Designing a space debris removal mission targeting a Cosmos 3M rocket body in leo using a chemical engine and an elechtrodynamic tether to perform the de-orbiting
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- Proton Family of Launch Vehicles
- Simulation of Launch
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Soyuz Launch VehicleThe Soyuz family of launch vehicles is the world’s most successful launch system, with more than 1200 launches and an overall success rate of about 96.8 %. It is based on the R-7 ICBM design and has been in service since 1963. The current operational models are the Soyuz-U, Soyuz-FG, and Soyuz 2. The Soyuz 2 vehicle is planned to replace all previous models by 2014. Hence, we will focus on this vehicle. The Soyuz 2 is a 4 stage launch vehicle, with an overall length of 43.42 m, maximum diameter of 10.3 m and a maximum lift off mass of 311.7 tons. It can launch up to 4.9 tonnes to a sun-synchronous orbit with an altitude of 820 km, inclination of 98.7 degrees from the Plesetsk cosmodorme. Table summarizes some of the characteristics of the soyuz 2 vehicle. Table : Soyuz 2 characteristics
An analysis of Soyuz launches during the last 3 years (2009-2011) was performed using online resources which are summarized in Table . Not much data was available about non LEO launches. For launches to the ISS, an elliptical parking orbit was used with an inclination of 51.62-51.68 degrees, a perigee of 189.6-201.2 km, an apogee of 232.41-267.02 km and a period of 88.47-88.87 minutes (7). Table : Soyuz launch statistics 2009-2011 (8)
Figure : Fregat upperstage mission profile (SSO orbit from Guiana Space Center) (9) Proton Family of Launch VehiclesThe proton family of launch vehicles is another successful Russian/Soviet launch system. It has been in service since 1965, with more than 400 launches and a success rate of about 90%. The Proton M vehicle is currently operational and we will focus only on this vehicle. The Proton M vehicle is a 4 stage launch system, capable of delivering 19975 kg to a 170 km circular orbit at an inclination of 75 degrees from Baikonur. It has a length of 57.2 m, a maximum diameter of 7.4 m and a maximum lift off mass of 691.27 t. Table summarizes the characteristics of this vehicle. It should be noted that the Angara launch vehicle family which is going to replace the proton vehicle in the future will be using the same upper stage. Table : Characteristics of the Proton M launch vehicle (6)
The proton launches for the last three years (2009-2011) were analyzed for patterns of target orbits. The results are summarized in Table . The most detailed data existed for GEO launches by Proton M. It revealed that typically a parking orbit with an altitude of 173 km, an inclination of 51.5 degrees and a RAAN of 9 degrees was used (10). Table : Proton M launches (2009-2011) (8)
Figure : Typical Proton M mission profile (10) Simulation of LaunchCHALLENGES
References1. Instability of the present LEO satellite populations. Liou, J.C e Johnson, N.L. 7, 2008, Advances in Space Research, Vol. 41, p. 1046-1053. 2. Chatters, E.P. e Crothers, B.J. Space Surveillance Network. AU-18 Space Primer. 2009. 3. United States Strategic Command: Space Track. [Online] http://www.space-track.org. 4. Collision activities in the future orbital debris environment. Liou, J.C. 9, 2006, Advances in Space Research, Vol. 38, p. 2102-2106. 5. Satellite Collision Leaves Significant Debris Clouds. Orbital Debris - Quarterly News. s.l. : NASA, 2009. Vol. 13. 6. European Space Agency. Launch Vehicle Catalogue. s.l. : European Space Agency, 2004. 7. History of Flights. S. P. Korolev Rocket and Space Corporation (Energia). [Online] http://www.energia.ru/en/archive/launch-book.html. 8. Space Launch Log. [Online] http://www.spacelaunchreport.com/. 9. Soyuz from the Guiana Space Center User's Manual. 2006. 1. 10. Launch Information Processing and Display Center (LIPDC). Khrunichev (KhSC) State Research and production Space Center. [Online] http://coopi.khrunichev.ru/main.php?id=11. 11. Isakowitz, Steven J., B., Hopkins Joshua e P., Hopkins Joseph. International Reference Guide to Space Launch Systems. s.l. : American Institute of Aeronautics and Astronautics, 2004. 12. Characterization of the cataloged Fengyun-1C fragments and their long-term effect on the LEO environment. Liou, J.C e Johnson, N.L. 2009, Advances in Space Research, Vol. 43, p. 1407-1415. 13. [Online] http://www.satellitedebris.net/whatsup/. Directory: resources resources -> General text for tender (recommendations) for Pilkington Profilit™ Contents Page resources -> North Carolina Inclusion Initiative Mapping Where Children with ieps are Being Served Purpose resources -> Practice learning resources -> The Rise of Video Games Section “Word” Matt Spencer resources -> Request for proposal contract form for the transit industry resources -> Request for Proposal [insert date] resources -> The University of York 13th 16th April 2004 resources -> Biological and Biomedical Sciences Program Community Education Initiative resources -> Region III standing regional response team (rrt) meeting williamsburg, Virginia Thursday, January 12, 2012 resources -> Efca eastern District and TouchGlobal, the crisis response ministry of efca Download 173.09 Kb. Share with your friends:
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