A complete optical wireless interface for the ARINC 429 avionics bus has been presented as part of this paper. After evaluating the previous results, we conclude that the described system complies with all electrical and timing restrictions imposed by the ARINC 429 specification, ensuring the compatibility with such avionics bus
We have seen how to avoid the cold finger areas in order to get a better segmented TH image. These approaches are only necessary when temperatures from the finger are close to the surface. Once the TH image is well segmented we have observed different performance.
We have seen how to avoid the cold finger areas in order to get a better segmented TH image. These approaches are only necessary when temperatures from the finger are close to the surface. Once the TH image is well segmented we have observed different performance
Romeral, L.; Rosero, J.; Garcia, A.; Cusido, J.; Ortega, J.A. IEEE aerospace and electronic systems magazine Vol. 25, num. 3, p. 4-9 DOI: 10.1109/MAES.2010.5463950 Data de publicació: 2010-03 Article en revista
This paper presents an embedded hardware/software architecture specially designed to be applied on mini/micro Unmanned Aerial Vehicles (UAV). An UAV is low-cost non-piloted airplane designed to operate in D-cube (Dangerous-Dirty-Dull) situations . Many types of UAVs exist today; however with the advent of UAV's civil applications, the class of mini/micro UAVs is emerging as a valid option in a commercial scenario. This type of UAV shares limitations with most computer embedded systems: limited space, limited power resources, increasing computation requirements, complexity of
the applications, time to market requirements, etc. UAVs are automatically piloted by an embedded system named “Flight Control System”. Many of those systems are commercially available today, however no commercial system exists nowadays that provides support to the actual mission that the UAV should perform.
This paper introduces a hardware/software
architecture specially designed to operate as a flexible payload and mission controller in a mini/micro UAV. Given that the missions UAVs can carry on justify their existence, we believe that specific payload and mission controller s for UAV should be developed.
Our architectonic proposal for them orbits around four key elements: a LAN based distributed and scalable hardware architecture, a service/subscription
based software architecture and an abstraction communication layer.
The latest advances in electric and electronic aircraft technologies from the point of view of an "all-electric" aircraft are presented herein. Specifically, we describe the concept of a "more electric aircraft" (MEA), which involves removing the need for on-engine hydraulic power generation and bleed air off-takes, and the increasing use of power electronics in the starter/generation system of the main engine. Removal of the engine hydraulic pumps requires fully-operative electrical power actuators and mastery of the flight control architecture. The paper presents a general overview of the electrical power generation system and electric drives for the MEA, with special regard to the flight controls. Some discussion regarding the interconnection of nodes and safety of buses and protocols in distributed systems is also presented.
Harry Rowe Mimno Award for the March 2007 AESS Magazine Paper: “Moving Towards A More Electric Aircraft”