نشریه فناوری در مهندسی هوافضا
سال سوم شماره 1 (پیاپی 8، بهار 1398)

Giventhe importance of air engine control systems and the necessity of developing this specialty in the country, the establishment of appropriate infrastructures for implementing applied research in this section field is very important. In order to establish a jet engine thermotronic control laboratory at Babol noshirvani University of Technology, an effort has been made to develop a turbojet engine cycle with measuring and control equipment.The turbocharger is used as the heart of the Brighton cycle in order to maintain the simplicity and functionality of the engine and change the performance parameters of the engine.The developed engine includes: refueling, fueling, combustion chamber, cooling, lubrication and measurement. After the initial design, Substandard has been manufactured and assembled. Finally, using the governing equations for the motor subtypes, the overall engine performance is analyzed and the engine's operation points are analyzed

In this research, the flow field around the space re-entry capsule, which has blunt and symmetric geometry has been investigated. The simulation of the flow around aerial vehicles in the hypersonic flight regime is the one of the topics discussed in aerospace projects.The Successful return of the re-entry capsule to the earth of depends strongly on its angle when entering the atmospher. Due to the importance of aerodynamic calculations of aerial vehicles, and because tactical aerial vehicles, such as rockets, usually fly at an angle of attack, this issue is of particular importance in aerospace industries. In many cases, the results of theresearch have not been published and this is the main reason for the difficulties of research in this subject. This research the flow analysis of symmetric body at different angles of attack. For this purpose, the flow field was simulated in Mach number 7 at different angles of attack and its results were compared with the reference data, which gives an appropriate accuracy especially for the axial force coefficients and the form of the contour lines for the axial component of the velocity.

The lighting system is one of the most important components of greenhouse or plant growth chambers in Advanced Life-support System (ALSS). Several designs of such lighting systems have been proposed including the use of natural sunlight and electric supplemental lighting. Due to the limitations of plant growth under natural sunlight on the surface of the moon or Mars, it is essential to use electric lighting although it is high-energy consuming. The characteristics of different electric light types are important in space applications. Different lighting systems are recomended for Earth-based advanced life-support (ALS) system based on electric lighting that have advantages and disadvantages. The results state that LEDs are appropriate for life support system design due to low- energy consumption, lack of heat production, and induction of crop production. In this paper, effect of different light is investigated for usage in the life support system.

The most important application of functionally graded materials (FGM) is in the aerospace industry, these materials at high temperatures are very resistant to stresses especially residual stresses. In this study, a numerical solution for a circular branch made of FGM material with simple supports on radial edges, under transverse load along the thickness line, is presented. For this purpose, based on the first-order shear deformation theory and the principle of minimum energy, the potential of the entire equations of equilibrium is obtained. These equations are not independent. It is formulated for ease in solving, re-formulation, and for a circular sector with simple supports in radial edges and are solved numerically for the various boundary conditions in the periphery edges of the sector. In fact, this study aims to singularity of stress in a near-zero radius with calculations that indicate this stress is infinite in the near-zero radius, so failure will not occur.

Regarding the importance of the design and development of small satellites as a newfoundspace project in the near future in this country, as a first step, it is essential to study similar models and their performances. This paper aims to investigate the status of Cubesats with different subsystems and their capabilities based on advanced high performance space exploration and scientific missions. Technical appropriateness, organizations, manufacturing custodians, types of missions, weight, configuration, orbit, launchers, life-time, subsystems such as payloads, structure, thermal control, propulsion, command and data handling unit, telemetry, tracking, and control, serve as indicators for this analysis. Among over a thousand launched and proposed missions reviewed from various sources including journal publications, conference proceedings, mission webpages, and other available satellite databases, a number of relatively high performance missions were selected and categorized into six groups including astrophysics, earth science and spaceborne applications, deep space exploration, space in situ laboratory, technology demonstration, and space weather.

The burning rate plays animportant role in determining the performanceandballistic behavior of solid rocket propellant. In this paper, the effect of various factorson burning rate, such as combustion chamber pressure, poropellant grain initial temperature, fuel/oxidizer ratio, composition of the components propellant, oxidizer particle size, motor rocket size, and grain size have been investigated.For this purpose, technologies, methods, and various laboratory equipment are used, the most important of which are the methods such as Crawford, Closed Vessel, Ultrasound Measurement, Microwave, X-Ray X-ray, Plasma Electrical Capacity Measurement, Optical Techniques, Audio Publishing Systems. All of these methods are used in leading countries to measurethe propellants burning rate.Consequently, the appropriate method andequipmentconsidering general aspects (operational, economic, functional, safety, etc.) can be selected, comparing the advantages and disadvantages of each above-mentioned technologies, equipment and methods forthedetermination ofthe burning rate of solid propellants.