IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0702510
(2010-02-09)
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등록번호 |
US-8393206
(2013-03-12)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Jenkins, Registered Patent Attorney, LLC, Keith L.
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인용정보 |
피인용 횟수 :
0 인용 특허 :
7 |
초록
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This invention is a ground flutter testing system without a wind tunnel, called Dry Wind Tunnel (DWT) System. The DWT system consists of a Ground Vibration Test (GVT) hardware system, a multiple input multiple output (MIMO) force controller software, and a real-time unsteady aerodynamic force genera
This invention is a ground flutter testing system without a wind tunnel, called Dry Wind Tunnel (DWT) System. The DWT system consists of a Ground Vibration Test (GVT) hardware system, a multiple input multiple output (MIMO) force controller software, and a real-time unsteady aerodynamic force generation software, that is developed from an aerodynamic reduced order model (ROM). The ground flutter test using the DWT System operates on a real structural model, therefore no scaled-down structural model, which is required by the conventional wind tunnel flutter test, is involved. Furthermore, the impact of the structural nonlinearities on the aeroelastic stability can be included automatically. Moreover, the aeroservoelastic characteristics of the aircraft can be easily measured by simply including the flight control system in-the-loop. In addition, the unsteady aerodynamics generated computationally is interference-free from the wind tunnel walls. Finally, the DWT System can be conveniently and inexpensively carried out as a post GVT test with the same hardware, only with some possible rearrangement of the shakers and the inclusion of additional sensors.
대표청구항
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1. A Dry Wind Tunnel (DWT) method that is used to predict the flutter boundaries of a structure without using a wind tunnel, said DWT method comprising the following steps: (a) providing: (i) at least one shaker, for shaking such structure, coupled to such structure at at least one shaker location;(
1. A Dry Wind Tunnel (DWT) method that is used to predict the flutter boundaries of a structure without using a wind tunnel, said DWT method comprising the following steps: (a) providing: (i) at least one shaker, for shaking such structure, coupled to such structure at at least one shaker location;(ii) at least one computer communicatively coupled to said at least one shaker and storing and operable to execute a force controller software for generating force control signals for controlling said at least one shaker;(iii) at least one displacement sensor mounted on such structure;(iv) at least one velocity sensor mounted on such structure;(v) at least one acceleration sensor mounted on such structure;(vi) at least one load cell mounted between said at least one shaker and such structure; and(vii) a data acquisition system communicatively coupled to said at least one displacement sensor, said at least one velocity sensor, said at least one acceleration sensor, said at least one load cell, and said at least one computer;(b) loading a real-time unsteady aerodynamic force generation software stored in and executable on said at least one computer that is able to compute initial real-time unsteady aerodynamic force on said structure at said at least one shaker location;(c) controlling, using said at least one computer, said at least one shaker to exert an initial impulse on such structure;(d) receiving, in said at least one computer, initial data from said at least one displacement sensor, said at least one velocity sensor, and said at least one acceleration sensor via said data acquisition system, responsive to said initial impulse;(e) computing test inputs for controlling said at least one shaker, responsive to said initial data and using said real-time unsteady aerodynamic force generation software;(f) controlling said at least one shaker, responsive to said test inputs and using said force controller software, to shake such structure;(g) measuring, via said at least one computer: i) structural response of said structure using said real-time unsteady aerodynamic force generation software and structural response data from said at least one displacement sensor, said at least one velocity sensor, and said at least one acceleration sensor; andii) said force exerted on said structure, using said force controller software and said at least one computer, responsive to data from said at least one load cell;(h) computing, using said at least one computer running said force generation software and responsive to said measured structural response as input, an unsteady aerodynamic force at said at least one shaker location;(i) applying said computed unsteady aerodynamic force to said structure through said at least one shaker;(j) controlling, using said force controller software, said applied forces to be the same as said real-time unsteady aerodynamic forces computed using said real-time unsteady aerodynamic force generation software;(k) monitoring said structural response data in real time;(l) if said structural response data indicates a decay motion, incrementally changing said inputs to create incremented test inputs to said real-time unsteady aerodynamic force generation software;(m) repeating steps (f) to (l) until said structural response data indicates a divergent motion;(n) designating a condition between said decay motion and said divergent motion of such structure as a predicted flutter boundary of such structure.
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