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2 edition of Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices found in the catalog.

Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices

Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices

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  • 2 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Attitude (Inclination).,
  • Attitude indicators.,
  • Dynamic response.,
  • Inertial platforms.,
  • Optical measurement.,
  • Wind tunnel models.,
  • Wind tunnel tests.

  • Edition Notes

    StatementR.D. Buehrle.
    SeriesNASA technical memorandum -- 109182.
    ContributionsBuehrle, Ralph., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15411348M

      1. Introduction. Recent technological developments in the automotive industry, telecommunications and electronics have enabled a major evolution in the possibilities of measuring and monitoring human movement [].One of the main current interests is analyzing human motion in fields such as sports [] and health [].From the point of view of the field of Cited by: Inertial Frequency Response Test Methods The most direct approach for testing frequency response in a gyroscope is with an inertial rate table, which is capable of introducing the appropriate frequency content. Rate tables typically include a programmable servo motor and an optical encoder that verifies programmed rotation on the motor shaft.

    shaking table test of offshore platform model scaled down an actual one. Fiber Bragg grating (FBG) is a promising measurement technology for its superior ability of explosion proof, immunity to electromagnetic interference and high accuracy. Some FBG sensors and strain gauges were used to monitor the dynamic response of offshore platform model.   The potential of inertial measurement units (IMUs) for ergonomics applications appears promising. However, previous IMUs validation studies have been incomplete regarding aspects of joints analysed, complexity of movements and duration of by:

    Dynamic Response of NASA Rotor Test Apparatus and Sikorsky S Hub Mounted in the by Foot Wind Tunnel RANDALL L. PETERSON AND MUHAMMED S. HOQUE* Ames Research Center Abstract A shake test was conducted in the by Foot Wind Tunnel at NASA Ames Research Center, using the NASA Ames Rotor Test Apparatus (RTA) and the File Size: 1MB. Dynamic analysis and motion measurement of ski turns using inertial and force sensors biomechanical analysis of ski racing using inertial measurement units and GPS receiver [3] have been is defined as the 3D link rigid body model consists of .


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Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices Download PDF EPUB FB2

Schematic of wind-tunnel model system. Effect of vibration on inertial model attitude measurement. Sting bending in yaw plane, Hz vibration mode.

Model yawing on balance, Hz vibration mode. Results are presented for an experimental study of the response of inertial and optical wind-tunnel model attitude measurement systems in a wind-off simulated dynamic environment. Get this from a library. Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices.

[Ralph D Buehrle; Langley Research Center.;]. Results are presented for an experimental study of the response of inertial and optical wind-tunnel model attitude measurement systems in a wind-off simulated dynamic environment. This study is part of an ongoing activity at the NASA Langley Research Center to develop high accuracy, advanced model attitude measurement systems that can be used in a dynamic wind-tunnel environment.

The research investigates the effect of wind tunnel model system dynamics on measured aerodynamic data. During wind tunnel tests designed to obtain lift and drag data, the required aerodynamic measurements are the steady-state balance forces and moments, pressures, and model attitude.

Analysis of the dynamic response of the car suspension based on inertial MEMS sensors. ROSEN MILETIEV. 1, VLADIMIR BASHEV1, IVAYLO SIMEONOV2, EMIL IONTCHEV3 1 Technical University of Sofia, Faculty of Telecommunication. 2 Technical University of Sofia, Faculty of Computer Sciences.

3 Higher School of Transport “ Size: 1MB. Test results are presented in this paper showing the performance of the integrated MEMS GPS/inertial navigation system.

Data is provided showing the position, velocity and attitude accuracy when operating with GPS aiding and also forFile Size: KB. The Measurement Covariance Matrix represents the noise level of the accelerometer and is often choose as constant matrix Hypothesis: The lack on the sensor model for the effects of external acceleration acting on the body can be compensated with a dynamic choice of the Measurement Covariance Matrix () 1 k T K k k k k P k H k R Decem The marks on the custom made testing apparatuses were used as the gold standard comparison for the sensor output.

Dynamic testing assessed the sensor’s ability to obtain angular velocity measures for the manufacturer’s specified range. The angular velocity of a custom made dynamic testing device was compared to the sensor output.

Cited by: 4. Measurement system Motion measurement system The motion measurement system shows in Fig. This system that consists of three gyro sensors (Analog Devices, ADIS) and a 3-axis accelerometer (Hitachi Metals, H30CD) measures 3-axis angular velocity and 3-axis acceleration.

The size of this system is 45 65 25mm, and the weight is 60g Cited by: 9. The preceding Engineering Model was subjected to tests at the DFVLR, on an air bearing platform and to fixed base tests. Dynamic response analysis was utilized in order to find a linear dynamic model describing the dynamics of the wheel and the interaction with the air.

Inertial-magnetic measurement units are inexpensive sensors, widely used in electronic systems (smartphones, GPS, micro-UAV, etc).

However the. the output of the model attitude inertial sensor in the presence of model dynamics during on-line wind tunnel operation is proposed. INTRODUCTION Measurement of model attitude or angle of attack (AOA) in modern wind tunnels is based on the use of high accuracy servo accelerometers (see ref.

The tunnel flow is calibrated with respect to the local gravity vector, while the model attitude sensor. ACTA AERONAUTICAET ASTRONAUTICA SINICA ››Vol. 37 ›› Issue (8): doi: /S • Numerical Simulation and Wind Tunnel Test Technologies • Previous Articles Next Articles A model attitude control and measurement technique for improving quality of wind tunnel dynamic test data.

Inertial measurement with trapped particles: A microdynamical system E. Rehmi Post,a George A. Popescu, and Neil Gershenfeld Center for Bits and Atoms, Massachusetts Institute of Technology, 20 Ames Street, Cambridge, tiple distinct devices whose dynamic response is. Inertial measurement units (IMUs) are electronic devices used for detection of the current object orientation.

Usually they measure changes in object’s rotation and acceleration. As a measurement devices, they must fulfill a set of requirements e.g. smallest possible size and weight, configurable filtered output by: 8.

Model attitude The measurement of model attitude is a critical measurement in any wind tunnel test'. The pitch angle of a balance that rotates with the model must be known in order to properly resolve balance force components.

The predominant instrument used for model attitude is an inertial sensor, the servo accelerometer. However, dynamic response problems encounteredCited by: The aim of this study was to compare kinematic measurements by an IMU attached on the lower back to a MOCAP system with optical markers placed on anatomical landmarks during gait, sit–stand transfers and step-up transfers, relevant for the assessment of physical function in patients with hip or knee OA [17], [18].Cited by: The inertial sensor, also known as the inertial navigation system (INS), uses an accelerometer and gyro to determine spacecraft attitude in relation to the inertial system.

The accelerometer is used to test the motion acceleration of the carrier, which is then used to calculate the real-time location of the carrier.

Abstract. To improve the output accuracy of strap-down inertial measurement unit which is in compound dynamic environment of missile which has a high acceleration, strong impact, and high vibration, an adaptive damping method of taking the magneto rheological elastomer as the vibration damper is : Heng Zhang, Xiaoting Rui, Fufeng Yang, Gangli Chen.

produced devices, the accuracy have been significantly improved and it is now possible to find many applications that previously were not available for mobile devices.

One of these applications is to support the GPS satellite navigation using a set of inertial navigation sensors, called inertial measurement unit (IMU). AfterCited by: 2.A navigation algorithm is proposed to increase the inertial navigation performance of a ground vehicle using magnetic measurements and dynamic constraints.

The navigation solutions are estimated based on inertial measurements such as acceleration and angular velocity measurements. To improve the inertial navigation performance, a three-axis magnetometer is Cited by: 7.

Inertial Measurement Units. The IMUs consist of an all-attitude, four-gimbal, inertially stabilized platform. They provide inertial attitude and velocity data to the GN&C; software functions.

Navigation software uses the processed IMU velocity and attitude data to propagate the orbiter state vector.