Underactuated Release Control Method Based on Nonlinear Space Tether System
A space tethering and release control technology, applied in non-electric variable control, vehicle position/route/height control, attitude control, etc., can solve the problem of insufficient radial release control perturbation factors, time-consuming calculation, and lack of global stability Sexual Analysis, etc.
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[0092] The parameters are selected to numerically verify the stability of the release control process of the tethered satellite system. Let the true anomaly angle v at the initial moment of the system be 0 = 0, dimensionless tether length ξ 0 =0.01, and the eccentricity of the Kepler orbit e=0.05, the stability of the system near the equilibrium point can be determined based on the Floquet theory.
[0093] Study the desired out-of-plane roll angle φ e = 0 where the equilibrium point (θ e ,0,φ e ,0), according to the expression (11) of the value range of the expected in-plane pitch angle, we can get θ e ∈[-π / 4,-0.0334). Numerical simulation can obtain the relationship between the maximum eigenvalue modulus of the single-valued matrix of the system within the definition domain and the pitch angle in the expected plane, as shown in image 3 shown. It can be seen from the figure that for φ e =0, when the desired pitch angle θ e ∈[-π / 4,-0.0334), there is |λ i | max e ∈[-...
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