# A Brazilian Space Launch System for the Small Satellite Market
## 3 Results and Discussion  
Figure 6 presents vehicle performance curves (_DBallistic_ model) for a range of orbital altitudes (300 to 900 km) in sun synchronous missions. For the calculated altitude range, the vehicle concepts could launch payload masses stretching from about 350 to 650 kg, thereby covering the entire spectrum of the small satellites class. We considered, throughout our analysis, 500 km altitude, circular polar mission, as a reference orbit. As it can be seen, concept 1 would deliver a payload mass up to about 436 kg, to the reference orbit, while concepts 2 and 3 would deliver a total mass of about 467 and 593 kg, respectively. Concept 3 is the only one capable of sending a satellite relying on the Brazilian Multi Mission Platform-MMP (500 kg) on polar-orbiting missions in the range of 300 to nearly 900 km. The Brazilian Space Program [18], in its 10 year long program, lists a certain number of remote sensing and scientific missions based on the multi mission platform. The qualification flight of the platform is schedule to take place in 2020, carrying a wild field image sensor for optical remote sensing application. When operational, concept 3 would, therefore, give access to space to the majority of the Brazilian satellite missions for LEO. The performance plots show a modest gain in payload capacity by changing the upper stage solid motor (S-44) of concept 1 by a pressure fed liquid engine of 2.50 kN thrust. Thrust modulation and re-ignition capabilities would make concept 2 preferable over concept 1, from a purely operational point of view. The choice between these two concepts would depend on a cost analysis prior to the definition of a business plan for the space launch system. It can also be seen, in Figure 5, that the use of four RD-843 engines (concept 3), performing up to 10 kN of thrust, greatly increases the capacity of the launch system. The definition of which transportation system could be implemented must rely on performance and cost assessment for various scenarios and vehicle configurations. As far as performance is concerned, concept 3 would be a potential launch system for the small satellite market, operating from the Alcantara Launch Center. At lower altitudes, about 500 km (circular polar orbit), concept 3 would deliver a payload as heavy as 593 kg. For lower orbit inclination (near equatorial), the capacity of the concept 3 launch system increases to about 725 kg, at 500 km altitude mission from the Alcantara Launch Center. With regards to concepts 1 and 2 the launch systems would deliver payloads up to 550 and 565 kg, respectively, in LEO equatorial missions. The launch capacity of the three concepts are higher than most of the vehicles (micro launchers) under development, reported in a recent compilation [9]. Concept 3, thus, would fill a gap for the mini-satellite launch market (500 kg) considering dedicated missions for low Earth orbit, in any requested inclination, from the Alcantara Launch Center. Figure 6: Launch vehicle concept performance in polar missions for different altitudes. In addition to vehicle performance, we also conducted a cost estimation analysis for the selected vehicle configurations. Cost analysis was based on the specific set of Equations (18)-(30) and correction factors. Table 3 summarizes the value of each correction factor for system development, fabrication and ground and flight operations costs analysis. System engineering integration factor (\(f_{0}\)) was taking into account for the launch system development cost by simply setting the number of stages equal to three. Development standard factor (\(f_{1}=1.1\)) was taken as a first generation system, which require new techniques and new technologies along with the development. IAE-Brazil is internationally recognized as a preeminent organization in solid rocket propulsion development based on metal casing technology, and is rapidly acquiring knowledge in composite casing structures. The first S-50 motor engineering model had been subjected to structural analysis.