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#Redundant flight control system pdf

Combining the inputs to the control computers assures that sensor bias will not cause divergence, while cross-strapping control strings bounds divergent response to all bias error inputs. If the response modes associated with these components are not stable, bias errors can cause the components to diverge, leading to the possibility of “nuisance trips” in failure detection/isolation logic and eventual control system lockup (at saturation). It is found that state components which appear in the parallel signal paths, e.g., individual actuator-commands, are not controllable, although the sum of the command signals is well behaved. N2 - The controllability and steady-state response of parallel-redundant flight control systems are examined. Index categories: Aircraft Handling, Stability and Control Navigation, Control, and Guidance Theory Aircraft Subsystem Design. This research was supported by NASA Contract NAS9-10268. Received Jrevision received December 14, 1972. Feedback and balancing of the different control valves is provided by the visibility accorded each actuator remote processing unit by the second communication link.T1 - Some effects of bias errors in redundant flight control systems Each of the actuator remote processing units is linked through a second communication link (46). The actuator remote processing unit receive position commands and generate a command signal that controls movement of the actuator (12) using the control valves. Each of the flight controllers forwards the position command to actuator remote processing unit (40,42,44). A first communication link (38) is provided between several flight controllers (32,34,36) to share information. A flight controller (32,34,36) generates a position command that is indicative of the position desired for the control surface. Each stage (16,18) includes several control valves (20,22,24,26,28,30) that are controlled independently to provide a desired redundancy. B64C13/505- Transmitting means with power amplification using electrical energy having duplication or stand-by provisionsĪ flight control system (10) includes a dual stage actuator (12) for moving a control surface (14).B64C13/504- Transmitting means with power amplification using electrical energy using electro-hydrostatic actuators.B64C13/50- Transmitting means with power amplification using electrical energy.B64C13/38- Transmitting means with power amplification.

B64C13/00- Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers.

Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp Publication of EP2505496A2 publication Critical patent/EP2505496A2/en Publication of EP2505496A3 publication Critical patent/EP2505496A3/en Application granted granted Critical Publication of EP2505496B1 publication Critical patent/EP2505496B1/en Status Active legal-status Critical Current Anticipated expiration legal-status Critical Links Original Assignee Hamilton Sundstrand Corp Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Avritch Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Granted Application number EP12162772.3A Other languages German ( de)

#Redundant flight control system pdf

Google Patents Redundant two stage electro-hydraulic servo actuator controlĭownload PDF Info Publication number EP2505496A3 EP2505496A3 EP12162772.3A EP12162772A EP2505496A3 EP 2505496 A3 EP2505496 A3 EP 2505496A3 EP 12162772 A EP12162772 A EP 12162772A EP 2505496 A3 EP2505496 A3 EP 2505496A3 Authority EP European Patent Office Prior art keywords actuator remote processing communication link processing unit flight Prior art date Legal status (The legal status is an assumption and is not a legal conclusion. Google Patents EP2505496A3 - Redundant two stage electro-hydraulic servo actuator control

EP2505496A3 - Redundant two stage electro-hydraulic servo actuator control