[특허]Methods and apparatuses for aerial interception of aerial threats

Orbital ATK, Inc.

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Methods and apparatuses for aerial interception of aerial threats

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/34 F42B-010/66 F42B-015/01 F41G-007/00 F41H-011/02 F41G-007/30 F42B-015/10 G05D-001/08 F42B-010/00 F42B-015/00
출원번호	US-0839637 (2013-03-15)
등록번호	US-9551552 (2017-01-24)
발명자 / 주소	Kolanek, James Baseghi, Behshad Sharpin, David Visco, Anthony Shieh, Falin
출원인 / 주소	Orbital ATK, Inc.
대리인 / 주소	TraskBritt
인용정보	피인용 횟수 : 0 인용 특허 : 53

초록
▼

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

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청구항
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1. An eject vehicle for disposition in and ejection from a dispenser, the eject vehicle comprising: a plurality of pitch thrusters configured to perform a pitch maneuver to generate a perpendicular force on the eject vehicle relative to a longitudinal axis of the eject vehicle after ejection of the eject vehicle to rotate and substantially align the eject vehicle with an intercept vector pointed toward an interception point for an identified aerial threat;a rocket motor configured to perform a thrust maneuver to accelerate the eject vehicle along the longitudinal axis of the eject vehicle;one or more divert thrusters configured to perform a divert maneuver on the eject vehicle in a direction substantially perpendicular to the intercept vector; andtwo orthogonal linearly polarized receive antennas, outputs thereof being adaptively combined to match incoming polarization of received signals to substantially eliminate polarization mismatch loss induced by body rotation of the eject vehicle. 2. The eject vehicle of claim 1, wherein the one or more divert thrusters are further configured to compensate for an expected high pressure region forward of the divert thrusters and an expected low pressure region aft of the divert thrusters. 3. The eject vehicle of claim 1, further comprising a plurality of attitude control thrusters positioned forward or aft of the eject vehicle center of gravity and configured to make adjustments to an attitude of the eject vehicle when activated. 4. The eject vehicle of claim 3, further comprising an electronics module configured for performing an attitude control algorithm to use a determination of an angle of attack of the eject vehicle to determine an appropriate time to fire an attitude control thruster of the plurality of attitude control thrusters to adjust the attitude of the eject vehicle to a desired orientation. 5. The eject vehicle of claim 1, further comprising an inertial management unit configured to determine at least one of acceleration, velocity, and position information in at least an angular coordinate of the eject vehicle responsive to one or more sensors selected from the group consisting of accelerometers, gyros, and magnetometers. 6. The eject vehicle of claim 5, further comprising an electronics module for performing a Joint Adaptive Polarization and Roll Angle Estimator (JAPRAE) configured to determine a roll estimation by synthesizing information from the two orthogonal linearly polarized receive antennas and information from the inertial management unit. 7. The eject vehicle of claim 6, wherein the JAPRAE is configured to determine the roll estimation using an extended Kalman filter. 8. The eject vehicle of claim 5, further comprising an electronics module for performing a Joint Adaptive Polarization and Roll Angle Estimator (JAPRAE) configured to adaptively combine the signals from the two orthogonal linearly polarized receive antennas to match the polarization of the incident signal. 9. The eject vehicle of claim 1, further comprising: an impulse cartridge configured to fire responsive to a command from an aerial platform bearing the eject vehicle; andan ejection piston configured to propel the eject vehicle away from the aerial platform responsive to the firing of the impulse cartridge. 10. The eject vehicle of claim 1, further comprising a warhead configured to detonate when the eject vehicle is away from the dispenser and within a predetermined range of the identified aerial threat. 11. A method of intercepting an aerial threat, comprising: ejecting an eject vehicle from a dispenser;performing a pitch maneuver with a plurality of pitch thrusters of the eject vehicle to align the eject vehicle along an intercept vector pointed substantially toward a projected intercept point with an identified aerial threat;performing a thrust maneuver with a rocket motor of the eject vehicle to accelerate the eject vehicle;performing a divert maneuver with one or more divert thrusters of the eject vehicle to divert the eject vehicle from the intercept vector one or more times after commencement of accelerating the eject vehicle to adjust a course of the eject vehicle to align the eject vehicle along an updated intercept vector; andprocessing received signals from two orthogonal linearly polarized receive antennas to match incoming polarization of the received signals to substantially eliminate polarization mismatch loss induced by body rotation of the eject vehicle. 12. The method of claim 11, further comprising compensating for an expected high pressure region forward of the divert thrusters and an expected low pressure region aft of the divert thrusters when diverting the eject vehicle. 13. The method of claim 11, further comprising making adjustments to an attitude of the eject vehicle with a plurality of attitude control thrusters positioned near a front or rear of the eject vehicle. 14. The method of claim 13, further comprising performing an attitude control algorithm using a determination of a roll estimation of the eject vehicle to determine an appropriate time to fire an attitude control thruster of the plurality of attitude control thrusters to adjust the attitude of the eject vehicle to a desired orientation. 15. The method of claim 11, further comprising determining at least one of acceleration, velocity, and position information in at least an angular coordinate of the eject vehicle with an inertial management unit. 16. A method of intercepting an aerial threat, comprising: ejecting an eject vehicle from a dispenser;performing a pitch maneuver with a plurality of pitch thrusters of the eject vehicle to align the eject vehicle along an intercept vector pointed substantially toward a projected intercept point with an identified aerial threat;performing a thrust maneuver with a rocket motor of the eject vehicle to accelerate the eject vehicle;performing a divert maneuver with one or more divert thrusters of the eject vehicle to divert the eject vehicle from the intercept vector one or more times after commencement of accelerating the eject vehicle to adjust a course of the eject vehicle to align the eject vehicle along an updated intercept vector;determining at least one of acceleration, velocity, and position information in at least an angular coordinate of the eject vehicle with an inertial management unit; andperforming a Joint Adaptive Polarization and Roll Angle Estimator (JAPRAE) to determine a roll estimation by synthesizing information from two orthogonal linearly polarized receive antennas and information from the inertial management unit. 17. The method of claim 16, wherein performing the JAPRAE further comprises determining the roll estimation with an extended Kalman filter. 18. An active protection system for an aerial platform, comprising: an onboard system on an aerial platform comprising one or more sensor modules, the onboard system configured to: detect a plurality of aerial vehicles within a threat range of the aerial platform;determine if any of the plurality of aerial vehicles is an aerial threat;determine an intercept vector to the aerial threat, the intercept vector pointed toward a projected interception point of an identified aerial threat;communicate with at least one eject vehicle responsive to determining the intercept vector; andthe at least one eject vehicle configured to be ejected from the aerial platform, the at least one eject vehicle comprising: a plurality of pitch thrusters configured to adjust a pitch of the at least one eject vehicle relative to the intercept vector to rotate a longitudinal axis of the at least one eject vehicle to substantially align with an intercept vector; anda rocket motor configured to accelerate the at least one eject vehicle along the longitudinal axis of the at least one eject vehicle; andone or more divert thrusters configured to divert the at least one eject vehicle in a direction substantially perpendicular to the longitudinal axis of the at least one eject vehicle. 19. The active protection system of claim 18, wherein: the onboard system is further configured to: track the at least one eject vehicle as it moves along the intercept vector;determine a diversion vector in a direction substantially perpendicular to a travel direction of the at least one eject vehicle; andcommunicate a divert command to the at least one eject vehicle responsive to determining the diversion vector; andthe at least one eject vehicle is further configured to activate at least one of the one or more divert thrusters responsive to the divert command. 20. The active protection system of claim 18, wherein the at least one eject vehicle further comprises a plurality of attitude control thrusters positioned near a front of the at least one eject vehicle and configured to make adjustments to an attitude of the at least one eject vehicle when activated. 21. The active protection system of claim 20, wherein the at least one eject vehicle further comprises an electronics module configured for performing an attitude control algorithm to use a determination of a roll estimation of the at least one eject vehicle to determine an appropriate time to fire an attitude control thruster of the plurality of attitude control thrusters to adjust the attitude of the at least one eject vehicle to a desired orientation. 22. The active protection system of claim 18, wherein the at least one eject vehicle further comprises two orthogonal linearly polarized receive antennas to match incoming polarization of received signals to substantially eliminate polarization mismatch loss induced by body rotation of the at least one eject vehicle. 23. The active protection system of claim 22, wherein the at least one eject vehicle further comprises an inertial management unit configured to determine at least one of acceleration, velocity, and position information in at least an angular coordinate of the at least one eject vehicle responsive to one or more sensors selected from the group consisting of accelerometers, gyros, and magnetometers. 24. The active protection system of claim 23, wherein the at least one eject vehicle further comprises an electronics module for performing a Joint Adaptive Polarization and Roll Angle Estimator (JAPRAE) configured to determine a roll estimation by synthesizing information from the two orthogonal linearly polarized receive antennas and information from the inertial management unit. 25. The active protection system of claim 24, wherein the JAPRAE is configured to determine the roll estimation using an extended Kalman filter. 26. The active protection system of claim 18, wherein the onboard system is configured to communicate directional coordinates of the intercept vector to the at least one eject vehicle. 27. The active protection system of claim 18, wherein the onboard system is configured to communicate pitch commands derived from the intercept vector to the at least one eject vehicle. 28. The active protection system of claim 18, wherein the onboard system is configured to communicate information associated with the intercept vector to the at least one eject vehicle at least one of before ejection or after ejection of the at least one eject vehicle. 29. An eject vehicle for disposition in a dispenser of an active protection system, comprising: an airframe shell containing a warhead;a nose portion attached to the airframe shell;a rocket motor removably attached to the airframe shell and configured to accelerate the eject vehicle along an intercept vector and to detach from the airframe shell upon exhaustion; anda plurality of attitude control thrusters attached to the nose portion of the eject vehicle and configured to rotate a longitudinal axis of the eject vehicle about an axis orthogonal to the longitudinal axis of the eject vehicle,wherein each attitude control thruster of the plurality of attitude control thrusters is configured to rotate the longitudinal axis of the eject vehicle a first amount within a first range of angles while the rocket motor is attached to the airframe shell, andwherein each attitude control thruster of the plurality of attitude control thrusters is configured to rotate the longitudinal axis of the eject vehicle a second amount within a second different range of angles after the rocket motor has detached from the airframe shell. 30. The eject vehicle of claim 29, wherein the plurality of attitude control thrusters comprises a plurality of micro-thrusters. 31. The eject vehicle of claim 29, wherein the plurality of attitude control thrusters is configured to adjust a velocity vector of the eject vehicle. 32. An active protection system for a platform, comprising: at least one eject vehicle for disposition in a dispenser on the platform, the at least one eject vehicle comprising: an airframe shell containing a warhead;a nose portion attached to the airframe shell and including a plurality of thrusters for controlling a pitch and attitude of the at least one eject vehicle; anda rocket motor attached to the airframe shell and configured to accelerate the at least one eject vehicle along an intercept vector upon launch from the dispenser; anda computing system in communication with at least one engagement management module onboard the platform and the at least one eject vehicle, the at least one engagement management module configured to detect an aerial vehicle within a threat range of the platform,wherein the computing system is configured to: determine if the aerial vehicle is an aerial threat;transmit a launch command to at least one eject vehicle to be launched from the platform to intercept a determined aerial threat; andtransmit guidance commands to the at least one eject vehicle while the at least one eject vehicle is in flight along the intercept vector for intercepting the determined aerial threat, andwherein the computing system includes at least one thruster module configured to control ignition and use of the plurality of thrusters of the at least one eject vehicle in order to maintain thrust for the at least one eject vehicle throughout an intercept operation. 33. The active protection system of claim 32, wherein the computing system is configured to maintain a count of which thrusters of the plurality of thrusters have already been fired and a count of which thrusters of the plurality of thrusters remain available to fire. 34. The active protection system of claim 32, wherein the plurality of thrusters comprises a plurality of attitude control thrusters configured to maintain an angle of attack of the eject vehicle while the eject vehicle is in flight toward the interception point. 35. The active protection system of claim 32, wherein the plurality of thrusters comprises a plurality of divert thrusters configured to divert the eject vehicle in a direction at least substantially perpendicular to the intercept vector. 36. The active protection system of claim 32, wherein the plurality of thrusters comprises a plurality of pitch thrusters configured to rotate a longitudinal axis of the at least one eject vehicle to substantially align the longitudinal axis of the at least one eject vehicle with the intercept vector. 37. The active protection system of claim 32, further comprising a plurality of micro-thrusters attached to the nose portion of the at least one eject vehicle. 38. The active protection system of claim 32, wherein the computing system is configured to determine how many thrusters of the plurality of thrusters are required to intercept the determined aerial threat based on a remaining total mass of the at least one eject vehicle, a center of gravity location of the at least one eject vehicle, and an inertia tensor of the at least one eject vehicle. 39. The active protection system of claim 32, wherein the computing system is configured to update a remaining total mass of the at least one eject vehicle, a center of gravity location of the eject vehicle, and an inertia tensor of the at least one eject vehicle as the plurality of thrusters is fired. 40. The active protection system of claim 32, wherein the computing system is configured to determine a closest point of approach of the at least one eject vehicle and the determined aerial threat and to transmit a detonation command to the at least one eject vehicle to detonate when the at least one eject vehicle reaches the closest point of approach. 41. An eject vehicle for disposition in a dispenser of an active protection system, comprising: an airframe shell containing a warhead, the airframe shell comprising: a plurality of attitude control thrusters configured to maintain an angle of attack of the eject vehicle throughout an intercept operation;a plurality of pitch thrusters configured to rotate a longitudinal axis of the eject vehicle to at least substantially align the longitudinal axis of the eject vehicle with an intercept vector; anda plurality of divert thrusters configured to divert the eject vehicle in a direction at least substantially perpendicular to the intercept vector; anda rocket motor removably attached to the airframe shell and configured to accelerate the eject vehicle along the intercept vector upon launch from the dispenser. 42. The eject vehicle of claim 41, wherein the plurality of attitude control thrusters is positioned forward or aft of a center of mass of the eject vehicle and oriented to generate a force on the eject vehicle at least substantially perpendicular to the longitudinal axis of the eject vehicle. 43. The eject vehicle of claim 41, wherein the plurality of pitch thrusters is positioned offset from a center of mass of the eject vehicle and oriented to generate a force on the eject vehicle at least substantially perpendicular to the longitudinal axis of the eject vehicle. 44. The eject vehicle of claim 41, wherein the plurality of divert thrusters is positioned proximate a center of mass of the eject vehicle and oriented to generate a force on the eject vehicle at least substantially perpendicular to the longitudinal axis of the eject vehicle. 45. The eject vehicle of claim 41, wherein the plurality of attitude control thrusters and the plurality of pitch thrusters are positioned proximate a nose portion of the eject vehicle.

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Methods and apparatuses for aerial interception of aerial threats

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Methods and apparatuses for aerial interception of aerial threats

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