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WO2011019424A2 - Missile guidé - Google Patents

Missile guidé Download PDF

Info

Publication number
WO2011019424A2
WO2011019424A2 PCT/US2010/035178 US2010035178W WO2011019424A2 WO 2011019424 A2 WO2011019424 A2 WO 2011019424A2 US 2010035178 W US2010035178 W US 2010035178W WO 2011019424 A2 WO2011019424 A2 WO 2011019424A2
Authority
WO
WIPO (PCT)
Prior art keywords
missile
wings
fins
set forth
aft
Prior art date
Application number
PCT/US2010/035178
Other languages
English (en)
Other versions
WO2011019424A3 (fr
Inventor
Michael P. Unger
Stephen D. Witherspoon
James T. Schleining
Original Assignee
Raytheon 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 Raytheon Company filed Critical Raytheon Company
Priority to EP10784603.2A priority Critical patent/EP2433084B1/fr
Publication of WO2011019424A2 publication Critical patent/WO2011019424A2/fr
Publication of WO2011019424A3 publication Critical patent/WO2011019424A3/fr

Links

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
    • 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

  • a guided missile having a projectile body and aerodynamic surfaces that stabilize, guide, and/or lift the projectile body during various stages of a flight path.
  • Range e.g., 25 nautical miles
  • accuracy e.g., within 10 meters of identified target
  • effectiveness e.g., greater than 99% lethality
  • these key factors need to be balanced within a missile design to insure that all three are optimized. For example, while range can be prolonged by faster muzzle velocity, the resulting increased setback acceleration can negatively impact crucial instrumentation and thereby shortchange accuracy and/or effectiveness.
  • a missile also often inherits other variables that afford little or no liberties during design development.
  • the projectile body usually must have a size/shape to accommodate an intended artillery platform and/or gun barrel (e.g., 155 mm diameter and 1 m length).
  • a missile includes a payload (e.g., a warhead), its size, shape, and/or weight are almost always dictated primarily by mission objectives.
  • a missile design is provided that reduces costs, increases reliability, and/or simplifies structure without compromising key performance parameters.
  • Range performance is achieved by enhanced acceleration capability and improved lift-to- drag ratio, not faster muzzle velocities and/or greater launch charges.
  • setback acceleration is decreased, whereby the missile's instrumentation can reside in a less reliability-threatening environment.
  • the missile's structural-strength requirements can be relaxed.
  • the missile achieves its enhanced-acceleration feature by combining the functionality of certain aerodynamic surfaces.
  • the missile comprises tail fins that perform a stabilizing function during the just-launched stage of the flight path and perform a guiding function during post-ballistic stages of the flight path.
  • the missile achieves its improved-lift feature by a pair of wings that are deployed from a mid portion of the projectile body.
  • the missile can cruise during an apogee stage, precisely adjust direction during a midcourse trajectory stage, and/or situate itself for a near vertical angle-of-attack during terminal trajectory.
  • the missile can be constructed to have a conventional projectile-body shape) and to carry a payload adequate for most mission objectives.
  • the projectile body can have a diameter (e.g., 155 mm) and length (e.g., 1 m) compatible with current and future artillery platforms and/or howitzers.
  • the missile can provide accurate, first round fire-for-effect capacity.
  • a missile includes: a projectile body having a fore-aft axis and comprising a nose portion, and a mid portion aft of the nose portion, and a tail portion aft of the mid portion; a bearing coupler within the projectile body allowing at least a part of the tail portion to rotate freely relative to the mid portion about the fore-aft axis; a clutch within the projectile body that
  • wings engages/disengages to selectively allow/prevent tail rotation
  • wings stowed within pockets in the mid portion, each having an airfoil and a leading edge
  • a deployer within the mid portion, that selectively deploys the wings from the pockets to deployed positions whereat their leading edges extend radially outward from the aft- fore axis in lift-imparting orientations
  • an obturator maintaining the fins within the slots
  • a deflector that deflects the fins from their roll-stabilizing orientations to angularly align their leading edges relative to the aft-fore axis in direction-controlling orientations.
  • a missile includes: a projectile body having a fore-aft axis and comprising a nose portion, and a mid portion aft of the nose portion, and a tail portion aft of the mid portion; a bearing coupler within the projectile body allowing at least a part of the tail portion to rotate freely relative to the mid portion about the fore-aft axis; a clutch within the projectile body that
  • a method of missile flight includes the steps of: launching a missile from a launch unit; deploying fins of the missile; during an initial roll-stabilized flight regime, allowing free rotation of a tail of the missile that includes the fins; and after the roll-stabilized flight regime, engaging a clutch of the missile to prevent tail rotation.
  • Figure 1 is schematic diagram of a mission wherein a missile is launched and then guided to encounter a target.
  • Figures 2A - 2C are side, top, and aft schematic views of a missile having wings deployed in an aft direction.
  • Figures 3A - 3C are side, top, and aft schematic views of a missile having wings deployed in a fore direction.
  • Figure 4 is a schematic diagram of a controller of the missile.
  • a missile 10 is shown in a military setting as it follows a flight path from a launch unit 1 1 to a target 12.
  • the launch unit 1 1 can comprise a howitzer 13, or other gun or cannon, having conventional specifications and/or capabilities.
  • muzzle velocity can be
  • the illustrated flight path includes a just-launched stage (immediately after exit from the howitzer 13) and post-launch stages thereafter.
  • the post-launch stages include a ballistic stage (determined primarily by muzzle velocity and launch angle), an apogee stage (upon reaching a cruise elevation), a mid-course trajectory stage (optimized for target range/arrival), and a terminal trajectory stage (optimized for target impact).
  • Other flight paths are possible and contemplated. For example, if the missile 10 was on a battle-damage-assessment or other information-collecting mission, the flight path may not includes the latter trajectory stages.
  • the missile's pursuit of the target 12 can be collaborated by other manned and unmanned units, such as a remote command unit 15, a field intelligence unit 16, and/or a global-positioning-system unit 17.
  • the missile 10 comprises a projectile body 20 having a generally cylindrical shape with a fore-aft axis 21 .
  • the projectile body 20 can be shaped/sized to accommodate a conventional launch unit (e.g., launch unit 1 1 ).
  • the projectile body 20 can have a diameter of 155 mm and a length of 1 - 3 meters (e.g. , 1 m, 1 .55 m, 2.25 mm, etc.).
  • the projectile body 20 comprises a nose portion 30, a mid portion 40 aft of the nose portion 30, and a tail portion 50 aft of the mid portion 40.
  • the nose portion 30 can comprise a payload chamber 31 occupying most of its interior space.
  • the mid- portion 40 comprises diametric wing slots 41 and can comprise instrument bays 42 occupying the space around the slots 41 .
  • the tail portion 50 can comprise a base part 51 , a retainer part 52, a bearing coupler 53, and a clutch 54.
  • the base part 51 can be fixedly mounted to the mid portion 40 and the retainer part 52 attached to the base part 51 by the bearing coupler 53.
  • the retainer part 52 includes radial slots 55 (e.g., four) spaced circumferentially around its outer surface.
  • the bearing coupler 53 allows the retainer part 52 to rotate freely relatively to the base 51 (and/or the mid portion 40) about the fore-aft axis 21 .
  • the clutch 54 can be engaged-disengaged to allow-prevent tail rotation.
  • the entire tail portion 50 could be coupled to the mid portion 40 by the bearing coupler 53, whereby it would constitute the retainer part 52. In either event, at least part of the tail portion 50 can rotate freely relative to the mid portion 40.
  • the retainer part 52 includes (has in it) the slots 55.
  • the missile 10 can comprise a payload 60, contained within the chamber 31 in the nose portion 30.
  • the payload 60 could comprise a warhead (e.g., destructive munitions).
  • the nose portion 30 and/or the chamber 31 can include other objects or devices, such as communication/guidance gear for actively or passively interacting with remote units 1 1 , 15, 16, and/or 17.
  • the missile 10 further comprises wings 70 and fins 80.
  • the wings 70 are shown stowed within the pockets 41 in the mid portion 40 and the fins 80 are shown stored within the slots 55 in the tail portion 50.
  • the wings 70 each comprise an airfoil 71 having a leading edge 72.
  • a wing deployer 73 within the mid portion 40 is operative to deploy the wings 70 from their stowed positions ( Figure 2A and Figure 3A) to their deployed positions ( Figures 2B -
  • the wings 70 can comprise arms 74 connected to their inboard edges and the wing deployer can comprise a rod 75 to which the distal ends of the arms 74 are pivotally attached.
  • the rod 75 can be located in an aft region of the mid portion 40, and the wings 70 can symmetrically move in the aft direction to deploy from the pockets 71 .
  • the rod 75 can be located in a fore region of the mid portion 40, and the wings 70 can symmetrically move in the fore direction to deploy from the pockets 71 .
  • the deployed position of the wings 70 can be rigid whereby their leading edges 72 remain at a constant deflection angle relative to the fore-aft axis 21 .
  • the fins 80 each comprise an airfoil 81 having a leading edge 82.
  • An obturator 83 maintains the fins in their stored condition ( Figure 2A and Figure 3A) until muzzle exit and releases them upon muzzle exit for movement to their released conditions ( Figures 2B - 2C and Figures 3B - 3C)
  • the obturator 83 is designed to break, fracture, or otherwise destruct to release the fins 80 during the just-launched stage of the flight path.
  • the obturator 83 is located towards the aft end of the tail portion 50, to protect the fins 80 during firing and/or reduce pressure on protective covers (not shown).
  • a fin deflector 84 within the tail portion 50, is operative to deflect the fins 80 from their roll- stabilizing orientations to angularly align their leading edges 82 relative to the aft-fore axis 81 in direction-controlling orientations.
  • the missile 10 can further comprise a controller 90, such as schematically shown in Figure 4.
  • the controller 90 can comprise, for example, an output panel 91 that conveys control signals to the clutch 54, the wing deployer 73, and the fin deflector 84.
  • the illustrated controller 90 also comprises an input panel 92 that receives information from onboard sensors, a GPS receiver 93, a collector 94, a command-unit receiver 95, a command-unit transmitter 96, a processor 97, and memory/storage 98.
  • the controller 90 can be housed within the instrument bay 42 in the mid portion 40 and/or it can be powered by a battery 99 also housed within the instrument bay 42.
  • the wings 70 Prior to launch of the missile 10, the wings 70 would be stowed within the mid portion 40, the fins 80 would be stored within the tail portion 50, and the obturator 83 would be intact. As the missile 10 exits the gun muzzle, the obturator 83 would release the fins 80 and they would move to released conditions whereat their leading edges 82 are in roll-stabilizing orientations.
  • the clutch 54 would be disengaged, thereby allowing tail rotation during the ballistic stage of the path flight.
  • the clutch 54 would be disengaged, thereby allowing tail rotation during the ballistic stage of the path flight.
  • the controller 90 can begin its contribution to the flight path. Specifically, the controller 90 can be programmed to send control signals (via its output panel 91 ) to the deployer 73 to deploy the wings 70.
  • the wings 70 can be adapted to impart substantial lift to the projectile body 20, with little or no steering or guiding responsibilities. To this end, the tip-to-tip span of the wings 70 can be greater (e.g. , 50% greater, 75% greater, 100% greater, 150% greater, and/or 200% greater) than the tail span of the fins 80.
  • the wings' leading edge 72 can rigidly remain at a constant angle relative to the fore-aft axis 21 .
  • the clutch 54 can be engaged to prevent tail rotation.
  • the controller 90 can signal the fin deflector 84 to deflect the fins' leading edges 82 in particular direction-determining orientations.
  • the fins 80 and/or the deflector 84 are designed to deflect in a multitude of orientations (about a plurality of axes) for optimum guidance of the missile 10.
  • the wings 70 can remain deployed or be returned to stowage (depending upon descent angle). And the fins 80 can continue to be maneuvered to direct the missile 10 towards the target 12.
  • the wings 80 can be returned to stowed positions (if not already there) during the terminal trajectory stage, to allow a near vertical angle of attack.
  • the controller 90 can ascertain the missile's stage in the flight path in a variety of ways. For example, the controller 90 can continuously obtain the missile's current global position (via its GPS receiver 93) and compare this to previously input positions (e.g., input prior to launch). Flight path stages can be ascertained by the altitude of the missile 10 and/or predetermined period of times. If the missile 10 and/or the controller 90 are equipped with target-seeking instrumentation (e.g., the collector 94), visual data concerning the target 12 can be used for this purpose. And/or a remote unit, such as the command unit 15, can receive data from and/or convey instructions to the controller 90 (e.g., via receiver 95 and transmitter 96).
  • target-seeking instrumentation e.g., the collector 94
  • visual data concerning the target 12 can be used for this purpose.
  • a remote unit such as the command unit 15, can receive data from and/or convey instructions to the controller 90 (e.g., via receiver 95 and transmitter 96).
  • missile 10 has design that reduces costs, increases reliability, and/or simplifies structure without compromising key
  • fins 80 function both as stabilizing components during the ballistic stage of the flight path and later as guiding components during post-ballistic stages of the flight path. This combined functionality removes the need for canards or other separate guiding components.

Landscapes

  • 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)

Abstract

Missile (10) comprenant un corps de projectile (20), une charge utile (60) contenue dans la partie nez (30), des ailes (70) repliées dans la partie centrale (40), et des ailerons (80) repliés dans la partie queue (50). Les ailes (70) peuvent être déployées au cours de phases intermédiaires de la trajectoire de vol où une portance s'avère avantageuse, et repliées au cours des phases terminales où un angle d'attaque quasi vertical s'avère souhaitable. Les ailerons (80) jouent le rôle de composants stabilisateurs au cours de la phase balistique initiale de la trajectoire de vol, puis de composants de guidage.
PCT/US2010/035178 2009-05-19 2010-05-18 Missile guidé WO2011019424A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10784603.2A EP2433084B1 (fr) 2009-05-19 2010-05-18 Missile guidé

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US17939109P 2009-05-19 2009-05-19
US61/179,391 2009-05-19

Publications (2)

Publication Number Publication Date
WO2011019424A2 true WO2011019424A2 (fr) 2011-02-17
WO2011019424A3 WO2011019424A3 (fr) 2011-05-05

Family

ID=43586715

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2010/035178 WO2011019424A2 (fr) 2009-05-19 2010-05-18 Missile guidé

Country Status (3)

Country Link
US (1) US20120068002A1 (fr)
EP (1) EP2433084B1 (fr)
WO (1) WO2011019424A2 (fr)

Families Citing this family (12)

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KR102007617B1 (ko) 2009-02-02 2019-10-01 에어로바이론먼트, 인크. 멀티모드 무인 항공기
KR102033271B1 (ko) * 2009-09-09 2019-10-16 에어로바이론먼트, 인크. 엘리본 제어 시스템
CN102596722B (zh) 2009-09-09 2016-08-03 威罗门飞行公司 用于远程工作的无人驾驶航空飞行器的带有便携式rf透明发射管的抑制爆炸声的发射器的系统和设备
SE535991C2 (sv) * 2011-07-07 2013-03-19 Bae Systems Bofors Ab Rotationsstabiliserad styrbar projektil och förfarande därför
SG11201500073VA (en) * 2012-06-07 2015-03-30 Aerovironment Inc System for detachably coupling an unmanned aerial vehicle within a launch tube
WO2015179101A2 (fr) * 2014-04-30 2015-11-26 Bae Systems Land & Armaments L.P. Munition tirée par un pistolet et dotée de listons
GB2543376A (en) * 2015-06-05 2017-04-19 Lockheed Corp Deployment mechanism
FR3041744B1 (fr) * 2015-09-29 2018-08-17 Nexter Munitions Projectile d'artillerie ayant une phase pilotee.
DE102015013913A1 (de) * 2015-10-27 2017-04-27 Deutsch Französisches Forschungsinstitut Saint Louis Vollkalibriges, drallstabilisiertes Lenkgeschoss mit einer hohen Reichweite
KR101903250B1 (ko) 2016-12-22 2018-10-01 주식회사 한화 정밀유도키트용 롤카나드 구동장치 및 이를 이용한 롤카나드 구동방법
DE102020105188B4 (de) 2020-02-27 2023-08-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Flugkörper-Finnenausklappeinrichtung, Flugkörper und Verfahren zum Betrieb eines Flugkörpers
US11624594B1 (en) * 2020-03-31 2023-04-11 Barron Associates, Inc. Device, method and system for extending range and improving tracking precision of mortar rounds

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Also Published As

Publication number Publication date
US20120068002A1 (en) 2012-03-22
WO2011019424A3 (fr) 2011-05-05
EP2433084A2 (fr) 2012-03-28
EP2433084B1 (fr) 2013-05-08

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