US20120091253A1 - Method of intercepting incoming projectile - Google Patents
Method of intercepting incoming projectile Download PDFInfo
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- US20120091253A1 US20120091253A1 US12/198,146 US19814608A US2012091253A1 US 20120091253 A1 US20120091253 A1 US 20120091253A1 US 19814608 A US19814608 A US 19814608A US 2012091253 A1 US2012091253 A1 US 2012091253A1
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- missile
- launching
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- interceptor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
- F41H11/00—Defence installations; Defence devices
- F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/073—Silos for rockets, e.g. mounting or sealing rockets therein
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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
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/10—Missiles having a trajectory only in the air
Definitions
- the invention is in the field of devices and methods for defending against incoming projectiles.
- Rocket propelled grenades are examples of a type of projectile that poses a great threat to ground vehicles, aircraft, and helicopters.
- RPGs are commonly used during close-in military engagements, where the shooter and the target are close to one another. Defending against such incoming projectiles presents a difficult problem. From the foregoing it will be appreciated that it may be desirable to have improved ways of dealing with incoming projectiles.
- a method of intercepting an incoming projectile includes soft launching an interceptor missile, and altering course of the interceptor missile within 250 milliseconds to an interception course for intercepting the incoming projectile.
- a method of intercepting a projectile includes the steps of: determining a desired interception direction for an interceptor missile; launching the missile in a given direction at a speed less than or equal to 40 m/sec (130 ft/sec); and altering course of the missile to the desired interception direction for intercepting the projectile, wherein the altering course is substantially accomplished within 250 milliseconds of launch.
- FIG. 1 is a side view of an interceptor missile in accordance with an embodiment of the present invention
- FIG. 2 is a side sectional view of the interceptor missile of FIG. 1 ;
- FIG. 3 is an oblique view illustrating a soft launching process of the interceptor missile of FIG. 1 ;
- FIG. 4 is an oblique view of a ground vehicle having a launcher attached for launching the interceptor missiles of FIG. 1 ;
- FIG. 5 is a diagram illustrating the launch and interception process using the interceptor missile of FIG. 1 ;
- FIG. 6 is an oblique view of an air vehicle having a launcher mounted there upon for launching interceptor missiles of the type shown in FIG. 1 .
- a method of defeating an incoming missile includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction.
- launching at a relatively slow speed such as a speed less than or equal to 40 m/sec (130 ft/sec)
- the interceptor missile may reach the desired interception direction within 250 milliseconds of launch.
- the interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location.
- the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.
- an interceptor missile 10 is used for intercepting an incoming projectile, such as a rocket propelled grenade (RPG).
- RPG rocket propelled grenade
- the interceptor missile 10 is soft launched in a predetermined orientation, such as vertically up or vertically down.
- the course of the missile is then altered to a desired interception direction. This altering of course may be substantially accomplished over a wide range of possible directions, such as a hemisphere of directions relative to the launch direction, over a time of 250 milliseconds or less.
- the interceptor missile 10 is then accelerated toward the incoming missile or projectile.
- the interceptor missile 10 At its front end the interceptor missile 10 includes a dome 12 which covers a warhead 14 and warhead fragments 16 .
- the interceptor missile 10 is configured to detonate the warhead 14 at a predetermined time after launch. This propels the fragments 16 out the forward end of the missile 10 , displacing the dome 12 . Warhead fragments 16 collide with the incoming missile or projectile and damage the incoming missile or projectile, preventing it from reaching its intended target.
- the warhead 14 and the warhead fragments 16 are enclosed in a tubular forward body 20 .
- the body 20 is capped at its front end by the dome 12 .
- An igniter 22 in a middle body 24 is used to detonate the warhead 14 .
- the igniter 22 may be controlled by suitable control logic within the middle body 24 .
- Control logic may include, for example, integrated circuits that are used to control the timing of the firing of the igniter 22 .
- Control logic may also be used to control the propulsion system of the interceptor missile 10 .
- a propulsion system 28 of the interceptor missile 10 is located in the aft half of the missile.
- the propulsion system 28 includes a solid rocket motor 30 , with multiple propellant grains 31 , which provide the main propulsion system for acceleration or boost of the interceptor missile 10 .
- the solid rocket motor 30 may include conventional solid rocket fuel, configured so as to burn quickly when ignited.
- the solid rocket motor 30 may be ignited by a boost igniter 32 .
- the boost igniter 32 is at an opposite end of the middle body 24 from the warhead igniter 22 . Pressurized gas produced by combustion of the solid rocket motor 30 is directed rearward through a main boost nozzle 36 at the aft end of the interceptor missile 10 .
- the interceptor missile 10 also has a series of pitch over motors 40 for altering the orientation and course of the interceptor missile 10 .
- the interceptor missile 10 has four pitch over motors 40 axisymmetrically spaced around the back or aft end of the circumferential perimeter of a back or aft body 44 .
- the back or aft body 44 includes not only the pitch over motors 40 , but also the solid rocket motor 30 .
- the pitch over motors 40 each include pitch over motor fuel 46 , and a pitch over motor thrust chamber 48 .
- the pitch over motors 40 provide thrust substantially perpendicular to an axis 49 of the interceptor missile 10 .
- the pitch over motor fuel 46 may be a solid fuel that may be identical to the fuel used in the solid rocket motor 30 .
- a suitable ignition device may be used for igniting the pitch over motor fuel 46 as necessary. Pressurized gases from the burning of the pitch over motor fuel 46 are received through the pitch over motor thrust chamber 48 , and exit out through pitch over motor openings 50 .
- the pitch over motor openings 50 are circular or other suitable-shape openings along a circumference or perimeter of the back or aft body 44 .
- the pitch over motors 50 may each have substantially the same impulse, and each may be substantially identical.
- the control of orientation of the missile 10 may be accomplished by controlling the timing of the firing of the pitch over motors 50 .
- a small rotation in a given axis may be obtained by closely spacing in time the firings of a pitch over motor and its diametrically-oppose counterpart. Greater rotation of the missile about the axis may be obtained by increasing the time between firings of diametrically-opposed motors. Since the diametrically-opposed motors have substantially the same impulse, there will be no residual rotation of the missile after both pitch over motors have completed their burns.
- use of the pitch over motors 50 such as described above advantageously does not require any additional control of the pressurized gasses (such as by a variable nozzle) other than by control of the timing of the ignition of the pitch over motors 50 .
- the interceptor missile 10 also may have a series of deployable fins 52 that deploy from slots 54 in the aft body 44 .
- the fins 52 stabilize the interceptor missile 10 .
- the fins 52 may be axisymmetrically deployed around the circumference of the aft body 44 at substantially the same longitudinal location as the pitch over motor openings 50 . There may be the same number of fins 52 as pitch over motor openings 50 . Alternatively, and especially for short-range missiles, the fins may be omitted.
- the interceptor missile 10 may weigh 5.7 kg (12.5 pounds), may be 46 cm (18 inches) long, and may have a diameter of 8.9 cm (3.5 inches). It will be appreciated that these are only values for a single embodiment, and that the weight and dimensions of the interceptor missile 10 may vary over a wide variety of values.
- FIG. 3 illustrates the launching process for the interceptor missile 10 .
- the missile is soft launched from a launcher 80 .
- Soft launch refers to launching without firing of a propulsion system of the interceptor missile 10 .
- the launcher 80 may use a pressurized gas launch system to soft launch the missile 10 , for example by using pressurized expanding gases, from the missile or cannister from a separate system, to provide lift to the missile.
- Soft launching allows for a smoother launch of the interceptor missile 10 , with less tip over relative to a hard launch that involves emission of pressurized gases from the missile while the missile is still in the launcher.
- An example of a system for soft launching is the pressurized gas launcher described in co-owned patent application Ser. No. 12/135,512, filed Jun. 6, 2008, which is incorporated herein by reference.
- the soft launch of the interceptor missile 10 enables a faster and more predictable transition to a desired interception course for intercepting an incoming missile or projectile.
- the missile 10 is able to quickly redeploy from a predetermined initial launch trajectory 82 ( FIG. 3 ) to substantially any trajectory within at least a hemisphere 84 ( FIG. 3 ) about the launch trajectory 82 .
- the interceptor missile 10 may be capable of redeploying over more than merely the hemisphere 84 .
- the interceptor missile 10 may be capable of deploying over substantially a full circle, to any trajectory, even a downward trajectory vertically upward launch shown in FIG. 3 .
- the pitch over motors 40 may be such as to be able to deploy interceptor missile 10 to a desired interceptor trajectory within 250 milliseconds of launch from the launcher 80 .
- the pitch over motors 40 may be strong enough to provide at least 2,000° per second of rotation to the interceptor missile 10 .
- the pitch over motors 40 may be sufficiently strong to provide at least 6,000° or 7,000° per second of rotation to the interceptor missile 10 .
- the interceptor missile 10 may be coupled by an umbilical 90 ( FIG. 3 ) to a launcher controller 92 . This allows the interceptor missile 10 to receive continuous updates regarding the position, velocity, and/or other characteristics of incoming missiles or projectiles. Such information may be utilized by internal control logic of the interceptor missile 10 to aid in setting the course of the interceptor missile 10 , through use of the pitch over motors 40 .
- the umbilical 90 may be a wire or cable that feeds out and allows the interceptor missile 10 to be connected to the launcher controller 92 during launch. It will be appreciated that further details concerning umbilical connections or missiles in flight may be found from descriptions of prior art wire-guided missiles. As another alternative, the umbilical 90 may be omitted.
- the launcher controller 92 may obtain information regarding incoming missiles or projectiles from suitable sensors, or from other equipment, such as radar devices. Information may be communicated to the controller 92 by any of a variety of ways, including radio signals. The launcher controller 92 may also provide communication and power to the interceptor missile 10 .
- the interceptor missile 10 may be an unguided missile, in that it has no control surfaces used for generating aerodynamic forces to change the course of the missile.
- the term “unguided,” as used herein, is so defined. It will be appreciated that it is necessary for a missile to have a certain minimum velocity in order to allow for guidance with control systems.
- the interceptor missile 10 is able to change course quickly even when moving at small velocity. This allows it to obtain its desired course or trajectory in a short distance. As a result, the interceptor missile 10 is able to engage incoming missiles or projectiles even when such incoming missiles or projectiles are fired close to the launch location of the interceptor missile 10 .
- FIG. 4 shows a ground vehicle 100 that has a launcher 80 attached to it.
- the launcher 80 is able to fire interceptor missiles 10 ( FIG. 1 ) for defending the ground vehicle 100 (and possibly other nearby targets), against incoming missiles or projectiles.
- the ground vehicle 100 may be any of a wide variety of vehicles, including trucks, tanks, and personnel carriers.
- FIG. 5 illustrates the process of the interception and disabling of an incoming projectile or missile (such as an RPG) 120 , fired at the ground vehicle 100 .
- an incoming projectile or missile such as an RPG
- the interceptor missile 10 is fired in a soft launch, shown at reference number 122 .
- the speed of the interceptor missile 10 when soft launched may be relatively small. If the missile 10 is soft launched at a sufficiently slow speed, then the pitch over motors 40 can provide sufficient thrust to get to any angle within a desired time and distance.
- the interceptor missile 10 may have a speed of 18-37 m/sec (60-120 ft/sec).
- the launch speed may be from 21 to 30 m/sec (70 to 100 ft/sec), from 21 to 27 m/sec (70 to 90 ft/sec), or about 24 m/sec (80 ft/sec).
- the soft launching may occur at a speed less than or equal to 30 m/sec (100 ft/sec).
- the soft launching may occur at a speed greater than or equal to 18 m/sec (60 ft/sec).
- the fins 52 deploy as shown at step 124 .
- the deployment of the fins 52 may be automatic once the interceptor missile 10 leaves the launcher 80 .
- the fins 50 may be spring loaded or otherwise configured to automatically deploy.
- the course alteration of the interceptor missile 10 is shown at step 128 .
- the course alteration is accomplished by selectively firing of the pitch over motors 40 , in order to quickly and efficiently move the interceptor missile 10 onto its desired course for intercepting the projectile 120 .
- Information regarding the desired final course, or other instructions or information, may be forwarded to the interceptor missile 10 through the umbilical 90 .
- the course alteration shown at step 128 may be accomplished within 250 milliseconds.
- the solid rocket motor 30 ( FIG. 2 ) of the interceptor missile 10 is fired. This results in the boost phase shown at 130 . In this phase the interceptor missile 10 greatly accelerates, speeding toward its intersection with the incoming projectile or missile 120 . Velocity at motor burn out (the burn out of the solid rocket motor 30 , the main boost propellant system for the interceptor missile 10 ) may be about 150 m/sec.
- the missile warhead 14 detonates, as shown at 134 . This violently propels the warhead fragments 16 ( FIG. 2 ) toward the incoming projectile 120 . Damage from the warhead fragments 16 disables the incoming projectile 120 , preventing the projectile or missile 120 from reaching its target, the ground vehicle 100 .
- the fragments may be of a heavy material, such as steel or tungsten.
- FIG. 6 shows an alternate embodiment in which the launcher 80 for launching interceptor missiles 10 ( FIG. 1 ) is mounted on an air vehicle 200 .
- the illustrated air vehicle 200 is a helicopter.
- launchers may be mounted on other types of air vehicles to protect the air vehicles from incoming missiles or projectiles. Examples of other types of air vehicles include airplanes, gliders, drones, and balloons.
- the launcher 80 may be configured to launch the interceptor missiles 10 in a vertically up direction, a vertically down direction, or some other predetermined direction.
- the launcher may be mounted on a sea vehicle, or on a stationary (though perhaps temporary or movable) structure.
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Abstract
Description
- 1. Technical Field of the Invention
- The invention is in the field of devices and methods for defending against incoming projectiles.
- 2. Description of the Related Art
- Rocket propelled grenades (RPGs) are examples of a type of projectile that poses a great threat to ground vehicles, aircraft, and helicopters. RPGs are commonly used during close-in military engagements, where the shooter and the target are close to one another. Defending against such incoming projectiles presents a difficult problem. From the foregoing it will be appreciated that it may be desirable to have improved ways of dealing with incoming projectiles.
- According to an aspect of the invention, a method of intercepting an incoming projectile includes soft launching an interceptor missile, and altering course of the interceptor missile within 250 milliseconds to an interception course for intercepting the incoming projectile.
- According to another aspect of the invention, a method of intercepting a projectile includes the steps of: determining a desired interception direction for an interceptor missile; launching the missile in a given direction at a speed less than or equal to 40 m/sec (130 ft/sec); and altering course of the missile to the desired interception direction for intercepting the projectile, wherein the altering course is substantially accomplished within 250 milliseconds of launch.
- To the accomplishment of the foregoing and related ends, the invention comprises the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative embodiments of the invention. These embodiments are indicative, however, of but a few of the various ways in which the principles of the invention may be employed. Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the drawings.
- In the annexed drawings, which are not necessarily to scale:
-
FIG. 1 is a side view of an interceptor missile in accordance with an embodiment of the present invention; -
FIG. 2 is a side sectional view of the interceptor missile ofFIG. 1 ; -
FIG. 3 is an oblique view illustrating a soft launching process of the interceptor missile ofFIG. 1 ; -
FIG. 4 is an oblique view of a ground vehicle having a launcher attached for launching the interceptor missiles ofFIG. 1 ; -
FIG. 5 is a diagram illustrating the launch and interception process using the interceptor missile ofFIG. 1 ; and -
FIG. 6 is an oblique view of an air vehicle having a launcher mounted there upon for launching interceptor missiles of the type shown inFIG. 1 . - A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.
- Referring initially to
FIGS. 1 and 2 , aninterceptor missile 10 is used for intercepting an incoming projectile, such as a rocket propelled grenade (RPG). As described in greater detail below, theinterceptor missile 10 is soft launched in a predetermined orientation, such as vertically up or vertically down. The course of the missile is then altered to a desired interception direction. This altering of course may be substantially accomplished over a wide range of possible directions, such as a hemisphere of directions relative to the launch direction, over a time of 250 milliseconds or less. Theinterceptor missile 10 is then accelerated toward the incoming missile or projectile. - At its front end the
interceptor missile 10 includes adome 12 which covers awarhead 14 andwarhead fragments 16. Theinterceptor missile 10 is configured to detonate thewarhead 14 at a predetermined time after launch. This propels thefragments 16 out the forward end of themissile 10, displacing thedome 12.Warhead fragments 16 collide with the incoming missile or projectile and damage the incoming missile or projectile, preventing it from reaching its intended target. - The
warhead 14 and thewarhead fragments 16 are enclosed in a tubularforward body 20. Thebody 20 is capped at its front end by thedome 12. Anigniter 22 in amiddle body 24 is used to detonate thewarhead 14. It will be appreciated that theigniter 22 may be controlled by suitable control logic within themiddle body 24. Control logic may include, for example, integrated circuits that are used to control the timing of the firing of theigniter 22. Control logic may also be used to control the propulsion system of theinterceptor missile 10. - A
propulsion system 28 of theinterceptor missile 10 is located in the aft half of the missile. Thepropulsion system 28 includes asolid rocket motor 30, withmultiple propellant grains 31, which provide the main propulsion system for acceleration or boost of theinterceptor missile 10. Thesolid rocket motor 30 may include conventional solid rocket fuel, configured so as to burn quickly when ignited. Thesolid rocket motor 30 may be ignited by aboost igniter 32. Theboost igniter 32 is at an opposite end of themiddle body 24 from thewarhead igniter 22. Pressurized gas produced by combustion of thesolid rocket motor 30 is directed rearward through a main boost nozzle 36 at the aft end of theinterceptor missile 10. - The
interceptor missile 10 also has a series of pitch overmotors 40 for altering the orientation and course of theinterceptor missile 10. In the illustrated embodiment theinterceptor missile 10 has four pitch overmotors 40 axisymmetrically spaced around the back or aft end of the circumferential perimeter of a back oraft body 44. The back oraft body 44 includes not only the pitch overmotors 40, but also thesolid rocket motor 30. The pitch overmotors 40 each include pitch overmotor fuel 46, and a pitch overmotor thrust chamber 48. The pitch overmotors 40 provide thrust substantially perpendicular to anaxis 49 of theinterceptor missile 10. The pitch overmotor fuel 46 may be a solid fuel that may be identical to the fuel used in thesolid rocket motor 30. It will be appreciated that a suitable ignition device may be used for igniting the pitch overmotor fuel 46 as necessary. Pressurized gases from the burning of the pitch overmotor fuel 46 are received through the pitch overmotor thrust chamber 48, and exit out through pitch overmotor openings 50. The pitch overmotor openings 50 are circular or other suitable-shape openings along a circumference or perimeter of the back oraft body 44. - The pitch over
motors 50 may each have substantially the same impulse, and each may be substantially identical. The control of orientation of themissile 10 may be accomplished by controlling the timing of the firing of the pitch overmotors 50. For example, a small rotation in a given axis may be obtained by closely spacing in time the firings of a pitch over motor and its diametrically-oppose counterpart. Greater rotation of the missile about the axis may be obtained by increasing the time between firings of diametrically-opposed motors. Since the diametrically-opposed motors have substantially the same impulse, there will be no residual rotation of the missile after both pitch over motors have completed their burns. It will be appreciated that use of the pitch overmotors 50 such as described above advantageously does not require any additional control of the pressurized gasses (such as by a variable nozzle) other than by control of the timing of the ignition of the pitch overmotors 50. - The
interceptor missile 10 also may have a series ofdeployable fins 52 that deploy fromslots 54 in theaft body 44. Thefins 52 stabilize theinterceptor missile 10. Thefins 52 may be axisymmetrically deployed around the circumference of theaft body 44 at substantially the same longitudinal location as the pitch overmotor openings 50. There may be the same number offins 52 as pitch overmotor openings 50. Alternatively, and especially for short-range missiles, the fins may be omitted. - The
interceptor missile 10 may weigh 5.7 kg (12.5 pounds), may be 46 cm (18 inches) long, and may have a diameter of 8.9 cm (3.5 inches). It will be appreciated that these are only values for a single embodiment, and that the weight and dimensions of theinterceptor missile 10 may vary over a wide variety of values. -
FIG. 3 illustrates the launching process for theinterceptor missile 10. The missile is soft launched from alauncher 80. “Soft launch,” as the phrase is used herein, refers to launching without firing of a propulsion system of theinterceptor missile 10. Thelauncher 80 may use a pressurized gas launch system to soft launch themissile 10, for example by using pressurized expanding gases, from the missile or cannister from a separate system, to provide lift to the missile. Soft launching allows for a smoother launch of theinterceptor missile 10, with less tip over relative to a hard launch that involves emission of pressurized gases from the missile while the missile is still in the launcher. An example of a system for soft launching is the pressurized gas launcher described in co-owned patent application Ser. No. 12/135,512, filed Jun. 6, 2008, which is incorporated herein by reference. - The soft launch of the
interceptor missile 10 enables a faster and more predictable transition to a desired interception course for intercepting an incoming missile or projectile. Using the pitch over motors 40 (FIG. 2 ), themissile 10 is able to quickly redeploy from a predetermined initial launch trajectory 82 (FIG. 3 ) to substantially any trajectory within at least a hemisphere 84 (FIG. 3 ) about the launch trajectory 82. Even more broadly, theinterceptor missile 10 may be capable of redeploying over more than merely thehemisphere 84. Theinterceptor missile 10 may be capable of deploying over substantially a full circle, to any trajectory, even a downward trajectory vertically upward launch shown inFIG. 3 . While altering course over a hemisphere may be sufficient for launching in a vertical trajectory from the ground as shown inFIG. 3 , it will be appreciated that it may be desirable for other situations to be able to deploy about a full sphere. For example it may be desirable for an air-launched interceptor missile to be able to launch upward or downward and still be able to quickly engage incoming targets fired from both lower and higher altitudes. - The pitch over
motors 40 may be such as to be able to deployinterceptor missile 10 to a desired interceptor trajectory within 250 milliseconds of launch from thelauncher 80. The pitch overmotors 40 may be strong enough to provide at least 2,000° per second of rotation to theinterceptor missile 10. The pitch overmotors 40 may be sufficiently strong to provide at least 6,000° or 7,000° per second of rotation to theinterceptor missile 10. - The
interceptor missile 10 may be coupled by an umbilical 90 (FIG. 3 ) to alauncher controller 92. This allows theinterceptor missile 10 to receive continuous updates regarding the position, velocity, and/or other characteristics of incoming missiles or projectiles. Such information may be utilized by internal control logic of theinterceptor missile 10 to aid in setting the course of theinterceptor missile 10, through use of the pitch overmotors 40. The umbilical 90 may be a wire or cable that feeds out and allows theinterceptor missile 10 to be connected to thelauncher controller 92 during launch. It will be appreciated that further details concerning umbilical connections or missiles in flight may be found from descriptions of prior art wire-guided missiles. As another alternative, the umbilical 90 may be omitted. - The
launcher controller 92 may obtain information regarding incoming missiles or projectiles from suitable sensors, or from other equipment, such as radar devices. Information may be communicated to thecontroller 92 by any of a variety of ways, including radio signals. Thelauncher controller 92 may also provide communication and power to theinterceptor missile 10. - The
interceptor missile 10 may be an unguided missile, in that it has no control surfaces used for generating aerodynamic forces to change the course of the missile. The term “unguided,” as used herein, is so defined. It will be appreciated that it is necessary for a missile to have a certain minimum velocity in order to allow for guidance with control systems. By operating in an unguided mode, with its course altered through use of the pitch overmotors 40, theinterceptor missile 10 is able to change course quickly even when moving at small velocity. This allows it to obtain its desired course or trajectory in a short distance. As a result, theinterceptor missile 10 is able to engage incoming missiles or projectiles even when such incoming missiles or projectiles are fired close to the launch location of theinterceptor missile 10. -
FIG. 4 shows aground vehicle 100 that has alauncher 80 attached to it. Thelauncher 80 is able to fire interceptor missiles 10 (FIG. 1 ) for defending the ground vehicle 100 (and possibly other nearby targets), against incoming missiles or projectiles. Theground vehicle 100 may be any of a wide variety of vehicles, including trucks, tanks, and personnel carriers. -
FIG. 5 illustrates the process of the interception and disabling of an incoming projectile or missile (such as an RPG) 120, fired at theground vehicle 100. Once the projectile 120 is detected theinterceptor missile 10 is fired in a soft launch, shown atreference number 122. The speed of theinterceptor missile 10 when soft launched may be relatively small. If themissile 10 is soft launched at a sufficiently slow speed, then the pitch overmotors 40 can provide sufficient thrust to get to any angle within a desired time and distance. Upon launch theinterceptor missile 10 may have a speed of 18-37 m/sec (60-120 ft/sec). More narrowly the launch speed may be from 21 to 30 m/sec (70 to 100 ft/sec), from 21 to 27 m/sec (70 to 90 ft/sec), or about 24 m/sec (80 ft/sec). The soft launching may occur at a speed less than or equal to 30 m/sec (100 ft/sec). The soft launching may occur at a speed greater than or equal to 18 m/sec (60 ft/sec). - After the soft launch, the
fins 52 deploy as shown at step 124. The deployment of the fins 52 (if present) may be automatic once theinterceptor missile 10 leaves thelauncher 80. Thefins 50 may be spring loaded or otherwise configured to automatically deploy. - The course alteration of the
interceptor missile 10 is shown atstep 128. As discussed above, the course alteration is accomplished by selectively firing of the pitch overmotors 40, in order to quickly and efficiently move theinterceptor missile 10 onto its desired course for intercepting the projectile 120. Information regarding the desired final course, or other instructions or information, may be forwarded to theinterceptor missile 10 through the umbilical 90. As discussed above, the course alteration shown atstep 128 may be accomplished within 250 milliseconds. - After the desired orientation for the
interceptor missile 10 has been achieved, the solid rocket motor 30 (FIG. 2 ) of theinterceptor missile 10 is fired. This results in the boost phase shown at 130. In this phase theinterceptor missile 10 greatly accelerates, speeding toward its intersection with the incoming projectile ormissile 120. Velocity at motor burn out (the burn out of thesolid rocket motor 30, the main boost propellant system for the interceptor missile 10) may be about 150 m/sec. - Finally, when the
interceptor missile 10 is within a predetermined distance of the incoming projectile ormissile 120, the missile warhead 14 (FIG. 2 ) detonates, as shown at 134. This violently propels the warhead fragments 16 (FIG. 2 ) toward theincoming projectile 120. Damage from the warhead fragments 16 disables theincoming projectile 120, preventing the projectile ormissile 120 from reaching its target, theground vehicle 100. The fragments may be of a heavy material, such as steel or tungsten. -
FIG. 6 shows an alternate embodiment in which thelauncher 80 for launching interceptor missiles 10 (FIG. 1 ) is mounted on anair vehicle 200. The illustratedair vehicle 200 is a helicopter. However, it will be appreciated that launchers may be mounted on other types of air vehicles to protect the air vehicles from incoming missiles or projectiles. Examples of other types of air vehicles include airplanes, gliders, drones, and balloons. Thelauncher 80 may be configured to launch theinterceptor missiles 10 in a vertically up direction, a vertically down direction, or some other predetermined direction. As a further alternative, the launcher may be mounted on a sea vehicle, or on a stationary (though perhaps temporary or movable) structure. - Although the invention has been shown and described with respect to a certain preferred embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings. In particular regard to the various functions performed by the above described elements (components, assemblies, devices, compositions, etc.), the terms (including a reference to a “means”) used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments of the invention. In addition, while a particular feature of the invention may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.
Claims (19)
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US12/198,146 US8173946B1 (en) | 2008-08-26 | 2008-08-26 | Method of intercepting incoming projectile |
PCT/US2009/046359 WO2010036418A2 (en) | 2008-08-26 | 2009-06-05 | Method of intercepting incoming projectile |
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US12/198,146 US8173946B1 (en) | 2008-08-26 | 2008-08-26 | Method of intercepting incoming projectile |
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Also Published As
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US8173946B1 (en) | 2012-05-08 |
WO2010036418A3 (en) | 2010-06-10 |
WO2010036418A2 (en) | 2010-04-01 |
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