Title :
C-17 flight control system
Author :
Kowal, Brian W. ; Scherz, Carl J. ; Quinlivan, Richard
Abstract :
The authors describe the C-17 flight control system (FCS), starting with the aircraft requirements for deep stall avoidance, probability of loss of control, all engine out control, and safe go-around requirements. FCS requirements derived from the aircraft requirements are described. The apportionment of FCS requirements to the fly-by-wire (FBW) electronic flight control system (EFCS) and to the backup mechanical flight control system (MFCS) is described. The EFCS architecture that meets the FCS requirements is discussed, including the apportionment of the control between primary and secondary control surfaces, sensor suites, and pilot controls and displays. A significant feature of the C-17 EFCS is the integration of the primary FBW system and the AFCS system, which permits a significant efficiency in the amount and utilization of light control hardware relative to current and planned comparably sized commercial aircraft that feature FBW flight control systems. The combined EFCS and MFCS is designed to meet a 1×10-9 permission catastrophic failure rate
Keywords :
aerospace computer control; aircraft control; probability; redundancy; safety systems; C-17 flight control; FBW; aircraft; catastrophic failure rate; deep stall avoidance; efficiency; electronic flight control system; engine out control; fly-by-wire; loss of control; mechanical flight control system; pilot controls; pitch rate control; primary control surfaces; probability; safety; secondary control surfaces; Aerospace control; Aerospace electronics; Aircraft propulsion; Automatic frequency control; Control systems; Displays; Engines; Lighting control; Mechanical sensors; Size control;
Conference_Titel :
Digital Avionics Systems Conference, 1992. Proceedings., IEEE/AIAA 11th
Conference_Location :
Seattle, WA
Print_ISBN :
0-7803-0820-4
DOI :
10.1109/DASC.1992.282191
