Drag control system for flying machine, process for estimating drag of flying machine, boundary layer control system, and boundary layer control process
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0606010
(2000-06-29)
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우선권정보 |
JP-0185909 (1999-06-30); JP-0185910 (1999-06-30) |
발명자
/ 주소 |
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출원인 / 주소 |
- Honda Giken Kogyo Kabushiki Kaisha JP
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
10 인용 특허 :
10 |
초록
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The thrust T of an airplane is estimated by a thrust estimating device, and the motion state (the speed, the angular speed, the attitude angle and the elevation angle) of the airplane is detected by a motion state detecting device. Then, a drag estimating device estimates the drag D of the airplane,
The thrust T of an airplane is estimated by a thrust estimating device, and the motion state (the speed, the angular speed, the attitude angle and the elevation angle) of the airplane is detected by a motion state detecting device. Then, a drag estimating device estimates the drag D of the airplane, based on the thrust T and the motion state of the airplane. An operation-amount calculating device converges the steering angle into a target steering angle at which the drag of the airplane is minimized, by repeating the operation of varying the steering angle of a flap by a very small angle by an operating device, and further varying the steering angle by a very small angle, while monitoring the increase or decrease in drag resulting from such variation. Such a drag reducing control is carried out, while monitoring the actual drag and hence, is extremely effective, and also can exhibit an effectiveness, irrespective of the motion state of the airplane.
대표청구항
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1. A drag control system for a flying machine, comprising a thrust estimating means for estimating the thrust of the flying machine while flying in the air, a motion state detecting means for detecting a given motion state of the flying machine, a drag estimating means for estimating the drag of the
1. A drag control system for a flying machine, comprising a thrust estimating means for estimating the thrust of the flying machine while flying in the air, a motion state detecting means for detecting a given motion state of the flying machine, a drag estimating means for estimating the drag of the flying machine, based on the detected motion state and the estimated thrust, a drag varying means for varying the drag of the flying machine, an operation-amount calculating means for calculating the amount of operation of the drag varying means for minimizing the estimated drag, and an operating means for operating the drag varying means, based on the calculated amount of operation,said drag estimating means comprising (a) a means for estimating the thrust T of the flying machine, (b) a means for detecting the following motion state parameters of the flying machine: .phi.: the roll attitude angle (an Eulerian angle about an X axis); .theta.: the pitch attitude angle (an Eulerian angle about a Y axis); U: the speed in a direction of the X axis; V: the speed in a direction of the Y axis; W: the speed in a direction of the Z axis; P: the roll angular speed (an angular speed about the X axis); Q: the pitch angular speed (an angular speed about the Y axis); R: the yaw angular speed (an angular speed about the Z axis); .alpha.: the pitch angle formed by the direction of movement of the flying machine and the center line of the flying machine, (c) a means for calculating components Xa and Za of the air force in the directions of the X and Z axes applied to the flying machine by substituting the detected motion state into the following equations: Xa=m?(dU/dt+Q?W-R?V)+m?g?sin .theta.Za=m?(dW/dt+P?V-Q?U)-m?g?cos .theta.?cos .phi. wherein g is the gravitational acceleration, and m is the mass of the flying machine, (d) a means for calculating the drag D of the flying machine by substituting the estimated thrust T, the detected pitch angle .alpha. and the calculated components Xa and Za of the air force in the directions of the X and Z axes into the following equation: D=(T-Xa)?cos .alpha.-Za?sin .alpha. wherein the operations of means (c) and (d) are carried out sequentially, after the operations of means (a) and (b) are carried out, irrespective of the order, to thereby estimate the drag of the flying machine without using a drag coefficient.
이 특허에 인용된 특허 (10)
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Maestrello Lucio (Newport News VA), Active control of boundary layer transition and turbulence.
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Middleton David B. (Yorktown VA) Srivatsan Raghavachari (Yorktown VA) Person ; Jr. Lee H. (Yorktown VA), Airplane takeoff and landing performance monitoring system.
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Anderson Leonard R. (Phoenix AZ) DeCamp Ronald W. (Dayton OH), Camber control system.
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Mangiarotty Rudolph A. (Seattle WA), Control of laminar flow in fluids by means of acoustic energy.
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Stack John P. (Yorktown VA) Mangalam Sivaramakrishnan M. (Hampton VA), Method and apparatus for detecting laminar flow separation and reattachment.
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Palmer Steven D., Method and apparatus for flight parameter monitoring and control.
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Katz Richard A. (East Lyme CT), Method and system for reducing drag on a body moving through a fluid medium.
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McGough John G. (Ridgewood NJ), Method for developing air data for use in flight control systems.
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Smith Joseph A. (Phoenix AZ) Ringnes Erik A. (Glendale AZ) Tarbutton Victor F. (Glendale AZ), Method of airplane performance estimation and prediction.
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Lewis George E. (Renton WA) Thomasson Robert E. (Seattle WA) Nelson David W. (Redmond WA), Wing lift/drag optimizing system.
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Parikh, Pradip G., Combined cabin air and heat exchanger RAM air inlets for aircraft environmental control systems, and associated methods of use.
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Wood, Norman, Laminar flow monitor.
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Chang, Ming; Meza, Victor; Morgenstern, John M.; Arslan, Alan E., Supersonic aircraft with channel relief control.
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Mangalam,Siva M., System and method for closed loop control of boundary layer shear stress.
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Mangalam, Arun S.; Mangalam, Siva M., System and method for control of aeroelasticity effects.
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Mangalam, Siva M., System and method for real time determination of unsteady aerodynamic loads.
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