Currently the test airframe is being built and flight testing is slated for October 31st to prove the system works in flight. Primary systems should have identical computers and software and is the case on many airborne vehicle systems computers. Our current results have proven we can use the backup Pixhawk to take over from the primary Pixhawk via a kill-switch controlled by the backup Pixhawk during ground testing. It will also test telemetry feedback to the operators when notifying the operator of a failure, and also verify efficiency gains with the Pixhawk-controlled variable-pitch propulsion system. There also was lack of guidance for the interfaces of flight control systems with area navigations systems, Traffic Collision and Avoidance System and supervisory functions this also should be addressed in future efforts. Ground testing and flight testing the RFC will verify systems reliability, and also the simulation of hardware and software failures to test the system’s resiliency to failures. Suggested is to use multiple pilots, interfaces, computers and.
#Redundant flight control system verification#
An example applied in Boeing 747 flight control system and the simulation verification analyses are shown in Sections 4 and 5, respectively. This kind of redundancy has to be applied in every subsystem.
The use of variable pitch propellers in larger aircraft has proven to be an effective tool for increasing endurance, range and efficiency. Theoretical performance degradation analysis method of the redundant flight control systems is presented by applying MDHMM to characterize the correlated digital upsets in Section 3. The RFC project is part of a NASA-supported research initiative to enhance the safety of sUAS flying in the national airspace system, and allow the FAA to reconsider beyond visual line of site (BVLOS) sUAS operations.Ī secondary goal of this project will be the development of an efficient and low cost variable-speed for propeller for sUAS integration. However, the IMU data is received over three independent and separate miltiplex systems. The flight control sensors are all triple redundant with the exception of the single IMU.
The proposed system would serve as a “back-up” to the primary flight computer in the case of an in-flight loss of communications or control. flight control computers operate on data received from thie sensor subsystems and generate commands for the control mechanisms. This platform is composed of controller processing. The exosystem is used to generate common-source correlated digital upsets fed to distributed redundancy platform. The disturbance model includes the exosystem and the distributed redundant platform. Currently the test airframe is being built and flight testing is slated for October 31st to prove the system works in flight.The Redundant Flight Computer (RFC) project focuses on enhancing the reliability and safety of small Unmanned Aircraft Systems (sUAS) by creating a redundant flight control system. The distributed redundant flight control system with disturbance model is described in Figure 1. It will also test telemetry feedback to the operators when notifying the operator of a failure, and also verify efficiency gains with the Pixhawk-controlled variable-pitch propulsion system. The use of variable pitch propellers in larger aircraft has proven to be an effective tool for increasing endurance, range and efficiency. The proposed system would serve as a “back-up” to the primary flight computer in the case of an in-flight loss of communications or control. The Redundant Flight Computer (RFC) project focuses on enhancing the reliability and safety of small Unmanned Aircraft Systems (sUAS) by creating a redundant flight control system. The fly-by-wire flight control system utilizes redundant flight computers and wires to deliver electrical signals between the pilot and flight actuators.
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