Consider the interaction of a spacecraft with the LEO equatorial plasma. Assume

Question

Consider the interaction of a spacecraft with the LEO equatorial plasma. Assume that the spacecraft (a) has a conductive structure with total surface area A_tot and cross-sectional area A_cs;(b) is negatively grounded to a solar array of width w and length l;and (c) 0.2% of solar array surface area is exposed metallic interconnects. Starting from 4.43 and the constraint that the sum of the current to the entire system (the structure and the solar array must be zero, obtain a closed-form solution for the floating potential of the structure (i.e., the value of f in equation 4.43). Verify that, depending on the ratio A_cs/wl, the spacecraft can float negative by a significant fraction of the array voltage.

Explanation / Answer

please give equation 4.43

your question asks to start from equation 4.43. without which we can not proceed. OR you can also give reference to the book from where you have posted this question so we can see equation 4.43 there.

Thanks!

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