Characterization of the orbital debris environment from Haystack radar measurements

Stansbery, Eileen K.; Kessler, Donald J.; Tracy, T.; Matney, Mark; Stanley, John F.

doi:10.1016/0273-1177(95)98748-d

Cited by 22 publications

(14 citation statements)

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“…where the units are in detections per hour for the Haystack radar [Stansbery et al, 1993]. This model closely resembles size distributions from EVOLVE and other models for determining debris populations.…”

Section: Caudmiammentioning

confidence: 73%

Proceedings of the Annual Space Surveillance Workshop (12th) Held in Lexington, Massachusetts on 5-7 April 1994. Volume 1

Schwan¹,

Rodvold²,

Muolo³

et al. 1994

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Section: Caudmiammentioning

confidence: 73%

Proceedings of the Annual Space Surveillance Workshop (12th) Held in Lexington, Massachusetts on 5-7 April 1994. Volume 1

Schwan¹,

Rodvold²,

Muolo³

et al. 1994

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“…Only objects with a diameter larger than about 10 cm in the low Earth orbits (LEO) and objects larger than 1 m in the geostationary orbits (GEO) may be permanently tracked by radar or optical facilities and then catalogued. Although the Haystack radar is able to track debris objects as small as 1 cm at 500 km altitude and has been used to characterise the orbital debris environment in low Earth orbit (Stansbery et al, 1995), it does not regularly make observations in the frame of the U.S. Space Surveillance Network (SSN). Therefore, objects with a diameter smaller than 10 cm are not included in the Satellite Catalogue maintained by the U.S. Space Command's Space Surveillance Center.…”

Section: The Current Population Of Space Debrismentioning

confidence: 99%

Space debris ? The short term orbital evolution in the earth gravity field

Wnuk

1997

Celestial Mech Dyn Astr

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Two aspects of the orbital evolution of space debris -the long-term evolution and the short-term one -are of interest for an exploration of the near-Earth space. The paper presents some results concerning the estimation of the accuracy of predicted positions of Earth-orbiting objects for the short-term: a few revolutions or a time-span interval of a few days. Calculations of predicted positions take into account the influence of an arbitrary number of spherical coefficients of the Earth gravity potential. Differences in predicted positions due to differences in the best contemporary geopotential models (JGM-2, JGM-3 and GRIM4-S4) are estimated with the use of an analytical theory of motion and a numerical integration.

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“…Recently, some measurements have been made using the Haystack radar. 4 With Haystack, measurements have been made at three elevation angles: 10 degi 20 deg, and 90 deg (vertical). Measurements were made at elevation angles other than the vertical because Haystack is at a latitude greater than the 28-deg inclined orbit of the Space Station and cannot measure the total environment of the Space Station looking vertically.…”

Section: Introductionmentioning

confidence: 99%

Estimation of the low-Earth-orbit debris population and distribution

Alfriend

Lewis

1994

Journal of Spacecraft and Rockets

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In this paper an algorithm for estimating the low-Earth-orbit space object population and distribution from measurements taken by a vertical, staring narrow beam radar is developed and validated. The radar measures the altitude, inclination, and radar cross section of each object which passes through the beam. Validation of the algorithm is achieved by simulating the orbits of the objects in the North American Aerospace Defense Command (NORAD) data base, determining those which pass through a vertical staring radar and by estimating the population and distribution of the NORAD data base from the altitude, inclination, and radar cross section of those which pass through. The effects of the assumptions made in developing the algorithm and measurement errors are discussed. An estimate of the operational time of the radar needed to achieve a specified accuracy in the space object population is also developed. Nomenclature h= orbit altitude / = orbit inclination N = number of objects in population A^st = estimated number of objects in population r = orbit radius T = orbit period T m -measurement time a -Earth central angle subtended by radar j8 = radar beamwidth 6j = latitude of radar A = expected rate of objects through radar beam X* = measured rate of objects through radar beam

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Characterization of the orbital debris environment from Haystack radar measurements

Cited by 22 publications

References 0 publications

Proceedings of the Annual Space Surveillance Workshop (12th) Held in Lexington, Massachusetts on 5-7 April 1994. Volume 1

Proceedings of the Annual Space Surveillance Workshop (12th) Held in Lexington, Massachusetts on 5-7 April 1994. Volume 1

Space debris ? The short term orbital evolution in the earth gravity field

Estimation of the low-Earth-orbit debris population and distribution

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