نشریه علوم و فناوری فضایی
پیاپی 5 (پاییز و زمستان 1388)

In this paper, a closed-loop optimal guidance with final position and velocity constraints is obtained by applying time-varying weighting coefficient in the performance index in order to shape the commanded acceleration. The control system is assumed to be linear, time-varying, and of arbitrary order with a throttleable engine. The acceleration due to drag is also modeled as a linear function with respect to velocity vector multiplied by a given function of time. In addition, different weighting functions are suggested for different acceleration constraints, such as maximum dynamic pressure, separation of stages, and zero acceleration at the final time. Finally, the performance of the guidance law for a combined weighting function is evaluated and discussed.

In this paper, Design of flight trajectory in unpowered phase namely “Coast Phase” which is important in energy reduction in transition orbit of spacecrafts and launch vehicles is considered. To this aim, the velocity impulse at both sides of the transition phase (between initial and final orbits) is described as a parametric function of the geometry of the path. Then the optimal coasting trajectory is proposed using simple minimization techniques like Fibonacci Search Method and a Velocity-Required Based Steering technique simultaneously. A numerical study is performed using a three stage launch vehicle with a coast phase between second and third stages to show that the proposed technique is capable to produce optimum transition trajectory and since it is accompanied by guidance technique could be used as an online technique.

Satellite camera Charged Coupled Device (CCD) read out system needs a high Signal to Noise Ratio (SNR). This is because of the special and inevitable space imaging payload noises. These noises include CCD noises, satellite noises such as lack of complete stability, and environmental noises such as atmospheric interferences, charged particles, relative earth and satellite movement and electromagnetic interferences. CCD noises because of their low output voltage compose the main part of the final read out system noise. Therefore if the CCD read out system is not designed properly, SNR declines significantly. These noises depend on CCD characteristics and design parameters such as temperature and frequency. On the other hand, in a satellite temperature and frequency range is partially controllable. The algorithm presented in this paper, with respect to the applied limitations and dependencies, designs the system parameters so that the optimized SNR is achieved.

Corrugated tunnel is a pipe, which its outer surface is corrugated and is generally used for fluid transfer in different industries. Owing to complicated geometrical structure of corrugated tunnels, very limited numbers of closed-form equations have been presented for analysis of their mechanical behavior. In the present study, a mathematical model is proposed for strength and buckling analysis of corrugated pipes. In addition, an algorithm is presented for designing of corrugated tunnels. In order to verify the presented model, its results were compared with those obtained by finite element method (the ABAQUS software was used) and a good agreement was observed. Finally, some corrugated tunnels were designed, fabricated and tested for a special industrial application. Critical pressure values obtained from the tests were less than those calculated from the theoretical method, which could be due to fabricated flaws.

This paper presents an optimal attitude maneuver by means of Reaction Wheels to achieve desired attitude for a Satellite. At first, Dynamic Equations of motion for a satellite with three Reaction Wheels as its active actuators has been educed, and then State Equations of this system has been obtained. In derivation of equations, coupling of Reaction Wheel electrical equations with dynamic equations of satellite motion, and Reaction wheel saturation avoidance approaches are considered. Then an optimal attitude control with the LQR method has exerted for a distinct satellite by its Reaction Wheels. As a result of simulation has presented an optimal effort by calculated Gain matrix to achieve desired attitude for chosen Satellite. It shows that satellite becomes stable in desired attitude with a low energy and time consumption.

Weight optimization is one of important parameters in space structure design. Size optimization is usually performed using gradient or genetic algorithm. Gradient algorithm is based on derivation of objective function and constraints of problem. The performance of gradient method is depended on start point and do not search all design domain. Genetic algorithm searches all design domains, but it cannot get close to the global optimum. In this paper, a new method is presented for size optimization. The algorithm starts with genetic algorithm and result of genetic algorithm is then used as start point for gradient algorithm. The presented method is used for size optimization of two trusses with three and ten elements. It is also applied on for optimization of a lattice structure of parabolic antenna. The results show that the present algorithm can perform better results compared to genetic algorithm alone.

What is done in this paper is simulation of telemetry and telecommand communication between satellite and earth station as what exists in real earth station. Three software: Satellite predictive motion software, Monitoring and Control (M&C) software, processing Software are used in the simulation. Satellite predictive motion software uses orbital equation extracted from Two Line Elements (TLE) to generate tracking elevation and azimuth angles of satellite. These angles as text file are input of M & C software. The M & C software has four modes as simulation mode, online mode, test mode and emergency mode. In simulation mode Acquisition Of satellite (AOS), Loss Of Satellite (LOS) and Pass Time (PT) are seen. The angles are produced and transferred to antenna servo system for moving antenna to desirable direction. Time of simulation is controllable and received signal level is displayed simultaneously. In this mode when satellite is observable, the telecommand can be send. In online mode all explained capabilities are valid except changing of time. In test mode antenna axis could move in desirable velocity and acceleration. In the other hand, when the satellite becomes lost, the system enters to emergency mode for searching of satellite. In the normal mode after receiving the telemetry data by M & C software this data as text file transferred to processing software. Processing software by protocol which accepted by satellite (HDLC based) recognizes the first and the end of telemetry frame and then extracts and displays the parameters. The telemetry parameters include online and offline data.