Analysis of reentry survivability of UARS spacecraft

Rochelle, W. C.; Marichalar, Jeremiah J.; Johnson, Nicholas L.

doi:10.1016/j.asr.2003.01.011

Cited by 14 publications

(6 citation statements)

References 1 publication

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“…The simulation and experimental investigation of this complex process was out of the scope of our present work. Such computations have been performed in the prediction of break‐up and survival of spacecrafts and satellites (e.g., Allen & Eggers, ; Bouslog et al ; Fritsche et al , ; Klinkrad ; Klinkrad et al ; Koppenwallner et al ; Rochelle et al ).…”

Section: Discussionmentioning

confidence: 99%

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Dynamics of spherical space debris of different sizes falling to Earth

et al. 2020

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Space debris larger than 1 cm can damage space instruments and impact Earth. The low-Earth orbits (at heights smaller than 2,000 km) and orbits near the geostationary-Earth orbit (at 35,786 km height) are especially endangered because most satellites orbit at these latitudes. With current technology, space debris smaller than 10 cm cannot be tracked. Smaller space debris fragments burn up and evaporate in the atmosphere, but larger ones fall to Earth's surface.For practical reasons, it would be important to know the mass, composition, shape, velocity, direction of motion, and impact time of space debris re-entering the atmosphere and falling to Earth. Since it is very difficult to measure these physical parameters, almost nothing is known about them. To partly fill this gap, we performed computer modeling with which we studied the dynamics of spherical re-entry particles falling to Earth due to air drag. We determined the time, velocity, and angle of impact as functions of the launch height, direction, speed, and size of spherical re-entry particles. Our results can also be used for semispherical meteoroid particles of the interplanetary dust entering the Earth's atmosphere.

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Section: Discussionmentioning

confidence: 99%

“…Such computations have been performed in the prediction of break-up and survival of spacecrafts and satellites (e.g. Allen & Eggers (1953); Bouslog et al (1994);Fritsche et al (1999Fritsche et al ( , 2000; Klinkrad (2004); Klinkrad et al (2006); Koppenwallner et al (2001); Rochelle et al (2004).…”

Section: Discussionmentioning

confidence: 99%

Dynamics of spherical space debris of different sizes falling to Earth

et al. 2020

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“…Examples of such pieces of software are for instance DEBRISK developed at Centre d'Etude Spa-tiale (CNES) [2] coupled with a risk estimation tool [3]. Similarly, ORSAT [4] is an object-oriented spacecraft that has been used to predict the reentry of UARS spacecraft [5]. Similar approaches are implemented in DRAMA [6] from the European Space Agency (ESA) and DRAPS [7] that uses a Monte Carlo approach to account for the uncertainties in the breakup prediction and the debris survivability.…”

Section: Introductionmentioning

confidence: 99%

Breakup prediction under uncertainty: Application to upper stage controlled reentries from GTO orbit

Sanson

Bertorello

Bouilly

et al. 2019

Aerospace Science and Technology

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“…On-orbit spacecraft breakup models due to both collision and explosion, and the evolution of resulting space debris have been well studied in the literature ( [2], [3], [9], [23]). A variety of methods have been employed to analyze the debris reentry trajectories ( [7], [10], [11], [17], [22]) and to estimate the risk posed to people and the property on the ground ( [4], [14], [15]). …”

Section: Introductionmentioning

confidence: 99%

Estimation of debris hazard areas due to a space vehicle breakup at high altitudes

Reyhanoglu

Alvarado

Carmi

2013

2013 9th Asian Control Conference (ASCC)

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With the recent developments in the Commercial Space Transportation industry, there has been a surge of interest in the analyses of the debris hazard areas due to a space vehicle breakup and the risk posed to the aircraft in the national airspace system as well as to the people and the property on the ground. The focus of this paper is to study the problem of estimation of the extent of the airspace containing falling debris due to a space vehicle breakup. A precise computation of propagation of debris to the ground is not practical for many reasons. There is insufficient knowledge of the initial state vector; ambient wind conditions; and key parameters, including the ballistic coefficient distributions. In addition, propagation of all debris pieces to the ground would require extensive computer time. In this paper, a computationally efficient covariance propagation method is employed for the estimation of debris dispersion.

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Analysis of reentry survivability of UARS spacecraft

Cited by 14 publications

References 1 publication

Dynamics of spherical space debris of different sizes falling to Earth

Dynamics of spherical space debris of different sizes falling to Earth

Breakup prediction under uncertainty: Application to upper stage controlled reentries from GTO orbit

Estimation of debris hazard areas due to a space vehicle breakup at high altitudes

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