EP2322896A1 - Kragen für Munition - Google Patents

Kragen für Munition Download PDF

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Publication number
EP2322896A1
EP2322896A1 EP09252614A EP09252614A EP2322896A1 EP 2322896 A1 EP2322896 A1 EP 2322896A1 EP 09252614 A EP09252614 A EP 09252614A EP 09252614 A EP09252614 A EP 09252614A EP 2322896 A1 EP2322896 A1 EP 2322896A1
Authority
EP
European Patent Office
Prior art keywords
collar
projectile
canard
barrel
actuator
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
EP09252614A
Other languages
English (en)
French (fr)
Inventor
designation of the inventor has not yet been filed The
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.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
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 BAE Systems PLC filed Critical BAE Systems PLC
Priority to EP09252614A priority Critical patent/EP2322896A1/de
Priority to GB1207820.0A priority patent/GB2487334B/en
Priority to ES10778713T priority patent/ES2428365T3/es
Priority to EP10778713.7A priority patent/EP2499451B1/de
Priority to PCT/GB2010/051879 priority patent/WO2011058359A1/en
Priority to AU2010317740A priority patent/AU2010317740B2/en
Priority to US13/508,633 priority patent/US8674277B2/en
Publication of EP2322896A1 publication Critical patent/EP2322896A1/de
Ceased legal-status Critical Current

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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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/346—Direction control systems for self-propelled missiles based on predetermined target position data using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/34—Direction control systems for self-propelled missiles based on predetermined target position data
    • F41G7/36—Direction control systems for self-propelled missiles based on predetermined target position data using inertial references
    • 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
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the present invention relates to a collar for guiding a projectile, and in particular to a collar for improving the precision of a ballistic projectile.
  • kits such as the XM1156 Precision Guidance Kit (as may be supplied by Alliant Techsystems to the US Army), whereby a standard (i.e. non-guided) 155mm artillery shell may be converted into a guided munition.
  • the kit comprises means for controlling the trajectory of the projectile.
  • Such controlling means may include a set of control surfaces, a processor, and an actuator for moving the control surfaces in response to a correcting signal from the processor.
  • the processor may be interfaced with Global Positioning System (GPS) and Inertial Navigation (IN) sensors to determine the correcting signal which is to be applied.
  • GPS Global Positioning System
  • I Inertial Navigation
  • the kit which further includes a fuze, can be retrofitted into a shell by detaching the fuze section of the shell from the body section of the shell and then attaching the kit to the body section.
  • the kit may therefore give users the option of converting munitions and thus selecting the precision of each round fired.
  • the Precision Guidance Kit may have a deep intrusion body that necessitates the removal of some of the shell's explosive payload in order to fit the PGK instead of the original fuze.
  • the act of replacing the original fuze with the kit may be undesirably time consuming, particularly given the urgency with which a muniton may need to be fired. Indeed, it may not even be possible to replace the original fuse with the kit on the battlefield, for example if some of the payload must be removed as described above.
  • the kit may only be applicable to munitions which have a detachable fuze. Where the munition does not originally have a fuze, the kit cannot readily be applied.
  • a collar for guiding a projectile comprising a collar body, a surface for capturing the projectile as it leaves the barrel, a sill for supporting the surface at the muzzle of the barrel, and a guidance means for altering the flow of air around the collar, wherein the collar may attach to the projectile at the surface to integrate with the projectile as the projectile is fired.
  • Such a collar can be transported into battlefield with the munitions and the weapon system to offer a more precise firing should this be desired.
  • the collar is simple to mount on the muzzle and does not require the detachment or reattachment of munition components prior to firing.
  • a further benefit when compared to guidance kits that require replacement of parts is that the use of the above collar will tend to minimise the number of components which must be transported after a set of precise firings.
  • this invention is in contrast to a system where fuzes may be replaced in the field because in that situation, the replacements must be brought into the field and the replaced fuzes brought back.
  • the collar may comprise a control surface, an actuator for altering the configuration of the control surface, and a guidance controller, the guidance controller comprising a navigation sensor for determining an actual trajectory the projectile is following, a memory at which data describing a predicted trajectory is stored, a processor operably connected to the actuator, the memory and the navigational sensor, wherein the processor calculates a correction signal which determines how the configuration of the control surface may be altered and transmits the correction signal to the actuator.
  • the processor may calculate the correction signal by determining the difference (which may alternatively be referred to as the error or the deviation) between the actual trajectory and the predicted trajectory.
  • control surface may comprise a pair of canards, each canard comprising a pivot joint connecting the canard to the collar and wherein the actuator may be a ring actuator which connects to the canards so as to be able to alter the configuration of the control surface by rotating the canards about their pivots.
  • pivot joint connects each of the canards to the collar body
  • the pivot joint is preferably connected forwards of the centre of pressure of the canard.
  • the ring actuator may correct the projectile course by applying a force to the control surface so as to move the control surface out of alignment with the air stream over the projectile body, such a location of the pivot leads to a stable control arrangement. This stability is conferred because as the actuator ceases to apply the force to the control surface, the air flow will return the control surface to its original configuration.
  • Such a position of the pivot should therefore also tend to simplify the control signals (i.e. the correction signal) which needs to be sent to the actuator because little consideration needs to be given to how the actuator must move in order to return the control surface to its original position;
  • the correcting signal can consist of a set of identical signals, which rise in repetition frequency with the projectile deviation but need not be transmitted if the projectile follows the predicted trajectory.
  • each canard may be connected to the ring actuator at a point on the canard towards or at the trailing edge of the canard.
  • the surface for capturing may be at an internal facet of the collar and may have a tapered inner diameter, operable to form an interference fit with said projectile, and thereby allow the collar to attach to the projectile.
  • the surface and the material providing the surface is capable of elastic deformation.
  • Metals would be suitable materials for the material providing the surface.
  • the surface for capturing may define a generally frustoconical form.
  • the sill may support the frustoconical form defined by the surface at the barrel so that the axis defined by the frustoconical form is generally collinear with the axis defined by the barrel.
  • This supporting arrangement can promote an even interference fit around the projectile and so enable the collar to attach to the projectile and create a symmetrical integrated projectile.
  • Such a symmetrical integrated projectile can be expected to have improved aerodynamic properties and tend to require less guidance.
  • Such a surface for capturing may be tapered at between 3° and 0.5°, and in particular may be tapered at approximately 1.2°.
  • the collar may be formed as one or more portions operable to be fastened together.
  • a collar 100 for guiding a mortar shell as shown for example in figure 1a, figure 1b and figure 5 , comprises a collar body 10.
  • the collar body 10 defines a generally cylindrical outer surface, which defines a collar axis 1.
  • the leading edge of the collar (that is the top edge in figure 1 a) is filleted so as to have appropriate aerodynamic properties.
  • the collar 100 is hollow and is open towards both ends of its axis 1 to define a conduit.
  • a first opening 16 of the conduit (alternatively referred to as the escape vent 16) is located at the leading edge of the collar 100 and defines a generally circular aperture, normal to the collar axis 10 and with a centre point which lies generally on the collar axis 1.
  • a second opening 17 is located at the trailing edge of the collar 100. The second opening 17 defines a circular aperture normal to the collar axis 10 and with a centre point which lies generally on the collar axis 1.
  • the capture surface 12 starts at the first opening 16 and extends down into the collar body 10 up to approximately the mid point of the body length. As the capture surface 12 extends away from the leading edge of the collar it tapers out, thereby defining a generally frustoconical surface, and eventually meets the sill 14.
  • the sill 14 is an annular surface normal to the collar axis 1 and with its centre point generally on the collar axis 1.
  • the inner diameter of the annular sill 14 meets the frustoconical surface 12 and the outer diameter of the annular sill 14 meets the cylindrical surface 18.
  • the cylindrical section 18 extends downwards to the second opening 17.
  • the diameter of the second opening 17 is generally identical to the outer diameter of the annular sill 14.
  • a guidance controller 50 which, as can be seen from figure 2 , comprises a navigation sensor unit 54, a memory 52, a processor 56 and a ring actuator I/O unit 58.
  • Guidance controller 50 is also provided with a power source (not shown).
  • the processor 56 is operably and independently connected to the sensor unit 54 and the memory 52 and generates as an output a correction signal 57 that is input to the I/O unit 58.
  • the I/O unit is operably connected to the ring actuator 40.
  • the sensor unit 54 comprises an inertial navigation system (comprising accelerometers for sensing linear motion and gyroscopes for sensing rotational rate), a magnetometer and a Global Positioning System (GPS).
  • an inertial navigation system comprising accelerometers for sensing linear motion and gyroscopes for sensing rotational rate
  • a magnetometer for sensing rotational rate
  • GPS Global Positioning System
  • the collar 100 is placed loosely over the mortar shell 200 with a forked safety plate 400 slotted on to the mortar 200 to hold the mortar 200 at the collar 100.
  • the collar 100 may then be placed at the muzzle 310 of a barrel 300 as shown in figure 3a to prepare the mortar 100 for firing.
  • the collar 100 is supported at the muzzle 310 by the sill 14 which rests at the lip of the muzzle 310 and is of such a form that the collar axis is generally collinear with the barrel axis.
  • the collar 100 is also supported by the cylindrical surface 18, which fits around the muzzle 310.
  • the mortar 200 drops in the known manner down the barrel 300 until the pin at the base of the barrel 300 is struck and the propellant charge at the rear of the mortar is initiated.
  • the initiation of the propellant charge accelerates the mortar towards the muzzle 310 and the collar 100.
  • the collar 100 remains supported at the muzzle 310 until the mortar strikes and engages with the capture surface 12.
  • the force of the mortar striking the collar 100 at the generally frustoconical capture surface 12 sets up an interference fit between the mortar and the collar 12. This interference fit attaches the collar 100 to the mortar 200, thereby integrating the collar 100 with the mortar 200.
  • the frustoconical form of the capture surface 12 may cooperate with the outer surface of the mortar to tend to ensure that the collar axis and the mortar axis are collinear.
  • the integrated mortar 500 is generally symmetrical.
  • a ballistic trajectory can be predicted from the inclination of the barrel axis and the muzzle velocity using classical mechanics, with adjustments made for air resistance made in the known way.
  • a predicted ballistic trajectory may not be followed in practice because of environmental inconsistencies (such as wind) which may cause the projectile to deviate.
  • the collar 100 monitors its trajectory 120 using the navigational sensors in unit 54 to feed data into the processor 56. Before applying any correcting signal, the processor 56 compares the monitored trajectory 120 to a set of predicted trajectories stored in the memory 52. The processor thus determines that, of the possible predicted trajectories which the projectile 500 may follow, projectile 500 is intended to follow a particular predicted trajectory 110. By making this determination in the early part of its flight, which is the part of its flight where the weather may have least effect on the trajectory, the selection of the predicted trajectory should tend to be correct.
  • the controller 50 may regulate the actual trajectory 120 of the integrated mortar 500, attempting to conform the actual trajectory 120 to the predicted trajectory 110.
  • Inertial Navigation sensors (in particular the accelerometers) at the projectile 500 will tend to give null readings for most of the flight because, in a projectile describing pure ballistic flight, there is a net zero acceleration at a strapdown accelerometer sensing the lateral axes within the projectile (a small deceleration followed by small acceleration will be sensed in the longitudinal axis).
  • the IN sensors may include solid-state rate gyros and their output may be considered in determining the actual position of the projectile.
  • the processor 56 may, by frequently sampling the position of the projectile 500 from the signals from the sensors 54, determine the actual trajectory 120 of the projectile 500.
  • the processor 56 can compare the actual trajectory 120 to the predicted trajectory 110. At the point A of figures 4 and 5 , the processor 56 determines that the actual trajectory 120 differs from the predicted trajectory 110. In order to conform the actual trajectory 120 to the predicted 119, the processor 56 sends a correcting signal 57 to I/O unit 58. I/O unit 58 then outputs a more powerful signal to the ring actuator 40, which signal momentarily energises the ring actuator 40 so that the ring actuator 40 momentarily deflects the canard pair 20a, 20b to apply lift to the integrated mortar 500. The course of the integrated mortar should then alter and once the ring actuator is de-energised, the air flow will return the canard pair 20a, 20b to their original configuration.
  • the processor 56 determines that the integrated mortar 500 is now above the predicted trajectory 110 and so the correcting signal 57 is generated to energise the ring actuator 40 so that the canards deflect in the opposite direction to that at point A.
  • the projectile 500 proceeds to land at the target Y, which is the predicted target for the predicted trajectory 110 and so avoids potentially sensitive targets X and Z.
  • the first type is for both canards to be deflected a specific amount in a first (glide) direction.
  • the second type is for both canards to be deflected by the same specific amount but in a second (brake) direction.
  • a simple control algorithm may be employed whereby the frequency of repetition of this corrective action is proportional to the deviation of the actual trajectory 120 from the predicted trajectory 110.
  • the invention alternatively contemplates the use of more sophisticated control methods which employ for example PID control algorithms.
  • the collar body 10 may be made from milled aluminium or an alloy of aluminium. Where the collar is for attaching to an 81mm mortar, the first opening has a diameter of approximately 78mm and tapers at approximately 1.6° to a diameter of approximately 80mm at the inner diameter of the annular sill 14. The outer collar body diameter is 108mm. With such a fabrication, the capture surfaces are the surfaces of the milled aluminium form.
  • the collar 100 is for attaching to and guiding a mortar round and in particular an 81mm mortar round.
  • the skilled man would realise that the invention could be applied to other calibres of mortar and indeed, other types of projectile.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
EP09252614A 2009-11-13 2009-11-13 Kragen für Munition Ceased EP2322896A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP09252614A EP2322896A1 (de) 2009-11-13 2009-11-13 Kragen für Munition
GB1207820.0A GB2487334B (en) 2009-11-13 2010-11-11 Guidance device
ES10778713T ES2428365T3 (es) 2009-11-13 2010-11-11 Dispositivo de guiado
EP10778713.7A EP2499451B1 (de) 2009-11-13 2010-11-11 Lenkvorrichtung
PCT/GB2010/051879 WO2011058359A1 (en) 2009-11-13 2010-11-11 Guidance device
AU2010317740A AU2010317740B2 (en) 2009-11-13 2010-11-11 Guidance device
US13/508,633 US8674277B2 (en) 2009-11-13 2010-11-11 Guidance device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09252614A EP2322896A1 (de) 2009-11-13 2009-11-13 Kragen für Munition

Publications (1)

Publication Number Publication Date
EP2322896A1 true EP2322896A1 (de) 2011-05-18

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Family Applications (1)

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EP09252614A Ceased EP2322896A1 (de) 2009-11-13 2009-11-13 Kragen für Munition

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EP (1) EP2322896A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3961145A1 (de) * 2020-08-31 2022-03-02 Simmonds Precision Products, Inc. Kurskorrektursysteme für projektile

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE245032C (de) *
GB104382A (en) * 1916-03-01 1917-03-01 Arnold Henry Savage Landor Improvements in and relating to Projectiles for Destroying Wire and like Entanglements.
US1294604A (en) * 1917-11-20 1919-02-18 Hans Gustav Berentsen Marine projectile.
FR619481A (fr) * 1926-07-07 1927-04-02 Nouveau type de canon et projectile
US3179052A (en) * 1961-06-29 1965-04-20 Hotchkiss Brandt Drag collar for varying the range of rockets
EP0441670A1 (de) * 1990-01-26 1991-08-14 Thomson-Brandt Armements Regeleinrichtung des Rollverhaltens eines durch Leitwerk stabilisierten Projektiles
EP1953494A1 (de) * 2007-01-31 2008-08-06 NEXTER Munitions Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE245032C (de) *
GB104382A (en) * 1916-03-01 1917-03-01 Arnold Henry Savage Landor Improvements in and relating to Projectiles for Destroying Wire and like Entanglements.
US1294604A (en) * 1917-11-20 1919-02-18 Hans Gustav Berentsen Marine projectile.
FR619481A (fr) * 1926-07-07 1927-04-02 Nouveau type de canon et projectile
US3179052A (en) * 1961-06-29 1965-04-20 Hotchkiss Brandt Drag collar for varying the range of rockets
EP0441670A1 (de) * 1990-01-26 1991-08-14 Thomson-Brandt Armements Regeleinrichtung des Rollverhaltens eines durch Leitwerk stabilisierten Projektiles
EP1953494A1 (de) * 2007-01-31 2008-08-06 NEXTER Munitions Vorrichtung zur Lenkung einer Munition mit ausklappbaren Steuerflächen

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3961145A1 (de) * 2020-08-31 2022-03-02 Simmonds Precision Products, Inc. Kurskorrektursysteme für projektile

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