## 5 Conclusions  
The key design considerations for spaceborne SAR systems are examined focusing on minimizing satellite size and mass. Aspects such as altitude optimization, incidence  
Figure 14: Antenna dimensions–NESZ graph, and antenna dimensions–peak transmitting power graph. Figure 12: Antenna area–peak transmitting power graph, and NESZ–peak power graph. Figure 13: NESZ–bandwidth graph, and NESZ–system losses graph. angle selection, operating frequency, antenna sizing, and transmitting power requirements are considered. The balance between system parameters is emphasized to achieve the desired resolutions while minimizing satellite mass and size. The trade-offs between antenna area and transmitting power requirements are critical for SAR microsatellite design. By comparing different scenarios, the importance of multiple factors like operating frequency, altitude, incidence angle, system losses, and noise figures for optimal design are demonstrated. The study findings indicate the optimal transmitting power and antenna dimensions required for the desired resolutions and system performance. It is emphasized that the transmitting power and antenna area are two primary constraints to achieve designs within micro satellite size limits. In this context, the optimized performance metric NESZ is approximately \(-30\) dB. For the desired range and azimuth resolutions, assumed to be 5 m each in this study, the optimized transmitting peak power is around 2 kW, the bandwidth is 150 MHz, and the antenna area is approximately 10-15 m\({}^{2}\). Detailed dimensions can be derived from the depicted optimization graphs. Though these optimized results were derived using optimization techniques, they might also depend on other parameters. The present work highlights their theoretical and operational usage and values. After detailed research and trade-offs, it is concluded that the altitude of the platform for a micro-sized satellite should be 500-600 km, with an incidence angle of 15-45 degrees for SAR geometry and imaging. Moreover, other SAR parameters, such as PRF, duty cycle, system loss, and pulse width, should be considered to achieve the desired image quality. For real operational scenarios, to achieve optimized and reasonable sizes and values, trade-offs between these main SAR parameters and various scenarios are studied. Apart from these variables, a fixed parameter which is the operating frequency of the SAR system is used. After extensive research on recent micro-SAR satellites, the X-band is considered as the most suitable for remote sensing with a micro-SAR satellite. As shown in Table 1, the transmitting power requirements and antenna size vary depending on the mission objectives and other interrelated parameters. If the size of the spacecraft decreases, the antenna size may need to increase due to electric power system constraints, and the desired resolution directly impacts the satellite design. Solutions involving foldable antenna installations for antennas around 10-15 m\({}^{2}\), as well as the overall satellite mass analysis, have not been explored in this paper. The present study highlights the complexity of designing spaceborne SAR systems, where factors like the transmitting power of the payload, antenna size, and system losses are crucial for mission success. This paper offers a detailed guide for future SAR system designs, particularly for microsatellites, which face strict size and weight constraints. Future SAR satellite development is expected to focus on miniaturization, advanced materials, and innovative power management. Emerging technologies, such as efficient power amplifiers and advanced antenna designs, will help to create smaller and more capable SAR systems. The integration of design optimization algorithms, like those used in modeFRONTIER, shows promising potential. The main aim is to provide optimized values for designers and guide to innovative methods like AI processes.