Relative orbit design and high-precision attitude and pointing control method for non-cooperative space targets
A non-cooperative target and relative orbit technology, which is applied in the field of relative orbit design and high-precision attitude pointing control, can solve problems that affect attitude pointing accuracy and orbit control difficulties, and achieve the purpose of suppressing constant interference, not easily revealing identity, and maintaining stability Effect
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specific Embodiment approach 1
[0043] Specific implementation mode one: the relative orbit design and the high-precision attitude pointing control method for space non-cooperative target spacecraft of the present embodiment, it is realized according to the following steps:
[0044] 1. The design of the skimming trajectory of the tracking spacecraft relative to the non-cooperative target spacecraft in space;
[0045] 2. The design of the transfer trajectory of the tracking spacecraft relative to the non-cooperative target spacecraft in space;
[0046] 3. The attitude controller design of the tracking spacecraft relative to the space non-cooperative target spacecraft, that is, the relative orbit design and high-precision attitude pointing control method for space non-cooperative targets have been completed.
[0047]x, y, z: position components in the relative orbital coordinate system;
[0048] the velocity component in the relative orbital coordinate system;
[0049] r 0 : The relative position of the e...
specific Embodiment approach 2
[0062] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the design of the flying trajectory in the step one is specifically:
[0063] 1. Establish the relative positional relationship between the space non-cooperative target and the spacecraft in the relative motion coordinate system of the hill equation
[0064] Select the appropriate entry point A information and exit point B information of the spacecraft based on the relative motion coordinate system of the hill equation
[0065] In the relative motion coordinate system based on the hill equation, such as figure 1 Shown e=[e 1 ; e 2 ; e 3 ] is the sight direction vector e of the non-cooperative target hill The unit vector of e i (i=1,2,3) is the component in the relative motion coordinate system of the hill equation; the line of sight direction e h i ll The range of distance between the target spacecraft and the tracking spacecraft determines the allowable grazing range ...
specific Embodiment approach 3
[0102] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is:
[0103] Orbit Transfer Optimization Algorithm
[0104] 1. Transformation of nonlinear programming problems
[0105] Assuming that there are N speed pulse points in the whole orbit transfer process (the start point and the end point are two fixed pulse points), define Δt i is the time interval between the i-th speed pulse point and the i+1-th speed pulse point, t f is the total transfer time.
[0106] From the previous analysis, the following expression can be obtained:
[0107]
[0108] in ——Indicates the speed of the tracking spacecraft before applying the i-th speed pulse;
[0109] ——Indicates the velocity of the tracking spacecraft after the i-th velocity pulse is applied.
[0110] Then the i-th velocity pulse increment imposed by the tracking spacecraft is:
[0111]
[0112] in, Considering that the fuel that the spacecraft can carry is always ...
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