Iterative guidance method for interstellar transfer limited thrust into orbit of low thrust-to-weight ratio vehicle
A thrust-to-weight ratio, aircraft technology, applied in the aerospace field, can solve problems such as non-convergence in solving constraint equations, inability to solve orbital transfer problems, long calculation time, etc.
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[0084] Taking the Earth-Moon transfer as an example, in order to verify the feasibility of the method, we choose to start guidance from the Earth's near-Earth 170km circular orbit at 8:00 pm on October 12, 2020, and the goal is to reach the Moon's 300km altitude orbit. The parameters of the detector engine during the guidance process are shown in Table 1, and the initial state and the state of the reference orbit point are shown in Table 2:
[0085] Table 1 Initial detector engine parameters
[0086]
[0087] Table 2 Initial state and terminal state
[0088]
[0089] Such as figure 1 As shown, a low thrust-to-weight ratio interstellar transfer limited thrust iterative guidance method for orbital transfer disclosed in this embodiment, the specific implementation steps are as follows:
[0090] Step 1: Establish the dynamic equation of the detector under the inertial system of the earth's center of mass.
[0091] The probe moves outside the earth's atmosphere, and the ex...
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