Methods and apparatus for a tandem divert and attitude control system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-015/00
B64B-001/36
B64C-009/38
B64C-023/00
B64C-015/02
출원번호
US-0696395
(2010-01-29)
등록번호
US-8800913
(2014-08-12)
발명자
/ 주소
Pagliara, Philip W.
Leal, Michael A.
Jenia, Justin C.
Dalbello, Teryn
Hitner, John M.
출원인 / 주소
Raytheon Company
대리인 / 주소
Gifford, Eric A.
인용정보
피인용 횟수 :
2인용 특허 :
2
초록▼
An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and
An aeronautical vehicle includes at least one set of tandem divert thrusters incorporated into the body. Each set of tandem divert thrusters includes a first divert thruster and a second divert thruster, each configured to provide substantially equal thrust forces at substantially the same time and in substantially opposite directions such that the moment reference point lies between the first and second divert thrusters.
대표청구항▼
1. A divert and attitude control system for an aeronautical kill vehicle having a moment reference point lying along a longitudinal axis, comprising: a first thruster configured to produce a first force on the aeronautical kill vehicle proximate a first end of the aeronautical vehicle and substantia
1. A divert and attitude control system for an aeronautical kill vehicle having a moment reference point lying along a longitudinal axis, comprising: a first thruster configured to produce a first force on the aeronautical kill vehicle proximate a first end of the aeronautical vehicle and substantially perpendicular to the longitudinal axis within a first plane;a second thruster configured to produce a second force on the aeronautical kill vehicle proximate a second end of the aeronautical kill vehicle opposite the first end and substantially perpendicular to the longitudinal axis within the first plane in a direction opposite that of the first force, and wherein the moment reference point lies between the first and second thrusters;a third thruster configured proximate the first end of aeronautical vehicle to produce a third force in the first plane substantially collinear with the first force in the opposite direction;a fourth thruster configured proximate the second end of the aeronautical vehicle to produce a fourth force in the first plane substantially collinear with the second force, and wherein the moment reference point lies between the third and fourth divert thrusters;wherein said first, second, third and fourth thrusters are each at a fixed and non-rotating position in the first plane,wherein said first, second, third and fourth thrusters produce first, second, third and fourth forces that are co-planar in the first plane and perpendicular to the longitudinal axis in the first plane, anda common gas source communicating with each of the first, second, third, and fourth thrusters, said common gas source comprising a gas generator with solid propellant grain; anda controller communicatively coupled to the common gas source and the thrusters to control the forces produced by the first, second, third and fourth thrusters to perform both divert and attitude control maneuvers only in the first plane. 2. The control system of claim 1, wherein each and every said thruster in the control system is configured to produce a force in said first plane or a different plane in which the longitudinal axis lies, each said force being perpendicular or co-axial with said longitudinal axis. 3. The control system of claim 1, further including: a fifth thruster configured to produce a fifth force on the aeronautical kill vehicle proximate the first end of the aeronautical kill vehicle and within a second plane orthogonal to the first plane, wherein the longitudinal axis lies in the second plane, wherein the fifth force is substantially perpendicular to the longitudinal axis of the aeronautical kill vehicle;a sixth thruster configured to produce a sixth force on the aeronautical kill vehicle proximate the second end of the aeronautical kill vehicle and within the second plane, wherein the moment reference point lies between the fifth and sixth thrusters;a seventh thruster configured to produce a seventh force in the second plane substantially collinear with the fifth force in the opposite direction, andan eighth thruster configured to produce an eighth force in the second plane substantially collinear with the sixth force, wherein the moment reference point lies between the fifth and sixth thrusters;said controller communicatively coupled to the common gas source and the thrusters to control the forces produced by the fifth, sixth, seventh and eighth to perform both divert and attitude control maneuvers only in the second plane. 4. The control system of claim 3, further including a ninth thruster aligned coaxially with the longitudinal axis. 5. The control system of claim 3, wherein the controller is configured to provide thrust signals to the first, second, third, fourth, fifth, sixth, seventh, and eighth thrusters to produce paired thrust forces to either substantially only divert the kill vehicle in said first or second planes or substantially only rotate the kill vehicle in said first or second planes. 6. A method of adjusting the attitude of an aeronautical kill vehicle having a moment reference point lying along a longitudinal axis, comprising: receiving a command associated with a required attitude adjustment within a first plane intersecting the longitudinal axis of the aeronautical kill vehicle;generating a first thrust force from a fixed and non-rotating position on the aeronautical vehicle proximate a first end of the aeronautical kill vehicle within the first plane, wherein the first thrust force has an orientation substantially perpendicular to the longitudinal axis of the aeronautical kill vehicle;generating a second thrust force from a fixed and non-rotating position on the aeronautical kill vehicle proximate a second end of the aeronautical kill vehicle opposite the first end within the first plane, wherein the second thrust force has an orientation substantially opposite that of the first thrust force;wherein the first and second thrust forces are substantially equal and are generated substantially simultaneously on opposite sides of the moment reference point to produce only the required attitude adjustment in the first plane;receiving a command associated with a required divert adjustment within the first plane;generating a third thrust force from a fixed and non-rotating position on the aeronautical kill vehicle proximate the first end of the aeronautical kill vehicle within the first plane, wherein the third thrust force has an orientation substantially perpendicular to the longitudinal axis of the aeronautical kill vehicle; andgenerating a fourth thrust force from a fixed and non-rotating position on the aeronautical kill vehicle proximate the second end of the aeronautical kill vehicle opposite the first end within the first plane, wherein the first thrust force has an orientation substantially the same as that of the third thrust force;wherein the third and fourth thrust forces are substantially equal and are generated substantially simultaneously on opposite sides of the moment reference point to produce only the required divert adjustment in the first plane. 7. The method of claim 6, further including generating the first and second thrust forces from a common gas source. 8. The method of claim 6, further including applying an axial thrust force along the longitudinal axis of the aeronautical kill vehicle. 9. An aeronautical kill vehicle comprising: a body having a moment reference point lying along a longitudinal axis; andat least four sets of tandem divert thrusters incorporated into the body;wherein each set of tandem divert thrusters includes a first divert thruster and a second divert thruster positioned at opposite ends of the kill vehicle to either side of the moment reference point, each said thruster configured to provide substantially equal thrust forces in substantially opposite and fixed directions perpendicular to the longitudinal axis,wherein the first and second sets effecting rotation only in a first plane, and the third and fourth sets effecting rotation only in a second plane orthogonal to the second plane, wherein the first and second planes intersect along the longitudinal axis of the body,wherein the first and second thrusters in said first and second sets are each at a fixed and non-rotating position in the first plane orthogonal to the longitudinal axis,wherein the first and second thrusters in said third and fourth sets are each at a fixed and non-rotating position in the second plane orthogonal to the longitudinal axis; anda controller configured to provide paired thrust signals to produce paired thrust forces to substantially only divert the kill vehicle in said first or second planes or to substantially only rotate the kill vehicle in said first or second planes. 10. The aeronautical kill vehicle of claim 9, wherein each and every said thruster in the control system is configured to produce a force in the first or second planes or a different plane in which the longitudinal axis lies, each said force being perpendicular or co-axial with said longitudinal axis. 11. The aeronautical kill vehicle of claim 9, further including at least one axial thruster having an orientation aligned with the longitudinal axis of the aeronautical vehicle. 12. The aeronautical kill vehicle of claim 9, further including a common gas source in fluid communication with each of the sets of tandem divert thrusters. 13. The aeronautical kill vehicle of claim 12, wherein the common gas source comprises a gas generator with solid propellant grain. 14. The control system of claim 1, wherein each said thruster comprises a throttleable nozzle. 15. The control system of claim 1, wherein said controller is configured to control the forces produced by the first and second thrusters or the third and fourth thrusters to provide substantially only an attitude adjustment in the first plane and is configured to control the forces produced by first and fourth thrusters or the second and third thrusters to provide substantially only a divert adjustment in the first plane.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (2)
Dunn Michael J. (Auburn WA), Projectile with integrated propulsion system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.