IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0514456
(2007-11-04)
|
등록번호 |
US-8091482
(2012-01-10)
|
우선권정보 |
IL-179224 (2006-11-13) |
국제출원번호 |
PCT/IL2007/001342
(2007-11-04)
|
§371/§102 date |
20090512
(20090512)
|
국제공개번호 |
WO2008/059477
(2008-05-22)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Rafael Advanced Defense Systems Ltd.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
10 |
초록
▼
A warhead system for a projectile-intercepting munition, the warhead system includes a fuselage having an axis and one or more explosively-formed-projectile charge. The explosively-formed-projectile is with a length and configured to generate one or more explosively formed blade projectile propagati
A warhead system for a projectile-intercepting munition, the warhead system includes a fuselage having an axis and one or more explosively-formed-projectile charge. The explosively-formed-projectile is with a length and configured to generate one or more explosively formed blade projectile propagating substantially perpendicular to the length, the explosively-formed-projectile charge assuming a deployed state wherein the length of the explosively-formed-projectile charge is non-parallel to the axis, the deployed state and the explosively-formed-projectile charge configured such that, when the explosively-formed-projectile charge is detonated in the deployed state, the explosively formed blade projectile propagates in a direction non-coplanar with the length of the explosively-formed-projectile charge and the axis of the fuselage.
대표청구항
▼
1. A warhead system for a projectile-intercepting munition, the warhead system comprising: (a) a fuselage having an axis; and(b) at least one explosively-formed-projectile charge having a length and configured to generate at least one explosively formed blade projectile propagating substantially per
1. A warhead system for a projectile-intercepting munition, the warhead system comprising: (a) a fuselage having an axis; and(b) at least one explosively-formed-projectile charge having a length and configured to generate at least one explosively formed blade projectile propagating substantially perpendicular to said length, said at least one explosively-formed-projectile charge assuming a deployed state wherein said length of said at least one explosively-formed-projectile charge is non-parallel to said axis, said deployed state and said explosively-formed-projectile charge being configured such that, when said explosively-formed-projectile charge is detonated in said deployed state, said explosively formed blade projectile propagates in a direction non-coplanar with said length of said explosively-formed-projectile charge and said axis of said fuselage. 2. A warhead system for a projectile-intercepting munition, the warhead system comprising: (a) a fuselage having an axis; and(b) at least one explosively-formed-projectile charge having a length and configured to generate at least one explosively formed blade projectile propagating substantially perpendicular to said length, said at least one explosively-formed-projectile charge assuming a deployed state wherein said length of said at least one explosively-formed-projectile charge is non-parallel to said axis, said deployed state and said explosively-formed-projectile charge being configured such that, when said explosively-formed-projectile charge is detonated in said deployed state, said explosively formed blade projectile propagates in a direction forming an angle of between 80 degrees and 180 degrees with a forward direction of said fuselage along said axis. 3. A warhead system for a projectile-intercepting munition, the warhead system comprising: (a) a fuselage having an axis;(b) at least two explosively-formed-projectile charges, each having a length and configured to generate at least one explosively formed blade projectile propagating substantially perpendicular to said length, said explosively-formed-projectile charges being deployable between a stowed state in which said length lies substantially parallel with said axis of said fuselage and a deployed state wherein said length of each of said explosively-formed-projectile charges is non-parallel to said axis; and(c) a deployment mechanism configured to allow deployment of a first of said explosively-formed-projectile charges to a deployed position at a first angle relative to said axis and deployment of a second of said explosively-formed-projectile charges to a deployed position at a second angle relative to said axis, said second angle being different from said first angle. 4. The warhead system of claim 3, further comprising at least one sensor deployed for sensing a position of a target projectile, said deployment mechanism being responsive to a sensed position of the target projectile to select an opening angle for at least one of said explosively-formed-projectile charges. 5. A warhead system for a projectile-intercepting munition, the warhead system comprising: (a) a fuselage having an axis; and(b) at least one explosively-formed-projectile charge having a length and configured to generate at least two explosively formed blade projectiles propagating substantially perpendicular to said length, said at least one explosively-formed-projectile charge assuming a deployed state wherein said length of said at least one explosively-formed-projectile charge is non-parallel to said axis. 6. The warhead system of claim 5, wherein each said explosively-formed-projectile charge is operative, when detonated, to emit between two and six of said blade projectiles propagating substantially perpendicular to said length. 7. The warhead system of claim 5, further comprising a control system including: a detonation subsystem for detonating said at least one explosively-formed-projectile charge; and a sensor configured for sensing a location of the warhead system relative to a target, said control system being configured to detonate said at least one explosively-formed-projectile charge in accordance with said location. 8. The warhead system of claim 7, wherein said control system is further configured to derive a velocity of the warhead system relative to said target, the mechanism being operative to detonate said at least one explosively-formed-projectile charge in accordance with both said location and said velocity. 9. The warhead system of claim 5, wherein each said explosively-formed-projectile charge is hingedly attached to said fuselage. 10. The warhead system of claim 5, wherein each said explosively-formed-projectile charge is rigidly attached to said fuselage. 11. A method for defeating a short-range surface-to-surface projectile, the method comprising the steps of: (a) estimating a trajectory of the projectile;(b) firing a projectile-intercepting munition on an intercepting flight path so as to bring the projectile-intercepting munition within an engagement distance from the projectile, the projectile intercepting munition comprising a fuselage having an axis and carrying a warhead system including a charge; and(c) detonating said charge so as to defeat the projectile, wherein said charge is an explosively-formed-projectile charge having a length and configured to generate at least one explosively formed blade projectile propagating substantially perpendicular to said length, said explosively-formed-projectile charge assuming a deployed state in which said length is non-parallel to said axis. 12. The method of claim 11, wherein said explosively-formed-projectile charge is configured to generate at least two explosively formed blade projectile propagating substantially perpendicular to said length. 13. The method of claim 11, wherein said deployed state and said explosively-formed-projectile charge are configured such that, when said explosively-formed-projectile charge is detonated in said deployed state, said explosively formed blade projectile propagates in a direction non-coplanar with said length of said explosively-formed-projectile charge and said axis of said fuselage. 14. The method of claim 11, wherein said deployed state and said explosively-formed-projectile charge are configured such that, when said explosively-formed-projectile charge is detonated in said deployed state, said explosively formed blade projectile propagates in a direction forming an angle of between 80 degrees and 180 degrees with a forward direction of said fuselage along said axis. 15. The method of claim 11, wherein said warhead system includes at least a first and a second explosively-formed-projectile charge, and wherein said warhead system is configured to allow selective detonation of a first of said explosively-formed-projectile charges without detonation of a second of said explosively-formed-projectile charges. 16. The method of claim 11, wherein said projectile-intercepting munition further including a deployment mechanism configured to allow selective deployment of said explosively-formed-projectile charge to a deployed position at each of a plurality of different angles relative to said axis, the method further comprising activating said deployment mechanism so as to deploy said explosively-formed-projectile charge for directing said explosively formed blade projectile towards the projectile.
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