Fuel consumption and collision avoidance strategy in multi-static orbit formations |
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| Authors: | E.F. Jochim H. Fiedler G. Krieger |
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| Affiliation: | 1. Department of Electrical and Computer Engineering, University of Missouri, Columbia, MO 65201, USA;2. Department of Biological Engineering, University of Missouri, Columbia, MO 65201, USA;3. General Atomics Electromagnetic Systems, San Diego, CA 92127, USAn;4. Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO 65201, USA;1. Department of Mechanical Engineering, Stanford University, Stanford, CA 94305, USA;2. Department of Mechanical Engineering, Massachusetts Institute of Technology, Cambridge, MA 02139, USA;3. Department of Materials Science and Engineering, Stanford University, Stanford, CA 94305, USA;1. Department of Biomedical, Biological, and Chemical Engineering, University of Missouri, Columbia, MO 65211, United States;2. Department of Engineering and Technology, Southern Utah University, Cedar City, UT 84720, United States;3. Department of Electrical Engineering and Computer Science, University of Missouri, Columbia, MO 65211, United States;4. Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO 65211, United States;5. Department of Chemical Engineering, University of Maryland, College Park, MD 20740, United States;6. Department of Chemical Engineering and Material Science, University of California, Riverside, CA 95207, United States;1. Department of Biological Engineering, University of Missouri, Columbia, MO 65211, United States;2. Department of Electrical and Computer Engineering, University of Missouri, Columbia, MO 65211, United States;3. Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO 65211, United States |
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| Abstract: | This paper analyses the fuel consumption of interferometric radar missions employing small satellite formations like, e.g., Cross-track Pendulum, Cartwheel, CarPe, or Trinodal Pendulum. Individual analytic expressions are provided for each of the following contributions: separation from a simultaneously injected master satellite, formation set-up, orbit maintenance, formation maintenance, and distance maintenance. For this, a general system of equations is derived describing the relative motion of the small satellites in a co-rotating reference frame. The transformation into Keplerian elements is carried out. To evaluate fuel consumption, three master satellites are assumed in different orbital heights, which are typical for Earth observation missions. The size of the exemplarily analysed formations is defined by remote sensing aspects and their respective fuel requirements are estimated. Furthermore, a collision avoidance concept is introduced, which includes a formation separation and formation set-up after a desired time period. |
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