Spinning Spacecraft Attitude Filtering with Spin Parameters: Performance Evaluation with Real Data

Date

2017-06-07

Author

Söken, Halil Ersin
Van Der Ha, Jozef C.

Metadata

Show full item record

Item Usage Stats

183
views

0
downloads

Three-axis attitude estimation for spinning spacecraft is recently of considerable practical interest. In this scope, sequential filtering algorithms are also being studied recently. In this study, we extend our recent research for a nonlinear filtering algorithm for spinning spacecraft attitude estimation. In the filter the attitude of the spacecraft is represented using a set of spin parameters. These parameters consist of the spin-axis orientation unit vector in the inertial frame and the spin phase angle. As the system and measurement models are nonlinear an Unscented Kalman Filter (UKF) is implemented to estimate the spacecraft’s attitude. In this paper, we investigate the accuracy of the algorithm by using telemetry data gathered by the CONTOUR spacecraft in 2002. We discuss different methods for satisfying the spherical norm constraint for the spinaxis orientation unit vector terms. The filter works well and produces consistent results with those of the Tanygin-Shuster and TRIAD algorithms. Investigations on the norm constraint condition shows that unit vector normalization must be applied specifically in the presence of measurement biases.

Subject Keywords

spinning spacecraft, Attitude filtering, UKF, Spin parameters

URI

http://www.vanderha.com/Soken%20et%20al%20-%20Spinning%20Spacecraft%20Attitude%20Filtering__%20Performance%20with%20real%20Data%20(ISTS-2017-d-078).pdf
https://hdl.handle.net/11511/80480

Conference Name

26th International Symposium on Space Flight Dynamics, (09 Haziran 2017,)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Study on an Advanced Attitude Determination Algorithm for the ERG Spacecraft Söken, Halil Ersin; Asamura, Kazushi; Nakamura, Yosuke; Takashima, Takeshi (null; 2017-06-07) AXA’s Arase Spacecraft, which is formerly known as Exploration of Energization and Radiation in Geospace (ERG), was launched on 20 December 2016. The spacecraft is spin-stabilized. Its mission is exploring how relativistic electrons in the radiation belts are generated during space storms. Two on-ground attitude determination algorithms are considered for the mission: a conventional simple algorithm that inherits from old missions and an advanced algorithm that is newly designed. This paper discusses the de...
Pseudo-Linear Kalman Filter for Attitude Estimation of a Spinning Nanosatellite Söken, Halil Ersin; Kallio, Esa; Visala, Arto; Selkainaho, Jorma (null; 2017-06-09) This paper presents the pseudo-linear estimation approach to the high-rate spinning small spacecraft attitude estimation problem. The sensor suit utilised in the presented approach uses gyro, magnetometer and sun-sensor measurements. The presented estimation technique has been designed particularly for the problem of attitude determination during the Aalto-1 nanosatellite's Plasma Brake Experiment (PBE). The design of the PBE demands the satellite to be spun up to 200 deg/s for deploying the tether by the u...
Real-Time Attitude Independent Calibration of Spinning Spacecraft Magnetometers Using Quasi-Measurements Cetin, Mustafa Efe; Söken, Halil Ersin; Sakai, Shin-ichiro (2022-11-01) Magnetometers are essential sensors for attitude estimation in small spacecraft due to their robust, inexpensive, and lightweight characteristics. However, the raw measurements contain sensor errors. These errors degrade the attitude estimation accuracy. This study proposes a complete real-time attitude-independent magnetometer calibration algorithm for spinning spacecraft. The recursive algorithm aims to estimate the full error state, bias, scale factor, and non-orthogonality corrections in real-time and w...
Pseudo-Linear Approach to Nanosatellite Attitude Estimation and Magnetometer Calibration Khurshid, Osama; Selkainaho, Jorma; Kallio, Esa; Visala, Arto; Söken, Halil Ersin (2017-01-01) This paper presents the pseudo-linear estimation approach to the high-rate spinning small spacecraft attitude estimation problem. The sensor suit utilised in the presented approach uses gyro, magnetometer and sun-sensor measurements. The presented estimation technique has been designed particularly for the problem of attitude determination during the Aalto-1 nanosatellite's Plasma Brake Experiment (PBE). The design of the PBE demands the satellite to be spun up to 200 deg/s for deploying the tether by the u...
Attitude and Orbit Control of a Solar Sail Spacecraft for Responsive Operational Concept Polat, Halis Can; Tekinalp, Ozan; Department of Aerospace Engineering (2021-6-15) Utilization of the propellant-free thrust capability of Solar Sail Spacecraft (SSS) is addressed. For this purpose, an elliptical orbit with a very low perigee altitude and an apogee altitude high enough to have solar sail acceleration is proposed for Earth observation mission. In the mission part, regional observation tasks are carried out that take place in very Low Earth Orbit region. The orbit maintenance and control are handled in the high altitude regions. The baseline SSS design is accomplished and p...

Citation Formats

H. E. Söken and J. C. Van Der Ha, “Spinning Spacecraft Attitude Filtering with Spin Parameters: Performance Evaluation with Real Data,” presented at the 26th International Symposium on Space Flight Dynamics, (09 Haziran 2017,), Matsuyama, Japonya, 2017, Accessed: 00, 2021. [Online]. Available: http://www.vanderha.com/Soken%20et%20al%20-%20Spinning%20Spacecraft%20Attitude%20Filtering__%20Performance%20with%20real%20Data%20(ISTS-2017-d-078).pdf.