Yemets V. Scientific and Technological Basis for the Development of Launch Vehicles equipped with Combustible Tank Shells

Object. The thesis aims developing the scientific and technological basis for designing a new type of launch vehicles (LVs), combustible LVs (CLVs), which is intended to decrease space launch cost and based on using rocket tank structures as fuel. Methods of investigations combine theoretical assessments and experimental proofs. Novelty. The design principles of the CLVs equipped with a combustible tank shells were chosen. The most suitable materials for the shells are hydrocarbon polymers like polyethylene. The specific mass of the compressor for the gasiform products of thermal destruction of polyethylene was estimated A mathematical model of the gasification chamber (GC) intended to transform the solid tank shell into gas to provide a CLV engine with the gas was developed. Main characteristics of the GC were estimated, the relations between them and the main design parameters of the CLV were derived. Reliability of the mathematical model for the GC and the theoretical evaluation of its characteristics as well as its engineering feasibility are proven by means of experimental investigations of the GC physical analogs. Design principles for the magnetic powder obturator to seal the gap between the CLV tank shell and mobile engine were developed. A magnetic powder every particle of which consists of a magnetized core and polymeric slidable envelope was made for the obturator. A mathematic model and physical analogue for the obturator were developed and successfully tested. Result. To put into an orbit the satellites with masses more than 100 kg the reusable 2-stage CLVs are capable of decreasing specific launch cost for LEO by an order in comparison with conventional expandable 2-stage LVs powered with kerosene-LOX propellant if the reusable parts are used 10 times. To orbit the microsatellites with masses of 10-100 kg the SSTO expandable or reusable CLVs are preferable. They need no impact area for used rocket parts. For launching the nano- and picosatellites with masses of 0.5-5 kg the reusable quasi SSTO inertial CLVs are preferable. Field of application is aerospace engineering.