High-Precision Pointing and Attitude Determination and Control on ExoplanetSat

Pong, Christopher M.; Knutson, Matthew W.; Miller, David W.; Seager, Sara; Lim, Sungyung; Henderson, Timothy; Murphy, Shawn D.

doi:10.2514/6.2012-4783

Cited by 13 publications

(15 citation statements)

References 16 publications

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“…(11) show that the kinetic energy Tt can have at most exponential growth either forward or backward in time, and is consequently finite for all t ∈ R. Therefore, it must be that C bI t; ω bI t exists for all t ∈ R.…”

Section: Problem Formulationmentioning

confidence: 97%

“…Note that C ϕ;sI corresponds to a rotation about s I through angle ϕ ( [19] pp. [10][11][12], and consequently C ϕ;sI s I s I . Therefore,…”

Section: A Indistinguishability For a Torque-free Spacecraftmentioning

confidence: 99%

“…Therefore, the applicability of the aforementioned estimation schemes are limited to the use of magnetometer measurements, because the Earth's magnetic field vector varies sufficiently over an orbit. An analytical investigation of observability of angular velocity alone for a torque-free spacecraft using a single inertially fixed vector measurement has been performed in [11]. It is shown that angular velocity is locally observable provided the spacecraft is not in an equilibrium spin condition with angular velocity parallel to the sun vector.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Ruiter¹,

Tran²,

Kumar³

et al. 2016

Journal of Guidance, Control, and Dynamics

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This paper examines the problem of attitude estimation for passively magnetically stabilized spacecraft using only sun-vector measurements. An analytical investigation of local observability is performed in the case where the spacecraft magnetic dipole is constant. This is relevant because for passively stabilized spacecraft using permanent magnets and magnetic hysteresis rods, the hysteresis rod dipole moments are nearly constant at steady state. It is shown that under reasonable assumptions on the Earth's magnetic field, not only are the attitude and angular velocity locally observable, but if one component of the magnetic dipole moment is known, then the remaining two components of the magnetic dipole moment are locally observable also. Numerical examples of three attitude estimation schemes are presented, demonstrating successful state estimation of passively magnetically stabilized spacecraft.

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Section: Problem Formulationmentioning

confidence: 97%

“…Note that C ϕ;sI corresponds to a rotation about s I through angle ϕ ( [19] pp. [10][11][12], and consequently C ϕ;sI s I s I . Therefore,…”

Section: A Indistinguishability For a Torque-free Spacecraftmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Ruiter¹,

Tran²,

Kumar³

et al. 2016

Journal of Guidance, Control, and Dynamics

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show abstract

“…The detector involved in the closed loop is an auxiliary sensor with a pixel size smaller than the scientific detector pixel size, and thus it reaches a higher frame rate. According to [25] this technique (together with the MIT driver code) let to reach the pointing accuracy of 2.3 arcsec.…”

Section: The Satellite Projectmentioning

confidence: 99%

A Cubesat Payload for Exoplanet Detection

Iuzzolino

Accardo

Rufino

et al. 2017

Sensors

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The search for undiscovered planets outside the solar system is a scientific topic that is rapidly spreading into the astrophysical and engineering communities. In this framework, the design of an innovative payload to detect exoplanets from a nano-sized space platform, like a 3U cubesat, is presented. The selected detection method is photometric transit, and the payload aims to detect flux decrements down to ~0.01% with a precision of 12 ppm. The payload design is also aimed at false positive recognition. The solution consists of a four-facets pyramid on the top of the payload, to allow for measurement redundancy and low-resolution spectral dispersion of the star images. The innovative concept is the use of a small and cheap platform for a relevant astronomical mission. The faintest observable target star has V-magnitude equal to 3.38. Despite missions aimed at ultra-precise photometry from microsatellites (e.g., MOST, BRITE), the transit of exoplanets orbiting very bright stars has not yet been surveyed photometrically from space, since any observation from a small/medium sized (30 cm optical aperture) telescope would saturate the detector. This cubesat mission can provide these missing measurements. This work is set up as a demonstrative project to verify the feasibility of the payload concept.

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“…6 While the coarse stage performance depends on the host CubeSat, parameters were based on recent CubeSat missions developed in the MIT Space Systems Lab. 11,12 Incorporating the results of the uplink beacon simulation described in the previous section, the accuracy of the detector is taken to be 30 µrad on average. The rate at which the FSM can be driven is limited by the beacon detector readout and processing.…”

Section: Control System Simulationmentioning

confidence: 99%

Development of a pointing, acquisition, and tracking system for a CubeSat optical communication module

et al. 2015

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Miniaturized satellites such as CubeSats continue to improve their capabilities to enable missions that can produce significant amounts of data. For most CubeSat missions, data must be downlinked during short lowearth orbit ground station passes, a task currently performed using traditional radio systems. Free-space optical communications take advantage of the high gain of a narrow optical beam to achieve better link efficiency, allowing more valuable data to be downlinked over the mission lifetime. We present the Nanosatellite Optical Downlink Experiment (NODE) design, capable of providing a typical 3U (30 x 10 x 10 cm) CubeSat with a comparatively high data-rate downlink. The NODE optical communication module is designed to fit within a 5 x 10 x 10 cm volume, weigh less than 1 kg, and consume no more than 10 W of power during active communication periods. Our design incorporates a fine-steering mechanism and beacon-tracking system to achieve a 10 Mbps link rate. We describe the system-level requirements and designs for key components, including a transmitter, a beacon tracking camera, and a fast-steering mirror. We present simulation results of the uplink beacon tracking and fine steering of the downlink beam, including the effects of atmospheric fading and on-orbit environmental disturbances to demonstrate the feasibility of this approach.

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High-Precision Pointing and Attitude Determination and Control on ExoplanetSat

Cited by 13 publications

References 16 publications

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

A Cubesat Payload for Exoplanet Detection

Development of a pointing, acquisition, and tracking system for a CubeSat optical communication module

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