Prepared Survey doing deliberat on effective reasons on Mashhad Citizens intention to Sutelite with descriptive explanation Method that is the kind of comparative reason and effect that on Mashhad Citizen,s religious beliefs and behaviours Statistical community of this survey contains 400 person of Mashhad Citizen that ages are about 15 and more it on 1385 year. Bulk of Sample assigns by ranking method like kokran formula. Finding of research shows thah Age, Sex, leavel of education, locotion, how is spending rest times and evalution persons of internal Tv programmes are effectivy on intention them to Satelite. In testing of cognitive aspect, intention to Satelite the majority of those who were under study, believed that Satelit is the reason of increasing their knowledge and it satisfied the different needs o any age and sex group and in emotional aspect of intention to satellite again they consider the satelite program, fun, intresting and attractive In behaviour aspect most persons are tendency to watching the satelite program. but don,t pension to encouraging others to watching satelite and results of research shows that average of confidence to religious beliefs and behaviours so many difference between two groups that access to satelite and don,t access to it” so that persons don,t use satilite more confidence to religious beliefs and behaviours

PARS1 Satellite is a Remote Sensing satellite with a 3-years mission. Main mission is imaging from earth by three camera named MS, SWIR, TIR. PARS1 OnBoard Software (OBSW) is developed as a performance platform, satellite components control, data management, algorithm management included normal status control and event handling. Because of OBSW complexity and its different features, it has more priority than other subsystems in satellite. So PARS1 satellite OBSW design, development and test is a useful platform for gaining of worthwhile experiences in the field of satellite onboard software which is very wide and complicated in its field. So we decided in this paper to present here as lesson-learned and results experiences. These results is gained from development and test phase from developer and tester view. Use of these experiences will be very efficient in smoothing of test and development path in future projects and works in Satellite Research Institute.

In this paper, the effective parameters in access time of a low earth orbit (LEO) satellite, in a ground user, are studied and outcome of each one is estimated on it. Then the total access time of a single LEO satellite has been maximized. For this purpose, the inclination angle of orbit, to the equator, has been optimized in various satellite altitudes and ground station’s latitudes. The obtained results, once considered along with the power supply issue, give a comprehensive vision for LEO satellite orbit design. Then the satellite access to the sun, as the energy source, has also been evaluated. Simulations have been done by the satellite tool kit (STK) software.

The present paper is based on a case study of the relationship between gender, social adjustment and socio-political attitude of adolescents watching satellite TV in Tehran. The samples consists of 60 female adolescents (30 girls from families holding satellite TV and 30 girls from non-satellite TV households) and 60 male adolescents (30 boys from families holding satellite TV and 30 boys from non-satellite TV households) living in Strict 4 and 16 of Tehran City. To assess the variables, the researcher used questionnaire of California social adjustment and socio-political attitude. Variance analysis shows that the level of social adjustment among satellite-TV holding adolescents is weaker than that of adolescents who watch satellite TV. Multivariate analysis of variance also indicates that there is a significant difference between satellite-watching adolescents and those without satellite TV in terms of obeying social norms and intra-family relations. In other words, using satellite TV in family has a negative relationship with the boys and girls adjustment as well as boy’s socio-political attitude.

In the mission of satellites, instantaneous positioning and estimation of the future position are necessary. In the communication satellite, this matter is so important. Thus in the Tadbir satellite, for the first time in the country, we consider an orbit determination subsystem that equipped with a spaceborne GPS receiver and contains appropriate algorithms in order to achieve satellite position data during the lunch period and in the orbit. In this paper a brief review of the software and hardware parts of this subsystem is presented. In additional the process of testing to achieve good performance, including functional tests of ODS processor board and functional test of GPS receiver with GPS simulator, environmental condition tests, mechanical tests, thermal vacuum cycle tests, electromagnetic compatibility test and finally integrated satellite tests are stated. This paper, in addition to a description of the Tadbir satellite orbit determination subsystem, an implementation testing of a satellite subsystem is demonstrated, which can be useful to other space field researchers.

In this paper predicting of position of satellite based on extended kalman filter with considering hardware implementation consideration and simultaneously maintaining desired accuracy is investigated. For this purpose, first, effective forces on orbital dynamic and nonlinear equation of orbital motion are presented. In order to increasing accuracy of prediction in position of satellite, J2, J3 and J4 harmonics of potential function of the earth are considered and future position of satellite is predicted using linearized dynamic model and applying EKF on this model. Here Measurement data are position and velocity vector of satellite which are extracted by GPS receivers. Since in this paper systematic satellite design is considered, scenario of “ON TIME” of GPS receivers based on power consumption considerations is discussed. Finally simulation results for a LEO satellite and comparing these results with STK results, shows accuracy of presented modeling and equations.

In this paper, a precise method for calculating albedo and IR heat flux applied to a satellite is presented. For obtaining albedo heat flux applied to a satellite, a point on the earth’s surface that sun flux reflected at that point and reach to the satellite is obtained, hence albedo heat flux reaches to a satellite is obtained as a function of longitude, attitude and longitude. IR heat flux is integration of emitting heat flux for points on the earth surface that in satellite’s view. Atmospheric transparency for calculating albedo and IR heat is considered for sun light and IR spectrum using MODTRAN algorithm using PcModWin software. For a generic LEO satellite, IR and albedo heat fluxes are calculated at a time period and compare with reference values. Obtained heat fluxes are used to obtain temperature variation of satellite’s components during its mission.

One of the challenges facing satellites is the satellite thermal control process. The mission of the satellite thermal control system is maintaining the temperature of the satellite's components in the permitted temperature range during the satellite mission. Because the radiation is the only way to exchange heat in vacuum, so the surface coating of the radiators plays the most important role in this field. On the other hand, the environmental conditions of the vacuum and the satellite orbit strongly affect the external surfaces, including the radiator surface, such as ultraviolet radiation and charged particles, contamination, micrometeoroids and the erosion of atomic oxygen. This research aims to guide and facilitate the selection of radiator coating for satellites with various missions, such as student satellites, Telecommunication, Weather, radio-television, research, military, etc. To fully examine the role of factors Effect on the radiator coating and the comparison between the current coatings of modern satellites.

The structure of a satellite, during its operational life, should be tolerated all applied mechanical loads which the most important of them is vibration loads during the launch. To verification of design process, finite element analysis and vibration tests should be performed on the structure of satellite according to the ECSS standard. In this paper, while simultaneously examining the optimal design process for a satellite structure with an increase in the strength to mass ratio, the required finite element analyzes along with the mechanical tests of the structure of a telecommunication satellite, including random vibrations, sinusoidal vibrations, shock and quasi-static, are fully presented. The results showed that by employing the cross section design for the satellite structure, the natural frequency of the satellite in the longitudinal direction have increased appreciably, which increases the strength of the satellite in the longitudinal direction. The experimental results proved that the designed structure meets the frequency requirements of the launcher while tolerate the mechanical loads during launch. Also, the experimental results were in good agreement with the numerical results, including the modal analysis, random and sine vibration. Therefore, design processes of the satellite structure were verified by experimental tests.