Design of Guidance and Control System for Manned Spaceplane Accommodating Variation in Dynamic Characteristics and Failure

以提高载人航天器的可靠性为目标，研究了两种自适应控制律。一种是新的非参数方法，另一种是传统的参数方法。在第一种方法的基础上，结合干扰观测器和反馈线性化技术设计了飞行控制系统。利用航天飞机轨道飞行器的数据成功地进行了自动着陆的数值模拟。在第二种方法中，采用横向运动设计最小相位系统，并通过数值仿真验证了其有效性。容错控制律也被开发，以便飞行性能可以保持，即使一个或两个执行器中的五个控制面发生故障。

Two types of adaptive control law were studied with the aim of improving the reliability of manned space transportation. One is a novel nonparametric approach and the other is a conventional parametric approach. On the basis of the first approach, a flight control system was designed by combining disturbance observers and a feedback linearization technique. A numerically simulated automatic landing on a runway was successfully carried out using the data of a space shuttle orbiter. In the second method, lateral directional motion was adapted to design a minimum phase system, and its effectiveness was confirmed by numerical simulation with a disturbance observer. A fault-tolerant control law was also developed so that a flight performance can be maintained, even if one or two actuators among the five control surfaces break down.