Use of accelerometers for measurement of pitch and bank angles in an aerodynamic experiment

Gorbachev, N. A.; Gorbushin, A. R.; Krapivina, E. A.; Sudakova, Iraida Alekseevna

doi:10.1007/s11018-012-0054-4

Cited by 14 publications

(11 citation statements)

References 2 publications

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“…Q-Flex or similar accelerometers have been implemented at other facilities around the globe for AoA measurements. 5,6 NTF typically conducts performance testing of transport aircraft due to the high Reynolds capability that demands high AoA accuracies. It is widely accepted that for performance wind-tunnel test require AoA measurement accuracy be on the order of 0.01°to measure a 0.0001 change in the drag coefficient.…”

Section: Introductionmentioning

confidence: 99%

Cryogenic Angle Measurement at NASA Langley

Toro

Parker

2019

AIAA Scitech 2019 Forum

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NASA's National Transonic Facility is one of the few cryogenic wind-tunnel facilities in the world, where tunnel conditions may reach -250°F. Model angle of attack (AoA) at NTF is typically measured by an on-board accelerometer package that is exposed to the cryogenic tunnel conditions. These NTF AoA packages house two Q-Flex accelerometers in a compact heated environment in order to maintain constant temperature of the sensors for stability. Recently, drift in sensor output was observed in one of the NTF AoA packages. The drift is correlated with the AoA package temperature and cryogenic soak time. This paper studies the temperature and time dependent behavior of the NTF AoA packages, and reviews their design and calibration. Recommended improvements to the AoA packages are made to improve the stability of the model angle of attack measurements at cryogenic conditions.

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Section: Introductionmentioning

confidence: 99%

Cryogenic Angle Measurement at NASA Langley

Toro

Parker

2019

AIAA Scitech 2019 Forum

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“…As aircraft model sweeps to big angle-of-attack, flow separation appears over the wings and buffeting [2] causes a kind of low-frequency and big-amplitude vibration at the first resonant frequency [3], which results in poor balance data quality in pitch plane and yaw plane [4]. As a result, the balance works disorderly and the test safety will suffer the serious threat if the test is not stopped immediately [5,6]. Therefore, the vibration control methods and systems to ensure the tests data quality and the safety of wind tunnel tests have paid more attention to such wind tunnel tests condition.…”

Section: Introductionmentioning

confidence: 99%

Multidimensional Vibration Suppression Method with Piezoelectric Control for Wind Tunnel Models

Zhou

Liu

Tang

et al. 2019

Sensors

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In wind tunnel tests, the low-frequency and large-amplitude vibration of the cantilever sting result in poor test data in pitch plane and yaw plane, more seriously, even threatens the safety of wind tunnel tests. To ensure the test data quality, a multidimensional vibration suppression method is proposed to withstand the vibration from any direction, which is based on a system with stackable piezoelectric actuators and velocity feedback employing accelerometers. Firstly, the motion equation of the cantilever sting system is obtained by Hamilton’s principle with the assumed mode method. Then, the multidimensional active control mechanism is qualitatively analyzed and a negative velocity feedback control algorithm combined with a root mean square (RMS) evaluation method is introduced to realize active mass and active damping effect, meanwhile, a weight modification method is performed to determine the sequence number of the stacked piezoelectric actuators and the weight of control voltages in real time. Finally, a multidimensional vibration suppression system was established and verification experiments were carried out in lab and a transonic wind tunnel. The results of lab experiments indicate that the damping ratio of the system is improved more than 4.3 times and the spectrum analyses show reductions of more than 23 dB. In addition, wind tunnel test results have shown that for the working conditions (α = −4~10° with γ = 0° or α = −4~10° with γ = 45°) respectively at 0.6 Ma and 0.7 Ma, the remainder vibration is less than 1.53 g, which proves that the multidimensional vibration suppression method has the ability to resist vibration from any direction to ensure the smooth process of wind tunnel tests.

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“…When recalculating the normal and longitudinal components of the force from the measurement coordinate system to the velocity frame (lift and drag), additional errors related to the accuracy of measurements of the pitch, roll and yaw angles are introduced into the test results. In [3] it was shown that for the cruise mode of fl ight of the main aircraft (lift coeffi cient C Ya ≈ 0.5) an error of 0.005° in determining the pitch angle leads to an error ΔC Хa = 5 •10 -5 . This means that the error Δθ of measuring the pitch angle in aerodynamic studies should not exceed 0.005-0.01°.…”

mentioning

confidence: 99%

“…In [3], a one-component mathematical model of an accelerometer was developed as a means for measuring the pitch or roll angle and error estimates were obtained.…”

mentioning

confidence: 99%

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A Three-Component Mathematical Model of a Single-Axis Accelerometer for Measuring Pitch and Roll Angles

Gorbushin

Kolesnikov

2019

Meas Tech

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We consider measurements of pitch and roll angles using compensation pendulum accelerometers with closed feedback. A three-component mathematical model of a single-axis accelerometer has been developed as a means of measuring pitch and roll angles. The model takes into account the effect of acceleration applied perpendicular to the axis of sensitivity of the accelerometer. The error of the mathematical model is investigated. Methods for accelerometer calibration and a method for taking into account the effect of temperature on its readings using a three-component mathematical model are proposed. The mathematical model is verifi ed using accelerometer calibration results.

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Use of accelerometers for measurement of pitch and bank angles in an aerodynamic experiment

Cited by 14 publications

References 2 publications

Cryogenic Angle Measurement at NASA Langley

Cryogenic Angle Measurement at NASA Langley

Multidimensional Vibration Suppression Method with Piezoelectric Control for Wind Tunnel Models

A Three-Component Mathematical Model of a Single-Axis Accelerometer for Measuring Pitch and Roll Angles

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