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Flight control system design considering rate saturation

AEROSPACE SCIENCE AND TECHNOLOGY 1998年第4期2卷 265-275页

作者： Duda, H DLR Inst Flight Mech German Aerosp Ctr D-38022 Braunschweig Germany

In this paper the design process of modern flight control systems is discussed with respect to pilot-in-the-loop oscillations (PIO) due to rate saturation. At first the PIO phenomenon is characterised briefly. Well-known design criteria with respect to flight control system stability and handling qualities based on linear aircraft models are presented. A new design criterion considering the nonlinear effects of rate limiting is described. The criterion is based on the 'open loop onset point' (OLOP) of the rate limiter in a Nichols chart, The background for the development, and the verification of the OLOP-criterion are presented briefly. In order to demonstrate the applicability of the OLOP-criterion in the design process a simple example is examined, The flight control system parameters of a basically unstable aircraft are optimised with respect to the linear design criteria and the OLOP-criterion. Two alternative designs were discussed, a 'nominal design' and a 'low gain design' with reduced feedback loop gain. The low gain design is favourable with respect to rate limiting in the feedback loop of the flight control system, which is proved by nonlinear simulations in the time domain. Finally, the utilisation and the design of a rate limitation in the forward path of the flight control system are discussed. (C) Elsevier, Paris.

关键词： flying qualities flight control system aircraft-pilot coupling pilot-in-the-loop oscillations nonlinear system rate limiting

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