Above the Horizon Satellite Coverage with Dual-Altitude Band Constraints

Marchand, Belinda G.; Kobel, Christopher J.

doi:10.2514/1.37140

Cited by 9 publications

(5 citation statements)

References 4 publications

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“…Accordingly, the number of sensors required for the global coverage of the DABS is fully determined by setting the required coverage diversity and minimal latitude. Furthermore, the coverage scale provided by constellations can be quantitatively analyzed [283]. The ultimate constellation meeting the coverage requirements is designed by numerical optimizations instead of specialized equations.…”

Section: Multiagent Awareness Technologiesmentioning

confidence: 99%

Research Advancements in Key Technologies for Space-Based Situational Awareness

Wang

et al. 2022

Space Sci Technol

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The space environment has become highly congested due to the increasing space debris, seriously threatening the safety of orbiting spacecraft. Space-based situational awareness, as a comprehensive capability of threat knowledge, analysis, and decision-making, is of significant importance to ensure space security and maintain normal order. Various space situational awareness systems have been designed and launched. Data acquisition, target recognition, and monitoring constituting key technologies make major contributions, and various advanced algorithms are explored as technical supports. However, comprehensive reviews of these technologies and specific algorithms rarely emerge. It disadvantages the future development of space situational awareness. Therefore, this paper further reviews and analyzes research advancements in key technologies for space situational awareness, emphasizing target recognition and monitoring. Many mature and emerging methods are presented for these technologies while discussing application advantages and limitations. Specially, the research prospects of multiagent and synergetic constellation technologies are expected for future situational awareness. This paper indicates the future directions of the key technologies, aiming to provide references for space-based situational awareness to realize space sustainability.

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Section: Multiagent Awareness Technologiesmentioning

confidence: 99%

Research Advancements in Key Technologies for Space-Based Situational Awareness

Wang

et al. 2022

Space Sci Technol

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“…The condition for repeating RSO tracks is similar to that for periodic relative orbits, given in Eq. (9), except the resonance is instead in the Hill frame, expressed as…”

Section: B Repeating Rso Tracksmentioning

confidence: 99%

“…Growing interest in chipscale and swarm spacecraft, as evidenced by the recent launch of 104 Sprites, which are 3.5 × 3.5 cm, 5 g printed circuit boards, pose even further challenges in RSO resolution [4][5][6][7]. Spurred by the need to overcome ground-based sensor obstacles, the second direction is a pursuit of alternative resources, such as in the form of space-based sensors, whether acting as part of a satellite constellation [8][9][10][11] or alone [12,13]. This latter field of single-vehicle space-based space surveillance is the focus of the present study, specifically obtaining and understanding possible orbits that offer good surveillance of RSOs using one spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Periodic Orbits in the Elliptical Relative Motion Problem with Space Surveillance Applications

Biria

Russell

2015

Journal of Guidance, Control, and Dynamics

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Periodic orbits with respect to an object in an eccentric Keplerian reference orbit can be found in a variety of ways, including the use of Tschauner-Hempel equations and orbital element differences, which both admit linearized solutions, as well as through direct analyses of two orbits. An alternative parameterization of the last approach is proposed in the current study, using an inertial frame and simple geometrical constructs inherent to the relative motion problem. In this manner, an intuitive and straightforward characterization of periodic orbits is established that retains the nonlinear dynamics. The resulting multidimensional space that defines the periodic orbits is surveyed, archiving 336 orbits and their characteristics, and direct comparisons are made with the Tschauner-Hempel equations to assess the linear region of validity. Applications focus on resident space object (RSO) surveillance and circumnavigation orbits. An orbit's effectiveness is analyzed in terms of object coverage using coverage figures of merit, including the concept of "RSO tracks", the analogy of ground tracks on the bodyfixed surface of an RSO. Nomenclature a = semimajor axis, LU C = chief body-fixed frame e = chief eccentricity vector e = chief eccentricity e D = deputy eccentricity H = Hill frame or local-vertical-local-horizontal frame M = number of grid points distributed over the chief's surface N = number of points evaluated along a trajectory n = chief mean motion, rad · TU −1 P = unit vector directed along the chief eccentricity vector P = percentage of chief surface covered by the deputy P = perifocal framê Q =Ŵ ×P B Q A = rotation matrix from the A frame to the B frame B q A = quaternion describing the orientation of the A frame with respect to the B framê R = unit vector directed along the chief position vector R = Earth-centered rotating frame r = inertial position vector, LU r = magnitude of inertial position vector, LÛ S =Ŵ ×R T = orbital period, TU v = inertial velocity vector, LU · TU −1 v = magnitude of inertial velocity vector, LU · TU −1 W = unit vector normal to the plane of motion of the chief orbit, along the angular momentum vector x, y, z = deputy coordinates in the Hill frame, LU α = deputy position in-plane colatitudelike angle relative to the chief, rad β = deputy position out-of-plane longitudelike angle relative to the chief, rad δ = precedes a deputy quantity defined relative to the chief λ = longitude, rad μ = gravitational parameter of primary body, LU 2 · TU −3 ν = chief true anomaly, rad σ = standard deviation, LU ϕ = latitude, rad B ω A = angular velocity of the A frame relative to the B frame, rad · TU −1 B ω A = magnitude of B ω A , rad · TU −1 Subscripts C = quantity associated with the chief D = quantity associated with the deputy ds = inertially dual-axis spin attitude mode NL = quantity computed using the full, nonlinear equations of motion for Keplerian orbits np = inertially nadir-pointing attitude mode ns = inertially nonspinning attitude mode s = angular velocity spin component about t...

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“…Strictly to introduce the general notation employed in this report, Figure 1 illustrates a cross-sectional view of the single satellite dual-altitude band ATH coverage problem. 5 In this figure, the upper and lower target altitude shells are labeled UTAS and LTAS, respectively. The satellite is identified as point S. The horizon is defined relative to the tangent height shell, labeled THS.…”

Section: Project Backgroundmentioning

confidence: 99%

“…The regions shaded in yellow represent the ATH region covered by the satellite at its current altitude, and that area is a piece-wise differentiable function of the satellite altitude. 5 Of course, in the generalized case, where the sensors are not omni-directional and the satellites in the constellation are unevenly distributed among multiple non-coplanar orbits, an analytical solution is not available. This motivates the numerical approach that is the focus of this effort.…”

Section: Project Backgroundmentioning

confidence: 99%

Optimal Constellation Design for Maximum Continuous Coverage of Targets Against a Space Background

Marchand¹,

Takano²

2012

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Above the Horizon Satellite Coverage with Dual-Altitude Band Constraints

Cited by 9 publications

References 4 publications

Research Advancements in Key Technologies for Space-Based Situational Awareness

Research Advancements in Key Technologies for Space-Based Situational Awareness

Periodic Orbits in the Elliptical Relative Motion Problem with Space Surveillance Applications

Optimal Constellation Design for Maximum Continuous Coverage of Targets Against a Space Background

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