Environmental simulation has an essential contribution in attitude determination and control verification tests of satellites. Specifically, real-time modeling of space environment can provide more precise and adapted simulation of real world in order to enable satellite attitude determination system by online outputs of sensors. Design and manufacturing of a moving mechanism which simulates the motion of real Sun relative to the satellite is proposed in this paper. Indeed, an artificial Sun carried by the mechanism will sensitize Sun Sensors mounted on a 3DOF model of satellite and finally the outputs of sensors are used to determine the attitude of the model satellite. The procedure of designing and manufacturing such a mechanism is described as follows. Firstly, the motion of Sun relative to the satellite on a specific orbit was ascertained. Next, considering the constraints such as laboratory space and its equipments, an appropriate mechanism was designed conceptually to satisfy the requirements. Then, the detailed characteristics of the mechanism were determined in the preliminary design phase and approved in the detailed design phase of the project. Finally, in order to verify the designed mechanism, a scaled down prototype was fabricated. Developmental tests on the prototype proved the ability of the model to simulate the Sun motion relative to the satellite properly.

In this paper, a full applicable procedure for design, optimization and manufacturing of an operational unmanned helicopter with deep and detailed research basis is presented. 12 The proposed process deals with challenging aspects of manufacturing of the mentioned type of aircraft such as cost, weight, operation ability, reliability, mission justification, stability, performance, etc. To show the applicability of the proposed procedure, a realization of the process in production of an operational unmanned helicopter named as Parvan is described in this paper. Indeed, Parvan is a Remotely Piloted Helicopter (RPH) with 9 kilograms takeoff weight, and main rotor diameter of 1.54 meters which can lift up a 2 kilograms payload and fly in 120 kilometer radius of action for about 1.5 hours.

In the present paper, a complete process from reliability evaluation to design modification is proposed and also applied to a newly designed and manufactured Remotely Piloted Helicopter (RPH) by the authors. First of all, a description of all platform subsystems is presented. After that, function diagram and also product tree of the whole system is depicted for further analysis. Then, the reliability of all parts and components are calculated through standard methods. The procedure is followed by FMEA/FMECA execution and determination of critical components and failures. Then, the reliability of the whole platform is calculated using standard block diagrams. Finally, in order to improve the mission operational reliability of the considered RPH, some modifications are implemented to the platform including configuration and mechanisms design changes.