摘要: A large flexible spacecraft (LFS) was simulated by a plate suspended from wires. Results revealed constraints, which were not predicted, so the controller was redesigned, to give reduced gain configurations, which the laboratory e... 展开 A large flexible spacecraft (LFS) was simulated by a plate suspended from wires. Results revealed constraints, which were not predicted, so the controller was redesigned, to give reduced gain configurations, which the laboratory experience showed feasible. The first test results exhibit considerable discrepancies with respect to the theoretical predictions. A laboratory reference model was developed for theoretical performance prediction. Applying this to the tests using the updated controller design, satisfactory agreement with the test results is achieved. The modeling uncertainty has severe consequences with respect to LFS controller design, where usually the aspect is often considered not to play such an important role. It is concluded that the controller design approaches must be checked and possibly developed to end up at feasible designs for space applications. 收起