HETZ3- חץ 3 - טיל נגד טילים

הטיל שהה שש דקות באוויר וחצה את האטמוספרה, שם פתח את המנוע הרקטי השני שלו • משרד הביטחון פרסם סרטון המתעד את הניסוי המוצלח במערכת "חץ 3" • כך זה נראה

הניסוי, שהיה הראשון של מיירט מסוג "חץ 3", התבצע על ידי אנשי משרד הביטחון משדה ניסויים במרכז הארץ -- ובוצע בשיתוף פעולה יחד עם הסוכנות האמריקנית להגנה מפני טילים.
הניסוי בוצע בשעה [You must be registered and logged in to see this link.] בבוקר, עם שיגור לכיוון הים התיכון. הטיל שהה באוויר שש דקות, חצה את האטמוספרה ופתח את המנוע הרקטי השני שלו. 
במשרד הביטחון ציינו כי לראשונה, נבחנו היכולות והביצועים של המערכת, שאמורה להתמודד ביעילות רבה יותר עם איומים עתידיים על ישראל. המערכת נועדה להעניק שכבת הגנה עליונה מפני טילים, הוספת הזדמנויות יירוט ובכך לעבות את מערך ההגנה על ישראל מפני איומי הטילים ארוכי הטווח.
מדובר בניסוי ראשון בתהליך פיתוח שיימשך בשנים הקרובות, ובעתיד יתבצעו ניסויים נוספים בטרם הצבת המערכת לשימוש מבצעי.
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חץ 3 הוא [You must be registered and logged in to see this link.] במסגרת מערכת הנשק [You must be registered and logged in to see this link.], ונועד ל[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.], בחלל. הטיל פותח ב[You must be registered and logged in to see this link.] של [You must be registered and logged in to see this link.]. הטיל הוא אקסו-אטמוספירי, כלומר, מיועד ליירט טילים ב[You must be registered and logged in to see this link.], יכולת המשפרת את סיכויי הפגיעה במטרה היות שהיא מאפשרת שיגור מיירטים נוספים במקרה של כישלון. יכולת זו גם מקטינה את הסכנה שראש הקרב, חומרי [You must be registered and logged in to see this link.] או [You must be registered and logged in to see this link.] או שרידי הטיל, יפלו בשטח ויהוו סכנה. על פי הערכת יושב ראש [You must be registered and logged in to see this link.], [You must be registered and logged in to see this link.], חץ 3 מסוגל ליירט גם [You must be registered and logged in to see this link.], יכולת השמורה לקומץ [You must be registered and logged in to see this link.] בעולם.^{[You must be registered and logged in to see this link.]}
ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] בוצע בהצלחה ניסוי יירוט מלא של מטרה בחלל, וב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] נמסרה המערכת הראשונה ל[You must be registered and logged in to see this link.] של [You must be registered and logged in to see this link.].^{[You must be registered and logged in to see this link.]} והיא המערכת הראשונה ב[You must be registered and logged in to see this link.] של ישראל.


עקרון הפעולה של חץ 3 מבוסס על פגיעה פיזית ישירה בטיל המטרה, שלא כמו ב[You must be registered and logged in to see this link.], בו [You must be registered and logged in to see this link.] שנועד ליזום כאשר מתקרב לטיל, ופוגע במטרה באמצעות מטען של [You must be registered and logged in to see this link.] ו[You must be registered and logged in to see this link.]. האנרגיה הקינטית במפגש עם המטרה גדולה מספיק להשמדת המטרה ללא צורך בחומר נפץ. מאידך, נדרש [You must be registered and logged in to see this link.] רב להשגת פגיעה ישירה. הראש הקרבי של חץ 3 מסוגל ל[You must be registered and logged in to see this link.] באמצעות [You must be registered and logged in to see this link.] (הנעה וקטורית) - כלומר נחיר פליטה מתכוונן אשר מסוגל להטות את ה[You must be registered and logged in to see this link.].^{[You must be registered and logged in to see this link.]}

מימון אמריקאי לפיתוח[[You must be registered and logged in to see this link.] | [You must be registered and logged in to see this link.]]

הגנרל [You must be registered and logged in to see this link.], ראש התוכנית האמריקנית להגנה מפני טילים, אמר בעדותו ב[You must be registered and logged in to see this link.] כך:

התכנון של החץ-3 מתקדם יותר מכל מה שאנחנו עושים בתכניות הטילים נגד טילים שלנו בארצות הברית. ... במערכת יוטמע חיישן מיוחד ומערכת הנעה חדשה למיירט.^{[You must be registered and logged in to see this link.]}

ב-20 במאי 2009 דיווחו כלי תקשורת בישראל על הסכמה של ממשל ארצות הברית לממן את פיתוח הטיל חץ 3. הסכום המדויק לא נמסר, אך הערכות מדברות על מאות מיליוני דולרים. בחודש אפריל 2013 פרסם צבא ארצות הברית מכרז לבניית בסיס למערכת הגנה מטילים בליסטיים בישראל.^{[You must be registered and logged in to see this link.]} על פי התוכנית תושלם בניית הבסיס עד סוף שנת 2014, בעלות הנעה בין 10–25 מיליון דולר. על פי פרסום בירחון [You must be registered and logged in to see this link.] הבסיס, אשר יוקם בבסיס הטילים של חיל האוויר ב[You must be registered and logged in to see this link.], נועד לטילי חץ 3 ובנייתו תושלם לקראת השלמת פיתוח הטיל.^{[You must be registered and logged in to see this link.]}




[th][הסתרה]סיוע ארצות הברית לתוכנית החץ 3 ל[You must be registered and logged in to see this link.]. המספרים הם במיליוני [You must be registered and logged in to see this link.].[/th][th]2008[/th][th]2009[/th][th]2010[/th][th]2011[/th][th]2012[/th][th]2013[/th][th]2014[/th][th]2015[/th][th]2016[/th][th]2017[/th][th]סך הכל[/th]

20.0[You must be registered and logged in to see this link.]	30.0[You must be registered and logged in to see this link.]	50.036[You must be registered and logged in to see this link.]	58.966[You must be registered and logged in to see this link.]	66.220[You must be registered and logged in to see this link.]	74.700[You must be registered and logged in to see this link.]	74.707[You must be registered and logged in to see this link.]	74.707[You must be registered and logged in to see this link.]	89.550[You must be registered and logged in to see this link.]	55.793[You must be registered and logged in to see this link.]	594.679

ניסויים ופיתוח[[You must be registered and logged in to see this link.] | [You must be registered and logged in to see this link.]]

• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] משרד הביטחון התיר לפרסום לראשונה צילומים מסדרת ניסויים של הטיל המיירט חץ 3 בעת שיגורו.^{[You must be registered and logged in to see this link.]}
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] ערכה ישראל ניסוי טיסה ראשון של הטיל, שהתנהל ללא תקלות וזכה להצלחה מלאה. משרד הביטחון פרסם את ההודעה הבאה:^{[You must be registered and logged in to see this link.]}"בשעה שמונה בבוקר המריא המיירט משדה הניסויים של חיל האוויר על שפת הים ועלה בתאוצה כלפי השמיים לכיוון הים התיכון. לאחר מכן המשיך המיירט בשיוט, חצה גובה של כמאה קילומטרים, ביצע סדרת תמרונים בחלל וערך מעקב אחר אובייקטים שונים, ביניהם גם כוכבים."
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] נערך ניסוי שני של הטיל וזכה אף הוא להצלחה מלאה במהלכו הושלם ניסוי טיסה חופשית מחוץ לאטמוספירה. ראש [You must be registered and logged in to see this link.], [You must be registered and logged in to see this link.]תיאר את הניסוי כך:^{[You must be registered and logged in to see this link.]}"לאחר השיגור, הטיל טס בצורה אנכית, יצא מהאטמוספירה, השליך את המנוע והפעיל את המנוע השני, שייט בגובה רב בשולי האטמוספירה, ביצע משימה מורכבת ונפל בים. לראשונה היה לנו מכ"ם חדש, המכונה אורן אדיר, שעקב אחרי הטיל וקיבל נתונים במהלך הטיסה. הטיסה בניסוי הזה הייתה ארוכה מבפעם קודמת. בקרוב נעבור לסדרת ניסויי יירוט מעשיים שבסיומם נתחיל בתהליך ייצור ואחריה תוגדר המערכת כמבצעית."
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] דווח משרד הביטחון על ניסוי מוצלח לכאורה של מערכת החץ 3 אולם בהמשך היום דווח על ידי גורמי ביטחון כי הניסוי לא נערך במלואו מכיוון שהתנאים לשיגור המיירט לא בשלו. מטרת הניסוי הייתה יירוט אקסו אטמוספירי מלא.^{[You must be registered and logged in to see this link.]} זו הייתה הפעם השנייה תוך 3 חודשים בה משרד הביטחון דיווח על ניסוי כהצלחה בפרויקט החץ אף שלא הושגו כל יעדי הניסוי.^{[You must be registered and logged in to see this link.]} רק לאחר שנודע כי תוצאות הניסוי דווחו לסוכנות הידיעות [You must be registered and logged in to see this link.], משרד הביטחון יצא בהודעה שנייה באותו היום וזו לשונה:^{[You must be registered and logged in to see this link.]} "בהמשך להודעה שהפצנו בצהריים, נבקש להבהיר כי טיל המטרה יצא לדרכו וכי מערכת החץ עקבה אחריו במהלך מעופו. התנאים לשיגור המיירט לא בשלו, ולכן הוחלט להגדירו כניסוי בטיל המטרה בלבד."
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] בוצע ניסוי מוצלח בטיל החץ 3 ב[You must be registered and logged in to see this link.]. במהלכו שוגר מירט לעבר מטרה, טיל מסוג [You must be registered and logged in to see this link.], מחוץ לאטמוספירה ופגע בה באופן ישיר.^{[You must be registered and logged in to see this link.][You must be registered and logged in to see this link.]}
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] פורסם כי פעילות יחידת ניסויי הטילים בבסיס פלמחים אשר ניהלה גם את ניסויי החץ תועבר ל[You must be registered and logged in to see this link.] משיקולי כדאיות כלכלית.^{[You must be registered and logged in to see this link.]}
  
  
• ב-[You must be registered and logged in to see this link.] [You must be registered and logged in to see this link.] נמסרה הסוללה הראשונה של ה"חץ 3" ל[You must be registered and logged in to see this link.].
  
  

Inventors:  [You must be registered and logged in to see this link.]  [You must be registered and logged in to see this link.] 
Agents:  [You must be registered and logged in to see this link.] 
Assignees: 
Origin: [You must be registered and logged in to see this link.] 
IPC8 Class: AF42B1066FI 
USPC Class: 244 322

Abstract:

According to an embodiment of the present invention there is provided a kill-vehicle to be used in an exo-atmospheric anti-missile interceptor aimed at hitting a target, the kill-vehicle having a main body and comprising: an electronic box; a sensor unit coupled to the electronic box and including at least one sensor for tracking the target at a certain field of view; an inertial measurement unit coupled to the sensor unit; and a divert system controlled by the electronic box for providing the kill-vehicle with thrust at a desired direction; said divert system and electronic box constituting said main body, wherein the kill-vehicle further comprises at least one gimbals unit coupled to the main body and to the sensor unit for controllably changing an angle between the sensor unit and the main body, and wherein said electronic box is configured to synchronically operate said divert system and gimbals unit such that the target remains in the field of view of said at least one sensor and the thrust is provided in a direction required for hitting the target.

Claims:

1-10. (canceled) 

11. A kill-vehicle to be used in an exo-atmospheric anti-missile interceptor aimed at hitting a target, the kill-vehicle comprising at least one gimbal unit capable of changing a relative angle between a main body of said kill vehicle and a sensor unit adapted for tracking the target along a LOS (Line of Sight). 

12. A kill-vehicle according to claim 11 further comprising an IMU (Inertial Measurement Unit) for measuring inertial velocity of the LOS and wherein the main body includes an electronic box coupled to a divert system, the sensor unit, the gimbal unit and the IMU and is adapted for providing synchronous operation of the divert system and the gimbal unit by dynamically adjusting said relative angle. 

13. A kill-vehicle according to claim 11 wherein said electronic box is further adapted for providing synchronous operation by having said at least one sensor maintaining the LOS to the target and controllably providing thrust along the main body at any direction required for hitting the target. 

14. A kill-vehicle according to claim 12 wherein said providing synchronous operation includes providing a relative angle of up to 90 degrees between the direction of thrust and the LOS. 

15. A kill-vehicle according to claim 12 wherein said sensor is one of a group consisting of: an electro-optic sensor; an electromagnetic sensor; a combination of an electro-optic and electromagnetic sensor. 

16. A kill-vehicle according to claim 12 wherein said gimbal unit includes at least one rotary motor, an angle-measuring mechanism and an electronic circuitry. 

17. A kill-vehicle according to claim 16 wherein said divert system comprises:a thruster;a nozzle coupled to the thruster for providing the kill-vehicle with acceleration; andat least two linear actuators for bending the nozzle with respect to said thruster,wherein said nozzle having a flexible part and wherein said at least two linear actuators are operable for steering the nozzle there-between, thereby providing said acceleration at a desired direction. 

18. A kill-vehicle according to any one of claim 17 wherein said electronic box is further adapted for measuring the LOS rate induced by a well-defined maneuver for deriving a range to the target. 

19. A kill-vehicle according to claim 17 wherein said electronic box further includes communication means, thereby allowing transmitting target trajectory to the interceptor. 

20. A method for operating an exo-atmospheric anti-missile interceptor aimed at hitting a target, said interceptor having a kill-vehicle that comprises at least one gimbal unit connecting a main body of the kill-vehicle with at least one sensor unit tracking the target along a LOS (Line of Sight), the method comprising controllably changing a relative angle between the main body and the LOS. 

21. A method according to claim 20 wherein said controllably changing a relative angle between the main body and the LOS comprises measuring inertial velocity of the LOS and in response dynamically adjusting the relative angle in accordance with a direction defined by a guidance law as a direction required for hitting the target by providing thrust along the main body at said relative angle. 

22. A method according to claim 21 further comprising providing a relative angle of 90 degrees between the main body and the LOS. 

23. A method according to any one of claim 21 further comprising measuring the LOS rate induced by a well-defined maneuver for deriving a range to the target. 

24. A method according to any one of claim 21 further comprising providing target trajectory from a remote system for deriving a range to the target.

Description:

FIELD OF THE INVENTION 

[0001]This invention relates to anti-missile defense system and a method thereof, and more specifically the invention relates to an exo-atmospheric intercepting system and a method thereof. 



BACKGROUND OF THE INVENTION 

[0002]According to a known approach, the interception of attacking ballistic missiles above the atmosphere can be achieved by launching an interceptor missile against the attacking missile. The interceptor is directed toward the attacking missile (the so called `target`) and preferably hits it or explodes in the vicinity of the target, hopefully causing the target severe damage and perhaps even complete destruction. Typically, the interceptor comprises a one (or several) stage booster and the so-called "kill vehicle", also known by its abbreviation, KV. 

[0003]Generally, the KV is required to maneuver in space in order to adjust its position with regard to its target, to compensate for e.g. cuing errors raised by ground or space detection and tracking systems and onboard navigation errors and in response to tracked target maneuvers. 

[0004]The following is a short description of known techniques for KV maneuvering in space: 

[0005]by using a rocket motor equipped with a flexible nozzle combined with an Attitude Control System (ACS) utilizing cold gas ejection for achieving and maintaining an orientation. This technique is used e.g. by the Arrow® interceptor, available by the Israel Aircraft Industry®. 



[0006]by firing small micro-rockets at the required direction. This technique is used e.g. in THADS (Theatre High Attitude Defense System), commercially available from Lockheed-Martin®. 

[0007]by using a Divert and Attitude Control System (DACS), used e.g. in liquid or solid propellant based missile, such as SM2 and SM3 (Standard Missile) used by the US Navy. 

[0008]There is a need in the art for an improved KV having improved maneuvering and divert capabilities. There is further a need in the art for an improved KV having improved sensor range and improved resolution. 

SUMMARY OF THE INVENTION 

[0009]According to one embodiment, the present invention provides for a kill-vehicle to be used in an exo-atmospheric anti-missile interceptor aimed at hitting a target, the kill-vehicle having a main body and comprising an electronic box; a sensor unit coupled to the electronic box and including at least one sensor for monitoring a field of view; an inertial measurement unit coupled to the sensor unit; and a divert system controlled by the electronic box for providing the kill-vehicle with thrust at a desired direction; the divert system and electronic box constituting the main body, wherein the kill-vehicle further comprises at least one gimbals unit coupled to the main body and to the sensor unit for controllably changing an angle between the sensor unit and the main body, and wherein said electronic box is configured to synchronically operate said divert system and gimbals unit such that the target remains in the field of view of said at least one sensor and the thrust is provided in a direction required for hitting the target. 




[0010]According to an embodiment of the invention, the electronic box includes a processor, a power source, and drivers for driving the divert system. According to another embodiment, the electronic box further includes communication means. 

[0011]According to one embodiment of the invention, the sensor is an electro-optic sensor. According to another embodiment, the sensor is an electromagnetic sensor. According to yet another embodiment, the sensor is a combination of electro-optic and electromagnetic sensor. 

[0012]According to one embodiment of the invention, the gimbals include at least one rotary motor, an angle-measuring mechanism and an electronic circuitry. 

[0013]According to another embodiment, the divert system comprises a thruster, a nozzle for providing the kill-vehicle with acceleration, and at least two linear actuators for bending the nozzle with respect to the thruster, wherein the nozzle having a flexible part and the linear actuators are operable for steering the nozzle there-between, thereby providing the acceleration at a desired direction. 

[0014]According to an embodiment of the present invention, the range to the target is measured by measuring the line-of-sight (LOS) rate induced by a well-defined maneuver. 

[0015]The present invention further provides for a method for operating an exo-atmospheric anti-missile interceptor aimed at hitting a target, said interceptor having a kill-vehicle that comprises at least a sensor unit, an electronic box, and a divert system, said electronic box and divert system constituting a main body; the method comprising: [0016]providing rotating means for controllably changing an angle [0017]between said main body and sensor unit; [0018]providing said divert system with controllable steering means for applying a thrust at a desired direction; [0019]tracking said target at certain a field of view of said sensor; and[0020]synchronically operating said rotating means, steering means and divert system such that the target remains in the field of view of the sensor and the thrust is applied in the direction required for the interceptor to hit the target. 



BRIEF DESCRIPTION OF THE DRAWINGS 

[0021]In order to understand the invention and to see how it may be carried out in practice, one embodiment will now be described, by way of non-limiting example only, with reference to the accompanying drawings, in which: 

[0022]FIGS. 1a-1b are schematic illustrations of an interceptor according to an embodiment of the present invention; 

[0023]FIG. 2 is a schematic illustration of a KV according to an embodiment of the present invention; 

[0024]FIG. 3 is another schematic illustration of a KV according to an embodiment of the present invention; 

[0025]FIG. 4a is a partial cross-section of a KV according to an embodiment of the invention; 

[0026]FIG. 4b is a partial side view of the KV shown in FIG. 4a; 

[0027]FIG. 5 is another partial side view of the KV according to an embodiment of the invention; and 

[0028]FIG. 6 is a schematic illustration of a method according to an embodiment of the present invention. 

DETAILED DESCRIPTION OF THE INVENTION 




[0029]FIGS. 1a-1b are schematic illustrations of an anti-missile interceptor 10 according to an embodiment of the present invention, having a booster rocket 21 and a KV 20. Also shown is a separation mechanism 22, e.g. pyro-electric separation mechanism, used for separating, the booster from the KV at the appropriate conditions. It should be noted that the invention is not limited by the kind and type of booster rocket. Specifically, the invention is not limited by the one-stage booster as shown in FIGS. 1a-1b, and can be used e.g. with a two-stage booster. 

[0030]According to one embodiment, the KV of the present invention is a commercially available KV in which modifications and additions are appropriately made in order to implement the concepts of the present invention. According to another embodiment of the invention, the KV is a dedicated device designed in accordance with the concept of the present invention. 

[0031]FIG. 2 is a schematic illustration of a KV 20 according to an embodiment of the present invention. KV 20 comprises, inter-alia, the following main elements: an electronic box 220 which includes, inter-alia, power source, a processor, control means (e.g. drivers) and optional communication means, for e.g. receiving updates from a ground station or a space system (these elements are not shown in FIG. 2). The electronic box 220 is coupled to a motor 230 (the so-called `thruster`), which, according to a non-limiting example shown in FIG. 2, is a solid propellant motor. The main body 215 of the KV, mainly comprising the electronic box 220 and the motor 230, is coupled to a sensor unit 200, which includes, inter-alia, a sensor (not shown in FIG. 2), e.g. an electro-optic or electromagnetic sensor used for detecting and tracking the attacking missile (the so-called `target`). KV 20 is further equipped with an inertial measurement unit (IMU) (not shown in FIG. 2), coupled to the control means and perhaps coupled to or accommodated in the sensor unit 200. According to an embodiment of the present invention, KV 20 is equipped with a divert system 235, the structure and operation of which will be described further below. 



[0032]According to an embodiment of the invention, the electronic box 220 and the sensor unit 200 are coupled via one or more gimbals 210, the function of which will be described now with reference to FIG. 2 together with FIGS. 3 and 4. Gimbals 210 control the relative angle between the main body 215 of the KV 20 (referring mainly to the electronic box 220 and the motor 230), represented in FIGS. 2-3 by a dashed axis line A, and the sensor unit 200, represented by a dashed axis line B. 

[0033]In FIG. 2, axis lines A and B coincide. In this position, any thrust given to the KV along axis A will need to comply with the limitations under which operates the sensor unit, which are, mainly, continuously directing the sensor (i.e. axis B) toward the target. According to an embodiment of the present invention, the relative angle θ between axis A (the direction of the main body of the KV) and axis B (the direction of the sensor) can be controlled and changed, for example to the position shown in FIG. 3 (a 90° angle between axis A and axis B), thereby allowing the sensor 200 to maintain its direction toward the target while providing thrust along axis A. It should be appreciated that by dynamically adjusting the relative angle θ between the sensor 200 and the KV body 215 (i.e. between axis A and axis B) while maintaining the sensor axis toward the target, required thrust can be provided to the KV in any required direction in order to correct the missile course. By this, improved KV maneuvering and divert capabilities are achieved, as well as improved sensor range and resolution. 



[0034]Reference is now made to FIG. 4a, showing a schematic cross-section of a KV according to an embodiment of the invention. Gimbals unit 210 connects the sensor unit 200 with the electronic box 220. Gimbals unit 210 comprises one or more rotary motors 280 (e.g. brush-less DC motors) and an angle-measuring mechanism 240 (e.g. optical encoder), which are mounted onto the gimbals axis 250. Not shown in FIG. 4a is the IMU, which, as described with reference to FIG. 2, can be integrated within the sensor unit 200. FIG. 4b is a schematic side view of the KV shown in FIG. 4a, showing the gimbals axis 250. Preferably, Gimbals 210 are powered and controlled by the electronic box 220 (e.g. by drivers accommodated in the electronic box). Note that the electronic circuitry of the gimbals unit 210 is not shown in FIGS. 4a-4b. 

[0035]In operation, gimbals 210 are operable (e.g. by drivers accommodated in the electronic box) to move the sensor unit 200 relative to the KV main body 215, thereby changing the angle θ there-between. The gimbals motors 280 are e.g. activated in a closed loop to minimize angular movements of the sensor unit in one or two directions perpendicular to the sensor axis B. Upon detection of the target, the motors 280 are activated such that the sensor axis B coincides with the line-of-sight (LOS) between the KV and the target. On a timely manner, the inertial velocity of the LOS is measured by the IMU and is used, in a manner known per-se, to calculate the maneuver along a direction perpendicular to the LOS needed to hit the target. Further considered is the range between the interceptor and the target, which is derived e.g. from the target trajectory transmitted to the interceptor by e.g. a ground station or a space system. The range can also be derived e.g. by measuring the change in the LOS angular velocity induced by the maneuvering of the KV. 

[0036]FIG. 5 is another partial side view of the KV shown in FIG. 2, showing schematically in a non-limiting manner, the divert system 235 mentioned above with reference to FIG. 2. According to an embodiment of the invention, the divert system 235 is controlled by the electronic box 220 (e.g. by drivers accommodated in the electronic box) and comprises, inter-alia, a nozzle 270 having flexible part 260, and linear actuators 290 coupling the nozzle to the thruster 230. The actuators 290 are located at a 90° angle to each other, steering the nozzle 270 there-between. Not shown in FIGS. 4a-4b and 5 are one or more gyros, used for working with one or more actuators 290 in closed loop to provide and maintain a desired direction. 



[0037]In operation, the linear actuators 290 are used to steer the nozzle to the desired direction required to provide the main body of the KV (element 215 in FIG. 2) appropriate moment thereby enabling KV maneuvering by producing angular accelerations of the main body along the direction of the moment. 

[0038]FIG. 600 schematically shows a method 600 according to an embodiment of the present invention, for operating an exo-atmospheric anti-missile interceptor aimed at hitting a target. The method is suitable for the operation of an interceptor having a kill-vehicle that comprises at least a sensor unit, and a main body that includes, inter alia, an electronic box and a divert system. The following are operational steps carried out according to the present invention: 

[0039]At step 610: providing rotating means for controllably changing an angle between said main body and sensor unit. 

[0040]At step 620: providing the divert system with controllable steering means for applying a thrust at a desired direction. 

[0041]At step 630: tracking a target at a certain field of view of the sensor. 

[0042]At step 640: synchronically operating the rotating means, steering means and divert system such that the target remains in the field of view of the sensor and the thrust is applied in the direction required for the interceptor to hit the target (interception). 



[0043]The guidance law that defines the require acceleration vector perpendicular to the line of sight to the target for an interception can be one of many e.g. Augmented Proportional Navigation or Zero Effort Miss proportional navigation as described in chapter 2 of Tactical and Strategic Missile Guidance by Paul Zarchan. Once the required acceleration vector is defined, the control system uses the flexible nozzle and the gimbals motors to change the direction of the KV's motor to the direction that produce the required acceleration perpendicular to the line of sight to the target. 

[0044]According to one embodiment of the invention, any change in the LOS direction (axis B shown in FIG. 3) is prevented while the motor (axis A shown in FIG. 3) is directed in the direction that ensures the required acceleration. 

[0045]While the invention has been described with regard to a divert system having flexible nozzle, it will be appreciated that the invention equally applies to other embodiments wherein other types of divert means are used 

[0046]Although certain embodiments of the present invention have been described, this should not be construed to limit the scope of the appended claims. Those skilled in the art will understand that modifications may be made to the described embodiments. Moreover, to those skilled in the various arts, the invention itself herein will suggest solutions to other tasks and adaptations for other applications. It is therefore desired that the present embodiments be considered in all respects as illustrative and not restrictive, reference being made to the appended claims rather than the foregoing description to indicate the scope of the invention. 
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America's Missile Defense System Works - Thank You Trump [You must be registered and logged in to see this link.] - Deplorable News The Pentagon successfully shoots down a mock nuclear warhead over California in test of missile that will stop ICBMs reaching the US. U.S. military shot down mock intercontinental ballistic missile over the Pacific in a successful test fire exercise
Ground-based Midcourse Defense (GMD) interceptor was fired from Vandenberg Air Force Base in California and successfully struck its target today 
Exercise comes amid high tensions between the U.S. and North Korea over their continued provocations
It took place just two days after North Korea's reported launch of a military projectile Monday morningThe U.S. military has shot down mock warhead over the Pacific in a key success for it missile defense program, just days amid growing fears over North Korea's weapons capability.
The Pentagon announced the first missile defense test was taking place today involving a simulated attack by an intercontinental ballistic missile, firing off an interceptor from Vandenberg Air Force Base in California, a Reuters witness at the base said.
The Ground-based Midcourse Defense (GMD) interceptor successfully struck its target over the Pacific Ocean in an exercise aimed at helping gauge American ability to counter any potential similar threat from North Korea. 
U.S. Missile Defense Agency Director Vice Adm. Jim Syring told NBC News the test was a 'critical milestone'. 
'This system is vitally important to the defense of our homeland, and this test demonstrates that we have a capable, credible deterrent against a very real threat. I am incredibly proud of the warfighters who executed this test and who operate this system every day,' Syring said.


IAI new arrow 3 anti ballistic Missile Simulation of capabilities

January 14, 2017, fired long-range rockets at the Israel Hatzor Airbase causing massive damage in an interesting warning to the Israel weasels that their airbases, their runways and hangars are all fair game in any new war. Even the Israeli media only reported civilians seeing billows of fiery smoke emanating from the base. This was Syria’s response to the unprovoked aerial missile attack which originated over Lake Tiberias and which destroyed some infrastructure at the Al-Mazza Airbase.
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Jan 18, 2017 Operational Arrow-3 Interceptors Transferred to Israel’s Air Force Missile Defense Forceand deployed for first time

Israel enhanced today its nationwide multi-layered missile defense system with the delivery of the first batch of Arrow 3 interceptors to be inducted to the Arrow Weapon System (AWS) made by Israel Aerospace Industries (IAI/MLM). Arrow system is the upper-most tier in the Israeli strategic missile defense capability. Until now the AWS was comprised of Arrow-2 interceptors. The induction of Arrow-3 adds an exo-atmospheric capability.
Arrow-3 will significantly reduce the possibilities of ballistic missiles ‘leakage’, when missiles that were not intercepted could hit the Jewish State.
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Israel Air Force Receives First Arrow 3 Anti-missile Interceptors 
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Air force gets first Arrow 3 missile defense battery
Israel enters ‘new age’ as US-Israeli system designed to shoot down ballistic missiles goes operational
“Today, we delivered to the air force the first Arrow 3 interceptor, with interception capabilities that are much greater and can be done from much farther away than anything that we have now,” Patel said.
The Arrow 3, which was developed in a joint Israeli-American program, is designed to shoot down intercontinental ballistic missiles outside the atmosphere, taking out the weapons and their nuclear, biological, chemical or conventional warheads closer to their launch sites.
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Top 5 Missile Defense Systems Leading 2017-2020