Suchergebnisse

The design of the aerospace systems for future aircraft requires the identification of new suitable communication infrastructures that can overcome the limitations that often come with the use of the legacy, albeit well-proven, protocols that are routinely integrated into aerospace. This allows us to overcome the bandwidth constraints, large deployment costs, or the lack of flexibility of other alternatives, such as SpaceWire, or legacy systems, such as the MIL-STD-1553B bus. These protocols can be replaced with new technologies that can fulfill the greater real-time and interconnectivity demands of advanced scientific probes or manned spacecraft. The advent of the new microlauncher systems has all but confirmed this trend. In this context, we describe the design and implementation of a time-sensitive networking (TSN) bus for the avionics of the Miura 1 suborbital microlauncher. TSN represents an appropriate interface for this type of platform given its ability to provide the determinism and reliability expected in space-grade systems in combination with the higher data rates (gigabit Ethernet) and greater flexibility of standard Ethernet. This has resulted in a TSN platform developed by Seven Solutions S.L. based on the commercially available Zynq-7000 devices from Xilinx. Thus, our design features a light-footprint field-programmable gate array (FPGA) architecture powered by a real-time executive for multiprocessor systems (RTEMS) operating system, which is currently pending its certification from the European space agency (ESA) for space applications. All these elements have been successfully integrated and validated for the avionics of the Miura 1 sounding rocket, which represents an illustrative case that verifies their applicability to similar scenarios. © 1965-2011 IEEE. ; This work was supported in part by the Amiga-7 under Grant RTI2018-096 228-B-C3 and it was conducted in the context of the Gigabit Ethernet TSN Deterministic Network (GETDEN) Project of the European Space Agency. ; With funding from the Spanish government through the Severo Ochoa Centre of Excellence accreditation SEV-2017-0709. ; Peer reviewed

NOMAD (Nadir and Occultation for MArs Discovery) is one of the four instruments on board the ExoMars Trace Gas Orbiter, scheduled for launch in March 2016. It consists of a suite of three high-resolution spectrometers - SO (Solar Occultation), LNO (Limb, Nadir and Occultation) and UVIS (Ultraviolet and Visible Spectrometer). Based upon the characteristics of the channels and the values of Signal-to-Noise Ratio obtained from radiometric models discussed in (Vandaele et al., 2015a, 2015b; Thomas et al., 2016), the expected performances of the instrument in terms of sensitivity to detection have been investigated. The analysis led to the determination of detection limits for 18 molecules, namely CO, HO, HDO, CH, CH, CH, HCO, CH, SO, HS, HCl, HCN, HO, NH, NO, NO, OCS, O. NOMAD should have the ability to measure methane concentrations Inter-university Attraction Poles> programme financed by the Belgian Government (Planet TOPERS no P7-15) and a BRAIN Research Grant BR/143/A2/SCOOP. The research leading to these results has received funding from the European Community's Seventh Framework Programme (FP7/2007-2013) under Grant Agreement no. 607177 CrossDrive. UK funding is acknowledged under the UK Space Agency Grant ST/I003061/1. ; Peer Reviewed