The Evaluation of a Digital Hardware Voter/monitor in an Aircraft Control System
Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1977 - Airplanes - 143 pages
This report describes an evaluation and presents the test results of a Digital Hardware Voter/Monitor used as an input signal selector and fault detector when used in conjunction with an electro-hydraulic control system. The DHVM operated as intended by design although asynchronous operation caused the failure detection to be frequency dependent. A digital filter could be incorporated to reduce the frequency dependency of the failure detection circuitry. (Author).
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2.5 Volt Input 40 Hz Input-Output 680J secondary actuator 680J Simulated A-7D Aerodynamic Air Force aircraft amplitude modulation analog-to-digital converters Asynch asynchronous operation Axis Step Response base line data Base Line Test bias bits of noise channel failure Channel Select clock pulses demodulator DHVM output DHVM's DHVMT 125 samples/sec DHVMT 80 samples/sec DHVMT and DHVM DHVMT operating Digital Hardware Voter electro-hydraulic evaluation flight control system Flight Dynamics Freq Frequency Response hardover Hardware Voter Monitor HFCS Input-Output Linearity ILLUSTRATIONS Cont'd indicates input frequency input signal input voltage input word Input-Output at 125 Input-Output at 80 LIST OF ILLUSTRATIONS low median signal low-limit counter measured normal acceleration off-set Phase II Test pitch rate pulse width modulated PWM Signal RC filter Resolution and Linearity sample frequency sample period Sample Rate Variation servo system servo valves shown in FIGURE slew rate snoA TABLE Test Description Test Set-Up Third Failure Transients triangle wave updates/sec X-Y plots