This paper shows the energy analysis of a thermoelectric system coupled to a turbofan engine, which is based on the mathematical modeling of the heat transfer of the system during the cogeneration process using fluid dynamics (CFD). The use of waste heat from a turbofan engine would allow us to increase its efficiency which has both economic (due to fuel savings) and environmental (reduction of polluting gases). The proposed section for the installation of the thermoelectric system is the one that covers the turbine and the nozzle section of the turbofan engine, since they are sections in which there are better operating temperatures, in the order of 600 to 200oC. As results of the CFD simulation you get the distribution of temperatures through the thermoelectric and the difference of electrical potential generated. These results determine the overall efficiency of the system and the electrical energy generated by the waste heat. The energy generated by the thermoelectric system can be used in secondary aircraft systems, such as the lighting system, entertainment, etc. The importance of the analysis lies in increasing the overall efficiency of the engine combustion process, to reduce fuel consumption and the costs associated with it.

Currently the generation of energy in space is of vital importance for research on other planets and moons, as all missions sent are powered by electricity so that they keep all their instruments operating properly and present no short-term problems. For the generation of energy outside the planet earth are presented the power converters which are able to convert thermal energy into electrical energy, currently there are two types of power converters which are dynamic and static, for this work are addressed the static, also called thermoelectric that work from a physical phenomenon called seebeck effect which USES two metals of different composition united, They take advantage of a temperature gradient where one end is kept at a hot temperature and the other at a cold temperature, causing a voltage differential. For a material to be considered thermoelectric and work properly has to have some properties such as the seebeck coefficient, electrical resistivity and thermal conductivity, in this work we study some thermoelectrics used in the aerospace sector which are Bi_2 Te_3, PbTe, SiGe, Skutterudite and BiSbTe Where its thermoelectric properties will be analyzed according to its operating temperature range, the merit figure zt will be calculated, the electrical power generated, the input heat and the output heat, finally a comparative table of the electrical power generated by the static converters and another of its applications in the space sector will be performed. This work provides information on the most used thermoelectrics in the space sector, as well as the physical phenomena involved in static converters.

The latest proposal for nuclear systems for application in space are 4th generation reactors that use liquid metals as coolant. The operating conditions, as well as its safety in these matters, is linked to its thermal and fluid dynamic behavior. This paper presents the estimation of the temperature profile of a sodium-cooled fast reactor from the conduction and convection heat transfer mechanisms. The temperature distribution is analyzed in the area of the fuel and the temperature profile of the coolant in the area of the high conductivity pipes. Is established the analysis of nuclear fuel in a one-dimensional, stationary and with power generation. In the GAP area, the analysis is carried out by natural convection, and finally, the cladding in contact with sodium by forced conduction-convection. As results, it is presented the simulation in Computational Fluid Dynamics to determine the temperature profile due to the behavior of the coolant in the pipe when subjected to a constant flow of heat supplied by the nuclear fuel pellets. The temperature profile will allow us to determine the parameters to establish the operating conditions of secondary power conversion systems.

This paper presents the design of a control strategy based on exact feedback linearization and dynamic stabilization for the mathematical model of a benchmark Quanser platform emulating the elevation, pitch, and travel motions of a three-degree-of-freedom (3-DOF) tandem helicopter. The orientation dynamics of the aerial vehicle are described by a set of highly coupled, inherently unstable nonlinear differential equations. Unlike conventional feedback linearization approaches, the core contribution of this work lies in a strategic subsystem decoupling technique combined with a symmetric input transformation and a formal proof of exact linearizability. Once the exact linear canonical representation is derived, optimal Linear Quadratic Regulator (LQR) control gains are synthesized directly within the transformed coordinates. Subsequently, a trajectory tracking scheme is developed for each degree of freedom, simulating aggressive trajectory changes that emulate obstacle-avoidance maneuvers during a mission. Numerical simulations in MATLAB/Simulink demonstrate that the proposed control scheme achieves precise tracking and rapid stabilization while strictly adhering to the physical angular bounds of the experimental platform and operational actuator constraints.