Switching controller design method of constrained space spacecraft orbital rendezvous system
A technology of orbital rendezvous and design method, which is applied in the aerospace field and can solve problems such as the failure of space spacecraft rendezvous missions
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[0064] A switching controller design method for constrained spacecraft orbital rendezvous, the design of the controller specifically includes the following steps:
[0065] a) The nonlinear differential equation of the spacecraft orbital rendezvous system is established, as follows:
[0066]
[0067] Among them, x, y, z, Respectively represent the relative distance and relative speed of the tracking spacecraft relative to the target spacecraft on the X, Y, and Z axes, a X , a Y and a Z Respectively represent the acceleration in the X, Y, Z axis, ω>0 ( η is the gravitational constant, R is the target orbital radius) is the orbital angular velocity of the target spacecraft. where the non-linear term
[0068] (b) Using Taylor series expansion, the nonlinear term Linearize and preserve to first-order terms, while selecting the state vector The following state space expression can be obtained
[0069]
[0070] where Sat represents an asymmetric saturation function,...
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