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This paper describes the software in loop test bed developed in order to test the control system of a tethered nano-satellite simulated under de-orbiting conditions. The entire ADCS architecture of the satellite along with the descriptions of the individual models constituting the Software in-the loop test bed, such as descent modeling algorithm, the sun model, the eclipse model, disturbance torques...
Stability of an embankment constructed on soft consolidating soil improved with pre-fabricated vertical drains is investigated. The factor of safety of the embankment is obtained at various time intervals from the end of construction till the end of consolidation in order to check the embankment stability. Finite element method is used to obtain the effective stresses at required points in soil at...
This paper describes the nominal control system design to counter the effect of deployment of an electro-dynamic tether on a polar low-earth orbit nano-satellite. The complete tether assembly including the deployment mechanism, choice of material, length of the tether, preferred door axis for deployment of tether have been explained in detail. Analysis of the effect of deployment of the tether on...
This paper describes the control systems employed by a nano-satellite ‘Parikshit’ to satisfy the payload requirement to limit the angular velocity of the satellite within 1 deg/sec. Also described is the satellite kinematics and dynamics model in space environment to test and evaluate the performance of the controller to meet the desired stability. The entire dynamics of the satellite have been modelled...
This paper describes the dynamics of a polar low earth orbit nano-satellite as a consequence of tether deployment; and the control system to counter its effect. The complete tether assembly, including the deployment mechanism, choice of material, length of the tether, preferred door axis for deployment of tether, have been explained in detail. A force sensor, to measure the forces associated with...
This paper describes a method to determine the rate of descent of a nano-satellite which uses an electrodynamic tether for de-orbiting. Also described, is an orbit propagator model of the continuously varying orbit and a control algorithm during its descent. An elaborate attitude control model is also proposed which is complemented by a set of sensors and actuators. Use of tethers provides an economical...
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