Space systems design (spacecraft, satellites, space stations and their equipment)
Amirhossain Adami; zahra pourJabari; Mohammad azhdari; Ali Saadat dar; Hanieh Eshaghnia; Kazem gholipour; seyedmohammad mirmohammadi; Alireza Ahangarani Farahani
Articles in Press, Accepted Manuscript, Available Online from 21 April 2024
Abstract
In this research, the structure of the probes sent to other planets is first investigated and the common structures are introduced. In the following, the system design process of the Armita probe, which was prepared for the first national competition of the probe robot (Iran Space Research Institute), ...
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In this research, the structure of the probes sent to other planets is first investigated and the common structures are introduced. In the following, the system design process of the Armita probe, which was prepared for the first national competition of the probe robot (Iran Space Research Institute), will be discussed. Armita team has won the first place in the first phase of the competition in 1401. The probe design process is based on the ECSS standard and is presented briefly, which includes the compilation and extraction of the requirements document, function-performance tree, product tree and finally the conceptual design of the sub-systems to achieve the intended mission. Based on the extracted results, the Armita probe with a mass of 6.9 kg and geometric dimensions of 48 x 38 x 36 cm with a total energy consumption of 112 amp hours will be able to perform the intended mission and satisfy all technical, dimensional and mass requirements well. shows
Space subsystems design: (navigation, control, structure and…)
Abbas Dideban; Alireza Ahangarani Farahani
Volume 16, English Special Issue , November 2023, , Pages 25-38
Abstract
This paper presents a new control methodology based on Continuous Time Delay Petri Nets (CTDPN) tool for the attitude control of satellite simulator. The graphical and mathematical features of this tool help the expert designer to design an appropriate controller using graphical model easily, and then ...
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This paper presents a new control methodology based on Continuous Time Delay Petri Nets (CTDPN) tool for the attitude control of satellite simulator. The graphical and mathematical features of this tool help the expert designer to design an appropriate controller using graphical model easily, and then apply the necessary changes to the mathematical model. In this approach, the controller gains are derived from the states and some other variables. Thus, the system states and variables must be available. The new gain tuning algorithm consists of three stages. First, A simulation environment is made for mathematical modeling based on the CTDPN tool and controller design. Secondly, using optimal methods, the controller gains are calculated at any given time and the data are collected. Finally, using the database, a relationship between the set of variables and the gains are derived. Experimental results indicate the promising performance of the controller in comparison to the conventional controller applied to the satellite simulator platform. The results indicate that the designed controller is robust against variation of parameters, as the controller gains are tuned based on the system state and variables.
Space subsystems design: (navigation, control, structure and…)
Alireza Ahangarani Farahani; Amirhossain Adami; Hamed Arefkhani
Volume 16, Issue 3 , September 2023, , Pages 79-89
Abstract
In this article, a new approach has been presented in the design of a satellite's status controller using reaction wheels. First, a non-linear controller whose gains depend on the state variables at any moment is proposed. In the first step, the process of extracting control coefficients using the GA ...
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In this article, a new approach has been presented in the design of a satellite's status controller using reaction wheels. First, a non-linear controller whose gains depend on the state variables at any moment is proposed. In the first step, the process of extracting control coefficients using the GA optimizer is described. Then, using the results of a number of tests, sufficient data for meta-modeling of the system is extracted and the relevant control gain functions are optimized using the data bank. The input of the mentioned function is the system states and its output is the control coefficients. Finally, a simulator platform was used to determine and control the position of the satellite based on the air bearing to evaluate the proposed approach. Laboratory test results show that the performance of the proposed method is up to 30% better than the classical PID controller with fixed coefficients.
