In this study, a quasi-time-optimal steering law for low-thrust orbit transfer is investigated. In the proposed steering law, the satellite attitude is controlled to suppress its error with respect to the ideal thruster direction under the orthogonality constraint between the Sun direction and the solar array driving mechanism's rotational axis as well as the angular momentum and torque constraints. All these constraints are satisfied by introducing a structure similar to Baumgarte's stabilization method and by formulating a quadratically constrained quadratic programming problem which can be analytically solved to obtain the control torque. Several numerical simulations show that the transfer time difference from the ideal unconstrained transfer is less than a few percent.

在这项研究中，研究了低推力轨道转移的准时间最优转向定律。在提出的转向定律中，在太阳方向与太阳电池阵列驱动机构的旋转轴之间的正交约束以及角动量和转矩约束下，控制卫星姿态以抑制其相对于理想推力器方向的误差。通过引入类似于鲍姆加特的稳定化方法的结构，并通过公式化二次约束二次规划问题，可以解决这些问题，从而获得控制转矩，从而满足所有这些约束条件。若干数值模拟表明，与理想的无约束传输相比，传输时间差小于百分之几。