Presentation delivered by Don Matthews of Pavement Recycling Systems Inc. at the 2015 CalAPA Fall Asphalt Pavement Conference Oct. 28 in Sacramento, Calif.
A brief description of how the PBN/RNAV concept works, together with an update of the FAA implementation programs for it in the US. This presentation has been made using public information only.
Jill Mcguire, NASA Goddard Space Flight Center: "Robotic Refueling Mission." Presented at the 2013 International Space Station Research and Development Conference, http://www.astronautical.org/issrdc/2013.
The PROuD project - Flying into the future with the PBN flight procedures PROuD Project
Collection of all the Consortium presentations at the Final Communication Event of the PROuD project, one of the SESAR JU Large Scale Demonstration Activity
Presentation delivered by Don Matthews of Pavement Recycling Systems Inc. at the 2015 CalAPA Fall Asphalt Pavement Conference Oct. 28 in Sacramento, Calif.
A brief description of how the PBN/RNAV concept works, together with an update of the FAA implementation programs for it in the US. This presentation has been made using public information only.
Jill Mcguire, NASA Goddard Space Flight Center: "Robotic Refueling Mission." Presented at the 2013 International Space Station Research and Development Conference, http://www.astronautical.org/issrdc/2013.
The PROuD project - Flying into the future with the PBN flight procedures PROuD Project
Collection of all the Consortium presentations at the Final Communication Event of the PROuD project, one of the SESAR JU Large Scale Demonstration Activity
International Journal of Engineering and Science Invention (IJESI)inventionjournals
International Journal of Engineering and Science Invention (IJESI) is an international journal intended for professionals and researchers in all fields of computer science and electronics. IJESI publishes research articles and reviews within the whole field Engineering Science and Technology, new teaching methods, assessment, validation and the impact of new technologies and it will continue to provide information on the latest trends and developments in this ever-expanding subject. The publications of papers are selected through double peer reviewed to ensure originality, relevance, and readability. The articles published in our journal can be accessed online.
Crossrail - Integrated Assurance, Chris Sexton, APM Assurance Specific Interest Group, Integrated Assurance - how to achieve it real organisations conference
With the advent of higher powered 3D scanners comes the challenge of dealing with the dense point cloud data sets. Direct Dimensions uses a wide variety of 3D scanning equipment to capture the as-built shape of existing objects. The common problem with all of these projects is the need to proces the point cloud data.
While applications fall generally into either reverse engineering and inspection, both directions present challenges for processing the large data sets efficiently, quickly, and properly. This presentation will focus on an overview of the software tools available commercially that address these problems with a comparison of the various workflows, strategies, and results that one can expect from the various solutions.
With the advent of higher powered 3D scanners comes the challenge of dealing with the dense point cloud data sets. Direct Dimensions uses a wide variety of 3D scanning equipment to capture the as-built shape of existing objects. The common problem with all of these projects is the need to proces the point cloud data.
While applications fall generally into either reverse engineering and inspection, both directions present challenges for processing the large data sets efficiently, quickly, and properly. This presentation will focus on an overview of the software tools available commercially that address these problems with a comparison of the various workflows, strategies, and results that one can expect from the various solutions.
Enabling Active Flow Manipulation (AFM) in Silicon-based Network Forwarding E...Tal Lavian Ph.D.
Programmable Internet:
Enhance internetworking functions.
Move computations into the network for value added services.
Manage the network more capably than possible with SNMP.
More quickly introduce Diffserv or Inserv to support new multimedia applications
Implement traffic control algorithms to support QoS.
1. RADARSAT Constellation Mission: “The Making of” Alain Carrier, Director Earth Observation Projects RCM Project Manager Representation courtesy of MDA Systems Ltd
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14. Launch 1 Launch 2 Nomenclature and Deliverables – Sequencing
17. Drawing courtesy of MDA Systems Ltd System Description – Specifications Bus Canadian Smallsat Bus Launcher Falcon 9 specifications (for design) can use PSLV, DNEPR Total Mass 1400 kg Antenna 9.45m 2 Power <1600 W peak; <220 W average Orbit 600 km, 100m radius orbital tube Polarisation Single Pol / Dual cross selectable pol & Compact polarimetry available on all modes; One fully polarimetric mode Imaging Time 12 minutes/orbit (peak 20 minutes every three orbits) 10 minutes continuous imaging Lifetime 7 years (each satellite)
18. Sun Sensor Magnetometer Reaction Wheel Star Tracker Battery Power Control Unit GPS S-Band Transponder S-Band Antenna Torque Rod N2 Pictures courtesy of Industrial team Bus Description – RCM Bus
19. SAR Antenna Power Distribution Unit Tx/Rx Module Tile Controller Unit Mass Memory Unit N2 AIS Representations courtesy of Industrial team System Description – RCM Payload Central Electronic Unit Payload Controller Unit
20. St-Hubert (X+S), Svalbard (X+S), Masstown and Aldergrove (X) System Description – Ground Segment Baseline
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22. Now N Ops Phase Phase D Y1 Y3 Y2 Y9 Y4 Y7 Y5 Y8 Y6 Y10 Y13 Y15 Y14 Y12 Y11 Phase A Phase B Project Status – Schedule and Cost Distribution
37. [SYS2010] Imaging Time Per Orbit . Each spacecraft in the system shall be capable of imaging at any time when all of the following constraints are satisfied: 1.No more than 36 minutes of imaging in any moving window time period of duration equal to three orbital periods. 2.No more than 20 minutes of imaging in any moving window time period of duration equal to one orbital period. 3.No more than 10 minutes of imaging in any moving window time period of duration 20 minutes. 4.The spacecraft is not in eclipse.
38. [SYS3100] AIS Operating Time Per Orbit . Each spacecraft in the system shall be capable of collecting AIS at any time when all of the following constraints are satisfied: 1.No more than 51 minutes of AIS collection in any moving window time period of duration equal to three orbital periods. 2.No more than 25 minutes of AIS collection in any moving window time period of duration equal to one orbital period. 3.No more than 15 minutes of AIS collection in any moving window time period of duration 25 minutes.
Editor's Notes
SUN SENSOR Su n acquisition / Fail Safe Recovery / Qualified by heritage and design / Single Detector Cosine FOV / 10g / 500uA to 1300 uA MAGNETOMETER Provides attitude reference through 3 analogue signals proportional to 3 mutually normal projections of earth magnetic field / Measurement Range: +/- 70000 nT (Adjustable) / Accuracy: 150 Nt / Mass: LE 300g / Power consumption: < 1W / Qualification Status: Delta Qual Required MAGNETO TORQUE ROD To be qualified / Nominal Input Voltage: 28 V / Dipole Moment: 140 Am 2 REACTION WHEEL Qualified / Momentum @ 6000 RPM: 18 NMS / Voltage: 22-34V / Mass: < 7kg / Power: Max :< 180W, Steady State: < 35W, Quiescent: < 11W. STAR TRACKER Configuration: 2 optical heads with 30 deg baffle, 2 Electronic Units with RS422 communication interface, Cross-strapping of optical heads and electronic units / Delta qualification required. BATTERY Cell level delta qualification (random vibrations) / Battery inherently fault tolerant / Mass for battery pack (2 modules): 33.6 kg / Vmax : 33.6 V, Vmin: 22V / Capacity: 66 A-Hr, Nominal / Operating Temperature: 0 degC to 25 degC.
SYNTHIETIC APERTURE RADAR ANTENNA Two identical panels / Motorized deployment system / ncreased pointing accuracy: Direct connection between the antenna and the star tracker, Decoupled from the bus distortions and movements. TRANSMIT / RECEIVE MODULE High Temperature Cofired Ceramic (HTCC) package / Simplified assembly process and low recurring cost compare to Radarsat-2 TRM / Use of MMIC (Monolithic Microwave Integrated Circuit) designed by CSA. TILE CONTROLLER UNIT Power distribution to 4 TRMs / Digital Interface between the PLCU and the TRMs / nterconnection to the TRMs using flat flexible cable and solder less compression connectors. MASS MEMORY UNIT Internal Redundant / Large storage capacity of 700Gb at end of life / Output Data Rate of 300Mb/s (2 X 150Mb/s) . CENTRAL ELECTRONIC UNIT Demodulation, modulation and filtering are performed by Digital Signal Processing for optimum performance and improve flexibility / 16 Resolution bandwidth from 14 to 100MHz / May store and generate up to 110 pre-defined pulse waveforms. PAYLOAD CONTROLLER UNIT Internal Redundant / Digital Interface between the Bus CDH ( Command and Data Handling) and the Payload / Digital interfaces with all payload sub-systems. POWER DISTRIBUTION UNIT Internal Redundancy / Power Interface between the Bus Power Control Unit (PCU) and the SAR Antenna / Prime power switching for the TCUs and operational heaters.
Based on MCP minus E1 Phase A: 1.4% (State between 1 – 2%) Phase B: 4.4% (State between 4 – 5%) Phase C: 21.3% (State between 15 – 25%) Phase D: 72.8% (State between 70 – 75%) Phase E1 is 3% of the total MCP cost.
10% of total value of Canadian contracts to Atlantic Canada’s firms; 10% of total value of Canadian contracts to Prairie Province firms; 10% of total value of Canadian contracts to BC’s firms; 35% of total value of Canadian contracts to Ontario firms and; 35% of total value of Canadian contracts to Quebec firms.
1) Maritime surveillance - ice - wind - ship monitoring 2) Ecosystem monitoring - forestry - agriculture - wetlands - coastal changes - permafrost) 3) Disaster management - mitigation - warning - response - recovery -Natural Resources Canada, Environment Canada , Department of Fisheries and Oceans, Department of National Defence , Transport Canada, Agriculture and Agri-foods Canada , Parks Canada, Industry Canada . -Atlantic Canada Opportunities Agency, Western Economic Diversification Canada , Canada Economic Development-Quebec, Department of Foreign Affairs and International Trade , Public Works and Government Services Canada, Communications Security Establishment Canada .
SOLAR ARRAY SUBSYSTEM Solar Cell type: BTJ, 2 nd generation triple junction Two Arrays: Main array with deployment angle = 33 deg relative to axial axis, Safe hold array fixed to opposite side panel (used during LEOP and in safe hold spin configuration) Maximum Power output of main array at End of Life: 917W Orbit Average Power output of main array at End of Life, Maximum Eclipse: 580W. PROPULSION SUBSYSTEM Qualification Status: Modified Development. All components have flight heritage / Propellant: High Purity Hydrazine / Mass: 90 kg (with propellant). BUS STRUCTURE Qualification Status: New Development / Honecomb panels: 13, including mid-deck and + Z (end) panels, Bus stiffener panel and payload stiffener panel / Edges of exterior panels equipped with threaded inserts / PFM level Modal Tests to be conducted to seek out natural frequencies using analogue payloads units.
POWER CONTROL UNIT New Development / Internally Redundant: Controller Cards / Highly radiation tolerant components / 30 kg / Controller Card (2), Switch Card (5), Pyro Card (2) Propulsion Card (1), Battery Card (1), Solar Array Card (1) . GPS Redundant GPS Receiver Systems / Qualified / Extensive flight heritage / High accuracy solution: 10m along track, 10m cross track and 15m radial, 3 sigma / On-orbit SW updatable . S-BAND ANTENNA Omni directional / To be qualified / 2200-2400 MHz / 50 deg to 90 deg half cone angle coverage / Power Handling: 5W / Temperature Range: -115 degC to 120 degC / Mechanical Load: 40g / Natural Frequency: > 100 Hz / Mass: 225g. S-BAND TRANSPONDER Requires delta Qualification / Frequencies (same as Radarsat-2): Uplink: 2053.458333MHz, Downlink: 2230 MHz / Bandwidth: Downlink: 500kbps nominal, 40 kbps emergency, Uplink: 4 kbps BPSK/PM demodulator / Power: 5W / Discrete unit commanding and telemetry: RS422 / Dual redundant.
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