Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters' landing point

Novel integrated guidance and control design for a three-stage satellite carrier using model-free adaptive control

“…To overcome such drawbacks, some methods are investigated by virtue of robust IGC which is of interest in a variety of applications. In this line, references can be made to the control of a skid-to-turn hypersonic missiles, 18 navigation with high automation, 19 3-D bank-to-turn maneuvering of a missile with a pulse angle, 20 control of a missile against an unrecognized maneuvering target despite uncertainties and control bounds, 21 increase of accuracy at the landing point of satellite carrier boosters, 22 and control of a flexible hypersonic vehicle. 23 Moreover, a robust adaptive IGC scheme relying on the model of the system is recently developed by Wang et al 24 for a re-entry hypersonic vehicle with online estimation of aerodynamic coefficients.…”

Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

“…However, considering that the dynamic equations of SE(3) are implicit and cannot be Taylor expanded, the traditional optimal control methods can only solve the optimal control problems with explicit discrete dynamic equations [23], so they cannot be applied to SE(3) . Thus, model prediction control (MPC) was proposed and applied to the system modeled by the Lie group SO(3) [24], [25] and SE(3) [26]. For example, optimal control theory is proposed based on linear equations in [24], [25].…”

“…Thus, model prediction control (MPC) was proposed and applied to the system modeled by the Lie group SO(3) [24], [25] and SE(3) [26]. For example, optimal control theory is proposed based on linear equations in [24], [25]. And the optimal control problem for the combined three-dimensional orbital and rotational motion of a rigid body is presented in the literature [27], and an effective computational method is given.…”

“…In [28], model predictive static programming (MPSP) is applied to SE(3) to optimize the spacecraft operation with the critical energy consumption as the objective function, so as to achieve optimal control. However, the methods mentioned above have the following drawbacks: The methods in [24], [25] are all based on linearization, which can only solve a class of linearization problem, and the applicable range is too small. The method designed in [27] needs to solve the two-point edge value problem, which has a high computational complexity and is not conducive to using in practical engineering applications.The MPSP proposed in the literature [28] does not consider the control input constraint problem in the control process.…”

“…Compared with the methods studied in the previous section [24], [25], [27], [28], the innovations of this paper are as follows:…”