EP3945279A1 - Lenkbares projektil - Google Patents

Lenkbares projektil Download PDF

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Publication number
EP3945279A1
EP3945279A1 EP20275128.5A EP20275128A EP3945279A1 EP 3945279 A1 EP3945279 A1 EP 3945279A1 EP 20275128 A EP20275128 A EP 20275128A EP 3945279 A1 EP3945279 A1 EP 3945279A1
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EP
European Patent Office
Prior art keywords
projectile
section
coupling device
ogive
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
EP20275128.5A
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English (en)
French (fr)
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designation of the inventor has not yet been filed The
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BAE Systems PLC
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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 EP20275128.5A priority Critical patent/EP3945279A1/de
Priority to PCT/GB2021/051866 priority patent/WO2022023706A1/en
Priority to EP21749267.7A priority patent/EP4189322A1/de
Priority to US18/007,133 priority patent/US20230228546A1/en
Publication of EP3945279A1 publication Critical patent/EP3945279A1/de
Ceased legal-status Critical Current

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    • 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
    • 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
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes

Definitions

  • the present invention relates generally to a steerable projectile and a related system and method for controlling a steerable projectile.
  • a further example of controlling a projectile is that used in both BAE Systems' Silver Bullet TM & Thales STARStreak ® , the control is achieved using a dual spin arrangement wherein the forward and aft sections of the projectile are spun relative to each other via a suitable mechanism in order to align the controllable pitch axis into the desired angle.
  • Such examples utilise protruding control surfaces in order to exert a force on the projectile.
  • a projectile comprising, a front ogive section, an aft section and a control module, wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface, where in use, the angular rotation of the front ogive section is selectively adjusted relative to the aft section by selective control of the coupling device, such that the change in angular rotation of said asymmetric surface exerts an imbalance upon the projectile to control the trajectory of said projectile.
  • the front ogive section is defined relative to the direction of travel of the projectile as the leading section of the projectile and the aft section defined as the trailing section relative to the direction of travel. It will be appreciated that although only two sections have been discussed, there may be further intermediate sections positioned between said front ogive section and aft sections or in advance of the front ogive section or to the rear of the aft section, for example, a fuze or sensor section in advance of the front ogive section. Base bleed, tracer effects or rocket assists may be located rearward of the aft section. Said intermediate sections may rotate relative to the front and/or aft sections or may remain stationary with respect to the front and/or aft sections. The aft section may be the entire section of the projectile that is rearward of the ogive section.
  • arrangement is such that the mass of the aft section is greater than the ogive section.
  • the front ogive section and aft section may be made of metal, metal alloys, polymers or composites.
  • the front ogive section and aft section may be made of the same or different materials.
  • the front ogive section and aft section may be made from materials chosen according to calibre.
  • the front ogive section and aft section are made from metal or metal alloys.
  • the chosen material may fulfil the demands of any engagement scenario or design requirement. For example being made of more/less dense materials to balance the centre of mass, or being made of hardened materials, for example hardened steels, titanium or carbides, nitrides, to improve terminal performances.
  • the front ogive section and aft section may be made from an inner core of lead or high hardness steel that is enveloped by a copper jacket or copper deposed coating.
  • the projectile is a shell, such as, for example in the range of from 29mm to 155mm the front ogive section and aft section are made from steels.
  • the intermediate calibres of 10 to 40mm may be made from their typical metal, metal alloys.
  • the ogive section may be made from a material which has a greater hardness than the aft section.
  • the asymmetric surface is required to control the trajectory, therefore it is desirable that the asymmetric surface is not damaged or deformed during launch.
  • the shape and form of said asymmetric surface will be precision formed, i.e. fine-tuned, so unwanted, or unpredictable, deformation may provide unwanted or unexpected movements of the projectile during activation, and thereby lead to a reduction in predictable control of the trajectory of the projectile.
  • the front ogive section, aft section and any intermediate sections may be solid to act as a mass damper.
  • the front ogive section, aft section and any intermediate sections may contain recesses and/or voids in order to carry auxiliary equipment, for example, sensors, propellant charges, pyrotechnics and explosives and such like.
  • the front ogive section may also contain grooves or striations to improve aerodynamic efficiency or enhance guidance capabilities.
  • the front ogive section and the aft section are rotatably connected by a coupling device.
  • the axis of rotation of the coupling device is about the longitudinal axis of the projectile.
  • the coupling device may be co-axially located within the projectile.
  • the coupling device function is to selectively couple and decouple the relative rotation between the front ogive section and aft section.
  • the front ogive section rotates at the same angular rotation as the aft section.
  • the uncoupled mode the front ogive section is allowed to or caused to rotate at a different angular rotation with respect to the aft section.
  • the coupling device may provide partial coupling, such that the rate of angular rotation between the front ogive and the aft section may be selectively controlled.
  • the coupling device may be a passive coupling device to slow rotation of the front ogive section relative to the aft section.
  • the passive coupling device may be mechanical, electromechanical, electromagnetic, or electronic.
  • the passive coupling device may be a brake or a piezoelectric stack.
  • the brake may be a mechanical device, for example a friction brake such as a disc or drum brake.
  • the brake may be a pumping brake.
  • the passive coupling device may comprise a piezoelectric stack which expands to form an interference fit between the front ogive section and aft section in order to slow the relative angular rotation.
  • a substantially friction free passive coupling device in the decoupled state, the mass of the aft section is greater than the ogive section, therefore the aft section will have greater momentum than the ogive section, the ogive section will start to rotate at a slower angular momentum.
  • the passive coupling device may be activated to decouple, partially decouple, or even stop the angular rotation of the ogive section relative to the aft section.
  • the passive coupling device is engaged, or partially engaged to re-couple i.e. couple the ogive section to the aft section, the angular rotation momentum of the aft section will be partially transferred to the ogive and cause them to rotate at the same rate.
  • the coupling device may comprise an active coupling device such that the angular rotation of the front ogive section can be increased or decreased relative to the angular rotation of the aft section.
  • active coupling devices may include a motor assembly.
  • the active coupling device is a motor, for example a servo motor
  • this allows for active control of the angular rotation of the front ogive section such that it can be progressively slowed and/or increased at differing rates relative to the aft section i.e. a non-linear reduction or increase in angular rotation.
  • the active coupling device may be an electromagnetic brake assembly, with embedded electromagnets between the front ogive section and aft section, which may be selectively energised in order to increase or decrease the angular rotation of the front ogive section relative to the aft section. This also allows for active control of the angular rotation of the front ogive section such that it can be progressively slowed and/or increased at differing rates relative to the aft section i.e. a non-linear reduction or increase in angular rotation.
  • the coupling device is a passive coupling device. More preferably, the passive coupling device is a brake.
  • the coupling device may comprise a central shaft linking the front ogive section to the aft section.
  • the aft section and ogive sections being rotatably mounted thereon.
  • the shaft may be the inner core of a projectile.
  • the projectile may comprise an electrical connection between the front ogive section and aft section.
  • the electrical connection may be completed between the front ogive section and aft section by way of an electrical slip ring or via the central shaft.
  • the asymmetric surface of the front ogive section may be any shape such that, in flight, said shape exerts an imbalanced force on the projectile by deflection of the oncoming airflow.
  • the profile of the asymmetric surface may be a chamfer, a fillet, a round, a bulbous profile or conversely, a relief such as a channel or any other suitable profile which enables oncoming air to be deflected to create a net imbalance on the projectile.
  • the asymmetric surface of the front ogive section may comprise an aerodynamic lifting surface.
  • the aerodynamic lifting surface may be any shape where, in flight, said shape exerts a lifting force on the projectile by deflection of the on-coming airflow.
  • the profile of the aerodynamic lifting surface may be a chamfer, a blunted ogive, a truncated ogive, a fillet, a round, a relief, a NACA profile or a bulbous profile or any other suitable profile which enables oncoming air to be deflected to create a lifting force on the projectile. It will be appreciated however that simpler designs such as a truncated ogive where there is provided a flattened face on the ogive lend themselves to mass production techniques.
  • the asymmetric surface of the front ogive section is an aerodynamic lifting surface. More preferably, the aerodynamic lifting surface is a truncated ogive.
  • the profile of the asymmetric surface is within the diameter of the projectile, i.e. it does not extend out-with the bounds of the plan view of the projectile.
  • Such arrangement avoids the need for deployment mechanisms, which use valuable internal space within the projectile, to deploy the asymmetric surface out-with the original diameter of the projectile after firing.
  • the projectile may be capable of deforming to create the asymmetric surface after firing.
  • asymmetric surface may be created by a piezoelectric effect, mechanical deformation, chemical decomposition or any other suitable means whereby the projectile may deform into an asymmetric surface after firing, for example, a secondary charge which explodes to deform the front ogive section into an asymmetric surface.
  • Such arrangement allows for lower drag coefficients on the projectile for a period of time whilst in the symmetric configuration, for example, during a long transit time.
  • the projectile may be actively and controllably deformed to create the asymmetric surface thereby enabling guidance and control.
  • the deformation of the projectile to create the asymmetric surface may be reversible such that in different phases of flight, the projectile can be selectively deformed and restored to selectively enable guidance and control.
  • the projectile may comprise a retractable element to selectively create the asymmetric surface.
  • Such retractable element may be selectively engaged and disengaged in order to create the asymmetric surface.
  • Said retractable element may be housed within the front ogive section or both the front ogive section and aft section.
  • the retractable element may be arranged in combination with, or separate to, the deformable asymmetric surface as herein described.
  • the asymmetric surface may extend in the range of from 1 to 359 degrees around the plan face of the projectile. Preferably, the asymmetric surface extends in the range of from 40 to 180 degrees around the plan face of the projectile.
  • the projectile may comprise a continuous surface, for example the outer profile of the projectile may be a smooth blended surface absent from protruding fins or control surfaces i.e. the projectile has a uniform ogive "bullet" shape.
  • the projectile may be suitable to be fired from a smooth bore barrel, such that no spin is imparted upon the projectile at launch, in such an arrangement an active coupling device may be required to cause a differential angular rotation between the aft and ogive section.
  • a smooth bore projectile In use, a smooth bore projectile will travel in a substantially straight line trajectory neglecting gravity.
  • the asymmetric surface may exert an imbalance upon the projectile creating a net force acting on the projectile thereby altering the course of the projectile.
  • the coupling device in a smooth bore, unspun projectile, the coupling device must be an active coupling device in order to change the relative angular rotation of the ogive compared to the aft section, to allow the resultant vector of the force imbalance caused by the asymmetric surface.
  • the front ogive section comprising the asymmetric surface is selectively rotated clockwise or anticlockwise relative to the aft section in order to direct the imbalanced force in the correct direction and thereby control the trajectory of the projectile.
  • the projectile may be a spun projectile which is fired from a rifled barrel, such that the rifling in the barrel imparts a spin on the projectile during launch and flight.
  • spin is often used by projectiles to provide ballistic stability during flight, the projectile may have inherent instability due to weight distribution along the length of the projectile being commonly biased to the aft end.
  • the projectile will travel in a substantially helical path towards a target.
  • the front ogive section comprising the asymmetric surface is selectively coupled and decoupled with the aft section.
  • the front ogive section will begin to slow the rate of spin with respect to the aft section due to an aerodynamic roll damping moment.
  • the coupling device may then be disengaged, to allow the front ogive section to be progressively re-coupled with the aft section, the front ogive section may then be accelerated by the aft section, which still has the relatively higher spin rate, back to the initial state the system was in before the brake was first decoupled returning to the substantially original, smaller helix diameter.
  • the arrangement may comprise an active coupling device, for example a servo motor, the front ogive section may be selectively rotated clockwise or anticlockwise relative to the aft section.
  • an active coupling device may result in faster settling times of the system to a steady state which enables the projectile to action more commands within a given timeframe thereby enabling greater precision in guiding the projectile towards a target.
  • the projectile is a spun projectile comprising a passive coupling device.
  • the control module is operably linked to issue guidance commands to the coupling device to steer the projectile to a target.
  • the control module causes the coupling device to selectively couple and decouple the ogive and aft section based on the issued guidance commands.
  • the control module may comprise internal guidance instrumentation such as for example, gyroscopes, accelerometers or other inertial sensors such that the projectile can inherently calculate its position relative to a pre-loaded target without reference to an external targeting and/or location system.
  • internal guidance instrumentation such as for example, gyroscopes, accelerometers or other inertial sensors such that the projectile can inherently calculate its position relative to a pre-loaded target without reference to an external targeting and/or location system.
  • the control module may further comprise sensors such as for example, optical sensors, RF sensors and such like in order to determine the location of a target in flight and calculate and issue guidance commands to steer the projectile to said target.
  • sensors such as for example, optical sensors, RF sensors and such like in order to determine the location of a target in flight and calculate and issue guidance commands to steer the projectile to said target.
  • the control module may be located in the front ogive section or the aft section or any intermediate section. Preferably, the control module is located in the aft section.
  • the projectile may comprise a receiver for receiving guidance instructions from an external targeting and/or location system.
  • Said receiver may include for example, an RF receiver or an optical receiver.
  • the projectile may be linked by a wire to a launch point wherein signals can be received via the wire.
  • the launch point may be in communication with the control module.
  • the projectile may comprise an optical receiver.
  • the guidance instructions may originate from an external targeting and/or location system, for example, a laser designator, GPS transmitter, RF transmitter or electrical signals via wire or optical guided projectile arrangement.
  • an external targeting and/or location system for example, a laser designator, GPS transmitter, RF transmitter or electrical signals via wire or optical guided projectile arrangement.
  • the projectile may be a beam rider projectile such that the projectile comprises an optical receiver wherein the projectile attempts to stay on the path of a laser beam based on the strength of laser signal on the optical receiver.
  • the projectile may comprise a transmitter for transmitting the projectile's position.
  • Said transmitter may include for example, an RF transmitter or an optical transmitter.
  • the projectile may be mounted with an array of sensors to relay position and orientations to the control system.
  • the projectile may also be fitted with some passive or active identifier, such as a reflective surface or RF beacon, which an external observer can use to identify the location of the projectile using imaging equipment and sensors.
  • the projectile may comprise a passive surface to reflect light back to an observer, so as to minimise power consumption.
  • the transmitter may be in communication with the control module.
  • the transmitter for transmitting the projectile position may aide in the location and acquiring of guidance instructions from an external transmitter.
  • the projectile may need to both transmit and receive, any may comprise a transceiver module, to allow two-way communication.
  • the projectile calibre may vary in the range of from small calibre direct fire projectiles, bullets, for example .22LR to indirect fire projectiles, artillery shells, such as, for example up to 155mm shells, or larger.
  • any calibre projectile providing a coupling device is embedded within the projectile to allow the rate of angular rotation of the front ogive and aft section to be selectively controlled, and wherein the front ogive section comprises an asymmetric surface such that an asymmetric force can be exerted upon the projectile thereby enabling guidance and control.
  • a system for controlling a projectile to a target comprising a projectile as defined herein; wherein in a first arrangement the coupling device is coupled, such that the front section spins at the same angular rotation as the aft section, the projectile travelling in a first helical trajectory, in a second arrangement the coupling device is decoupled, such that the front section spins at a different angular rotation relative to the aft section, the projectile travelling in a second helical trajectory, said first helical trajectory comprising a smaller radius than the second helical trajectory, selective activation between the first and second arrangements, causing a change in direction, thereby enabling the projectile to be steered to the target.
  • the system may be arranged such that the projectile receives guidance instructions from the targeting system as herein described in the first aspect.
  • the system may be arranged such that the projectile transmits its position to the targeting system as herein described in the first aspect.
  • one example of guidance is to determine the projectile lateral acceleration (Latax) as a function of the size of the angle through which the front ogive section is slowed (2 ⁇ a ) and the direction about which the bias manoeuvre is centred ( ⁇ B ).
  • a generalised decomposition of F c onto any orthonormal axis i,j, in the plan view plane of projectile, herein denoted as YZ has the corresponding forces F i ,F j .
  • ⁇ i be a particular angle between F c and the arbitrary decomposition axis i .
  • ⁇ a be the angle through which F c sweeps at a given rate ⁇ such that the sweep begins at the angle ( ⁇ B - ⁇ a ) and ends at ⁇ B .
  • the range of angles during which F c is slowed is defined as the bias angle.
  • the bias angle thus starts at ( ⁇ B - ⁇ a ) and ends at ( ⁇ B + ⁇ a ) with a midpoint of ⁇ B .
  • F c will continue to rotate through the rest of the angle ⁇ eventually sweeping another angular range ( ⁇ B + ⁇ ) ⁇ ⁇ a (wrapped so ⁇ ⁇ [0,2 ⁇ ]).
  • the resulting change in velocity is directed along the negative i th axis.
  • ⁇ a ⁇ / 2. which is evaluated for a given system.
  • QDGL Quasi-dynamic Guidance Law
  • the desired speed change and resulting bias angles are calculated when ⁇ lies in a small range, ⁇
  • , to account for the control module inaccuracy. While this calculation could be conducted and updated continuously, the relative speeds would have to transformed to the ⁇ 0 reference frame which adds another layer of computational complexity. In addition, this discrete computation of speeds at the beginning of each rotation accommodates the bandwidth of hardware with respect to the roll rate of the projectile.
  • V DR 0 u R + ⁇ V
  • ⁇ ⁇ / 4.
  • V PT ( d ) describes the chosen approach speed as a function of d .
  • This function can be calculated by starting with a stationary projectile and applying consecutive ⁇ V m ⁇ x biases, since the process is reversible.
  • V PT ( d ) V lim d ⁇ ⁇ , ⁇ ⁇ R ⁇ 0 where ⁇ is a constant to be optimised.
  • the radial velocity of the projectile to the target may be governed by the QDGL equation;
  • V PT d V lim d ⁇ ⁇ V k 0 ⁇ d ⁇ ⁇ d 1 ⁇ d d 2 ⁇ d ⁇ d 1 0 ⁇ d ⁇ d 2 wherein;
  • a method of controlling the projectile, as herein described, towards a target comprising:
  • the method may comprise a step wherein the projectile receives guidance instructions from an external targeting system.
  • the method may comprise the step wherein the projectile transmits its position.
  • a projectile 100 comprising: a front ogive section 102, an aft section 104; and a control module 106; wherein the front ogive section 102 is rotatably connected to the aft section 104 by a coupling device 108, the front ogive section 102 further comprising an asymmetric surface 110, where in use, the angular rotation of the front ogive section 102 can be selectively adjusted relative to the aft section 104 by commands from a control module 106 to the coupling device 108, such that the asymmetric surface 110 exerts an imbalance upon the projectile to selectively alter the trajectory of said projectile, and thereby steer and course correct the projectile.
  • the projectile is a gun launched projectile, such as a medium calibre shell wherein the front ogive section 102 and aft section 104 are made from steel.
  • a gun launched projectile such as a medium calibre shell wherein the front ogive section 102 and aft section 104 are made from steel.
  • features such as fuzes, driving bands, and other typical features are not shown.
  • the coupling device 108 is an active coupling device in the form of a servo motor.
  • the servo motor allows both clockwise and anticlockwise rotation of the front ogive section 102 with respect to the aft section 104.
  • the projectile rotates about axis X.
  • the projectile comprises an electrical slip ring (not shown) between the front ogive section 102 and the aft section 104.
  • the asymmetric surface 110 is an aerodynamic lifting surface, specifically a truncated ogive. Said asymmetric surface extends ⁇ °, in this example 90°, around the plane face of the projectile as seen in Section A-A.
  • the projectile 100 comprises a continuous surface such that the outer profile of the projectile 100 is smooth blended surface absent from protruding fins or protruding control surfaces.
  • the projectile may comprise a receiver for receiving guidance instructions from an external targeting system in the form of an optical receiver 112.
  • Said optical receiver 112 is in communication with the control module 106 and is a beam rider receiver such that the optical receiver senses the intensity of a guidance laser (not shown) wherein the control module 106 is configured to detect drift of the laser focus from the optical receiver 112 wherein the control module 106 issues commands to the coupling 108 in order to remain on the laser path.
  • FIG. 2 there is provided the projectile of Figure 1 as a force diagram.
  • the projectile 200 comprising both front ogive section 202 and aft section 204 travelling at velocity v.
  • the projectile is fired from a rifled barrel, the aft section 204 and ogive 202 both rotate at the same clockwise angular rotation w1 & w2 respectively against oncoming airflow A.
  • the oncoming airflow A is deflected by the asymmetric surface 210 to create a first imbalanced force vector F c on the projectile.
  • the servo motor On command of the control module (not shown), the servo motor changes the rate of angular rotation of the ogive 202, to either a reduced clockwise ⁇ 2' angular rotation rate or an anticlockwise ⁇ 3' with respect to the aft section 204 which continues to rotate at angular speed w1 thereby creating a second imbalanced force vector F c on the projectile, i.e. altering the angle of the force vector F c about the axis X.
  • the coupling device may be a passive coupling device in the form of a brake.
  • the brake can be selectively braked and un-braked to uncouple the front ogive section from the aft section thus allowing the front ogive section to slow due to an aerodynamic roll damping moment.
  • FIG. 3a & 3b there is provided a projectile 300 as shown in Figure 1 , travelling in a helical path substantially along the axis x after firing from a rifled barrel.
  • the front ogive section and aft section are in the decoupled mode, i.e. the front ogive section is spinning at a different angular rotation compared to the aft section, the helix radius is r2 on the superimposed YZ plane, wherein radius r2 is greater than radius r1.
  • the control force from the aerodynamic surfaces on the ogive act in a tangential direction for longer, resulting in a larger radial acceleration.
  • the projectile thus travels further radially before the control force rotates to oppose the motion.
  • the result is that in the decoupled state, the trajectory forms a larger helix r2 diameterthan in the coupled mode r1.
  • the front ogive section and aft section re-couple such that the front ogive section is restored to the spin rate of the faster spinning aft section thus returning to a helix radius r1 as shown in Figure 3a .
  • FIG 4 there is provided a system 400 for controlling a projectile, the system comprising a projectile 402 as shown in Figure 1 fired from a rifled artillery gun 404 towards a target 406 along a nominal trajectory 408.
  • the coupling device of projectile 402 is coupled such that the front section spins at the same angular rotation as the aft section, the projectile travelling in a first helical trajectory with radius r1.
  • the projectile 402' coupling device is decoupled, the front section spins at a different angular rotation relative to the aft section, the projectile travelling in a second helical trajectory with radius r2, wherein the first helical radius r1 is smaller than the second helical radius r2, thereby enabling the projectile 402 to be steered to the target 406.
  • an external targeting system in the form of a laser designator 410.
  • Said laser designator is trained on the target 406 by beam 412.
  • the laser designator in optical communication with the projectile 402 comprising an optical receiver on the projectile via optical signals 414.
  • a system for controlling a projectile 500 comprising a projectile 502.
  • said projectile 502 is a small arms calibre bullet fired from a rifle 504 towards a target 506 along a nominal trajectory 508.
  • the coupling device of projectile 502 is coupled such that the front section spins at the same angular rotation as the aft section, the projectile travelling in a first helical trajectory with radius r1.
  • the projectile 502' coupling device is decoupled, the front section spins at a different angular rotation relative to the aft section, the projectile travelling in a second helical trajectory with radius r2, wherein the first helical radius r1 is smaller than the second helical radius r2.
  • the second helical radius corrects the projectile flightpath such that the projectile is on a trajectory which will hit the target 506 wherein the front ogive section couples with the aft section to travel in a third helical trajectory with radius r3, wherein the third helical radius is smaller than radius r2, thereby enabling the projectile 502 to be steered to the target 506.
  • the projectile is further able to couple and decouple multiple times during flight to switch between larger and smaller helical trajectories in order to correct the trajectory to target 506.
  • an internal guidance system within the control module (not shown) of the projectile 502 in the form of an accelerometer and gyroscope wherein the projectile can inherently calculate its position and issue instructions to the coupling device to guide the projectile 502 to the target 506 without reference to an external targeting system.
  • FIG. 6 there is provided a method flow diagram 600 for controlling a projectile as herein described, the method comprising:

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP20275128.5A 2020-07-30 2020-07-30 Lenkbares projektil Ceased EP3945279A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP20275128.5A EP3945279A1 (de) 2020-07-30 2020-07-30 Lenkbares projektil
PCT/GB2021/051866 WO2022023706A1 (en) 2020-07-30 2021-07-21 Steerable projectile
EP21749267.7A EP4189322A1 (de) 2020-07-30 2021-07-21 Lenkbares projektil
US18/007,133 US20230228546A1 (en) 2020-07-30 2021-07-21 Steerable projectile

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EP20275128.5A EP3945279A1 (de) 2020-07-30 2020-07-30 Lenkbares projektil

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EP3945279A1 true EP3945279A1 (de) 2022-02-02

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005043474A1 (de) * 2005-09-13 2007-03-15 Deutsch-Französisches Forschungsinstitut Saint-Louis, Saint-Louis Vorrichtung zum Steuern eines Geschosses
WO2007030687A2 (en) * 2005-09-09 2007-03-15 General Dynamics Ordnance And Tactical Systems Projectile trajectory control system
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WO2010039322A2 (en) * 2008-07-09 2010-04-08 Bae Systems Land & Armaments L.P. Roll isolation bearing
EP2263058B1 (de) * 2008-03-13 2013-10-02 Thales Holdings UK Plc Steuerbares projektil
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* Cited by examiner, † Cited by third party
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WO2007030687A2 (en) * 2005-09-09 2007-03-15 General Dynamics Ordnance And Tactical Systems Projectile trajectory control system
DE102005043474A1 (de) * 2005-09-13 2007-03-15 Deutsch-Französisches Forschungsinstitut Saint-Louis, Saint-Louis Vorrichtung zum Steuern eines Geschosses
US20080142591A1 (en) * 2006-12-14 2008-06-19 Dennis Hyatt Jenkins Spin stabilized projectile trajectory control
EP2263058B1 (de) * 2008-03-13 2013-10-02 Thales Holdings UK Plc Steuerbares projektil
WO2010039322A2 (en) * 2008-07-09 2010-04-08 Bae Systems Land & Armaments L.P. Roll isolation bearing
US20160033244A1 (en) * 2014-07-30 2016-02-04 U.S. Army Research Laboratory ATTN: RDRL-LOC-1 Steerable munitions projectile

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