Analysts armed with advanced computer simulation codes and expertise can then employ these precision radiometric and thermal imaging capabilities to research phenomenology associated with nuclear proliferation. Originally only intended for a one- to three-year mission, the MTI satellite was designed to provide highly accurate radiometry with good spatial resolution in 15 spectral bands and measure ground temperatures from space with accuracies in the realm of one kelvin. On March 12, 2010, the MTI spacecraft marked its 10 th anniversary of service as it completed its 55,000th orbit - far exceeding both its intended maximum life and its potential applications.In 2011, the MTI spacecraft and its payload are operating nominally.The DPAC (Data Processing and Analysis Center) function is provided by LANL. S/C operations are performed at SNL (ground station). The CCSDS protocol is used for uplink and downlink communication. The TT&C communication is in S-band with an uplink rate of 2048 bit/s. RF communications: Downlink data transmission in X-band at 8 Mbit/s. The S/C has no orbit maintenance capability, resulting in an orbit decay over time. Orbit: Sun-synchronous near-circular polar orbit, altitude = 575 km x 609 km, inclination = 97.52º, period = 96.6 min, with a local equatorial crossing time of 13:00 on ascending node. The launch was funded by the Air Forces' Space Test Program (STP). Launch: A launch of MTI on a Taurus vehicle took place on Mafrom VAFB, CA, USA. 3) 4)įigure 2: MTI bus during integration (image credit: Ball Aerospace) The S/C design life is one year with a goal of three years. The largest single power consumption due to the Stirling cycle cryogenic cooler which cools the focal plane and adjacent structures.
The S/C mass at launch is 614 kg, average total power of 575 W, with 11 battery cells (plus one spare) for ecliptic operations support. The system does not have propulsion, so the orbit decays over time. The body-pointing feature may also be used for along-track stereo imaging support. This feature provides a FOR (Field of Regard) of ☒00 km for cross-track coverage (the nominal swath width of the imager is 12 km). The S/C is agile and can be body-pointed up to ±50º in all axis. A pointing accuracy of 0.25º is provided. Actuators are reaction wheels and torque rods. The S/C attitude is measured by multiple sun sensors, a horizon sensor, and gyros. The spacecraft bus is an aluminum frame and shear panel design structure, the dimensions (stowed for launch) are: 1.4 m diameter and 2.6 m in height.
The MTI satellite, with the bus built and integrated by Ball Aerospace (BCP2000 bus version), is three-axis stabilized.
Figure 1:Ěrtist's rendition of the MTI satellite in orbit (image credit: LANL, SNL)
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