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Aeroservoelastic Flight Control Design For Military Aircraft Weapon System
Wolfgang Luber
Last modified: 2010-04-25
Abstract
The aim of the aeroservoelastic flight control system design for a military aircraft weapon system is mainly to optimize for a given control law forward path and feedback structure the control law parameters like gains, phase advance filters and notch filters which cover all conditions in a full flight envelope for all envisaged aircraft configurations as external missiles, stores, bombs for all possible symmetric and asymmetric combinations. The control law gains and phase advanced filters which are derived during the optimization process are considered to be Mach number and altitude dependent whereas the structure filters i. e. notch filters may be constant or variables for all flight conditions and groups of the huge number of external store configurations.
The design strategy of the Flight Control System development and the procedure is described which includes the modelling of the coupled system of the flight dynamics, the structural dynamics of representative selected external stores, the actuators and sensors as well as the effects of the digital advanced flight control system.
Different external store examples are demonstrated which document the design procedure.
The design of FCS notch filters is based upon a model of the aircraft describing the coupled flight dynamic, flight control dynamics and in addition on the structural dynamic behaviour measured by on ground- and in flight structural coupling tests of a representative number of external store configurations. The paper outlines design procedures, design and clearance requirements, correlation tests and model update for on ground and in flight.
The design strategy of the Flight Control System development and the procedure is described which includes the modelling of the coupled system of the flight dynamics, the structural dynamics of representative selected external stores, the actuators and sensors as well as the effects of the digital advanced flight control system.
Different external store examples are demonstrated which document the design procedure.
The design of FCS notch filters is based upon a model of the aircraft describing the coupled flight dynamic, flight control dynamics and in addition on the structural dynamic behaviour measured by on ground- and in flight structural coupling tests of a representative number of external store configurations. The paper outlines design procedures, design and clearance requirements, correlation tests and model update for on ground and in flight.