[특허]System and method for dynamic aeroelastic control

The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration

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특허 상세정보

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System and method for dynamic aeroelastic control

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01C-023/00 B64C-019/00 G01N-021/00 G10K-015/04 G01J-001/04 G01S-015/88 B64C-025/20 G03B-039/00 G01M-003/04 G01N-021/43 G08G-005/06 B64D-043/00 B64D-047/00
출원번호	US-0207757 (2014-03-13)
등록번호	US-9073623 (2015-07-07)
발명자 / 주소	Suh, Peter M.
출원인 / 주소	The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소	Homer, Mark
인용정보	피인용 횟수 : 1 인용 특허 : 4

초록

The present invention proposes a hardware and software architecture for dynamic modal structural monitoring that uses a robust modal filter to monitor a potentially very large-scale array of sensors in real time, and tolerant of asymmetric sensor noise and sensor failures, to achieve aircraft performance optimization such as minimizing aircraft flutter, drag and maximizing fuel efficiency.

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1. A computerized system for controlling aeroelastic behavior of an aircraft, comprising: a fiber-optic sensor array comprising a plurality of optical fibers oriented substantially parallel along a wing of said aircraft, each said optical fiber having a plurality of spaced fiber Bragg Gratings (FBGs);a processor in communication with said fiber-optic sensor array, said processor including a non-transitory computer-readable storage device storing a plurality of software modules including, a plant model comprising a finite element model of said aircraft,an assembler software module comprising a series of instructions for performing the steps of calculating a reduced modal matrix representing one of spatial or strain information at each FBG in said fiber-optic sensor array,a modal matrix software module for computing modal coordinates,a function estimator for estimating an optimal aerodynamic state from said modal coordinates; anda flight controller for estimating a performance optimization adjustment to said modal coordinates to maintain said optimal aerodynamic state. 2. The computerized system according to claim 1, wherein said modal matrix software module is a concentrated modal estimator (CME) configured to recursively estimate said modal coordinates from said FBG data that is closest to a statistical multivariate center of data. 3. The computerized system according to claim 1, wherein said flight controller is configured to compute required control surface deflections to produce an optimal drag configuration for said aircraft. 4. A system for dynamic aeroelastic control of an aircraft, comprising: a sensor array attached to said aircraft, said sensor array comprising a plurality of fiber Bragg Grating (FBG) sensors;a processor in communication with said sensor array, said processor including a non-transitory computer-readable storage device storing software comprising a series of instructions for performing the steps of,maintaining a finite element model (FEM) of said aircraft comprising a set of finite elements interconnected at a plurality of nodes,mapping a spatial position of each of said FBG sensors,monitoring strain at each of said FBG sensors in real time;calculating a sensor strain matrix representing linear axial strain at each of said FBG sensors from said modal shape deformation;removing rows of sensor strain matrix based on which sensors are used;applying a robust modal filter software module for modal coordinate transformation of said reduced sensor strain matrix into a strain-based modal matrix by projecting said reduced sensor strain matrix from physical space to modal space to define projected modal coordinates; anda function estimator for estimating the functional relationship of modal coordinates and aerodynamic efficiency; a controller for performance optimization adjustment with said modal coordinates to maintain said optimal aerodynamic state. 5. The system according to claim 4, wherein said aircraft comprises a wing and said is plurality of fiber Bragg Grating (FBG) sensors are spaced along a plurality of optical fibers running substantially parallel along said wing. 6. The system according to claim 4, wherein said FEM comprises a wing model. 7. The system according to claim 4, wherein said FEM comprises a model of the entire aircraft. 8. The system according to claim 4, wherein said step of monitoring deformation at each of said FBG sensors comprises measuring strain at each of said FBG sensors and estimating modal deformation from said measured strain. 9. The system according to claim 4, wherein said step of reducing said sensor strain matrix comprises weighting data. 10. The system according to claim 9, wherein said step of weighting data includes zero-weighting outlier data. 11. The system according to claim 4, wherein said controller comprises a flutter suppression module for minimizing aircraft flutter. 12. The system according to claim 4, wherein said controller comprises a drag minimization module for minimizing aircraft drag. 13. The system according to claim 4, wherein said controller comprises a performance optimization module for maximizing aircraft fuel efficiency. 14. A system for dynamic aeroelastic control of an aircraft, comprising: a sensor array attached to at least a portion of said aircraft;a processor in communication with said sensor array, said processor including a non-transitory computer-readable storage device;a plurality of software modules each comprising a series of instructions stored on the machine-readable storage device and embodying executable code run by the processor to perform a series of steps, said software modules further comprising,an assembler module for mapping a spatial position of each sensor in said sensor array, for monitoring deformation at each said sensor, and for calculating a sensor matrix representing spatial position and strain modes at each of said sensors in said array;a robust modal filter software module for modal coordinate transformation of said reduced sensor strain matrix into a strain-based modal matrix. 15. The system according to claim 14, wherein said software modules further comprise a finite element model (FEM) comprising a set of finite elements interconnected at a plurality of nodes. 16. The system according to claim 14, wherein said robust modal filter software module accomplishes modal coordinate transformation by projecting said sensor strain matrix from physical space to modal space to define projected modal coordinates. 17. The system according to claim 16, wherein said robust modal filter software module accomplishes modal coordinate transformation by the substeps of, projecting sensor data from said sensor array onto the nodes of said FEM using a robust regression operator to define a data matrix,reducing said data matric, andprojecting said reduced data matrix from physical space to modal space to define projected modal coordinates. 18. The system according to claim 14, further comprising a function estimator for estimating an optimal aerodynamic state from said modal coordinates. 19. The system according to claim 18, further a control module for estimating a performance optimization measure to be imparted to a control surface to maintain said optimal aerodynamic state. 20. A method for dynamic aeroelastic control of an aircraft, comprising the steps of: providing said aircraft with a sensor array;maintaining a finite element model (FEM) of said aircraft comprising a set of finite elements interconnected at a plurality of nodes,mapping a spatial position of each of said FBG sensors,monitoring deformation at each of said FBG sensors from an un-deflected position in real time;calculating a sensor strain matrix representing spatial position and strain modes at each of said FBG sensors from said deformation;reducing said sensor strain matrix;applying a robust modal filter software module for modal coordinate transformation of said reduced sensor strain matrix into a strain-based modal matrix by projecting said reduced sensor strain matrix from physical space to modal space to define projected modal coordinates;estimating an optimal aerodynamic state of said aircraft from said projected modal coordinates; andestimating a performance optimization adjustment to said modal coordinates to maintain said optimal aerodynamic state.

이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 1

Hinnant, Jr., Harris O.; Brekke, Darin W.. Systems and methods to determine navigation states of a platform. USP2017089746392.

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System and method for dynamic aeroelastic control

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System and method for dynamic aeroelastic control

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