Abstract: The present invention relates to a system and method of mobile orbital launchers. The mobile launcher of the present invention mainly consists of the launch vehicle and launch related subsystems. All the systems will fit on a trailer which is capable of going anywhere via road or sea. It will carry the vehicle in a horizontal position and after reaching the required location, it will articulate and make the vehicle vertical to get ready for launch. The system and method of the present invention have all the subsystems which enable the launch without any hindrance.

Abstract: Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to inject the fuel to the combustion chamber, an igniter (502) to ignite the fuel mixture, a nozzle (506) to pass hot gas to produce thrust and cooling channels (508) for regenerative cooling, where all these components are fused to form a single piece integrated engine. The engine of the present invention eliminates the need of assembling the individual components. Further, the engine is additively manufactured with high grade aerospace materials. Thus, the cost and mass of the engine is reduced when compared to traditionally manufactured engines, which leads to frequent missions.

Abstract: The present invention relates to a modular configuration of the launch vehicle system. More specifically, it relates to the modular configuration technology developed to optimise the launch vehicle with respect to the number of engines in the lower stage or the number of stages itself in order to get a most efficient launch possible for a particular payload being launched. In the present invention the vehicle is such that the modularity is passed down to sub-system level which thereby reduces the mass of unused components and the modifiable cluster can be used as a booster unit to carry heavier payloads to higher orbits. Depending upon the mass of the payload to be carried to a particular orbit, either the number of stages or the number of engines, are either attached or removed from the vehicle and thus increasing the efficiency of the trajectory. The present invention reduces the time and cost involved in reconfiguration as well.

Abstract: A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.

Abstract: Disclosed herein is a single piece, integrated, light weighted, cost-effective 3D printed engine for space vehicles. FIG. 5 illustrates an integrated engine that comprises a combustion chamber to burn the fuel, an injector plate (504) to inject the fuel to the combustion chamber, an igniter (502) to ignite the fuel mixture, a nozzle (506) to pass hot gas to produce thrust and cooling channels (508) for regenerative cooling, where all these components are fused to form a single piece integrated engine. The engine of the present invention eliminates the need of assembling the individual components. Further, the engine is additively manufactured with high grade aerospace materials. Thus, the cost and mass of the engine is reduced when compared to traditionally manufactured engines, which leads to frequent missions.