Changes between Version 18 and Version 19 of TBR/UserApp/Space/Proba_2

Timestamp:

11/29/11 22:18:39 (13 years ago)

Author:

Iliyankatsarski

Comment:

TBR/UserApp/Space/Proba_2

@@ -173 +173 @@
 compensation of thermo-elastic misalignments of the star tracker relative to the instrument.
 
-
-[wiki:File:PROBA2_Auto2.jpeg File:PROBA2 Auto2.jpeg]
-Phoenix GPS architecture for PROBA-2 
-
-It is a miniature receiver specifically designed for high dynamics space applications. It is based on SigTech’s
-commercial-off-the-shelf MG5001 receiver board but operates a proprietary firmware developed by DLR.
-Though originally designed for automotive applications, the receiver board has been qualified for space use in a
-series of thermal-vacuum, vibration and total ionization dose tests. The receiver employs a GP4020 baseband
-processor which combines a 12 channel GP2021 correlator and an ARM7TDMI microprocessor kernel.
-At a power consumption of less than one Watt and a board size of 50 x 70 mm the receiver is among the
-smallest of its kind and particularly well suited for satellites with limited onboard resources. The Phoenix
-receiver is extensively used in European sounding rocket missions and has been selected for various other
-micro-satellite missions in low Earth orbit (LEO) such as X-Sat, ARGO, Flying Laptop and PRISMA. Specific
-features of the Phoenix receiver software for LEO applications include optimized tracking loops for high
-accuracy code and carrier tracking, precision timing and integer ambiguities for carrier phase based relative
-navigation, a twoline elements orbit propagator for signal acquisition aiding, and an attitude interface to
-account for non-zenith pointing antennas in the channel allocation process. A pulse-per-second signal enables
-synchronization to GPS (or UTC) time with an accuracy of better than 1ms. Noise levels of 0.4 m (pseudorange)
-and 0.5 mm (carrier phase) at representative signal conditions (C/N0=45dB-Hz) have been demonstrated in
-signal simulator and open air tests which render the receiver suitable for precise orbit determination. While
-the instantaneous (kinematic) navigation solution is restricted to an accuracy of roughly 10m (3D rms) due
-to broadcast ephemeris errors and unaccounted ionospheric path delays, an accuracy of about 0.5-1m
-can be achieved in a ground based precise orbit determination.
-
 The orbital information allows pointing of the  spacecraft towards any point on Earth (by using as well