Development of a Pneumatic High-Angle-of-Attack Flush Airdata Sensing (HI-FADS) System

Whitmore, Stephen A.; Moes, Timothy R.; Leondes, Cornelius T.

doi:10.1016/b978-0-12-012752-8.50016-7

Cited by 16 publications

(15 citation statements)

References 4 publications

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“…For instance, one could drill orifice arrays in the regions of interests and pneumatically link them to conventional multi-point pressure scanners [3,11]. Alternatively, one could think of sensors based on silicon micro-electromechanical systems (MEMS) and/or hybrid technologies [12].…”

Section: Sensing Technologiesmentioning

confidence: 99%

“…Note that the possibility of obtaining a closed-form F from physical models is generally hindered by the complications of fluid-dynamics. For instance, in [3] it was possible to rely on analytical models only thanks to the usage of particularly simple aerodynamic shapes. In this paper, F is approximated by using results from simulation and experimental data.…”

Section: System Calibrationmentioning

confidence: 99%

“…3 The signal processing aspects involve the definition of algorithms to properly consume this data and return high-level flight parameters including the free-stream air speed (V ∞ ) and the angle of attack (α). In general terms, one can think of a vector Φ = (V ∞ , α) T of quantities of interest with the provision of extending it to include the side-slip angle β too.…”

Section: Theory Of Operationmentioning

confidence: 99%

“…For instance, multi-hole/multifunctional probes have been introduced to infer a plurality of flight parameters at once [1,2]; techniques have been introduced to get free-stream parameters from measurement made on the air vehicle skin [3]; replicated systems have been introduced to enhance availability [4].…”

Section: Introductionmentioning

confidence: 99%

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Experiments on aircraft flight parameter detection by on-skin sensors

Callegari

Zagnoni²,

Golfarelli

et al. 2006

Sensors and Actuators A: Physical

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Air speed and flight attitude angles are fundamental parameters for manual of automatic control of flying bodies. Conventional measurement methods rely on probes (e.g. Pitot tubes or vanes) having a one-to-one correspondence with the physical quantities of interest and requiring specific placements. Here, a novel measurement approach is proposed, relying on indirect measurement and on a plurality of pressure readings made by thin capacitive sensors directly placed on the aircraft skin. A redundant number of probes relaxes the accuracy requirements posed on the individual units and helps achieving fault detection or fault tolerance. A strategy for efficiently processing/combining sensor data is herein presented together with an error propagation analysis, and experimental data.

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Section: Sensing Technologiesmentioning

confidence: 99%

Section: System Calibrationmentioning

confidence: 99%

Section: Theory Of Operationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Experiments on aircraft flight parameter detection by on-skin sensors

Callegari

Zagnoni²,

Golfarelli

et al. 2006

Sensors and Actuators A: Physical

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“…FADS (Flush Air Data System) depends on the pressure sensor array measurement of aircraft surface pressure distribution indirectly obtains dynamic pressure, total pressure, angle of attack, side slip angle and other atmospheric data through a specific algorithm. It can overcome the adverse effects the probe type pitot tube bring to hypersonic vehicle, stealth performance, high angle of attack maneuver, space layout size, and reduce the extra installation, use, maintenance costs, it also has the characteristics of high precision, wide application range etc.. FADS has been successfully applied to the X-15, F/A-18, X-31, X-33, X-34, X-38, X-43A and space shuttle and other types of aircraft [1][2][3][4][5][6][7][8][9][10][11],USA FADS development was shown in fig2. Japan in the last century 90's, carried out the research in FADS by the HYFLEX .…”

mentioning

confidence: 99%

Study on Algorithms of Flush Air Data Sensing System for HypersonicVehicle

Chen

et al. 2015

Procedia Engineering

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In this paper, according to the typical hypersonic vehicle,a study of flush air data sensing system using BP neural network algorithm were carried out. The independent research and development of CACFD software for solving the Euler equations, calculation of vehicle head pressure distribution as the neural network training input, the corresponding flow conditions, such as the static pressure, the Ma number, angle of attack and side slip angle as the target samples to train the neural network, set up FADS algorithm based on BP neural network and testing . Studies showed that the FADS algorithm based on neural network technique is robust and has good precision, strong real-time, is a very effective algorithm. Research results had showed that : in the sample number range, the precision of FADS is increasing with the the number of samples increasing ; the average error of FADS algorithm decreases with increase of pressure measuring point of layout combinations; contains large cone angle position measurement points, points than only the small cone angle measuring point combination results average error .To remove vertex pressure point, had little effect on the precision of algorithm, the FADS algorithm generalization performance is very stable with 1% pressure measurement error

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FADS based aerodynamic parameters estimation for mars entry considering fault detection and tolerance

Jiang

et al. 2021

Acta Astronautica

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Development of a Pneumatic High-Angle-of-Attack Flush Airdata Sensing (HI-FADS) System

Cited by 16 publications

References 4 publications

Experiments on aircraft flight parameter detection by on-skin sensors

Experiments on aircraft flight parameter detection by on-skin sensors

Study on Algorithms of Flush Air Data Sensing System for HypersonicVehicle

FADS based aerodynamic parameters estimation for mars entry considering fault detection and tolerance

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