Can. X-2 Briefing Ky. Sat Morehead, KY Michael Gailey
Can. X-2 Overview • • Canadian Advanced Nanospace e. Xperiment University of Toronto Launch Date: June 30, 2007 Launch Vehicle: Antrix Polar Satellite Launch Vehicle from India Deployment Mechanism: X-Pod Projected Orbit: Sun-synchronous Dimensions: 10 x 35 cm Weight: 3. 5 kg • Primary Mission – Pathfinder for a 2008 dual satellite mission that will test formation flying – Technologies that will be evaluated • Novel propulsion system • Custom Radios • Innovative attitude sensors and actuators • Commercial GPS receiver
Subsystems • Structure: Custom aluminum frame • EPS – 2 - 7 W from 22 triple-junction Ga. As solar cells – 3. 6 Ahr Lithium-Ion battery – Unregulated satellite power bus operates from 3. 6 to 4. 2 V • On Board Computers – Arm 7 main processor – Arm 7 payload processor – Each run at 15 m. Hz with 8 MB of total SRAM – Each has 16 MB of flash storage for telemetry, science data, images and code • Communications – Full duplex system – Uplink: UHF transceiver (4 kbps) using a quad canted monopole antenna – Downlink: S-band (32 -256 kbps) – Beacon: VHF which broadcasts telemetry on a continual basis
Attitude Control and Propulsion • Attitude Determination – Sun sensors developed in-house – 3 -axis Magnetometers developed inhouse, deployed at the end of a 20 cm boom – Accuracy of ± 1º • Attitude Control – Momentum bias system consists of: • • 3 Orthogonal vacuum-core magnetic torquer coils Dynacon Momentum Nanowheel – 3 -axis attitude control with accuracy of ± 10º and a pointing stability of ± 1º • Propulsion – Liquid fueled cold gas system – Uses sulfur hexaflouride as a propellent – Thrusting will induce a major axis spin which will be measured using the attitude determination systems
Science Payloads • Atmospheric Spectrometer – Purpose: Detect pollution variations to create better computer models of pollution distribution – How: Measures greenhouse gas levels using Earthshine spectra in the near infrared band. Surface resolution of 1 km • GPS Signal Occultation Experiment – Purpose: To develop models that can be used to help mitigate GPS positioning errors during periods of enhanced ionospheric activity – How: Compare space-based GPS signals to signals measured at ground-based stations. Atmospheric properties like total electron content and tropospheric water vapor as a function of altitude can be reconstructed • Atomic Oxygen Material Degradation Experiment – Purpose: Evaluate the effectiveness of a special coating in protecting materials from atomic oxygen erosion in space – How: Measure thicknesses of a coated material and an uncoated material over time • Communications Protocol Experiment – Purpose: To test an innovative low Earth orbit (LEO) satellite communication protocol. Addresses data transport errors that occur specifically in LEO satellite links
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