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Optimizing the trajectory of a spacecraft using an ideally regulated engine in the vicinity of a circular orbit
Table 1 - Results of calculating the magnitudes of velocity impulses and fuel consumption
t | ∆V2, m/s | m2, kg | ∆V3, m/s | m3, kg |
0 | 10.488 | 4.848 | 10.488 | 4.848 |
1.064 | 58.42 | 26.706 | 57.292 | 26.197 |
2.128 | 123.535 | 55.633 | 121.697 | 54.828 |
3.192 | 125.168 | 56.347 | 123.988 | 55.831 |
4.256 | 64.238 | 29.326 | 64.015 | 29.226 |
5.32 | 56.033 | 25.629 | 54.727 | 25.039 |
6.384 | 66.243 | 30.228 | 65.314 | 29.81 |
7.448 | 32.93 | 15.142 | 32.735 | 15.053 |
8.512 | 29.706 | 13.67 | 29.086 | 13.386 |
9.576 | 26.879 | 12.377 | 26.827 | 12.353 |
10.64 | 30.929 | 14.229 | 29.957 | 13.785 |
11.704 | 55.771 | 25.511 | 54.391 | 24.887 |
12.768 | 49.57 | 22.706 | 48.889 | 22.398 |
13.832 | 23.014 | 10.607 | 23.057 | 10.626 |
14.896 | 5.891 | 2.726 | 5.613 | 2.597 |
15.963 | 0.0027 | 0.00125 | 0.0024 | 0.00111 |