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The First Satellite Breakup of 2000

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The First Satellite Breakup of 2000 A publication of The Orbital Debris Program Office NASA Johnson Space Center Houston, Texas 77058 April 2000 Volume 5, Issue 2. NEWS The First Satellite Breakup of 2000 The most significant satellite breakup in assessments determined the breakup time to The ~1,000-kg upper stage was in an orbit nearly four years occurred on 11 March have been between 1301 and 1304 UTC, while of 725 km by 745 km with an inclination of 2000 when a 5-month old upper the vehicle was passing near the southern-most 98.5 degrees at the time of the event. A stage disintegrated into more than 300 portion of South America. Gabbard diagram of 280 tracked debris on 6 fragments large April (accompanying enough to be 1800 figure) indicated a tracked by the U.S. large altitude Space Surveillance dispersion of the Network (SSN). 1600 debris. A majority The vehicle Perigee (60%) of the debris (International Apogee was found in higher Designator 1999- 1400 orbits than the parent, 057C; U.S. but this may be due Satellite Number 1200 to the rapid decay of 25942) was the some debris thrown third stage of the in retrograde Chinese Long 1000 directions. March 4 booster Interestingly, the which had number of debris successfully (km) Altitude 800 with inclinations deployed the lower than the parent China-Brazil Earth was exactly the same: Resources Satellite 600 60%. However, due (CBERS 1) and the to the far southern Brazilian Satellite 400 latitude of the event, Cientifico (SACI all inclination 1) spacecraft on 14 changes were small: October 1999. 200 +/- 1 degree. Independent U.S. 94 96 98 100 102 104 106 108 110 112 and Russian (Continued on page 2) Orbital Period (min) Inside... 1999 Leonid Meteor Observations at the Johnson Space Center .......................................... 2 Compton Gamma Ray Observatory to be Deorbited .............................................................6 Kessler Receives Losey Award ................................................................................................. 7 Reentry Assessment for Taurus Upper Stage Performed ...................................................... 9 1 The Orbital Debris Quarterly News NEWS The First Satellite Breakup of 2000, Continued (Continued from page 1) this time after only a month on orbit. This Chinese analyses following the 1990 This mission was only the fourth for this earlier fragmentation, which took place at a breakup determined that the most likely cause version of the Long March launch vehicle higher altitude of 895 km, produced of the fragmentation was the residual family. The first two missions were flown in substantially fewer large debris. Less than 90 hypergolic propellants. Plans to passivate the 1988 and 1990, and flights did not resume until debris had been cataloged by the beginning of Long March 4 upper stage apparently were not 1999. The second mission in September 1990 this year. Cataloging of the debris from 1999- implemented for the two flights in 1999. was followed by a breakup of the third stage, 057C did not begin in earnest until April. 1999 Leonid Meteor Observations at the Johnson Space Center J. Pawlowski developed at JSC. The results were compared to small mass), however these meteors can be The November 1999 Leonids Meteor the Leonid Mass Distribution Model derived at detected by the LMT. Storm was videotaped on the grounds of the JSC and used in conjunction with orbital debris A modification of the software used to NASA Johnson Space Center (JSC) in models to compute risk assessments before each analyze orbital debris detected by the LMT has Houston, Texas and at the JSC observatory in Space Shuttle mission. recently enabled analysis of the Leonid Cloudcroft, New Mexico. Low light level video The observed data compared favorably to Meteors also detected by that instrument. This cameras were used in both locations and our the model in the .01 to.2 gram range but will result in a sizable sample of faint Leonid Liquid Mirror Telescope (LMT) was used at differed for the smaller masses. The difference Meteors for a complete comparison to the Cloudcroft. can be attributed to the limitations of the low model. The low light level videotapes were light level video equipment. This equipment is analyzed using a meteor analysis system unable to detect the faint meteors (those of HAPS Debris Separation Velocity Distribution P. Anz-Meador Meirovitch [Ref.2]. This technique is judged to mapped into the relevant planes. The X-Y The separation velocities of debris provide a superior mean of calculating delta-v, plane represents the local horizontal plane. The produced by a fragmentation event, hereafter based upon (a) the in-plane delta-v components X-Z plane represents the in-orbit plane referred to as the delta-v distribution, is of are similar to the cloud’s Gabbard diagram, (b) components, and the Y-Z plane represents interest because the magnitude and directional the magnitude of the delta-v vector is velocity components perpendicular to the (angular) distribution governs the initial comparable with the Gabbard diagram’s 450- tangential velocity (approximately the on-orbit deposition of a debris cloud throughout space 500 m/s maximum, and (c) there is a correlation velocity of the HAPS stage). Figures 4A, 4B, and provides information as to the severity or between delta-v and AOM, as should be and 4C depict these mappings, respectively. energetics of the event. The latter may be expected if more massive objects are associated The X-Z plane is also the local horizontal evidenced by the isotropy or anisotropy of the with low-AOM debris and less massive objects plane. Figure 4A indicates that the event directional distribution. We have examined the are associated with high-AOM debris. Figures distributed debris symmetrically about the orbit Hydrazine Auxiliary Propulsion Stage (HAPS) 1 and 2 illustrate conditions (b) and (c); figure 1 plane and, apparently , asymmetrically along rocket body debris cloud associated with the categorizes the magnitude of the delta-v vector the dv_T axis. As seen in Figure 4B, the in- STEP II launch (1994-029B) to characterize the for each object into 50 m/s bins. orbit plane components mimics the Gabbard cloud [Ref.1]; in this paper we examine the diagram as should be expected since only these delta-v distribution in particular. Angular Distributions components affect the change in semimajor Two methods were examined. The first A coordinate frame was defined such that axis, and hence orbital period, of each debris utilized US Space Command SGP4 v. 3.01 X (denoted by dv_T) points in the direction of object. Figure 4C again indicates an event software and the pseudo-ballistic coefficient the tangential velocity, Y (denoted by dv_L) symmetric about the orbit plane. The apparent B*, averaged over two solar rotations, to points in the direction of the positive orbit anisotropy evident in these figures, with the propagate the first cataloged element set of each angular momentum vector, and Z (denoted by majority of the debris delta-v vector piece back in time to the time of the dv_R) points in the radial or zenith velocity components oriented towards the velocity fragmentation event. Delta-v was then direction. The most convenient angles in this vector, may be attributable to atmospheric calculated by vector subtraction of the state coordinate system are pitch and yaw; pitch is removal of a portion of the original debris cloud vector velocity components. This technique defined to be positive for positive Z delta-v rather than being representative of a true provided poor results, as indicated by extreme components. Yaw is defined to be positive asymmetry. The time scale for atmospheric scatter in the delta-v calculated. The second when measured in a counter-clockwise direction removal due to object reentry ranges from technique utilized the Orbital Debris Program about the +Z axis, i.e. as in a standard right- immediately after the fragmentation event to a Office’s THALES program and the median handed coordinate system. Figure 3 depicts the relatively long life, based upon perigee height. estimated area-to-mass (AOM) ratio to distribution in yaw-pitch space. However, coupled with current US Space propagate the debris elements to the event time. To further examine the angular Delta-v was calculated using the equations of distribution, the debris delta-v components were (Continued on page 3) 2 The Orbital Debris Quarterly News NEWS HAPS Debris Separation Velocity Distribution, Continued (Continued from page 2) distribution of the velocity vectors. The However, the frequency distribution is a further Command cataloging criteria, the initial perigee frequency of higher velocities in the HAPS indicator of the unique nature of the HAPS height distribution can significantly alter the debris cloud differs significantly from similar rocket body fragmentation. apparent directionality of the debris cloud. distributions computed for the SPOT-1/Viking Ariane H8 rocket body, the P78G-1 References Discussion (SOLWIND) collision, and various Cosmos- [Ref.1] Settecerri, T., P. Anz-Meador, and N. The apparent symmetry of the debris cloud series fragmentations. Only in the case of the Johnson, “Characterization of the Pegasus-Haps indicates a fairly anisotropic directional Delta rocket body historical fragmentations do Breakup.” Presented at the 50th IAF Congress, distribution, given the limits imposed by we encounter velocities of a similar magnitude, Amsterdam, the Netherlands, October 1999. cataloging and the breakup altitude. However, although the relative frequency of HAPS debris low pitch angles are not apparent in either exceeds that of the Delta debris. This is [Ref.2] Meirovitch, L. Methods of Analytical Figure 3 or 4B, perhaps indicative of the probably indicative of the initial fragmentation Dynamics. McGraw Hill, 1970. In R. Kling, explosion occurring in the rear portion of the impulse and the combination of small sizes and “Postmortem of a Hypervelocity Impact: HAPS stage, i.e. that portion of the stage low masses of the HAPS debris, which may be Summary”, Teledyne Brown Engineering report oriented away from the velocity vector.
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