Study the Influence of Atmospheric Drag and J2 Effect in a Close-proximity Operation at LEO

 
 
 
  • Abstract
  • Keywords
  • References
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  • Abstract


    In this paper is to assess the mission stability and the influence of J2 effect and aerodynamic forces. To maintain the relative motion of satellites by using a feedback control law for tracking error bound in the presence of J2 perturbation. A constant relative orbit under the effect of earth oblateness and conservative forces is referred as J2 and targeting the presence of atmospheric drag. Although, Schweighart and Sedwick control strategy for satellite relative motion is considering both lift and drag forces. The simulation result shows a better performance with high accuracy than an elliptical orbit under J2 perturbation and atmospheric drag along in-track formation. The algorithm and control strategies is useful tools for analysing a future space mission. 

     

     


  • Keywords


    Cartosat-2C, J2 Effect, Atmospheric Drag, Close-Proximity, Low Earth Orbit.

  • References


      [1] Healy, L. M., and Henshaw, C. G., (2015) “Trajectory Guidance Using Periodic Relative Orbital Motion,” Journal of Guidance, Control, and Dynamics, Vol. 38, No. 9, pp. 1714–1724.

      [2] Sinclair, A. J., Sherrill, R. E., and Lovell, (2014) T. A., “Calibration of Linearized Solutions for Satellite Relative Motion,” Journal of Guidance, Control, and Dynamics, Vol. 37, No. 4, pp. 1362– 1367.

      [3] Chamberlin, J. A., and Rose, J. T., (1964) “Gemini Rendezvous Program,” Journal of Spacecraft and Rockets, Vol. 1, No. 1, pp. 13–18.

      [4] Koenig, A., Guffanti, T., and D’Amico, S., (2016), “New State Transition Matrices for Relative Motion of Spacecraft Formations in Perturbed Orbits,” AIAA/AAS Astrodynamics Specialist Conference, AIAA Paper 2016-5635.

      [5] Scharf, D.P., Hadaegh,F.Y., and Ploen, S. R., (2004) “A Survey of Spacecraft Formation Flying Guidance and Control (Part 2): Control,” Proceedings of the 2004 American Control Conference, IEEE Publ., Piscataway, NJ, pp. 2976–2985.

      [6] Alfriend, K. T., and Yan, H., (2005), “Evaluation and Comparison of Relative Motion Theories,” Journal of Guidance, Control, and Dynamics, Vol. 28, No. 2, pp. 254–261.

      [7] Russell, R., (2012), “Survey of Spacecraft Trajectory Design in Strongly Perturbed Environments,” Journal of Guidance, Control, and Dynamics, Vol. 35, No. 3, pp. 705–720.

      [8] Gaias, G,., Ardaens, j.S and Montenbruck,O., (2015), “Model of J2 Perturbed Satellite Relative Motion with Time-Varying Differential Drag,” Celestial Mechanics and Dynamical Astronomy, Vol. 123, No. 4, pp. 411–433.

      [9] Bevilacqua, R., and Lovell, T. A., (2014), “Analytical Guidance for Spacecraft Relative Motion Under Constant Thrust Using Relative Orbit Elements,” Acta Astronautica, Vol. 102, pp. 47–61.

      [10] Biria,A., and Russell,R., (2016), “ A satellite Relative Motion ModelUsing J2 and J3 via Vinti’s Intermediary” AIAA/AAS Space Flight Mechanics Conference, AAS Paper 16-537, Napa, CA.

      [11] Alfriend, K.,Vadali,S.R.,Gurfil,P.,How,J.,and Breger,L., (2009), ”Spacecraft Formation Flying: Dynamics, Control and Navigation”, Vol. 2, Butterworth Heinemann, Burlington, MA, 2009, pp. 25–28.

      [12] Chamberlin, J. A., and Rose, J. T., (2012), “Gemini Rendezvous Program,” Journal of Spacecraft and Rockets, Vol. 1, No. 1, 1964, pp. 13–18.

      [13] Sinclair, A. J., Sherrill, R. E., and Lovell, T. A., (2014), “Calibration of Linearized Solutions for Satellite Relative Motion,” Journal of Guidance, Control, and Dynamics, Vol. 37, No. 4, pp. 1362– 1367.

      [14] Goodman, J. L., (2006), “History of Space Shuttle Rendezvous and Proximity Operations,” Journal of Spacecraft and Rockets, Vol. 43, No. 5, pp. 944–959.

      [15] Schweighart, S, A., and Sedwick, R.J., (2002), "High-Fidelity Linearized J Model for Satellite Formation Flight," Journal of Guidance, Control, and Dynamics, Vol. 25, No. 6, pp. 1073-1080.

      [16] Bevilacqua, R., and Romano, M., (2008), “Rendezvous Manoeuvres of Multiple Spacecraft Using Differential Drag Under J2 Perturbation,” Journal of Guidance, Control, and Dynamics, Vol. 31, No. 6, pp. 1595– 1607.

      [17] Alfriend, K. T., and Yan, H., (2002), “An Orbital Elements BasedApproach to the Nonlinear Formation Flying Problem,” Proceedings of the International Formation Flying Conference: Missions and Technologies, Toulouse, France.

      [18] Gaias, G., Ardaens, J.-S., and Montenbruck, O., (2015), “Model of J2 Perturbed Satellite Relative Motion with Time-Varying Differential Drag,” Celestial Mechanics and Dynamical Astronomy, Vol. 123, No. 4, pp. 411–433.

      [19] Gaias, G., Ardaens, J.-S., and D’Amico, S., (2014), “The Autonomous Vision Approach Navigation and Target Identification (AVANTI) Experiment: Objectives and Design,” Proceedings of the 9th International ESA Conference on Guidance, Navigation & Control Systems, Porto, Portugal.

      [20] Gaias, G., D’Amico, S., and Ardaens, J.-S., (2015), “Generalised Multi- Impulsive Manoeuvres for Optimum Spacecraft Rendezvous in Near- Circular Orbit,” International Journal of Space Science and Engineering, Vol. 3, No. 1, pp. 68–88.

      [21] Gaias, G., and D’Amico, S., (2015), “Impulsive Manoeuvres for Formation Reconfiguration Using Relative Orbital Elements,” Journal of Guidance, Control, and Dynamics, Vol. 38, No. 6, pp. 1036– 1049.

      [22] Gaias, G., and Ardaens, J.-S., (2016), “Design Challenges and Safety Concept for the AVANTI Experiment,” Acta Astronautica, Vol. 123, pp. 409–419.

      [23] Alfriend, K. T., Gim, D.-W., and Schaub, H.,(2000), “Gravitational Perturbations, Nonlinearity and Circular Orbit Assumption Effects on Formation Flying Control Strategies,” Proceedings of Guidance and Control, pp. 139–158.

      [24] Gurfil, P., and Kasdin, N. J., (2004), “Nonlinear Modelling of Spacecraft Relative Motion in the Configuration Space,” Journal of Guidance, Control, and Dynamics, Vol. 27, No. 1, pp. 154–157.


 

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Article ID: 23815
 
DOI: 10.14419/ijet.v7i4.36.23815




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