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Saadatdar Arani, S., Nosratollahi, M., Adami Dehkordi, A., Ahangarani Farahani, A. (2024). Designing and Comparing Two Configurations of Space System Flying Simulator with Cold Gas Thrusters. Electronic and Cyber Defense, 20(2), 55-67.
Seyedali Saadatdar Arani; Mehran Nosratollahi; Amirhossein Adami Dehkordi; Alireza Ahangarani Farahani. "Designing and Comparing Two Configurations of Space System Flying Simulator with Cold Gas Thrusters". Electronic and Cyber Defense, 20, 2, 2024, 55-67.
Saadatdar Arani, S., Nosratollahi, M., Adami Dehkordi, A., Ahangarani Farahani, A. (2024). 'Designing and Comparing Two Configurations of Space System Flying Simulator with Cold Gas Thrusters', Electronic and Cyber Defense, 20(2), pp. 55-67.
Saadatdar Arani, S., Nosratollahi, M., Adami Dehkordi, A., Ahangarani Farahani, A. Designing and Comparing Two Configurations of Space System Flying Simulator with Cold Gas Thrusters. Electronic and Cyber Defense, 2024; 20(2): 55-67.

Designing and Comparing Two Configurations of Space System Flying Simulator with Cold Gas Thrusters

مکانیک هوافضا
Article 5, Volume 20, Issue 2 - Serial Number 76, July 2024, Pages 55-67    PDF (1.59 M)
Document Type: Dynamics, Vibrations, and Control
Authors
Seyedali Saadatdar Arani1; Mehran Nosratollahi* 2; Amirhossein Adami Dehkordi3; Alireza Ahangarani Farahani3
1Ph.D. Student, Faculty of Aerospace Engineering, Malek-e-Ashtar University of Technology, Tehran, Iran
2Corresponding auhtor: Associate Professor, Faculty of Aerospace Engineering, Malek-e-Ashtar University of Technology, Tehran, Iran
3Assistant Professor, Faculty of Aerospace Engineering, Malek-e-Ashtar University of Technology, Tehran, Iran
Receive Date: 14 January 2024,  Revise Date: 04 March 2024,  Accept Date: 17 March 2024 
Abstract
In the design of aerospace systems, certain requirements such as efficiency, weight, and cost are highly significant. This article presents the design and configuration of two flying platforms for simulation of space systems, using cold gas thrusters for in-space maneuvering, in SolidWorks software. In the first drone, three cold gas thrusters are mounted at the end of three arms, each installed with a 120-degree angle difference. The second platform design features four thrusters, and the angle difference between the arms where the nozzles are installed is 90 degrees. After extracting the dynamic model and analyzing the two systems, a PD controller with optimal coefficients was designed and simulated using the genetic algorithm optimization method to control their status. The simulation and data analysis results reveal that the platform with four cold gas thrusters performs better in accuracy and control effort, while the other with three thrusters performs better in weight and cost. By comparing and analyzing the results, the user and designer can make the appropriate choice for the intended operation.

Highlights
  • Designing and proposing two space simulator flying platform designs with four and three cold gas thrusters.
  • Dynamic model extraction and Attitude control design for each model using PD controller.
  • Comparison of two model with criteria of weight, cost, accuracy and control effort.
Keywords
Spacecraft simulator; Space maneuver; Cold gas thrusters; Attitude control; PD controller
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