![]() ![]() Orbit quantities including a semi-major axis deviation |delta a|, a tilt angle deviation |delta i|, and an eccentricity deviation |delta e| in satellite injection are used to determine whether maximum deviation of |delta aL|, |delta iL| and |delta eL| given by a carrier rocket are met and if all the maximum deviation are met, the satellite injection result is "a complete success". 230000035807 sensation Effects 0.000 description 1Ī satellite injection success evaluation method.230000001133 acceleration Effects 0.000 claims description 2. ![]() ![]()
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