Flight results of a low-cost attitude determination system

Springmann, John C.; Cutler, James

doi:10.1016/j.actaastro.2014.02.026

Cited by 45 publications

(24 citation statements)

References 22 publications

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“…Inertial sensors are robust to GNSS signal interruption and very precise over short time frames, which enables a reliable cycle slip correction, but low-cost inertial sensors suffer from a substantial drift. The authors propose a tightly coupled position and attitude determination method for two low-cost GNSS receivers, a gyroscope and an accelerometer, and obtain a heading with an accuracy of 0.25°/baseline length (m) and an absolute position with an accuracy of 1 m. Similar developments may be found within space vehicles, for example, in [16]. In [17], the use of an inertial navigation system (INS) and a multiple GPS antenna system for attitude determination of an off-road vehicle is developed, and in [18], attitude determination using the GPS carrier phase has been applied successfully to aircrafts in experiments by a number of researchers.…”

Section: Introductionmentioning

confidence: 83%

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Celis

Cadarso

2018

International Journal of Aerospace Engineering

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Aircraft and spacecraft navigation precision is dependent on the measurement system for position and attitude determination. Rotation of an aircraft can be determined measuring two vectors in two different reference systems. Velocity vector can be determined in the inertial reference frame from a GNSS-based sensor and by integrating the acceleration measurements in the body reference frame. Estimating gravity vector in both reference frames, and combining with velocity vector, determines rotation of the body. A new approach for gravity vector estimations is presented and employed in an attitude determination algorithm. Nonlinear simulations demonstrate that using directly the positioning and velocity outputs of GNSS sensors and strap-down accelerometers, aircraft attitude determination is precise, especially in ballistic projectiles, to substitute precise attitude determination devices, usually expensive and forced to bear high solicitations as for instance G forces.

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Section: Introductionmentioning

confidence: 83%

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Celis

Cadarso

2018

International Journal of Aerospace Engineering

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“…The sensors must be calibrated before using their measurement results as an input to the SaUKF. As discussed in several papers [1,2,18] particularly for the magnetometers, such a calibration should be performed on-orbit for nanosatellite missions. In addition, as it is clearly demonstrated by the simulation results, the estimation performance of the SaUKF degrades during the eclipse period and the UKF based on the results of nonlinear measurements provides more accurate estimations.…”

Section: Simulations For Nanosatellitementioning

confidence: 99%

“…Sun sensors and magnetometers are common attitude sensors for nanosatellite missions; they are cheap, simple, light and available as commercial of-the-shelf equipment [1,2]. However, the overall achievable attitude determination accuracy is limited with these sensors mainly as a result of their inherent limitations and unavailability of the Sun sensor measurements when the satellite is in the eclipse.…”

Section: Introductionmentioning

confidence: 99%

“…A basic solution is using a Kalman filtering algorithm for integrating the measurements under the propagation model of the satellite dynamics and estimating the satellite attitude possibly along with the sensor biases. For example, in [2] two filtering algorithms are proposed, both based on the multiplicative Extended Kalman Filter (EKF). The first algorithm is used for estimation of attitude quaternions, gyro biases and Sun sensor calibration parameters, whereas the second one estimates only the quaternions and gyro biases excluding the Sun sensor calibration parameters.…”

Section: Introductionmentioning

confidence: 99%

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Nanosatellite Attitude Estimation from Vector Measurements Using SVD-Aided UKF Algorithm

Çilden

Söken

Hajiyev

2017

Metrology and Measurement Systems

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The integrated Singular Value Decomposition (SVD) and Unscented Kalman Filter (UKF) method can recursively estimate the attitude and attitude rates of a nanosatellite. At first, Wahba's loss function is minimized using the SVD and the optimal attitude angles are determined on the basis of the magnetometer and Sun sensor measurements. Then, the UKF makes use of the SVD's attitude estimates as measurement results and provides more accurate attitude information as well as the attitude rate estimates. The elements of "Rotation angle error covariance matrix" calculated for the SVD estimations are used in the UKF as the measurement noise covariance values. The algorithm is compared with the SVD and UKF only methods for estimating the attitude from vector measurements. Possible algorithm switching ideas are discussed especially for the eclipse period, when the Sun sensor measurements are not available.

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“…In general, the main goal of the calibration methodologies is to improve sensor precision [1][2][3]. The calibration is particularly important if high precision of the miniature low-cost sensors is required.…”

Section: Introductionmentioning

confidence: 99%

Calibration of Magnetometer for Small Satellites Using Neural Network

et al. 2017

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The article presents the scalar calibration method that uses a neural network for the determination of parameters of the inverse model of the vector magnetometer. Utilization of the one layered, feed-forward neural network with the back propagation algorithm has suppressed the systematic errors of the vector magnetometers, namely the multiplicative, additive, orthogonality and linearity errors. Methodology shown in the article was designed and used for a pre-flight calibration of the magnetometer used in the first Slovak satellite skCUBE, where the magnetometer performs stabilization and navigation tasks. The experiment was performed in a 3D Helmholtz coil system, where the Earth magnetic field was suppressed and at the same time the stimulation field was created. Suppression of the Earth magnetic field was achieved by special positioning of the satellite. Honeywell HMC 5883L was used for the verification of the methodology.

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Flight results of a low-cost attitude determination system

Cited by 45 publications

References 22 publications

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Attitude Determination Algorithms through Accelerometers, GNSS Sensors, and Gravity Vector Estimator

Nanosatellite Attitude Estimation from Vector Measurements Using SVD-Aided UKF Algorithm

Calibration of Magnetometer for Small Satellites Using Neural Network

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