Space Debris Research in Shanghai Institute of Satellite Engineering

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Rudolf Hodges
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1 Space Debris Research in Shanghai Institute of Satellite Engineering Shen Junfeng (by Zhao Fagang) Laboratory of Space Mechanical and Thermal Integrative Technology (MTIT) October 2011 Date: 10/21/2011 Page: 1/13

2 Outline The Orbital Debris Environment Lifecycle Space Debris Mitigation Design Reorbit Tests of GEO Satellites Active Orbital Debris Removals Active Avoidance Maneuvers Conclusions Date: 10/21/2011 Page: 2/13

3 The Orbital Debris Environment Growth of the Satellite Population Over 16,000 objects (>10cm in diameter) tracked by U.S. Space Surveillance Network in 2011 Date: 10/21/2011 Page: 3/13

4 The Orbital Debris Environment Threatens of Space Debris Increasing Probability of Collisions collision happened between Irdium Satellite and Cosmos satellite in 2009 Potential Damage on Human Beings on Earth the reenter event of the U.S. s satellite (UARS) has already triggered the panic around the world in 2011 Figure 1 Configurations of an Irdium satellite (left) and one Cosmos satellite (right) Figure 2 Configurations of an UARS satellite Date: 10/21/2011 Page: 4/13

5 Lifecycle Space Debris Mitigation Design The space debris mitigation measures of GEO satellites are focus on the following four areas: Limitation of debris of the GEO satellites during normal operations; Minimization of the potential for on-orbit break-ups; Post-mission disposal; Prevention of on-orbit collisions. Date: 10/21/2011 Page: 5/13

6 Lifecycle Space Debris Mitigation Design Plans for debris mitigation GEO GTO Design Phase Plans for assessment and mitigation of risks Plans for disposal Earth Lifecycle space debris mitigation design of one GEO satellite Launch Phase Mission Phase Minimise release debris Minimise potential break-ups Surveillance and failure mode detection Grave orbit Transfer orbit Prevention of on-orbit collisions Earth Affirmance the beginning of disposal phase GEO Post-mission disposal Phase Strategy and managment of reorbit Passivation management Figure 3 Lifecycle space debris mitigation design of one GEO satellite Figure 4 Launch phase and post-mission disposal phase of one GEO satellite Date: 10/21/2011 Page: 6/13

7 Reorbit Tests of GEO Satellites The Reorbit Test of one GEO Weather Satellite is Implemented in 2006; During the reorbit test: the cumulative operation numbers of the satellite s control system is over 1,800 times; the vessels pressure dropped below 1.7 MPa; the remaining fuel is exhausted. At the end of the reorbit test: the anchor point of this satellite is degrees east longitude; the satellite drifts west by the rate of 0.75 degrees per day Figure 5 Configurations of one GEO weather satellite Date: 10/21/2011 Page: 7/13

8 Reorbit Tests of GEO Satellites The Other Reorbit Test of one GEO Weather Satellite is Implemented in 2007; In accordance with the IADC Space Debris Mitigation Guidelines Based on the disposal of experience of the former GEO weather satellite. At the end of the reorbit test: The perigee altitude and apogee altitude of the orbit of this GEO satellite are more 800 km and 1,650 km higher than the nominal elevation. GEO protected regions HGEO LEO region HGEO-200km 15 8% 8% Euqator 15 HGEO+200km Earth Figure 6 GEO protected regions Date: 10/21/2011 Page: 8/13

9 Active Orbital Debris Removals Table 1 Survey of solutions for active orbital debris removals LEO GEO Debris size <1cm 1 to 10cm Large (derelict spacecraft or expended rocket bodies) Large (derelict spacecraft or expended rocket bodies) Number of objects Millions 150,000 objects in LEO over 16,000(>10cm) Hundreds Potential options spacebased magnetic field generator / space based laser magnetic sail solar sail airborne based laser momentum tethers momentum tethers ground based laser (Orion) drag augmentation device capture/orbital transfer vehicle / / electrodynamic tethers attachable propulsive module / / attachable prop module or OTV / Systems with most potential no practical solutions Ground based lasers studied by MSFC in 1990s show promise. Advances in pico pulsed lasers may bring desirable effects. All 1-10cm debris under 1500 km in altitude could be removed in approx 3-5 years with one facility located near the equator. Either a electrodynamic tether or a large device must be attached to the large spacecraft via drawback to tethers is the reentry point is not controllable whereas a propulsive deorbit module allows precision guidance upon disposal. Decay times with tethers go from 325 yrs at an 800 km orbit to 200 days. GEO space junk needs to be put into a disposal or graveyard orbit at least 300 km greater in altitude than GEO. A space based vehicle stationed at GEO seems to offer the best solution. AR&D or Capture is needs. Propulsion options between storable or ion system driving design factor. Date: 10/21/2011 Page: 9/13

10 Active Orbital Debris Removals Advantages of tether technology: non-polluting; Lower energy requirements; Lower accuracy requirements; Flexible and reliable. Grave orbit Capture types suited for tether technology: Network structure; Clutch mechanism; Electromagnet; Cone / cone cover; Combination of capture mechanism. T P T GEO P P T P T P Release phase For the next P GTO P Patrol phase From GTO to GEO Approaching phase Capture phase Transfer phase P: platform T: debris target Figure 7 Procedure of tether assisted removal system Date: 10/21/2011 Page: 10/13

11 Active Avoidance Maneuvers In 2009, there was a uncertainty space debris would approach to one satellite on October 3 and the shortest distance might be only 160 m; First of all, the status of the satellite was confirmed within the ability of the domestic monitoring stations; Then the data packs were injected to altitude the satellite orbit height; On October 3, data showed that the altitude error was less than 4 m, the eccentricity error was less than three hundred thousandths, and the collision probability declined to Date: 10/21/2011 Page: 11/13

12 Conclusions Shanghai Institute of Satellite Engineering have made great breakthrough about debris mitigation in the following aspects: lifecycle space debris mitigation design of GEO satellites; reorbit technology of abandoned GEO satellites; active orbital debris removals; active avoidance technology. Date: 10/21/2011 Page: 12/13

13 Thanks! Date: 10/21/2011 Page: 13/13

US ACTIVE DEBRIS REMOVAL (ADR) EFFORTS

US ACTIVE DEBRIS REMOVAL (ADR) EFFORTS DR. DARREN MCKNIGHT VIENNA UN COPUOS FEBRUARY 2013 1 DISCLAIMER This presentation solely represents the opinions of the author and should not be construed as being