Error constraint control method for unmanned surface vehicle considering input saturation
A technology of error constraints and control methods, applied in two-dimensional position/channel control, adaptive control, general control system, etc., can solve the problem of low navigation control accuracy of surface unmanned boats, and improve navigation control accuracy , reduce errors, and solve the effect of low navigation control accuracy
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specific Embodiment approach 1
[0031] Specific implementation mode one: combine figure 1 Describe this embodiment, the specific process of an error-constrained control method for an unmanned surface vehicle considering input saturation in this embodiment is:
[0032] Ground coordinate system (O-XY): The coordinate origin O is located at the junction of the mooring line and the mooring terminal, and the plane where the XY axes are located is parallel to the ground.
[0033] Satellite coordinate system (o-xy): the origin o of the coordinates is located at the center of gravity of the surface unmanned boat, the x-axis points from the stern to the bow along the longitudinal axis, and the y-axis points to the port side.
[0034] Trajectory tracking control method: pre-set the sailing route of the surface unmanned boat, and control the surface unmanned boat to sail according to this trajectory.
[0035] Barrier Lyapunov function method in tan form: a state constraint control method based on the potential functi...
specific Embodiment approach 2
[0045] Specific embodiment two: the difference between this embodiment and specific embodiment one is that the closed-loop system of the surface unmanned boat is established in the step one; the specific process is:
[0046] Determine the symmetric positive definite inertia matrix M, the centripetal force and Coriolis force matrix C(ν), and the damping matrix D(ν);
[0047] According to the nature and hydrodynamic parameters of the target surface unmanned vehicle, the above M, C(ν), D(ν) can be determined;
[0048] Based on the symmetric positive definite inertia matrix M, the centripetal force and Coriolis force matrix C(ν), and the damping matrix D(ν), determine the non-singular transformation matrix J(η) of the surface unmanned vehicle from the satellite coordinate system to the ground coordinate system ;
[0049] And establish restoring force g (η) and unknown disturbance w according to the corresponding situation;
[0050] build the desired trajectory x 1d =[x 11d (t)...
specific Embodiment approach 3
[0063] Specific embodiment three: what this embodiment is different from specific embodiment one or two is that the inertial matrix M of described symmetry positive definite, centripetal force and Coriolis force matrix C (ν), and the expression of damping matrix D (ν) are as follows :
[0064]
[0065]
[0066]
[0067] Among them, m is the mass of the target surface unmanned vehicle, X du is the acceleration coefficient of the longitudinal force with respect to the movement along the x-axis of the body coordinate system, Y dv is the acceleration coefficient of the lateral force with respect to the movement along the y-axis of the body coordinate system, Y dr is the acceleration coefficient of the lateral force with respect to the z-axis rotation of the body coordinate system, x g is the longitudinal position of the center of gravity of the surface unmanned vehicle in the satellite coordinate system, N dr is the acceleration coefficient of the yaw moment with respe...
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