IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0002150
(2001-12-05)
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우선권정보 |
IL-140183 (2000-12-07) |
발명자
/ 주소 |
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출원인 / 주소 |
- Rafael-Armament Development Authority Ltd.
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대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
3 |
초록
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A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot. The missile includes a seeker operative to track a target. The method comprises providing a first indication to the pilot when the seeker is tracking a target, providing a second indication to the pilot
A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot. The missile includes a seeker operative to track a target. The method comprises providing a first indication to the pilot when the seeker is tracking a target, providing a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period.
대표청구항
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1. A method for providing indications to a pilot operating a short range, air-to-air missile carried by an aircraft flown by the pilot, the missile having a seeker operative to track a target, the method comprising:(a) providing a first indication to the pilot when the seeker is tracking a target; a
1. A method for providing indications to a pilot operating a short range, air-to-air missile carried by an aircraft flown by the pilot, the missile having a seeker operative to track a target, the method comprising:(a) providing a first indication to the pilot when the seeker is tracking a target; and(b) providing a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period. 2. The method of claim 1, wherein said first indication and said second indication are readily distinguishable audible signals. 3. A method for providing indications to a pilot operating a short range, air-to-air missile carried by an aircraft flown by the pilot, the missile having a seeker configured to track a target, the method comprising:(a) providing a signaling unit associated with the missile and configured to provide a first indication to the pilot when the seeker is tracking a target and to provide a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period; and(b) while the seeker is tracking a target visible to the pilot, flying the aircraft in such a manner that a rate of angular motion of the direction of a line of sight from the pilot to the target remains below said given value in a frame of reference moving with the aircraft for said predefined period, thereby causing said signaling unit to generate said second indication. 4. The method of claim 3, wherein said first indication and said second indication are readily distinguishable audible signals. 5. A short range, air-to-air missile to be carried by an aircraft flown by a pilot, the missile comprising:(a) a gimbaled seeker for tracking a target;(b) a processing system including at least one processor, said processing system providing a first indication to the pilot when the seeker is tracking a target;wherein said processing system further provides a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period. 6. The missile of claim 5, wherein said first and second indications are provided by generating corresponding readily distinguishable audible signals. 7. A short range, air-to-air missile to be carried by an aircraft flown by a pilot, the missile comprising:(a) a gimbaled seeker for tracking a target, said gimbaled seeker having a direction of regard defined by an angle of inclination θ from a predefined boresight direction and an orientation angle φ measured about an axis corresponding to said boresight direction, said angle of inclination θ being limited by a predefined maximum angle θ max ; and(b) a processing system including at least one processor associated with said seeker, said processing system to:(i) processing said angle of inclination while said seeker is tracking a target to derive a rate of change of said angle of inclination {dot over (θ)},(ii) evaluating an off-boresight tracking angle limitation parameter as a function of both said angle of inclination and said rate of change, and(iii) generating a tracking angle exceedance signal when said off-boresight tracking angle limitation parameter falls outside a predefined range. 8. The missile of claim 7, wherein said processing system evaluates said off-boresight tracking angle limitation parameter P according to a relation P=θ+t 0 {dot over (θ)} where t 0 is a predefined measure of time taken after firing for the missile to begin to turn, and wherein said processing system generates said tracking angle exceedance signal when P is greater than θ max . 9. The missile of claim 7, wherein said processing system generates said tracking angle exceedance signal as an electric signal corresponding to a distinctive audio output. 10. A short range, air-to-air missile to be carried by an aircraft flown by a pilot, the missile comprising:(a) a gimbaled seeker having a direction of rega rd defined by an angle of inclination θ from a predefined boresight direction and an orientation angle φ measured about an axis corresponding to said boresight direction; and(b) a processing system including at least one processor associated with said seeker, said processing system for:(i) selectively actuating said seeker to perform a scanning search pattern for a target, said scanning search pattern being confined to a range of orientation angles spanning no more than 20° and covering a range of inclination angles spanning no less than 30°, and(ii) when a target is found, causing said seeker to track the target. 11. The missile of claim 10, wherein said scanning search pattern covers a range of inclination angles spanning no less than 50°. 12. The missile of claim 10, wherein said angle of inclination θ is limited by a predefined maximum angle θ max , said scanning search pattern covering a range of inclination angles extending substantially up to said predefined maximum angle θ max . 13. The missile of claim 10, wherein said scanning search pattern is confined to a range of orientation angles spanning no more than 10°. 14. The missile of claim 10, wherein said scanning search pattern is confined to a range of orientation angles spanning between 5° and 10°. 15. The missile of claim 10, further comprising attachment features defining an orientation of attachment of the missile to an aircraft such that, when attached to an aircraft, a given value of seeker orientation angle φ v corresponds to a “vertical” direction in an aircraft frame of reference, wherein said scanning search pattern is confined to a range of orientation angles of φ v ±5°. 16. A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot, the missile including a gimbaled seeker having a direction of regard defined by an angle of inclination θ from a predefined boresight direction and an orientation angle φ measured about an axis corresponding to the boresight direction, the method comprising:(a) causing said seeker to perform a scanning search pattern for a target, said scanning search pattern being confined to a range of orientation angles spanning no more than 20° and covering a range of inclination angles spanning no less than 30°, and(b) when a target is found, causing said seeker to track the target. 17. The method of claim 16, wherein said scanning search pattern covers a range of inclination angles spanning no less than 50°. 18. The method of claim 16, wherein said angle of inclination θ is limited to a predefined maximum angle θ max , said scanning search pattern covering a range of inclination angles extending substantially up to said predefined maximum angle θ max . 19. The method of claim 16, wherein said scanning search pattern is confined to a range of orientation angles spanning no more than 10°. 20. The method of claim 16, wherein said scanning search pattern is confined to a range of orientation angles spanning between 5° and 10°. 21. The method of claim 16, wherein said scanning search pattern is confined to a range of orientation angles of φ v ±5°where φ v corresponds to a vertical direction in the aircraft frame of reference. 22. A method for providing indications to a pilot operating a short range, air-to-air missile carried by an aircraft flown by the pilot, the missile including a gimbaled seeker having a direction of regard defined by an angle of inclination θ from a predefined boresight direction and an orientation angle φ measured about an axis corresponding to the boresight direction, the angle of inclination θ being limited by a predefined maximum angle θ max , the method comprising:(a) processing the angle of inclination while the seeker is tracking a target to derive a rate of change of t he angle of inclination {dot over (θ)};(b) evaluating an off-boresight tracking angle limitation parameter as a function of both said angle of inclination and said rate of change; and(c) generating a tracking angle exceedance signal when said off-boresight tracking angle limitation parameter falls outside a predefined range. 23. The method of claim 22, wherein at least said steps of processing and evaluating are performed by a processing system located within the missile. 24. In an aircraft carrying a short range, air-to-air missile having a seeker for tracking a target within a missile field-of-view, the aircraft including a radar system which provides range-derive data relating to targets within a radar field-of-view smaller than the missile field-of-view, a method for evaluating whether the missile will be effective in reaching a target comprising the steps of:(a) during a first period when a given target lies within the radar field-of-view, evaluating at least one performance limitation criterion relating to the ability of the missile to reach the given target, the performance limitation criterion being evaluated using the range-derived data for the given target; and(b) during a second period subsequent to the given target leaving the radar field-of-view, evaluating the performance limitation criterion using approximate range-derived data for the given target, said approximate range-derived data being derived by extrapolation from range-derived data provided by the radar system during the first period. 25. The method. of claim 24, wherein said approximate range-derived data is derived by extrapolation based upon an assumption that a speed of the given target derived from radar measurements during a latter portion of the first period remains constant. 26. The method of claim 24, wherein said second period is at least five seconds. 27. The method of claim 24, wherein said second period is less than twenty seconds. 28. The method of claim 24, wherein the performance limitation criterion is additionally evaluated using target direction information related to a direction from the aircraft to the given target, wherein said target direction information is derived, at least during said second period, from tracking information provided by the missile seeker. 29. The method of claim 24, wherein said evaluating is performed, at least during said second period, by a processing system located within the missile. 30. The method of claim 24, further comprising selectively generating, dependent upon results of evaluating said at least one performance limitation criterion, an audible indication audible to a pilot of the aircraft.
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