This article surveys approaches to the selection of design parameters and modelling the functioning of the remote sensing satellite systems, taking into account the requirements and restrictions on customer resources. The objective of this research is to increase the efficiency of the use of space systems to solve urgent tasks of monitoring the earth’s surface. Firstly, an analysis of the requirements for space imagery materials and consumer information support was carried out, secondly, mathematical models of remote sensing equipment and onboard systems of small spacecraft were developed, and finally, a database with the technical characteristics of the onboard systems and remote sensing equipment of spacecraft, launch vehicles and ground-based reception and processing information facilities was created. As a result, software to determine main design parameters and modelling the functioning of cost-effective remote sensing satellite systems was developed.
The article presents a performance analysis of the small satellite thermocontrol system based on the telemetry data received by the ground control complex GCC-SSAU. The performance analysis was carried out on "AIST" (RS43-as) and "AIST" (RS-41at) small satellites. Ground testing of the thermocontrol system was performed in the thermo-vacuum chamber on the testing facility of RSС "Progress". The article gives an overview of the operational capabilities of the thermocontrol system. The performance analysis of the system is carried out and the primary guidelines for future thermovacuum testing are given.
The paper deals with the problem of estimating the rotational motion parameters of the prototype of the small spacecraft "Aist" using data on the current from solar panels. The spectral analysis of the signal is carried out. The continuous signal was restored by its discrete readings using the Kotelnikov series. The angular velocity of the rotational motion of the prototype of the small spacecraft "Aist" is estimated. A comparative analysis of the results with the results obtained by other authors. Conclusions are drawn about the changes in the parameters of the rotational motion of the prototype of the small spacecraft "Aist" during its orbital flight.
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