نشریه فناوری در مهندسی هوافضا
سال هشتم شماره 1 (پیاپی 28، بهار 1403)

The intended aircraft in this issue is an UAV type, capable of performing multiple missions. In this paper, after the linearization of the pitch channel, the transfer function for important points is extracted. After that, a robust classic compensator and an angular velocity damper are designed. According to the range of uncertainties, the compensator is adjusted by article bee colony algorithm. Also, the optimal value of the wing sweep back angle is obtained indirectly from the optimal value of the center of aerodynamic pressure. The optimization approach in this pepper is to make pitch channel robust to uncertainties. The results show that with the innovation in the design of the classic controller and its combination with Mont Carlo simulation and Optimization algorithm, the behavior of the pitch channel in the presence of uncertainties has been improved.

In this article, the deformable structures of a symmetrical airfoil and the discussion of aerodynamic forces are discussed inside the wind tunnel with miniature dimensions. The problem, which is checked in this article, is the investigation the effect of surface deformation in a small airfoil. In order to validate the tunnel, a flat plate is examined in the miniature wind tunnel test section and the experimental results are reported with the existing results with an error of less than 10%. The selected sample of airfoils is one of simple small airfoils and another example is smart . The selected structure material for both small airfoil samples is balsa wood and thermal coating is used for the shell. The test section is analyzed and investigated with simple small airfoil. The next step include the design, fabrication, and finally, the evaluation of the smart small airfoil in the test section.

In this study, the simulation of internal ballistics and the exhaust flow of a solid propellant engine have been investigated. The flow field considered in this problem including the cylindrical grain and the solid wall of the engine and the flow at the nozzle outlet have been studied. The governing equations are used in an axisymmetric and compressible form to model the fuel combustion in non-erosive combustion mode. In the present study, cylindrical type of grain fuel is considered, which is one of the most useful types of fuel grains in terms of simplicity in production. In order to obtain the results from the simulation model which are close to the real data, used UDF modules in the Fluent software to describe some specific quantities and phenomena of the problem. Finally, the results obtained from the simulation in different modes of fuel burning are examined and show the accuracy of the numerical model by entering the parameters affecting the fuel burning.

A comprehensive statistical analysis and comparison on the characteristics of star trackers used in the world can provide valuable information to researchers, manufacturers and customers in this field. In this regard, with a comprehensive search, 12 indicators of star sensors (accuracy, maximum trackable rotation rate, acquisition time, data transmission rate, field of view, star magnitude, mass, volume, power, voltage, temperature and lifetime) among 72 star trackers has been investigated and compared in this article. Also, by fitting the curves in the comparative graphs, relationships were extracted that provide statistical design for the manufacturers. By scoring each index,, it's possible to compare all the characteristics of the sensors to gives the satellite designers the opportunity to identify and choose the optimum choice for their purpose and mission by weighting the criteria. Present statistical study includes investigation of native sensors shows inspiring from the hardware and software of sensors such as PST3, makes possible to upgrade and improve products in less time.

This paper discusses how to implement the CAN bus protocol based on the ECSS standard in the space applications of satellites and various missions. The CAN protocol frame consists of the frameworks, arbitration and control, data, cyclic redundancy, and verification sections. The arbitration and control section are responsible for controlling the data flow. There are two standards for these two parts, which satellites usually use the developed CAN standard according to which the LDUT protocol is designed, due to the need to use the LDUT protocol for big data transmission. Also, to manage the redundancy of the CAN bus, the implementation conditions of the parameters of each node will be checked. Also, this protocol is implemented on the reaction wheel condition with microcontroller hardware and related converter considerations in MPLAB software environment and is approved by Microchip Analyzer CAN separately and OBC simulator as a quadruple group with the correct function of the approved bus redundancy.

Components of the LEO environment consisting of high vacuum, ultraviolet radiation, thermal cycles, Atomic Oxygen, charged particles, electromagnetic radiation, micrometeorites, and space debris significantly degrade the material properties of polymer matrix composite materials. Therefore, in the design of space structures using composite materials, the possible deterioration of mechanical properties due to long-term exposure in LEO space environment should be carefully considered. Accordingly, a reliable understanding of the LEO environment in its effects on composite materials as well as investigating its properties is very important. The space simulator system under vacuum is designed with the aim of creating a standard environment with the ability to reach high vacuums and also the ability to create low temperatures, as well as to check the qualification of space components and research materials used in the satellite. These systems analyze the behavior of satellite components, evaluate their thermal balance and performance to ensure mission success and survivability.