At present, solar remote sensing instruments face problems regarding the short detection time for solar activity and the need to preheat the electronics before detection. The accurate orbit prediction function ensures that the maximum error of the payload electronics system preheating time is less than 8 s, enabling the electronics to obtain stable and reliable solar remote sensing data, and allowing the prediction function to adapt to the changes in preheating time and the limit position of turntable rotation. To achieve the complete detection of solar activity by a payload in orbit, a turntable with two directions of rotation was accurately controlled to achieve rapid capture and track the Sun’s activity, and the delay time for tracking the Sun successfully was less than 8 s to ensure that the payload made full use of the solar detection time for full detection. The turntable’s tracking error was less than 0.002°, allowing the payload to obtain high-precision solar remote sensing data in orbit. The above methods enable the payload to realize the complete, stable, and high-precision detection of solar activity in orbit for wavelengths ranging approximately from 165 nm to 2400 nm.

/pdf/prediction-aerospace-software-to-detect-solar-activity-and-3jlfwn2b.pdf

Prediction Aerospace Software to Detect Solar Activity and the Fast Tracking of Solar Activity Using Remote Sensing Instruments in Orbit

MIL-STD 1553B serial bus is used in spacecraft for information exchange between subsystems. The three main elements of this 1553B bus are Bus Controller, Remote Terminal and Bus Monitor. This paper describes about the design and implementation of bus controller for a test system that focuses on the Test and Evaluation (T&E) of Onboard Bus interface (1553B) system. The design and implementation is carried out using Quartus 13.1.4 Web Edition on custom made Cyclone III FPGA board.

R Karthikeyan

Papers

Design and Implementation of 1553B Bus Controller on FPGA