&lt;title&gt;Air-bearing-based satellite attitude dynamics simulator for control software research and development&lt;/title&gt;

Agrawal, Brij N.; Rasmussen, Richard E.

doi:10.1117/12.438072

Cited by 23 publications

(13 citation statements)

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“…In order to use the Kalman filter, it is necessary to have the mathematical model of the body motion. Let us rewrite motion equation of the mock up (2.1) as where q is the vector part of the quaternion of transition from the inertial frame to the frame of the satellite, is the unit vector of direction of the local normal in the frame of the satellite, is ( ) 3 3 , where E is the identity matrix, W is the skew symmetric matrix introduced in (2.1), is the tensor of inertia of the mock up, is the matrix of the gravitational torque and are the components of the vector . Let us construct the Kalman filter using the measurements of the magnetometer and the solar sensor.…”

Section: Algorithm For Attitude Determination Based On Kalman Filtermentioning

confidence: 99%

“…It consisted of three pairs of orthogonal Helmholtz coils. The simulator of triaxial motion and control of a satellite [3] developed in 1995 at the Naval Post Graduate School (USNA), Optical Relay Spacecraft Laboratory (USA) represents a platform on an aerodynamic suspension with three flywheels, motors operating on compressed gas, a gyroscope, a magnetometer, and an optical attitude sensor. The platform mass is about 200 kg, the rotation in the horizontal plane can make 360°, and the rotation with respect to the two other angles is ±45°.…”

Section: Introductionmentioning

confidence: 99%

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Testing of attitude control algorithms for microsatellite “Chibis-M” at laboratory facility

Ivanov

Karpenko

Ovchinnikov

et al. 2012

J. Comput. Syst. Sci. Int.

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A laboratory facility developed at the Engineering Technological Center "Scan Ex" for testing algorithms for determination of attitude and stabilization of the attitude system of the satellite "Chibis M" is described. The results of experiments on damping initial angular rotation, using mag netorquers, stabilization of the mock up using flywheels, and flywheel unloading are analyzed. The operation of the algorithm for determination of the mock up attitude is studied; the main character istics of this algorithm are the accuracy of the state vector estimation and the time of convergence.(LABSat) were created for the laboratory workshop; each of these mock ups is designated for experiments with a particular system [4]. There are mock ups with magnetic stabilization system, flywheel stabilization system, control system of micro jet engines for investigation of attitude control systems.A simulation system consisting of two mock ups [5] was developed at the Virginia Polytechnic Univer sity (USA) based on commercial elements of aerodynamic suspension manufactured by Space Electronics Inc. (Germany). The first, smaller, mock up (Whorl I) is a platform with a mass of 135 kg and three degrees of freedom: rotation in the horizontal plane is not bounded, deviations with respect to inclination are bounded by ±5°. The mock up is equipped by three flywheels, a triaxial accelerometer, and a biaxial inclination sensor, a center of mass balancing system; the power is supplied from accumulator batteries. The large mock up (Whorl II) developed later [6,7] than Whorl I carries a 169 kg platform. The rotation in the horizontal plane is not bounded, the maximum possible deviation with respect to the inclination is ±30°. The hardware composition of the platform practically does not differ from Whorl I. The system similar to Whorl II is also available at the Michigan University (USA) [8].It should be noted that laboratory facilities for simulation of angular motion of a satellite with magne torquers were created in Technion, Israel, for testing control algorithms for the microsatellite TechSat, and the laboratory facility at the System Innovation Ltd., Great Britain. A laboratory facility at the Feder ico II University in Naples (Italy) Space Magnetic Field Simulator (SMAFIS) was created specially for testing the magnetic attitude system of the microsatellite SMART [9]. It is designated for calibration of magnetorquers and magnetometer, functional development of the magnetic stabilization system, investi gation of the device interaction with the magnetic field. The motion about the center of mass was ensured by the system with an air suspension MADS (Microsatellite Attitude Dynamics Simulator).A platform for testing nanosatellites was developed at the Delft University of Technology (Nether lands) [10]. The laboratory facility consists of Helmholtz coils creating a given magnetic field; this labo ratory facility enables to test active and passive attitude control systems of nanosatellites, in particular, cubesats (satellites with a size o...

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Section: Algorithm For Attitude Determination Based On Kalman Filtermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Testing of attitude control algorithms for microsatellite “Chibis-M” at laboratory facility

Ivanov

Karpenko

Ovchinnikov

et al. 2012

J. Comput. Syst. Sci. Int.

View full text Add to dashboard Cite

show abstract

“…Dynamics and Control Simulator [11], which provides full freedom in yaw and ± 45° in pitch and roll and the Georgia Tech's School of Aerospace Engineering simulator, which provides full freedom in yaw and ± 30° in pitch and roll [12]. The University of Michigan's Triaxial Air Bearing Testbed [13], [14] is a dumbbell rotational system.…”

Section: Fig 1 A) Tabletop System B) Umbrella System C) Dumbbell Smentioning

confidence: 99%

Advances on a 6 Degrees of Freedom Testbed for Autonomous Satellites Operations

Gallardo

Bevilacqua

Rasmussen

2011

AIAA Guidance, Navigation, and Control Conference

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This paper presents recent developments in designing a novel 6 degrees of freedom (DOF) experimental testbed for validation of guidance, navigation and control algorithms for nanosatellites. The main catalyst for this research is the desire to experimentally test these algorithms in a 1g laboratory environment, in order to increase system reliability while reducing time-to-launch and development costs. The system stands out among the existing experimental platforms because all degrees of freedom of motion are dynamically reproduced. The majority of the existing platforms guarantee at the most 5 DOF force-free motion, excluding the vertical motion. The sixth DOF, when considered, is reproduced only from a kinematic point of view, by using an electrical motor. The presented testbed achieves 6 DOF dynamical motion by using 12 cold gas thrusters. A condition of almost frictionless motion along the 6 DOF is realized using 3 sets of air bearings: linear air bearings for the planar translational motion of the platform over an epoxy floor, air bearing pulleys embedded in a mass balancing system for the gravity-free vertical motion, and a spherical air bearing providing the additional 3 rotational DOF. The challenges of near gravity-free vertical translation in a 1g field are addressed using a unique counterbalancing system.

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“…It shows the payload, which consists of several ADCS subsystems such as a star camera, is mounted on a flat bed that is attached to a counter-weight structure (CWS). The CWS consists of a total of 27 large and 6 small balance masses that are designed to be screwed in/out and up/down along the metal brackets [2,3]. Therefore, the platform is scalable making it suitable for testing complete satellites as well as satellite subsystems [4].…”

Section: Platform Configurationmentioning

confidence: 99%

A new testing platform for attitude determination and control subsystems: Design and applications

Almajed

Alsuwaidan

2009

2009 IEEE/ASME International Conference on Advanced Intelligent Mechatronics

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This paper presents a new experimental research and development platform for satellite attitude determination and control systems (ADCS). It is designed to easily accommodate any major component of a satellite ADCS. The platform provides a near-zero gravity condition using a Ball-and-Socket air bearing table that provides unconstrained satellite rotational motion. The pressurized air flow is passed through five microscale air holes carefully placed inside the socket to provide the required air gap between the socket and the ball. The platform provides full freedom of spin in the yaw axis but roll and pitch motions are constrained to angles of less than ±30 degrees. A special counter balance mechanism has been designed for a wide range of payloads that can be mounted on it. The satellite with its counter balance structure is attached to the ball and is carefully placed on the air cushion using a special mechanism. A dedicated UHF/VHF RF link is designed to allow for remote command and control of payloads under testing. All payloads will be connected to the RF system via a CAN bus.The paper discusses the detailed description of the testing platform and the challenges related to its commissioning and operation. In addition, it presents research projects that could be carried out using the platform including applying advanced robust control theory, system identification, validity tests and sensors integration and calibration in future satellite ADCSs. In particular, a multi-filters multi-sensors estimator is presented for the multiple MEMS gyros array system.

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<title>Air-bearing-based satellite attitude dynamics simulator for control software research and development</title>

Cited by 23 publications

References 0 publications

Testing of attitude control algorithms for microsatellite “Chibis-M” at laboratory facility

Testing of attitude control algorithms for microsatellite “Chibis-M” at laboratory facility

Advances on a 6 Degrees of Freedom Testbed for Autonomous Satellites Operations

A new testing platform for attitude determination and control subsystems: Design and applications

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