The system concept, its implementation, and some typical applications of an airworthy helicopter experimental system are described. The BO-105 is used as the test platform. This flight test platform is distinguished from the standard production machine by two substantial modifications: a modified, large capacity experimental cockpit, and a four axis fly by wire/fly by light control system. The items of equipment present in a general survey are presented and are discussed with regard to their functions or selection criteria. The equipment items in the BO-105 are as follows: flight controls (electronic signal pick off from the jogstick or side stick in all four control axes); fly by wire/light control (electro hydraulic actuators in all four control axes); sensors (Doppler ASI, strapdown attitude reference system, radio altimeter, air data computer); navigation (global positioning system, VOR (Very high frequency Omnidirectional Range), distance measuring equipment, instrument landing equipment receiver); data processing (aircraft computer, measurement data conditioning); data save (logging, quick look) (up/down PCM (Pulse Code Modulation) telemetry, data logging in the air and on the ground); and instruments (test cockpit) (electronic 5 inch color displays, multifunctional controls). Ground simulation, used for direct flight test preparation, is discussed. The five years of successful use of the helicopter experimental system is stressed.


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