[특허]Polaris guidance system

[미국특허] Polaris guidance system 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/36 F42B-015/18
출원번호	US-0502717 (1965-10-22)
발명자 / 주소	Hall Eldon C. (Wollaston MA) Sabo Joseph D. (Arlington MA) Forter Samuel A. (Hingham MA) Ragan Ralph R. (Lincoln MA) Laning J. H. (West Newton MA) Hoag David G. (Medway MA) Vander Velde Wallace E. (W
출원인 / 주소	The United States of America as represented by the Secretary of the Navy (Washington DC 06)
인용정보	피인용 횟수 : 28 인용 특허 : 0

초록 ▼

An inertial guidance system for a rocket powered ballistic missile which provides navigation and control while the missile is proceeding in its flight trajectory. Signals are generated within the confines of the missile and without outside information representative of angular and linear motion of the missile with respect to an inertial frame of reference, a digital computer compares these signals against a preset parameter stored in the computer to provide control signals along the pitch and yaw axes. An autopilot uses these control signals to provide mechanical control movements, and an exhaust nozzle deflection arrangement connected to the autopilot deflects the exhaust of the rocket for guidance along a predetermined flight trajectory.

대표청구항 ▼

An inertial guidance system for a ballistic missile that provides navigation and control while it is proceeding in a flight trajectory to a predetermined target comprising: first inertial reference frame having first, second and third mutually orthogonal axes, said second axis being substantially in a horizontal plane at the time of launch of said missile, and said first and third axes being in a vertical plane that is substantially in the plane of said trajectory, and said first axis is elevated 45°above said horizontal plane and essentially in the direction experiencing the highest dynamic range of input acceleration; second inertial reference frame having first, second and third mutually orthogonal axes R, J and V, said second axis of said second inertial reference frame aligned with said second axis of said first inertial reference frame in said horizontal plane, said first and third axes being in a vertical plane that is substantially in the plane of said trajectory; triad of accelerometers the sensitive axis of each being aligned with one axis of said first reference frame, said accelerometers providing signals representative of linear motion of said missile and requiring no information signals from sources external of the missile nor any airborne computation of the position of the missile in space; triad of gyros, the sensitive axis of each being aligned with one axis of said second reference frame, said gyros providing signals representative of angular motion about the respective axes of said second reference frame and requiring no information signals from sources external of the missile nor any airborne computation of the position of the missile in space; digital computer means coupled to receive said signals representative of linear motion from said triad of accelerometers for processing against preset parameters stored in said digital computer means for providing control signals along the pitch and yaw axes of said balistic missile; autopilot means coupled to receive said control signals from said computer means and said signals representative of angular motion from said triad of gyros for providing mechanical control movements; and exhaust nozzle deflection means mechanically coupled to said autopilot means to deflect the exhaust of said ballistic missile for guidance in a flight trajectory.

이 특허를 인용한 특허 (28) 인용/피인용 타임라인 분석

Gustafson Donald E. ; Lucia David J., Autonomous local vertical determination apparatus and methods for a ballistic body.
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Luu, Thu-Van T.; Boka, Jeffrey B.; Harcourt, Michael J.; Mookerjee, Purusottam, Burnout time estimation and early thrust termination determination for a boosting target.
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Campbell,Ray F.; Wada,Joan D.; Costello,Michael J.; Khatiblou,Mohsen A., Compensated composite structure.
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Wada,Joan D.; Campbell,Ray F.; Quan,Patricia S., Extended accuracy flexured plate dual capacitance accelerometer.
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Wicke Dallas C., Integrated boost phase and post boost phase missile guidance system.
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Campbell,Ray F.; Wada,Joan D.; Raab,John P., Integrated capacitive bridge and integrated flexure functions inertial measurement unit.
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Campbell,Ray F.; Wada,Joan D., Leveling device.
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Campbell,Ray F.; Wada,Joan D.; Costello,Michael J.; Khatiblou,Mohsen A., Magnetic null accelerometer.
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Lund, Christopher A.; Vallot, Lawrence C.; Soehren, Wayne A.; Ignagni, Mario, Method and apparatus for high accuracy relative motion determination using inertial sensors.
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Kirkland, Jeffrey W.; Eckert, Charles P., Method and system for processing pulse signals within an inertial navigation system.
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Biven Earl U. ; Mikelson Gary C. ; Scapellati Gary A., Method for safe flight testing of high velocity interceptor missiles.
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Kolanek, James; Baseghi, Behshad; Sharpin, David; Visco, Anthony; Shieh, Falin, Methods and apparatuses for aerial interception of aerial threats.
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Kolanek, James; Baseghi, Behshad; Sharpin, David; Visco, Anthony; Shieh, Falin, Methods and apparatuses for engagement management of aerial threats.
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Kolanek, James; Baseghi, Behshad; Sharpin, David; Visco, Anthony; Shieh, Falin, Methods and apparatuses for engagement management of aerial threats.
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Manoogian David V., Missile guidance system.
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Wicke Dallas C., Missile stage ignition delay timing for axial guidance correction.
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Campbell,Ray F.; Wada,Joan D.; Costello,Michael J.; Khatiblou,Mohsen A., Precision flexure plate.
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Geswender, Chris E., Projectile with inertial measurement unit failure detection.
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Geswender, Chris E., Projectile with inertial sensors oriented for enhanced failure detection.
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Stetson ; Jr. John B. (Newtown PA), Reaction wheel fricton compensation using dither.
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Campbell,Ray F.; Wada,Joan D., Single plate capacitive acceleration derivative detector.
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Pelto,John H., Submarine steam generator missile ejection system.
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Kim,Dong Yoon; Miller,Scott A., System and method for detection of freefall with spin using two tri-axis accelerometers.
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Linick James M., System and method for determining the angular orientation of a body moving in object space.
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Tournes, Christian; Shtessel, Yuri, System and method for guiding and controlling a missile using high order sliding mode control.
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Soehren, Wayne A.; Lund, Christopher A.; Vallot, Lawrence C., System and method for high accuracy relative navigation.
상세보기
Luu, Thu-Van; Boka, Jeffrey B.; Mookerjee, Purusottam; Harcourt, Michael J., Template updated boost algorithm.
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Campbell, Ray F.; Wada, Joan, Variable capacitance bridge accelerometer.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Polaris guidance system 원문보기