Determination of Foton M-2 satellite attitude motion by the data of microacceleration measurements

AbstractThe ESA space astrometry mission Gaia, due for launch in early 2012, will in addition to its huge output of fundamental astrometric and astrophysical data also provide stringent tests of general relativity. In this paper we present an updated analysis of Gaia's capacity to measure the PPN parameter γ as part of its core astrometric solution. The analysis is based on small-scale astrometric solutions taking into account the simultaneous determination of stellar astrometric parameters and the satellite attitude. In particular, the statistical correlation between PPN γ and the stellar parallaxes is considered. Extrapolating the results to a full-scale solution using some 100 million stars, we find that PPN γ could be obtained to about 10−6, which is significantly better than today's best estimate from the Cassini mission of 2 × 10−5.

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Attitude Behavior of a Variable Mass Cylinder

Journal of Applied Mechanics ◽

10.1115/1.2896025 ◽

1995 ◽

Vol 62 (4) ◽

pp. 935-940 ◽

Cited By ~ 12

Author(s):

F. O. Eke ◽

Song-Min Wang

Keyword(s):

Mass Loss ◽

Variable Mass ◽

Cylindrical Body ◽

Rigid Bodies ◽

Transverse Motion ◽

Attitude Motion ◽

Key Factors ◽

Great Contrast ◽

Attitude Behavior

This paper examines the attitude motion of a cylindrical body with mass loss. It is found that mass variation can have a substantial influence on the behavior of such a system. Specifically, the initial dimensions as well as the manner in which mass loss affects system inertia are found to be key factors in the determination of the characteristics of the lateral motion of the system. In great contrast to the attitude behavior of spinning rigid bodies, oblate variable mass cylinders exhibit divergent transverse attitude motion, while the transverse motion of prolate variable mass cylinders is found to be bounded in general.

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Transient Attitude Motion of TNS-0#2 Nanosatellite during Atmosphere Re-Entry

Applied Sciences ◽

10.3390/app11156784 ◽

2021 ◽

Vol 11 (15) ◽

pp. 6784

Author(s):

Danil Ivanov ◽

Dmitry Roldugin ◽

Stepan Tkachev ◽

Yaroslav Mashtakov ◽

Sergey Shestakov ◽

...

Keyword(s):

Permanent Magnet ◽

Data Transmission ◽

Geomagnetic Field ◽

Attitude Motion ◽

Satellite Motion ◽

Motion Reconstruction ◽

Satellite Attitude ◽

Magnetic Stabilization ◽

Tumbling Motion ◽

Magnet Axis

Attitude motion reconstruction of the Technological NanoSatellite TNS-0 #2 during the last month of its mission is presented in the paper. The satellite was designed to test the performance of the data transmission via the Globalstar communication system. This system successfully provided telemetry (even during its atmosphere re-entry) up to an altitude of 156 km. Satellite attitude data for this phase is analyzed in the paper. The nominal satellite attitude represents its passive stabilization along a geomagnetic field induction vector. The satellite was equipped with a permanent magnet and hysteresis dampers. The permanent magnet axis tracked the local geomagnetic field direction with an accuracy of about 15 degrees for almost two years of the mission. Rapid altitude decay during the last month of operation resulted in the transition from the magnetic stabilization to the aerodynamic stabilization of the satellite. The details of the initial tumbling motion after the launch, magnetic stabilization, transition phase prior to the aerodynamic stabilization, and subsequent satellite motion in the aerodynamic stabilization mode are presented.

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An implementation of optimal control methods (LQI, LQG, LTR) for geostationary satellite attitude control

International Journal of Electrical and Computer Engineering (IJECE) ◽

10.11591/ijece.v9i6.pp4728-4737 ◽

2019 ◽

Vol 9 (6) ◽

pp. 4728

Author(s):

Farid Djaballah ◽

M. A. Si Mohammed ◽

Nabil Boughanmi

Keyword(s):

Numerical Simulation ◽

Dynamic Model ◽

Attitude Control ◽

Geostationary Satellite ◽

Attitude Motion ◽

Linear Quadratic ◽

Integer Order ◽

Satellite Attitude ◽

Satellite Attitude Control ◽

Attitude Controller

This paper investigates a new strategy for geostationary satellite attitude control using Linear Quadratic Gaussian (LQG), Loop Transfer Recovery (LTR), and Linear Quadratic Integral (LQI) control techniques. The sub-system satellite attitude determination and control of a geostationary satellite in the presence of external disturbances, the dynamic model of sub-satellite motion is firstly established by Euler equations. During the flight mission at 35000 Km attitude, the stability characteristics of attitude motion are analyzed with a large margin error of pointing, then a height performance-order LQI, LQG and LTR attitude controller are proposed to achieve stable control of the sub-satellite attitude, which dynamic model is linearized by using feedback linearization method. Finally, validity of the LTR order controller and the advantages over an integer order controller are examined by numerical simulation. Comparing with the corresponding integer order controller (LQI, LQG), numerical simulation results indicate that the proposed sub-satellite attitude controller based on LTR order can not only stabilize the sub-satellite attitude, but also respond faster with smaller overshoot.

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