Determining characteristic mass for low-earth-orbiting debris objects

Dickey, Michael R.; Culp, Robert D.

doi:10.2514/3.26092

Cited by 11 publications

(4 citation statements)

References 2 publications

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“…The penetration depth by a high-velocity impact of a particle has been discussed often and Bjoke's equation expressed as in Eq. (1) has been given (Dickey and Culp, 1989),…”

Section: Resultsmentioning

confidence: 99%

Surface coating by diamond particles on an aluminum substrate by underwater shock wave

Tanaka

Hokamoto

Torii

et al. 2010

Journal of Materials Processing Technology

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“…The penetration depth by a high-velocity impact of a particle has been discussed often and Bjoke's equation expressed as in Eq. (1) has been given (Dickey and Culp, 1989),…”

Section: Resultsmentioning

confidence: 99%

Surface coating by diamond particles on an aluminum substrate by underwater shock wave

Tanaka

Hokamoto

Torii

et al. 2010

Journal of Materials Processing Technology

View full text Add to dashboard Cite

“…Mass m , exposed frontal area A , and drag coefficient C d are often very uncertain because these quantities require knowledge of the properties of the object being tracked that cannot be readily estimated directly from remote measurements. The rough size and mass of the object under study have been inferred from past orbital history (Gondelach et al., 2017), measurements of radar cross section (Dickey & Culp, 1989) or visual magnitude (Šilha, 2020). A and C d are a function of satellite attitude, which is difficult to measure in real‐time.…”

Section: Satellite Dragmentioning

confidence: 99%

Influences of Space Weather Forecasting Uncertainty on Satellite Conjunction Assessment

Parker,

Freeman,

Chisham

et al. 2024

Space Weather

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A significant increase in the number of anthropogenic objects in Earth orbit has necessitated the development of satellite conjunction assessment and collision avoidance capabilities for new spacecraft. Neutral mass density variability in the thermosphere, driven by enhanced geomagnetic activity and solar EUV absorption, is a major source of satellite propagation error. This work investigates the impacts of space weather driver forecasting uncertainty on satellite drag and collision avoidance maneuver decision‐making. Since most operational space weather driver forecasts do not offer an uncertainty assessment, the satellite operator community is left to make dangerous assumptions about the trustworthiness of the forecast models they use to perform satellite state propagation. Climatological persistence‐based forecast models are developed for F10.7 and Kp. These models accurately capture the heteroscedastic and, at times, highly non‐Gaussian uncertainty distribution on forecasts of the drivers of interest. A set of realistic satellite conjunction scenarios is simulated to demonstrate the contributions of space weather driver forecast uncertainty on the probability of collision and maneuver decisions. Improved driver forecasts, especially forecasts of F10.7, are demonstrated to be very useful for enabling durable maneuver decisions with additional lead time (up to 24 hr for the period examined), though the improvement depends on the specific conjunction scenario of interest.

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“…Mass m, exposed frontal area A, and drag coefficient C d are often very uncertain because these quantities require knowledge of the properties of the object being tracked that cannot be readily estimated directly from remote measurements. The rough size and mass of the object under study have been inferred from past orbital history (Gondelach et al, 2017), measurements of radar cross section (Dickey & Culp, 1989) or visual magnitude ( Šilha, 2020). A and C d are a function of satellite attitude, which is difficult to measure in real-time.…”

Section: Satellite Dragmentioning

confidence: 99%

Influences of Space Weather Forecasting Uncertainty on Satellite Conjunction Assessment

Parker,

Freeman,

Chisham

et al. 2023

Preprint

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A significant increase in the number of anthropogenic objects in Earth orbit has necessitated the development of satellite conjunction assessment and collision avoidance capabilities for new spacecraft. Often, the greatest source of uncertainty in predicting a satellite’s trajectory in low Earth orbit originates from atmospheric neutral mass density variability caused by enhanced geomagnetic activity and solar EUV absorption. This work investigates the impacts of solar and geomagnetic index forecasting uncertainty on satellite drag and satellite maneuver decision-making. During an averaged point in the solar cycle, accurate index forecasts with reduced uncertainty are shown to provide significantly improved advance notice for dangerous conjunction events above 500 km. Below 500 km, forecast improvements are less impactful. This boundary of utility from forecast improvements shifts upward and downward during solar maximum and solar minimum, respectively. Improved index forecasts are shown to have little impact on making maneuver decisions 12-24 hours from a potential conjunction event, but are demonstrated to be very useful when trying to make maneuver decisions with more lead time. These improved forecasts of the space weather indices help in making actionable, durable conjunction predictions sooner than is currently possible.

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Determining characteristic mass for low-earth-orbiting debris objects

Cited by 11 publications

References 2 publications

Surface coating by diamond particles on an aluminum substrate by underwater shock wave

Surface coating by diamond particles on an aluminum substrate by underwater shock wave

Influences of Space Weather Forecasting Uncertainty on Satellite Conjunction Assessment

Influences of Space Weather Forecasting Uncertainty on Satellite Conjunction Assessment

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