## 1 Introduction
### Problem Definition  
Globally, major concerns exist regarding the major real-time issues faced by the small-satellite constellations during a significant period of their operations. The questions that govern these issues can be framed as below:  
* How can the relief under the disaster situations be managed with the constellations with fast data rates and optimal travel path? * Which optimization technique can significantly reduce the travel path burden for each satellite in a plane or formation in constellation? * How can we achieve autonomy in the NewSpace constellations to efficiently reduce the human intervention and efforts to maintain the best possible orbit every time it passes through a ground station until its lifecycle? * How can we determine the major role of these constellations (with optimizers) in aligning the Artemis and support operations for initial lunar missions and deep-space network? This paper will provide insights on the optimization of the orbit travel period (range) by enhancing its orbital elements significantly by using predominant optimizing solutions. Mainly, the inclination and the semi-major axis of each orbit in constellation are of prime importance. The constellations launched globally have their own set of issues and concerns to maintain the quality of the incoming data as well as to maintain their respective orbits without losing them to perturbations or decaying due to LEO environmental conditions. A strong control on all the satellites can be balanced out by orbit travel period so that the data can be received by respective strategically placed ground stations timely. A detailed study on the parameters, situations, orbits, and related work carried out on constellations has been observed extensively. There has been a significant research undergoing in this aspect of the constellations with majority of the constellation developers are making efforts to reduce the cost of the satellite development and operating them for the given lifecycle. Optimizing the number of satellites in a constellation is also a major concern among manufacturers. The importance of choosing the best solution for the orbit remains to be higher than any other operating measure in real-time scenarios. The shortest path of travel with a longest reception pass of a satellite is the need of the hour. The cost, objective, and coverage fracture contribute to the constellation's best trajectories to be prepared and facilitate the end-users accordingly with the fastest receivable data. The increasing demand in the disaster management applications from the satellites is quite overwhelming. The data being received in a full package is an absolute necessity and managing them without many anomalies is an engineering challenge. The constellations of small satellites can contribute effectively towards filling up this vacuum with creative methodologies, continuous research, and implementation of unique techniques. This research is dedicated to the purpose of finding efficient solutions to the problem of providing effective, usable, continuous data to the end-user. This can be achieved through the optimization and analysis of essential parameters and relating their importance on ground and in orbit through constellation of small-satellites with a unique configuration. Towards this direction, the following terminologies were framed, discussed, and implemented. There are two terms used here, 'Long pass' and 'Long Period', as shown in Figure 3. The long pass is the always desirable from any ground station point of view because the longer the pass of a satellite over a ground station, the better the reception window of the data and possibility of a full packet to be received. If the pass is for a shorter period of time (calling it short pass), it can influence the delivery quality of the data to the ground station and have poor packet reception (possibilities are more). The long period can be defined as the period of wait for the satellite to reach again to the same ground station without an optimizer used.