## 9 Conclusions  
This research was directed towards making an impact on the utilization of the cost-effective solutions to build small satellite constellations mainly for disaster management applications globally. Small satellites utilizing COTS have great reach in terms of resource and cost effectiveness, along with MEMS as a primary technology for sub-system level development for real-time execution in a constellation. However, planning the operations and designing an autonomous constellation is a distinct challenge when involving small satellites under 500 kg with a global coverage and less resources and reachability, which represent the need of the hour. This paper mainly emphasized the coverage analysis and optimization of the orbits in a small satellite constellation to obtain the best feasible solutions in terms of travel time and fastest data transmission to the respective ground stations. This was achieved by altering the orbital elements most suitable to reach a particular location. The interior point (ipopt) optimizer was used with the proposed constellation set-up to analyze the best optimal solutions in Low-Earth Orbits autonomously. The simulation performed iterations as per the given initial mission design parameters, determined the feasibility of the solution, and then the best solution itself as per the given scenario. This optimizer (ipopt) has been used for several non-linear solutions for various other applications in the past. However, what is unique here is that on a non-linear large-scale such as a constellation with small satellites having limited resources and higher constraints on-board, the optimization of coverage has to be continuous and impactful in an autonomous and harsh environmental condition. ipopt provides solutions firmly for the continuous optimization problem in a non-linear state, which is suited predominantly for the LEO region under the influence of atmospheric and solar radiation-based issues. Though this work is mainly directed towards the disaster management and deep space strategy with Artemis, Refs. [21; 22; 23; 24] gave enough motivation to propel towards a contributing research. The uniqueness/novelty this paper brings about is to highlight the fact that the coverage analysis is not merely about having a global satellite reach with a number of satellites in a constellation, but it is about designing the configuration in such a way that even with minimum satellites forming the constellation, we can attain a wider coverage in due consideration of real and local environmental conditions, as is key for future missions. This initial mission design configuration in this paper is presented with a 45-degree inclination of the orbits in a walker-like pattern, which is usually not the scenario with traditional walker constellations. This has been detailed keeping in view the testing of the operation with a uniquely defined configuration of this proposed constellation for better coverage with minimum satellites. After the execution of the same, the operation seemed normal at changing altitudes ranging from 400 to 650 Kms (6500-7000 km semi-major axis). After the optimization for better coverage, the feasibility of iterations and the solution itself never failed and gave the best-case trajectory solution in terms of cost and objective functions along with a well-defined coverage fraction. It is extremely crucial to note here that this particular LEO region is of prime significance for disaster management application through a constellation of small satellites as proposed. All the major perturbations and solar radiation pressure concentrated in that region and became a matter of research concern in recent times of NewSpace era. This aspect has been thoroughly taken into due consideration while simulating the proposed configuration, analyzing and optimizing it. Also, Refs. [25; 26; 27; 28] give a good sense of how critical issues of planning, control and power of satellite constellations can be addressed unique methodologies.