A comparative study of spacecraft attitude determination and estimation algorithms (a cost–benefit approach)

Habib, Tamer Mekky

doi:10.1016/j.ast.2012.04.005

Cited by 23 publications

(6 citation statements)

References 5 publications

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“…[2] presents a significant platform to achieve a cost-benefit approach to implement the methodologies for attitude dynamics but lacks a practical exposure. [3] shows a better understanding of attitude estimation techniques to be implemented but do not discuss about the system development.…”

Section: Introductionmentioning

confidence: 99%

Optimal power operation of low-cost MEMS-Based Attitude Determination System for Nano-satellites

Rashed

Bang

2015

2015 IEEE Aerospace Conference

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The main purpose of this paper is to demonstrate the observed significance of power utilization and its operation within designed low-cost and optimal 3-Axis MEMS-Based Attitude Determination System for Nano-satellites. Nano-satellites have been most prominent portion of space research in the recent times and several of its real-time concerns requiring precise solution by maintaining appropriate balance of size, weight, cost and several other technical parameters pose a challenge in achieving enhanced missions objectives within this technology. In order to address these concerns relating to the attitude determination aspects of Nano-satellites, intensive research has been carried out through several statistical and experimental analyses to obtain a highly efficient, optimal and cost-effective attitude determination system specific to Nano-satellites. During the study and experimentation, many critical aspects have been significantly noted and unique conclusions have been made which are achieved by several creative and logical strategies, techniques and attitude dynamics. This paper will mainly focus on implementing efficient configurations to attain minimum power consumption especially using MEMS sensors acquired through practical scrutiny. A complete critical analysis is detailed after emphasizing the results which give substantial direction to make superior considerate and well-balanced applicability of low-cost sensors under severe space environment.

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Section: Introductionmentioning

confidence: 99%

Optimal power operation of low-cost MEMS-Based Attitude Determination System for Nano-satellites

Rashed

Bang

2015

2015 IEEE Aerospace Conference

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“…where: E is the expectation, k X is the true plant state vector, and ^k X is the estimated state vector [1]. The discrete Kalman filter structure given in [17] is based on:…”

Section: Kalman Filter Designmentioning

confidence: 99%

“…The estimation algorithm combines measurements in different ways to attain the required attitude estimation accuracy. In comparison with attitude determination algorithms (such as TRIAD and the Q-method), attitude estimation methods (such as the Kalman filter) are able to work with measurements of even a single attitude sensor which is an important advantage [1]. Over 50 years, the Kalman filter is still one of the most widely used data fusion systems.…”

Section: Introductionmentioning

confidence: 99%

Three-Axis Attitude Estimation Of Satellite Through Only Two-Axis Magnetometer Observations Using LKF Algorithm

Mehrjardi¹,

Sanusi²,

Ali³

2015

Metrology and Measurement Systems

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Estimation of satellite three-axis attitude using only one sensor data presents an interesting estimation problem. A flexible and mathematically effective filter for solving the satellite three-axis attitude estimation problem using two-axis magnetometer would be a challenging option for space missions which are suffering from other attitude sensors failure. Mostly, magnetometers are employed with other attitude sensors to resolve attitude estimation. However, by designing a computationally efficient discrete Kalman filter, full attitude estimation can profit by only two-axis magnetometer observations. The method suggested solves the problem of satellite attitude estimation using linear Kalman filter (LKF). Firstly, all models are generated and then the designed scenario is developed and evaluated with simulation results. The filter can achieve 10e-3 degree attitude accuracy or better on all three axes.

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“…Thus it is possible to obtain attitude estimation that is better than single sensor observation accuracy. Or in other words, to fulfill the same attitude determination accuracy requirement of a system, it presumably decreases the demand in performance indices of each sensor, remarkably reducing the total budget of the attitude determination system [4]. However, the characteristics of different sensors differ greatly.…”

Section: Introductionmentioning

confidence: 99%

Precise attitude determination strategy for spacecraft based on information fusion of attitude sensors: Gyros/GPS/Star-sensor

Mao¹,

Du²,

Fang³

2013

International Journal of Aeronautical and Space Sciences

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The rigorous requirements of modern spacecraft missions necessitate a precise attitude determination strategy. This paper mainly researches that, based on three space-borne attitude sensors: 3-axis rate gyros, 3-antenna GPS receiver and starsensor. To obtain global attitude estimation after an information fusion process, a feedback-involved Federated Kalman Filter (FKF), consisting of two subsystem Kalman filters (Gyros/GPS and Gyros/Star-sensor), is established. In these filters, the state equation is implemented according to the spacecraft's kinematic attitude model, while the residual error models of GPS and star-sensor observed attitude are utilized, to establish two observation equations, respectively. Taking the sensors' different update rates into account, these two subsystem filters are conducted under a variable step size state prediction method. To improve the fault tolerant capacity of the attitude determination system, this paper designs malfunction warning factors, based on the principle of residual verification. Mathematical simulation indicates that the information fusion strategy overwhelms the disadvantages of each sensor, acquiring global attitude estimation with precision at a 2-arcsecs level. Although a subsystem encounters malfunction, FKF still reaches precise and stable accuracy. In this process, malfunction warning factors advice malfunctions correctly and effectively

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A comparative study of spacecraft attitude determination and estimation algorithms (a cost–benefit approach)

Cited by 23 publications

References 5 publications

Optimal power operation of low-cost MEMS-Based Attitude Determination System for Nano-satellites

Optimal power operation of low-cost MEMS-Based Attitude Determination System for Nano-satellites

Three-Axis Attitude Estimation Of Satellite Through Only Two-Axis Magnetometer Observations Using LKF Algorithm

Precise attitude determination strategy for spacecraft based on information fusion of attitude sensors: Gyros/GPS/Star-sensor

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