Attitude dynamics of the first Russian nanosatellite TNS-0

Ovchinnikov, M Y; Ilyin, A. A.; Kupriynova, N.V.; Penkov, V.I.; Selivanov, A. S.

doi:10.1016/j.actaastro.2007.01.006

Cited by 24 publications

(12 citation statements)

References 4 publications

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“…In the passive magnetic attitude control, elements that do not require any power supply, like hysteresis rods or a permanent magnet, are used [4][5][6]. In active magnetic attitude control, magnetorquers are used as actuators.…”

mentioning

confidence: 99%

“…Superscripts disturbance torque, N • m time, s argument of latitude in circular orbit, rad angle between °B(t) X °B(t) and Z 0 , rad angle between z s and Z 0 , rad rotation angle between F E frame and F h rad second Euler angle, rad coelevation angle of dipole direction in F E , rad attitude correction torque, N • m first Euler angle, rad east longitude angle of dipole direction in F E , rad third Euler angle, rad orbital rotation rate, rad/s angular velocity of F 2 with respect to F 0 , rad/s satellite angular velocity vector, rad/s desired angular velocity, parameter of the control, rad/s vector components expressed in F E frame vector components expressed in F t frame vector components expressed in F s frame vector components expressed in F 0 frame vector components expressed in F\ frame vector components expressed in F 2 frame I. Introduction S INCE the successful operation of the magnetic controllers of the early space programs [1], the magnetic attitude control strategy has turned into an attractive alternative for the attitude control of those small satellites with not-too-demanding orientation requirements [2][3][4]. This strategy significantly saves overall power, weight, cost, and complexity of the system compared to other attitude control strategies, thanks to not having any propellant or moving parts.…”

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confidence: 99%

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Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Cubas

Farrahi

Pindado

2015

Journal of Guidance, Control, and Dynamics

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In this work, a new law for magnetic control of satellites in near-polar orbits is presented. This law has been developed for the UMPSat-2 microsatellite, which has been designed and manufactured by Universidad Politecnica de Madrid, Madrid. The control law is a modification of the B-dot strategy that enables the satellite to control the rotation rate. Besides, the satellite's equilibrium state is characterized by having the rotation axis perpendicular to the orbit's plane. The control law described in the present work only needs magnetometers and magnetorquers, as sensors and actuators, respectively, to carry out a successful attitude control on the spacecraft A description of the analysis is included. Performance and applicability of the proposed method have been demonstrated by control dynamics together with Monte Carlo techniques and by implementing the control law in the UPMSat-2 mission simulator. Results show good performance in terms of acquisition and stability of the satellite rotation rate and orientation with respect to its orbit's plane.

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confidence: 99%

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confidence: 99%

Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Cubas

Farrahi

Pindado

2015

Journal of Guidance, Control, and Dynamics

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“…Several teams have published flight results of nanosatellite (1-10 kg) on-board ADSs -ASUSat1 (Friedman et al 2000), UWE-1 (Barza et al 2006), TNS-0 (Ovchinnikov et al 2007), TestBed 1 (Taraba et al 2009), CanX-2 (Sarda et al 2009), COMPASS-1 (Scholz et al 2010), ZDPS-1A (Xiang et al 2012), PRISM (Inamori et al 2013), BRITE-Constellation (Johnston-Lemke et al 2013), UWE-3 (Busch et al 2014), as well as RAX-1 and RAX-2 (Springmann and Cutler 2014).…”

Section: Introductionmentioning

confidence: 99%

Flight Results of ESTCube-1 Attitude Determination System

et al. 2016

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This paper presents the characterization and in-orbit validation of the ESTCube-1 attitude determination system (ADS). ESTCube-1 is a one-unit CubeSat built by students and launched on May 7, 2013 to a Sun-synchronous, 700 km, polar low Earth orbit. Its primary mission is to centrifugally deploy a tether as a part of the first in-orbit demonstration of electric solar wind sail (E-sail) technology. The ADS uses magnetometers, gyroscopic sensors, Sun sensors and an Unscented Kalman Filter for attitude determination. Here we share the performance of commercial off-the-shelf (COTS) sensors and results from tuning the system-re-calibration, software and Kalman Filter adjustments. We validate the system by comparing the attitude determined by the on-board ADS with the attitude determined from on-board camera images. Uncertainty budgets for both attitude determination methods are estimated. The expanded uncertainty of comparison (95% confidence level, k=2) is 1.75 • and the maximum difference between attitudes determined by both methods is 1.43 • .

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“…Photodiodes, also referred to as cosine detectors [1], are a common method of sun sensing on small spacecraft because of their simplicity and low cost (for example, [2][3][4][5][6]). Multiple photodiodes can be combined to estimate the line-of-sight vector to the sun, which is subsequently used for attitude determination or instrument pointing.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Directional Sensor Orientation with Application to Sun Sensing

Springmann

Cutler

2014

Journal of Guidance, Control, and Dynamics

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A method is presented to optimize the orientation of directional sensors and instruments in a vehicle body-fixed frame. Directional dependence is included by creating a uniformly distributed set of directions in the body-fixed frame and formulating the objective as a function of these directions. The method is demonstrated by application to photodiodes for sun sensing, for which the covariance of the sun vector estimate is derived as a function of the photodiode configuration. The measured sun vector angular accuracy is then minimized as a function of the configuration, which enables the most accurate sun sensing with the given hardware. This technique maximizes subsystem performance and provides a design method to replace traditional, iterative design approaches to sensor placement.

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Attitude dynamics of the first Russian nanosatellite TNS-0

Cited by 24 publications

References 4 publications

Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Magnetic Attitude Control for Satellites in Polar or Sun-Synchronous Orbits

Flight Results of ESTCube-1 Attitude Determination System

Optimization of Directional Sensor Orientation with Application to Sun Sensing

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