Astrometric and photometric data fusion for inactive space object mass and area estimation

Linares, Richard; Jah, Moriba; Leve, Fred A.; Kelecy, Tom

doi:10.1016/j.actaastro.2013.10.018

Cited by 32 publications

(25 citation statements)

References 9 publications

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“…The approach presented in this paper is based on including the effects of solar radiation pressure (SRP) torques, modeled following [23], into the spacecraft model. Our analysis shows that, under appropriate assumptions, linear controllability is regained, and hence spacecraft stabilization can be achieved with conventional control schemes.…”

Section: Introductionmentioning

confidence: 99%

Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure

Petersen

Leve

Flynn

et al. 2016

Journal of Guidance, Control, and Dynamics

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This paper describes a method for recovering linear controllability for the attitude of an underactuated spacecraft by accounting for the effects of solar radiation pressure in the spacecraft attitude model. The developments are based on a spacecraft model that has at least two functional reaction wheels. A solar radiation pressure torque model that is a function of spacecraft attitude is incorporated and, under suitable assumptions, can be simplified for spacecraft with body symmetry. Conditions are given under which a symmetric-body spacecraft will experience zero solar radiation pressure torque. The stability of the underactuated spacecraft model is discussed, and necessary and sufficient conditions are given for linear controllability to be regained when solar radiation pressure torques are included in the spacecraft attitude model. With linear controllability restored, conventional controllers can be designed for underactuated spacecraft. Controllability of a cuboid spacecraft under the influence of solar radiation pressure is then analyzed. Nonlinear simulations illustrate this novel approach to recover pointing by controlling two functioning reaction wheels while two other wheels undergo subsequent failures. Nomenclature A = dynamics matrix of an open-loop linear model A w = dynamics matrix of an open-loop linear model for angular velocities A j = area of panel j B = input matrix of a linear model B = spacecraft bus-fixed frame C diff;j = diffusion coefficient of panel j c = speed of light d i;j = distance to point i on panel j from the center of the sun d 0 = 1 AÛ g i , i 1,2,3,4 = physical spin axis vectors of reaction wheels 1, 2, 3, and 4, respectively g i , i 1,2,3,4 = mathematical vector corresponding to the expressionĝ i expressed in B H = physical total angular momentum vector I = inertial frame I j = indicator function for determining if panel j contributes to solar radiation pressure torque J = diag(J 1 ,J 2 ,J 3 ) J = locked inertia matrix J = modified locked inertia matrix J ind = controllability index J w = moment of inertia of a reaction wheel about its spin axis J 1 ,J 2 ,J 3 = spacecraft principal moments of inertia L x , L y , L z = dimensions of the cuboid spacecraft l x , l y , l z = components of r C∕O M ext = physical external moment vector Mt f ; t 0 = controllability gramian n 1 , n 2 , n 3 = components of u s O B∕I = orientation matrix of B relative to I P j = physical vector of solar radiation pressure of panel j Q, R = weight matrices for linear quadratic controller r C∕O = physical position vector of the center of mass of the spacecraft C from a reference point O r C∕O = mathematical vector corresponding to r C∕O expressed in B r j = mathematical vector corresponding to r j∕O expressed in B when considering a pair of symmetric panels r j∕O = physical position vector of the center of the jth panel from a reference point O T= linearized solar radiation pressure torques influence matrix u j = mathematical vector corresponding to the expression ofû n;j expressed in B when considering...

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Section: Introductionmentioning

confidence: 99%

Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure

Petersen

Leve

Flynn

et al. 2016

Journal of Guidance, Control, and Dynamics

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show abstract

“…In particular, Reference [9] was able to deduce the rotation period, pole direction, and scattering parameters of an asteroid using only light curve information. Since magni-tude information can also be used to deduce information about position and attitude and their respective rates [12] utilizing photometric information can be considerably useful in determining mass information for a space object. This is because there are multiple ways to approach the modeling information of intrinsic parameters which are all not sensitive to the same restrictions.…”

Section: Photometric Datamentioning

confidence: 99%

“…in Reference [12]. Dr. Linares was instrumentally helpful in explanations for the process of unscented Kalman filtering which will be described in Section 3.6 as well as in code exchanges for the application of quaternions in the UKF seen in Section 3.6.2.…”

Section: Previous Workmentioning

confidence: 99%

“…The position states were either initialized with a two line element set or with initial orbit determination methods to simulate data which was run through an unscented Kalman filter to estimate the translational and rotational states of the space object as well as the mass and albedo area. In the geosynchronous and highly elliptic cases the tool was able to accurately predict the mass value to within ±5kg of the true value based on a 95% confidence interval which will allow applications to understanding high area-to-mass objects with high certainty.iv ACKNOWLEDGMENTS Thanks to:• My committee for helping me on this endeavor• Richard Linares for supporting me in building off his work from Reference [12] and for explaining topics I was unfamiliar with• My parents, Gene and Christina Richardson…”

mentioning

confidence: 99%

“…• Richard Linares for supporting me in building off his work from Reference [12] and for explaining topics I was unfamiliar with…”

mentioning

confidence: 99%

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Mass Estimation through Fusion of Astrometric and Photometric Data Collection with Application to High Area-to-Mass Ratio Objects

Richardson¹

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This thesis work presents the formulation for a tool developed in MATLAB to determine the mass of a space object from the fusion of astrometric and photometric data. The application for such a tool is to better model the mass estimation method used for high area-to-mass ratio objects found in high altitude orbit regimes. Typically, the effect of solar radiation pressure is examined with angles observations to deduce area-to-mass ratio calculations for space objects since the area-to-mass ratio can greatly affect its orbital dynamics. On the other hand, photometric data is not sensitive to mass but is a function of the albedo-area and the rotational dynamics of the space object. Thus from these two data types it is possible to disentangle intrinsic properties using albedo-area and area-to-mass and ultimately determine the mass of a space object. Three case studies were performed for the different orbit regimes: geosynchronous, highly elliptic, and medium earth orbit. The position states were either initialized with a two line element set or with initial orbit determination methods to simulate data which was run through an unscented Kalman filter to estimate the translational and rotational states of the space object as well as the mass and albedo area. In the geosynchronous and highly elliptic cases the tool was able to accurately predict the mass value to within ±5kg of the true value based on a 95% confidence interval which will allow applications to understanding high area-to-mass objects with high certainty.iv ACKNOWLEDGMENTS Thanks to:• My committee for helping me on this endeavor• Richard Linares for supporting me in building off his work from Reference [12] and for explaining topics I was unfamiliar with• My parents, Gene and Christina Richardson

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A Direct Light Curve Inversion Scheme in the Presence of Measurement Noise

Fan

Frueh

2019

J Astronaut Sci

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Astrometric and photometric data fusion for inactive space object mass and area estimation

Cited by 32 publications

References 9 publications

Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure

Recovering Linear Controllability of an Underactuated Spacecraft by Exploiting Solar Radiation Pressure

Mass Estimation through Fusion of Astrometric and Photometric Data Collection with Application to High Area-to-Mass Ratio Objects

A Direct Light Curve Inversion Scheme in the Presence of Measurement Noise

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