a series of switches being activated and kept activated in series.
  • phase II can be achieved by activating another switch first when an initiation has occurred by activating a first switch and keeping it activa ⁇ ted.
  • Figure 1 is a perspective view of an embodiment of the aiming unit mounted on a support with a control device; and Figure 2 is a perspective view of a handle for the control device in figure 1.
  • the aiming unit is supported to be swivelled in azimuth and in elevation on a support, which by means of a beam 1 is fixed to a barrel, not shown in the figure.
  • the support comprises a basis plate 2 supported by the beam 1 by means of rubber isolators 3 with the function to protect the aiming unit from shocks having a high level of acceleration. They are dimensioned and designed in such a way as not to effect the angular direction of the aiming unit in relation to the barrel.
  • Onto the basis plate 2 a vertical shaft 4 is pivotally mounted, supporting on its upper end a yoke 5, into whose uprising arms a platform 6 is mounted by means of a shaft 7 pivoting in elevation.
  • the platform 6 is supporting a laser range meter 8 also performing as field glasses.
  • the latter is provided with hair lines representing the optical axis of both the visual sight and the range meter.
  • the laser range meter 8 is also equipped with a coarse sight 9 and a forehead support for protection during firing.
  • a gyro unit 11 is mounted comprising two rate gyros measuring the angular velo ⁇ city, one for measuring the barrel movements in azimuth and the other for measuring the barrel movements in elevation.
  • an angle detector 12 for measu ⁇ ring the barrel elevation angle.
  • an angle detector 13 provided for measuring in azimuth ⁇ * ⁇ , the stationary part of which is fastened underneath the basis plate 2 and the vertical axis of which is connected to the shaft 4, sup ⁇ porting the yoke 5 and thereby the laser range meter.
  • the angle j Q in elevation between the sight line and the barrel direction is measured by means of an angle detector 14 connected to the shaft 7.
  • the guiding of the aiming unit is performed by means of guiding device 15 incorporating a number of links and shafts.
  • a vertical shaft 16 is pivotally mounted onto the underside of the basis plate 2.
  • a vertical shaft 17 is fastened into the shaft 16 .
  • a yoke 18 is pivotally mounted with one end supporting on the underside a vertical rod 19, which in turn is helding a switching unit 20 provided with handles 21 and 22 for each hand.
  • the yoke 18 is presenting on its other end a vertical shaft 23 pivotably mounted and presenting a vertical rod 24, which at its upper end by a ball joint 25 is connected to the platform 6.
  • the dimensioning of the parts appertaining to the guiding device 15 is made in such a way as to change down move ⁇ ments being performed by an operator by moving and turning the rod 19 respectively back and forth in comparison to the movements of the platform 6 and thus the movements of the laser range meter/field glasses 8.
  • the shape of the switching unit 20 can clearly be seen in figure 2.
  • the handles 21, 22 are on the upper side provided with switches 26, 27. When the operator is gripping the handles with the switches the means is activated as to actuate the barrel direction via the servomotors by the moving of the rod 19 forwards and backwards by the operator.
  • the switching unit is comprising four switches 28-31,- their shape and function being described in the following.
  • the device functions as follows:
  • the operator is activating the device by gripping the handles 21, 22 and thereby pressing in the switches 26, 27. Thereby said phase I is initiated.
  • the barrel is automatically directed in the same direction with an angular velocity in azi ⁇ muth and in elevation being proportional to the sight line by manual action achieving the angle pivoting in azimuth and in ele ⁇ vation from a neutral position.
  • the device is performing a slave function during the target tracking phase.
  • the target tracking is achieved by the operator after perception of a target with the eye fixed through the coarse sight 9 guiding the fields glasses so that the sight line approximately coincides with the direction to the target.
  • the operator is then moving his eyes to the field glasses eye piece 32 and is directing the field glasses so that its hair lines representing the optical axis of the field glas ⁇ ses, i.e. the sight line is coinciding with the target.
  • the laser range meter 8 of the aiming unit is initiated by the operator with his right thumb lifting the switch 28.
  • the range metering is then performed by the laser range meter sending a short period light impulse being reflected by the target lying in the sight line.
  • the reflected energy is detected by the range meter regis ⁇ tering the time interval between the output and the reflected light impulse and converting it to a corresponding range value, which then is transmitted to the calculating units calculating circuits.
  • This value is coordinated with the sight line angular position with in space fixed references, * ⁇ and Q .
  • the angles * and ⁇ are obtained the subtracting the difference angles between the sight line and the barrel direction A ⁇ and ⁇ ⁇ , re ⁇ spectively from the existing barrel angles ⁇ and ⁇ •
  • the laser range meter 8 is thereafter ranging automatical ⁇ ly in a fast sequence in continually aiming at the target a num ⁇ ber of target ranges. During this aiming the feeding into the calculating unit is performed of the corresponding range values and correlated time periods and angular values ⁇ and ⁇ .
  • the laser range meter has for reasons of costs an embodiment which is limiting the number of sent energy impulses per time period and thus the target tracking has to be extended in time.
  • the laser range measures are stopped and the directing of the barrel is changing from a directing by means of the angular velocity in proportion to the directing value, being adapted in phase I, to an automatic directing by means of calculated angles ' ⁇ , Q and angular speeds - , so that the barrel direction willl have the right lead angle and the right offset angle to have a fired projectile hitting the target.
  • an automatic direc ⁇ ting an accelerated movement of the barrel is created, which is slowed down, when the barrel is moved to the commanded direction and angular speed.
  • the switches 28, 29 are kept lifted and pressed down respective ⁇ ly.
  • the operator is lifting with his left thumb switch 30.
  • New measure values for the target range and correlated time periods and angular values for j and Q are registered in the same manner as during phase I.
  • the calculation of the required offset angle and of the lead angle are thus updated, the barrel direc ⁇ tion being immediately directed in a corresponding way.
  • the time period for phase II is about 1 to 3 seconds.
  • the firing of the projectiles is achieved by the operator in kee ⁇ ping the remaining switches 28, 29, 30 in their lifted resp. pressed down positions pressing down switch 31 with his left thumb.
  • the firing is continuing as long as the switch 31 is pres ⁇ sed down.
  • the barrel is directed in the same way as previously, i.e. automtaically by the servomotors with closed control circuits, incorporating the rate gyroes.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
  • Gyroscopes (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

Le dispositif décrit comprend des servomoteurs qui dirigent le canon, un viseur avec jumelles (8), un dispositif télémétrique et une calculatrice. Le viseur est maintenu pivotant sur un support (2, 5) fixé au canon. Des moyens (11) sont prévus pour mesurer directement et indirectement la vitesse angulaire de déplacement de la ligne de visée. La calculatrice calcule l'angle de correction requis et l'angle de déport du canon, et envoie des signaux de correction correspondants aux servomoteurs. Le dispositif fonctionne en trois phases. Pendant la phase I les vitesses angulaires du canon ont un rapport fixe avec le déplacement angulaire de la ligne de visée. Cette opération est effectuée manuellement en partant d'une position neutre. Une série de mesures télémétriques est effectuée et le bloc de calcul calcule une trajectoire de cible et la vitesse de la cible préliminaires. Pendant la phase II le télémétrage est interrompu et le canon est orienté en fonction de la trajectoire de cible et de la vitesse de la cible préliminaires. Pendant la phase III une autre série de mesures télémétriques est effectuée et la calculatrice calcule définitivement la vitesse de la cible et donc également l'angle de correction exacte ainsi que l'angle de déport du canon, les servomoteurs effectuant l'orientation du canon.
PCT/SE1992/000226 1991-04-17 1992-04-08 Dispositif de pointage vers une cible mobile et de guidage d'un canon anti-aerien sur ladite cible Ceased WO1992018823A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE69200849T DE69200849T2 (de) 1991-04-17 1992-04-08 Vorrichtung zur ausrichtung auf ein bewegliches ziel und zur führung einer flugabwehrkanone oder ähnlichem auf besagtes ziel.
EP92909132A EP0580701B1 (fr) 1991-04-17 1992-04-08 Dispositif de pointage vers une cible mobile et de guidage d'un canon anti-aerien sur la dite cible.
FI934557A FI107295B (fi) 1991-04-17 1993-10-15 Laite liikkuvaan kohteeseen tähtäämistä varten ja ilmatorjuntatykin tai vastaavan suuntaamiseksi siihen
NO933737A NO306579B1 (no) 1991-04-17 1993-10-18 Anordning for sikting mot et bevegelig mål og dirigering av et antiluftvernvåpen eller lignende ved samme

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9101148-6 1991-04-17
SE9101148A SE468330B (sv) 1991-04-17 1991-04-17 Anordning foer siktning mot ett mobilt maal och inriktning av en luftvaernspjaes eller liknande mot detsamma

Publications (1)

Publication Number Publication Date
WO1992018823A1 true WO1992018823A1 (fr) 1992-10-29

Family

ID=20382481

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1992/000226 Ceased WO1992018823A1 (fr) 1991-04-17 1992-04-08 Dispositif de pointage vers une cible mobile et de guidage d'un canon anti-aerien sur ladite cible

Country Status (7)

Country Link
EP (1) EP0580701B1 (fr)
AU (1) AU1659892A (fr)
DE (1) DE69200849T2 (fr)
FI (1) FI107295B (fr)
NO (1) NO306579B1 (fr)
SE (1) SE468330B (fr)
WO (1) WO1992018823A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2722280A1 (fr) * 1994-07-05 1996-01-12 Thomson Csf Dispositif d'aide au tir de precision pour une arme individuelle
EP1450125A1 (fr) * 2003-02-12 2004-08-25 Oerlikon Contraves Ag Procédé et dispositif pour combattre une cible
KR102213467B1 (ko) * 2019-10-16 2021-02-05 장안중 드론 시스템

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE501905C2 (sv) * 1993-11-03 1995-06-19 Saab Instr Ab Luftvärnspjässikte med kamera

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685159A (en) * 1969-01-03 1972-08-22 Bofors Ab Method and system for establishing a correct lead when firing at a moving target
GB1502406A (en) * 1975-02-20 1978-03-01 Hollandse Signaalapparaten Bv Weapon control system
GB2095799A (en) * 1981-03-27 1982-10-06 Baasch Hans An aiming device for use in firing at moving targets

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685159A (en) * 1969-01-03 1972-08-22 Bofors Ab Method and system for establishing a correct lead when firing at a moving target
GB1502406A (en) * 1975-02-20 1978-03-01 Hollandse Signaalapparaten Bv Weapon control system
GB2095799A (en) * 1981-03-27 1982-10-06 Baasch Hans An aiming device for use in firing at moving targets

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2722280A1 (fr) * 1994-07-05 1996-01-12 Thomson Csf Dispositif d'aide au tir de precision pour une arme individuelle
WO1996001404A1 (fr) * 1994-07-05 1996-01-18 Thomson-Csf Dispositif d'aide au tir de precision pour une arme individuelle
EP1450125A1 (fr) * 2003-02-12 2004-08-25 Oerlikon Contraves Ag Procédé et dispositif pour combattre une cible
KR102213467B1 (ko) * 2019-10-16 2021-02-05 장안중 드론 시스템

Also Published As

Publication number Publication date
DE69200849T2 (de) 1995-04-13
DE69200849D1 (de) 1995-01-19
NO933737L (no) 1993-10-18
EP0580701B1 (fr) 1994-12-07
FI934557A0 (fi) 1993-10-15
EP0580701A1 (fr) 1994-02-02
FI934557A7 (fi) 1993-10-15
SE468330B (sv) 1992-12-14
SE9101148D0 (sv) 1991-04-17
FI107295B (fi) 2001-06-29
NO306579B1 (no) 1999-11-22
SE9101148L (sv) 1992-10-18
AU1659892A (en) 1992-11-17

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