High spin rate magnetic controller for nanosatellites

Slavinskis, Andris; Kvell, Urmas; Kulu, Erik; Sünter, Indrek; Kuuste, Henri; Lätt, S.; Voormansik, Kaupo; Noorma, Mart

doi:10.1016/j.actaastro.2013.11.014

Cited by 51 publications

(30 citation statements)

References 25 publications

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“…With this set-up the spin axis will not tend to be turned because the magnetic Lorentz force and the E-sail force are both nearly parallel to the spin plane [8,13].…”

Section: Mission Analysismentioning

confidence: 98%

“…According to simulations, the ADCS is able to spin up the satellite in less than eight orbits. The subsystem is described in detail in [13,14].…”

Section: Attitude Determination and Control Subsystemmentioning

confidence: 99%

“…• design and production of the tether [10,11]; • development of a tether deployment subsystem [12]; • development of an attitude determination and control subsystem for centrifugal tether deployment [13,14]; • development of a tether end mass (a mass at the end of the tether) imaging subsystem for monitoring tether deployment [15]; • development of an electron gun for keeping the tether at a high positive potential [12]; • development of a high voltage source for charging the tether and for powering electron guns [12]. A nanosatellite, ESTCube-1, has been developed to demonstrate the performance of the listed technologies and to perform the first in-orbit demonstration of the E-sail concept.…”

Section: Introductionmentioning

confidence: 99%

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ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Lätt¹,

Slavinskis

Ilbis

et al. 2014

Proc. Estonian Acad. Sci.

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This paper presents the mission analysis, requirements, system design, system level test results, as well as mass and power budgets of a 1-unit CubeSat ESTCube-1 built to perform the first in-orbit demonstration of electric solar wind sail (E-sail) technology. The E-sail is a propellantless propulsion system concept that uses thin charged electrostatic tethers for turning the momentum flux of a natural plasma stream, such as the solar wind, into spacecraft propulsion. ESTCube-1 will deploy and charge a 10 m long tether and measure changes in the satellite spin rate. These changes result from the Coulomb drag interaction with the ionospheric plasma that is moving with respect to the satellite due to the orbital motion of the satellite. The following subsystems have been developed to perform and to support the E-sail experiment: a tether deployment subsystem based on a piezoelectric motor; an attitude determination and control subsystem to provide the centrifugal force for tether deployment, which uses electromagnetic coils to spin up the satellite to one revolution per second with controlled spin axis alignment; an imaging subsystem to verify tether deployment, which is based on a 640 × 480 pixel resolution digital image sensor; an electron gun to keep the tether at a high positive potential; a high voltage source to charge the tether; a command and data handling subsystem; and an electrical power subsystem with high levels of redundancy and fault tolerance to mitigate the risk of mission failure.

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“…With this set-up the spin axis will not tend to be turned because the magnetic Lorentz force and the E-sail force are both nearly parallel to the spin plane [8,13].…”

Section: Mission Analysismentioning

confidence: 98%

“…According to simulations, the ADCS is able to spin up the satellite in less than eight orbits. The subsystem is described in detail in [13,14].…”

Section: Attitude Determination and Control Subsystemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Lätt¹,

Slavinskis

Ilbis

et al. 2014

Proc. Estonian Acad. Sci.

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“…The antenna deployment system needs to be activated only once during the mission (just after deployment), so the maximum theoretical load is slightly over 8 W. The consumption is, however, divided between different voltage levels: CAM, CDHS, and COM microcontroller (plus minor PL consumption) operate on 3.3 V, ADCS and COM power electronics (plus minor PL consumption) operate on 5 V; PL major consumers operate on 12 V; and antenna deployment system and ADCS coils operate on battery voltage level directly. [17]; CDHS -command and data handling system, three separate 3.3 V lines are required to select which redundant module is active [18]; PL -payload [7]; ADCSattitude determination and control system [19,20]. In orbit, the satellite is subjected to cosmic radiation that causes both total dose and single event effects [21], which will eventually make the satellite's electronics inoperable.…”

Section: Requirements For the Subsystemmentioning

confidence: 99%

Design and pre-flight testing of the electrical power system for the ESTCube-1 nanosatellite

Pajusalu¹,

Ilbis²,

Ilves³

et al. 2014

Proc. Estonian Acad. Sci.

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This work describes the final design and implementation of the electrical power system for ESTCube-1, a 1-unit CubeSat tasked with testing the electrostatic tether concept and associated technologies for the electric solar wind sail in polar low Earth orbit. The mission required an efficient and reliable power system to be designed that could efficiently handle highly variable power requirements and protect the satellite from damage caused by malfunctions in its individual subsystems, while using only commercial-off-the-shelf components. The system was developed from scratch and includes a novel redundant standalone nearly 90% efficient maximum power point tracking system, based on a commercially available integrated circuit, a lithiumion battery based fault-tolerant power storage solution, a highly controllable and monitorable power distribution system, capable of sustaining loads of up to 10 W, and an AVR microcontroller based control solution, heavily utilizing non-volatile ferroelectric random access memories. The electrical power system was finalized in January 2013 and was launched into orbit on 7th of May, 2013. In this paper, we describe the requirements for the subsystem, the design of the subsystem, pre-flight testing, and flight qualification.

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“…Moreover, magnetic actuators can also be very useful in many other industry segments. They can be applied in the aerospace industry, for spacecraft [12] and satellite [13][14][15] attitude control and stabilization. In the field of predictive maintenance, these actuators can be used as external excitation source for fault detection and health monitoring, [16] or for parameter identification of journal bearings, [17] in both cases considering, especially, rotating machines in operation.…”

Section: Introductionmentioning

confidence: 99%

Electromagnetic actuators for controlling flexible cantilever beams

Martin

Mendes

Cavalca

2017

Struct Control Health Monit

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Electromagnetic actuators are very important for scientific and industrial applications. Their use may vary within a wide range of possibilities due to their most important feature: the ability to apply known and controllable forces to elements or structures without contact. In this article, an application within this range is analyzed: a proportional-integral-derivative (PID) controller is used with a pair of actuators to control the dynamic forced response of a flexible cantilever metallic beam and to keep it at a given reference position. In order to achieve this objective, both the actuators and the controller need to be adjusted. For the actuators, the main parameters evaluated consider mounting particularities, such as the differential assembly and the influence of the air-gap distance over the magnetic flux density and the magnetic force provided. Next, a brief review of PID controllers is pre- | INTRODUCTIONMagnetic actuators are components with a wide range of possibilities whose application field has been growing year after year. [1][2][3] In fact, the main feature of interest in these components is the ability to apply known and controllable forces over many types of elements and structures with no need of contact and no need of any kind of material medium. In this sense, magnetic actuators are a good alternative for common mechanical components. A simple example is a growing field of research and application on magnetic gears. [1,4] These gears offer clear advantages over their mechanical counterparts such as contactless torque transfer, lower maintenance, inherent overload protection, and physical isolation between input and output shafts, being suitable in a market that desires more efficient and reliable gears. Another example of magnetic actuators competing with mechanical devices occurs with magnetic bearings (both active and/ or passive). [1][2][3] These bearings also have some advantages [5] : besides allowing oil-free machines, magnetic bearings are frictionless (and therefore have low-power losses and no wear), allowing high rotational speed. Besides, the bearings can be remotely controlled and are good monitoring devices (because the bearing forces can be properly measured). Therefore, in the field of magnetic bearings, there are some interest applications. Among these, one may find flywheels for kinetic energy storage as peak power buffer units (i.e., for supplying energy on demand peaks) in vehicle applications, [1,6,7] in oil drilling platforms, [8] and even in electric power network applications. [9] Due to its operation characteristics, it is desirable that flywheels rotate at higher speeds and, if a long-term energy storage is needed, low-energy consumption during storage

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High spin rate magnetic controller for nanosatellites

Cited by 51 publications

References 25 publications

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

ESTCube-1 nanosatellite for electric solar wind sail in-orbit technology demonstration

Design and pre-flight testing of the electrical power system for the ESTCube-1 nanosatellite

Electromagnetic actuators for controlling flexible cantilever beams

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