[특허]Steerable rotating projectile

Hoffberg, Steven M.

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색도움말
검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Steerable rotating projectile

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01C-023/00 G05D-001/00 G05D-003/00 G06F-007/00 G06F-017/00 B64C-039/00 B64C-017/02 B64C-021/00 B64C-023/00 B64C-023/08 F42B-010/62 F42B-010/02
출원번호	US-0476275 (2017-03-31)
등록번호	US-10118696 (2018-11-06)
발명자 / 주소	Hoffberg, Steven M.
출원인 / 주소	Hoffberg, Steven M.
대리인 / 주소	Tully Rinckey PLLC
인용정보	피인용 횟수 : 0 인용 특허 : 1091

초록
▼

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

대표
청구항
▼

1. A flying projectile, comprising: an inertial mass, configured to spin during flight, about an axis of rotation to gyroscopically stabilize the flying projectile;an aerodynamic surface having a circular periphery, configured to interact and generate lift from forward movement of the flying projectile with respect to surrounding air during flight, to produce aerodynamic forces having an aerodynamic force profile having a center of pressure;a control system, configured to produce at least one control signal varying selectively in dependence on at least a rotation of the inertial mass about the axis of rotation; andat least two actuators, responsive to the control signal varying selectively in dependence on, and synchronized with, at least the rotation of the inertial mass about the axis of rotation, configured to selectively alter the aerodynamic forces produced by the aerodynamic surface by independently controlling an aerodynamic property of at least two different portions of the aerodynamic surface, to change a relationship between the axis of rotation and the center of pressure, to selectively generate a torque about the axis of rotation and steer the flying projectile. 2. The flying projectile according to claim 1, further comprising at least one second actuator configured to alter a relationship between a center of gravity of the flying projectile and the axis of rotation, to selectively generate a torque about the axis of rotation and steer the flying projectile synchronized with angular rotation of the flying projectile. 3. The flying projectile according to claim 1 further comprising at least one third actuator, selectively controllable to provide a Magnus effect force to shift a flight path of the flying projectile in a horizontal plane normal to the vertical axis of rotation. 4. The flying projectile according to claim 1, wherein the at least two actuators comprise a reconfigurable aerodynamic surface. 5. The flying projectile according to claim 1, wherein the at least two actuators comprise a vibrating transducer. 6. The flying projectile according to claim 5, wherein the vibrating transducer is configured to control a boundary layer separation from the aerodynamic surface. 7. The flying projectile according to claim 1, wherein the at least two actuators comprise a rotating motor. 8. The flying projectile according to claim 1, wherein the at least two actuators comprise a linear actuator. 9. The flying projectile according to claim 1, wherein the at least two actuators comprise a vane controlled selectively block and permit an airflow. 10. The flying projectile according to claim 1, wherein the at least two actuators comprise at least three actuators, configured to independently control an aerodynamic property of at least three different portions of the aerodynamic surface synchronized with respect to rotation about the axis of rotation. 11. The flying projectile according to claim 1, wherein the control system is further configured to be responsive to a guidance signal to selectively alter a flightpath of the flying projectile. 12. The flying projectile according to claim 1, wherein the control system is further configured to stabilize an instability of a flightpath of the flying projectile. 13. The flying projectile according to claim 1, wherein the at least two actuators are configured to alter at least the at least two portions of the aerodynamic surface during flight to selectively generate lift eccentric to an axis of rotation, wherein the generated lift is synchronized with angular rotation of the portion of the aerodynamic surface. 14. The flying projectile according to claim 1, wherein the at least two actuators are configured to control a radial movement of a mass with respect to the axis of rotation. 15. The flying projectile according to claim 1, wherein the at least two actuators are configured to selectively alter a turbulence of air flowing over the flying projectile during flight. 16. The flying projectile according to claim 1, wherein the control system is further configured to control each of the at least two actuators to selectively produce different aerodynamic forces as a function of an angle of rotation about the axis of rotation. 17. The flying projectile according to claim 1, wherein the control system further produces a servo control signal for a servo motor having a rotational speed corresponding to a rotational speed of the inertial mass about the axis of rotation modified by a steering perturbation. 18. The flying projectile according to claim 1, wherein the control system is further configured to execute flight control logic, dependent on at least two competing goals, and to control the at least two actuators to execute the flight logic to optimize between the at least two competing goals. 19. A method for controlling a gyroscopically-stabilized flying projectile having an inertial mass and a smooth peripheral edge which rotates about an axis of rotation during flight, comprising: determining an angle of rotation of the inertial mass spinning about the axis of rotation during flight; andcontrolling at least two actuators, to selectively alter a relationship between a center of gravity of the flying projectile with respect to a center of pressure of an aerodynamic force acting on the flying projectile, by independently controlling an aerodynamic characteristic of at least two different portions of an aerodynamic surface of the flying projectile, in response to at least one control signal which is synchronized to vary with a rotation of the inertial mass about the axis of rotation. 20. A rotating aerodynamic flying object, comprising: an aerodynamic surface having a circular peripheral edge, configured to produce an aerodynamic lift force with respect to air moving over the rotating aerodynamic flying object during flight;an orientation sensor configured to generate a sensor signal responsive to a rotational angle of the rotating aerodynamic flying object with respect to an external reference, the sensor signal having a periodic variation dependent on rotation of the rotating aerodynamic flying object during flight;a control system responsive to at least the sensor signal having a periodic variation dependent on rotation of the rotating aerodynamic flying object during flight and a control algorithm, to produce a control signal; andat least two actuators responsive to the control signal, configured to alter a flight path of the rotating aerodynamic flying object, by at least varying an aerodynamic property of each of at least two independently controllable aerodynamic surfaces, which varies in a manner synchronized to the rotational angle of the rotating aerodynamic flying object with respect to an external reference, to alter a relation of a center of gravity of the rotating aerodynamic flying object and an aerodynamic force distribution, dependent on the rotational angle.

인용문헌 (1091)

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

연합인증

특허 상세정보

Steerable rotating projectile

초록
▼

대표
청구항
▼

인용문헌 (1091)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Steerable rotating projectile

초록 ▼

대표청구항 ▼

인용문헌 (1091)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼